FN Thomson Reuters Web of Science™ VR 1.0 PT J AU Craig, DA Herrmann, NB Troutman, PA AF Craig, Douglas A. Herrmann, Nicole B. Troutman, Patrick A. GP IEEE TI The Evolvable Mars Campaign - Study Status SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB NASA is developing a long-term strategy for achieving extended human missions to Mars in support of the policies outlined in the 2010 NASA Authorization Act and National Space Policy. The Authorization Act states that "A long term objective for human exploration of space should be the eventual international exploration of Mars." Echoing this is the National Space Policy, which directs that NASA should, "By 2025, begin crewed missions beyond the moon, including sending humans to an asteroid. By the mid-2030s, send humans to orbit Mars and return them safely to Earth." Further defining this goal, NASA's 2014 Strategic Plan identifies that "Our long-term goal is to send humans to Mars. Over the next two decades, we will develop and demonstrate the technologies and capabilities needed to send humans to explore the red planet and safely return them to Earth." To accomplish these goals, NASA is employing a capability-driven approach to its human spaceflight strategy. This approach is based on developing a suite of evolving capabilities that provide specific functions to solve exploration challenges. These capabilities can be leveraged and reused, enabling more complex operations over time and exploration of more distant solar system destinations. The Evolvable Mars Campaign is an ongoing study identifying potential exploration options leading to sustainable human exploration of Mars. This campaign will leverage existing activities, adapt to capability developments, scientific discovery, and ever-changing programmatic environments. The results of this study will not produce "The Plan" for sending humans to Mars, but instead develop potential human Mars exploration strategies to inform NASA management on key decision options and investment priorities. This paper provides a summary of the 2014 study activities and key findings to date. C1 [Craig, Douglas A.] NASA, Headquarters, Washington, DC 20546 USA. [Herrmann, Nicole B.] NASA, Headquarters, Valador Inc, Washington, DC 20546 USA. [Troutman, Patrick A.] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Craig, DA (reprint author), NASA, Headquarters, Washington, DC 20546 USA. EM Douglas.A.Craig-1@nasa.gov; Nicole.B.Herrmann@nasa.gov; Patrick.A.Troutman@nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 14 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300050 ER PT J AU Cramer, A Christe, S Shih, A AF Cramer, Alex Christe, Steven Shih, Albert GP IEEE TI Vision Algorithm for the Solar Aspect System of the HEROES Mission SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT ID LEAST-SQUARES; SUN SENSOR; REGISTRATION; ELLIPSES; CIRCLES; IMAGER AB This work covers the design and test of a machine vision algorithm for generating high-accuracy pitch and yaw pointing solutions relative to the sun for the High Energy Replicated Optics to Explore the Sun (HEROES) mission. It describes how images were constructed by focusing an image of the sun onto a plate printed with a pattern of small fiducial markers. Images of this plate were processed in real time to determine relative position of the balloon payload to the sun. The algorithm is broken into four problems: circle detection, fiducial detection, fiducial identification, and image registration. Circle detection is handled by an "Average Intersection" method, fiducial detection by a matched filter approach, identification with an ad-hoc method based on the spacing between fiducials, and image registration with a simple least squares fit. Performance is verified on a combination of artificially generated images, test data recorded on the ground, and images from the 2013 flight. C1 [Cramer, Alex; Christe, Steven; Shih, Albert] Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP Cramer, A (reprint author), Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. EM alexander.cramer@nasa.gov; albert.y.shih@nasa.gov NR 25 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 14 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302010 ER PT J AU D'Ortenzio, MV Bresina, JL Crocker, AR Elphic, RC Galal, KF Hunt, DR Owens, BD Plice, L Hawkins, AM Policastri, LA AF D'Ortenzio, Matthew V. Bresina, John L. Crocker, Alan R. Elphic, Richard C. Galal, Ken F. Hunt, David R. Owens, Brandon D. Plice, Laura Hawkins, Alisa M. Policastri, Lisa A. GP IEEE TI Operating LADEE: Mission Architecture, Challenges, Anomalies, and Successes SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB NASA's Lunar Atmosphere and Dust Environment Explorer (LADEE) mission was both a lunar science and a technology demonstration mission. The goals identified for LADEE were to determine the composition of the lunar atmosphere and investigate the processes that control its distribution and dynamics, and to determine whether dust is present in the lunar exosphere and reveal the processes that contribute to its sources and variability. LADEE was also developed to serve as a platform for the Lunar Laser Communications Demonstration (LLCD), which had the goal of demonstrating the viability of high-speed optical communication to and from the Moon. LADEE met all of these objectives by operating a robotic spacecraft in a low-altitude, near circular, near equatorial lunar orbit where remote sensing and in-situ instruments measured the Moon's atmosphere and dust environment, and the LLCD demonstrated optical communications at lunar distances. The spacecraft was launched in September of 2013, and spent approximately one month in a transfer orbit before being inserted into lunar orbit in October. It orbited the moon for 188 days, logging time over five lunar synodic months, i.e., "lunations", before being decommissioned via surface impact in April of 2014. LADEE exceeded its baseline mission duration by greater than 40% in terms of time in the science orbit, and greater than 200% in terms of science data return. This paper summarizes the LADEE mission architecture and describes the operational phase of the LADEE mission in detail. The combination of an aggressive science campaign, the demonstration of a new optical communications payload, and the first-use of a new low-cost spacecraft bus resulted in an operational phase filled with challenges, both planned and unplanned. We explain our approach to orbit determination, maneuver planning, attitude planning, activity planning and command sequencing, which yielded exceedingly positive results in the face of a demanding operational timeline consisting of hundreds of interleaved instrument and spacecraft activities. In addition, we discuss the team's identification of, and response to, several in-flight anomalies including a shutdown of the spacecraft's reaction wheels immediately following launch and an on-going unexpected behavior of the on-board star-tracker and attitude state estimation system. Finally, we reflect on the operations experience overall, the successes that LADEE enjoyed, and some suggestions for future lunar missions. C1 [D'Ortenzio, Matthew V.] NASA, Ames Res Ctr, Intelligent Syst Div, Moffett Field, CA 94035 USA. [Bresina, John L.; Elphic, Richard C.; Galal, Ken F.; Hunt, David R.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Crocker, Alan R.] NASA, Ames Res Ctr, Chief Engineers Off, Moffett Field, CA 94035 USA. [Owens, Brandon D.] Stinger Ghaffarian Technol Inc, Moffett Field, CA USA. [Plice, Laura] Metis Technol Solut Inc, Moffett Field, CA USA. [Hawkins, Alisa M.] Aerosp Corp, El Segundo, CA 90245 USA. [Policastri, Lisa A.] Appl Def Solut Inc, Columbia, MD USA. RP D'Ortenzio, MV (reprint author), NASA, Ames Res Ctr, Intelligent Syst Div, Moffett Field, CA 94035 USA. EM matthew.dortenzio@nasa.gov; john.l.bresina@nasa.gov; alan.r.crocker@nasa.gov; richard.c.elphic@nasa.gov; ken.galal@nasa.gov; rusty.hunt@nasa.gov; brandon.d.owens@nasa.gov; laura.plice@nasa.gov; alisahawkins01@gmail.com; lisa@applieddefense.com NR 17 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 23 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300085 ER PT J AU Daigle, M Sankararaman, S Kulkarni, CS AF Daigle, Matthew Sankararaman, Shankar Kulkarni, Chetan S. GP IEEE TI Stochastic Prediction of Remaining Driving Time and Distance for a Planetary Rover SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT ID PROGNOSTICS AB The operations of a planetary rover depend critically upon the amount of power that can be delivered by its batteries. In order to plan the future operation of the rover, it is important to make reliable predictions regarding the end-of-discharge time, which, in turn, can be used to estimate the remaining driving time and distance of the rover. In addition, quantifying the uncertainty in these predictions is critical to making risk-informed decisions regarding the operations of the rover. This paper presents a computational methodology to stochastically predict end-of-discharge time, remaining driving time, and remaining driving distance for a planetary rover, based on monitoring the batteries that power the rover. We utilize a model-based prognostics framework that characterizes and incorporates the various sources of uncertainty into these predictions, thereby assisting operational decision-making. We consider two different types of driving scenarios, structured and unstructured driving, and characterize the uncertainty they create in the future usage of the rover. In structured driving, the rover navigates among a set of known waypoints, and in unstructured driving, the rover performs a sequence of unplanned maneuvers. Results from a set of field experiments illustrate these computational methods and demonstrate their applicability. C1 [Daigle, Matthew] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Sankararaman, Shankar] NASA, SGT Inc, Ames Res Ctr, Moffett Field, CA 94035 USA. [Kulkarni, Chetan S.] NASA, SGT Inc, Ames Res Ctr, Prognost Ctr Excellence, Moffett Field, CA 94035 USA. RP Daigle, M (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM matthew.j.daigle@nasa.gov; shankar.sankararaman@nasa.gov; chetan.s.kulkarni@nasa.gov NR 32 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 9 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302077 ER PT J AU Darrach, M Madzunkov, S Nikolic, RSD Simcic, J Kidd, R Neidholdt, E Pilinski, M Jaramillo-Botero, A Farley, K AF Darrach, Murray Madzunkov, Stojan Nikolic, Rembrandt Schaefer Dragan Simcic, Jurij Kidd, Richard Neidholdt, Evan Pilinski, Marcin Jaramillo-Botero, Andres Farley, Ken GP IEEE TI The Mass Analyzer for Real-time Investigation of Neutrals at Europa (MARINE) SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT ID ATMOSPHERE AB Presented herein is the progress on developing a new mass analyzer for analysis of the exospheres of planets, moons, and primitive bodies, such as found at Europa or Enceladus. Europa, one of Jupiter's four Galilean moons, may have a subsurface ocean plausibly containing the key ingredients for life as well as sources of chemical energy. Clues to the composition and chemical state of Europa's ocean can be found both on Europa's icy surface and in its tenuous atmosphere. Given the high scientific priority of assessing the habitability of Europa's ocean, the Europa Clipper notional payload includes a Neutral Mass Spectrometer whose purpose is to characterize the composition of ejected surface products during a series of flyby investigations. The Mass Analyzer for Real-time Investigation of Neutrals at Europa (MARINE) is capable of measuring the abundances of neutral particle species in Europa's exosphere including H2O, O-2, CO2, and SO2, and determining their number density profiles at per-second sampling rates as a function of altitude above Europa's surface. MARINE will either detect tracers of potential subsurface biological activity in Europa's exosphere, or place upper limits on their surface abundances. It exceeds all requirements for the proposed investigations with margins ranging from 100 to 1000%, while remaining fully compatible with spacecraft accommodation constraints for mass, power, data volume, and field-of-view. C1 [Darrach, Murray; Madzunkov, Stojan; Nikolic, Rembrandt Schaefer Dragan; Simcic, Jurij; Kidd, Richard; Neidholdt, Evan] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Pilinski, Marcin] ASTRA LLC, Boulder, CO 80301 USA. [Jaramillo-Botero, Andres; Farley, Ken] CALTECH, Pasadena, CA 91125 USA. RP Darrach, M (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Murray.R.Darrach@jpl.nasa.gov; mpilinski@astraspace.net; ajaramil@caltech.edu; farley@gps.caltech.edu NR 16 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 12 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501301048 ER PT J AU Deininger, W Porter, B Sexton, A Moler, V Marotta, B Osborne, R Riesco, M Wendland, R Acton, D McLean, C Tshudy, M Aggarwal, P AF Deininger, William Porter, Brad Sexton, Adam Moler, Vickey Marotta, Brian Osborne, Rob Riesco, Maureen Wendland, Ron Acton, David McLean, Christopher Tshudy, Michael Aggarwal, Pravin GP IEEE TI Incorporation of Secondary Payloads onto the Green Propellant Infusion Mission (GPIM) SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB The Green Propellant Infusion Mission (GPIM) Project is sponsored by the NASA Space Technology Mission Directorate (STMD) as part of the work conducted by the Technology Demonstration Mission (TDM) Office. The goal of GPIM is to advance the technology readiness level (TRL) of a green propulsion technology based on the monopropellant AF-M315E via flight demonstration. As the Project lead, Ball Aerospace & Technologies Corp. (Ball Aerospace) is coordinating contributions from industry, NASA, and the U.S. Air Force to execute the GPIM project. In May 2014, the GPIM Project was authorized to integrate three Air Force Science Experiments Review Board (SERB) secondary pay-loads onto the GPIM space vehicle: iMESA-R, SWATS and SOS. This paper summarizes the flexibility of the BCP-100 spacecraft and describes the work to accommodate the three Air Force SERB payloads. The GPIM space vehicle consists of a GPPS Module mounted on a BCP-100 bus module with the three SERB payloads mounted to a bus side panel. C1 [Deininger, William; Porter, Brad; McLean, Christopher] Ball Aerosp & Technol Corp, 1600 Commerce St, Boulder, CO 80301 USA. [Sexton, Adam] Ball Aerosp & Technol Corp, Dept Mech Engn, Boulder, CO 80301 USA. [Moler, Vickey] Ball Aerosp & Technol Corp, Spacecraft Syst Engn Dept, Boulder, CO 80301 USA. [Marotta, Brian] Ball Aerosp & Technol Corp, Attitude Determinat & Control Grp, Boulder, CO 80301 USA. [Osborne, Rob] Ball Aerosp & Technol Corp, Syst Test, Boulder, CO 80301 USA. [Riesco, Maureen] Ball Aerosp & Technol Corp, Cryogen & Thermal Engn, Boulder, CO 80301 USA. [Wendland, Ron] Ball Aerosp & Technol Corp, Struct Anal Grp, Boulder, CO 80301 USA. [Aggarwal, Pravin] NASA, Marshall Space Flight Ctr, Technol Demonstrat Mission Program Off, Huntsville, AL 35812 USA. RP Deininger, W (reprint author), Ball Aerosp & Technol Corp, 1600 Commerce St, Boulder, CO 80301 USA. EM wdeining@ball.com; bporter@ball.com; asexton@ball.com; vmoler@ball.com; bmarotta@ball.com; rosborne@ball.com; mriesco@ball.com; rwendlan@ball.com; dacton@ball.com; cmclean@ball.com; michael.tshudy@kirtland.af.mil; pravin.aggarwal@nasa.gov NR 25 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 10 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302067 ER PT J AU Depenbrock, B Balint, T Sheehy, J AF Depenbrock, Brett Balint, Tibor Sheehy, Jeffrey GP IEEE TI Leveraging Design Principles to Optimize Technology Portfolio Prioritization SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Research and development organizations frequently encounter challenges when attempting to identify an investment strategy and to accurately forecast the cost and schedule performance of selected projects. Fast moving and complex environments require managers to analyze quickly and to diagnose the value of returns on innovation investments versus allocated resources. Our Project Assessment Framework Through Design (PAFTD) tool facilitates decision making for NASA senior leadership to enable more strategic and consistent technology development investment analysis, beginning at implementation and continuing through the project life cycle. The framework leverages design principles of usability, feasibility, and viability and aligns them with methods employed by NASA's Independent Program Assessment Office for project performance assessment. The need exists to periodically revisit the justification and prioritization of technology development investments as changes occur over project life cycles. The framework informs management rapidly and comprehensively about diagnosed internal and external root causes of project performance. PAFTD offers a means to measure and quantify key aspects of different projects to enable consistent comparisons between projects in a loosely coupled investment portfolio. The model allows senior leadership to quickly diagnose project performance strengths and weaknesses to further improve their investment decisions. The framework has been employed to assess system level technology development investments across the high technology readiness levels of the NASA Space Technology Mission Directorate. It has been robust enough for assessment of investment efforts at NASA centers, federally funded research and development centers (FFRDCs), and industry. PAFTD can also be tailored depending on the strategy and the success parameters of the assessed entity. Specifically, it can be customized to any organization that invests in technology development projects and which could benefit from an easy to use, integrated means of analyzing the relevance of investments with technical and cost performance. In this paper we provide an overview of the framework, its capabilities, and its utility as demonstrated through example cases at NASA. C1 [Depenbrock, Brett] Booz Allen Hamilton, 901 15th St, Washington, DC 20005 USA. [Balint, Tibor] Royal Coll Art, Sch Design, Kensington Gore, London SW7 2EU, England. [Sheehy, Jeffrey] NASA Headquarters, Mission Directorate, Space Technol, Mail Code OA, Washington, DC 20546 USA. RP Depenbrock, B (reprint author), Booz Allen Hamilton, 901 15th St, Washington, DC 20005 USA. EM depenbrock_brett@bah.com; tibor.balint@network.rca.ac.uk; jeffrey.sheehy@nasa.gav NR 28 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 10 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303028 ER PT J AU Didier, J Chapman, D Aboobaker, AM Araujo, D Grainger, W Hanany, S Nelson, K Hillbrand, S Korotkov, A Limon, M Miller, A Reichborn-Kjennerud, B Sagiv, I Tucker, G Vinokurov, Y AF Didier, Joy Chapman, Daniel Aboobaker, Asad M. Araujo, Derek Grainger, Will Hanany, Shaul Nelson, Kyle Hillbrand, Seth Korotkov, Andrei Limon, Michele Miller, Amber Reichborn-Kjennerud, Britt Sagiv, Ilan Tucker, Greg Vinokurov, Yuri GP IEEE TI A High-resolution Pointing System for Fast Scanning Platforms: the EBEX Example SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB The E and B experiment (EBEX) is a balloon-borne telescope designed to measure the polarization of the cosmic microwave background with 8' resolution employing a gondola scanning with speeds of order degree per second. In January 2013, EBEX completed 11 days of observations in a flight over Antarctica covering similar to 6000 square degrees of the sky. The payload is equipped with two redundant star cameras and two sets of three orthogonal gyroscopes to reconstruct the telescope attitude. The EBEX science goals require the pointing to be reconstructed to approximately 10" in the map domain, and in-flight attitude control requires the real time pointing to be accurate to similar to 0.5 degrees. The high velocity scan strategy of EBEX coupled to its float altitude only permits the star cameras to take images at scan turnarounds, every similar to 40 seconds, and thus requires the development of a pointing system with low noise gyroscopes and carefully controlled systematic errors. Here we report on the design of the pointing system and on a simulation pipeline developed to understand and minimize the effects of systematic errors. The performance of the system is evaluated using the 2012/2013 flight data, and we show that we achieve a pointing error with RMS=25" on 40 seconds azimuth throws, corresponding to an error of similar to 4.6" in the map domain. C1 [Didier, Joy; Chapman, Daniel; Araujo, Derek; Limon, Michele; Miller, Amber; Reichborn-Kjennerud, Britt] Columbia Univ, New York, NY 10027 USA. [Aboobaker, Asad M.] Jet Prop Lab, Pasadena, CA 91101 USA. [Grainger, Will] Rutherford Appleton Lab, Oxford OX11 0QX, England. [Hanany, Shaul] Univ Minnesota, Minneapolis, MN 55455 USA. [Nelson, Kyle; Korotkov, Andrei; Tucker, Greg] Brown Univ, Providence, RI 02912 USA. [Sagiv, Ilan] Weizmann Inst Sci, IL-76100 Rehovot, Israel. [Vinokurov, Yuri] Carnegie Mellon Univ, Pittsburgh, PA 15213 USA. [Hillbrand, Seth] Calif State Univ Sacramento, Sacramento, CA 95819 USA. RP Didier, J (reprint author), Columbia Univ, New York, NY 10027 USA. NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 15 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501301041 ER PT J AU Divsalar, D Vilnrotter, V Asmar, S Cheung, KM AF Divsalar, Dariush Vilnrotter, Victor Asmar, Sami Cheung, Kar-Ming GP IEEE TI Radio Science Measurements using Phase Modulated Optical Links SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Radio Science experiments currently rely on un-modulated continuous wave RF signal carrier for spectral purity and maximized signal-to-noise ratio. This requires missions to carefully schedule them away from periods of high rate telemetry. In the era of optical communications, currently designed systems experience the same problem. In this paper, a data processing architecture is derived that will yield high-accuracy link science type of information on the ground from readily transmitted communication signals coming from space assets, through optical links. This technique is intended to save power, bandwidth and scheduling demands on the spacecraft. Our proposed technical approach is applicable to a phase modulated laser thus providing an architectural improvement to present state-of-the-art optical communication systems utilized by NASA as well as to future systems. The approach is to, first, obtain the achievable performance of Radio Science measurements from the received optical telemetry signals. This extends our previous results presented on Radio Science measurements for suppressed carrier RF signals. Secondly, a practical system is proposed that approaches the ultimate theoretical performance for estimating the amplitude, phase, and frequency variations due to the changes in the planet atmosphere. For optical links, our previous results to phase modulated CW laser communications are extended. The same information required for radio science data can be extracted by using either differential methods of encoding or phase modulated orthogonal signals and at the optical receiver a non-coherent local laser and an array of photon detectors are used. The performance of these phase modulated schemes is analyzed. C1 [Divsalar, Dariush; Vilnrotter, Victor; Asmar, Sami; Cheung, Kar-Ming] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Divsalar, D (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM dariush.divsalar@jpl.nasa.gov; victor.vilnrotter@jpl.nasa.gov; sami.asmar@jpl.nasa.gov; kar-ming.cheung@jpl.nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 7 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501301074 ER PT J AU Edwards, BL Israel, DJ AF Edwards, Bernard L. Israel, David J. GP IEEE TI Commercialization and Standardization Progress towards an Optical Communications Earth Relay SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB NASA is planning to launch the next generation of a space based Earth relay in 2025 to join the current Space Network, consisting of Tracking and Data Relay Satellites in space and the corresponding infrastructure on Earth. While the requirements and architecture for that relay satellite are unknown at this time, NASA is investing in communications technologies that could be deployed to provide new communications services. One of those new technologies is optical communications. The Laser Communications Relay Demonstration (LCRD) project, scheduled for launch in 2018 as a hosted payload on a commercial communications satellite, is a critical pathfinder towards NASA providing optical communications services on the next generation space based relay. This paper will describe NASA efforts in the on-going commercialization of optical communications and the development of inter-operability standards. Both are seen as critical to making optical communications a reality on future NASA science and exploration missions. Commercialization is important because NASA would like to eventually be able to simply purchase an entire optical communications terminal from a commercial provider. Inter-operability standards are needed to ensure that optical communications terminals developed by one vendor are compatible with the terminals of another. International standards in optical communications would also allow the space missions of one nation to use the infrastructure of another. C1 [Edwards, Bernard L.] NASA, GSFC Code 560, Greenbelt, MD 20771 USA. [Israel, David J.] NASA, GSFC Code 450, Greenbelt, MD 20771 USA. RP Edwards, BL (reprint author), NASA, GSFC Code 560, Greenbelt, MD 20771 USA. EM Bernard.L.Edwards@nasa.gov; David.J.Israel@nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 7 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300011 ER PT J AU Edwards, CD Barela, PR Gladden, RE Lee, CH De Paula, R AF Edwards, Charles D., Jr. Barela, Philip R. Gladden, Roy E. Lee, Charles H. De Paula, Ramon GP IEEE TI NASA Relay Planning for the 2016 Mars Mission Opportunity SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Two landers are scheduled to arrive at Mars in the fall of 2016. Telecommunication relay support from the network of Mars relay orbtiers will be crucial in supporting these landers' mission objectives. Arriving first, NASA's InSight Lander mission is scheduled to arrive at Mars in September 2016. Coverage of InSight's Entry, Descent, and Landing ( EDL) requires re-positioning of the Mars Reconnaissance Orbiter's orbit plane. After landing, InSight relay support is complicated by the proximity of its landing site to Gale Crater, where Curiosity may well be continuing its surface mission. We present strategies for addressing the relay needs of both landers. Three weeks later, the ESA/RSA ExoMars Trace Gas Orbiter will arrive, deploying an EDL Demonstrator Module ( EDM) to demonstrate Mars landing technologies and carrying out a short four-sol surface mission. NASA relay orbiters will be critical for support of the EDM surface mission. TGO will continue its science operation while also providing relay services to ESA and NASA landers using a NASA-provided Electra UHF transceiver. C1 [Edwards, Charles D., Jr.; Barela, Philip R.; Gladden, Roy E.; Lee, Charles H.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [De Paula, Ramon] NASA, Washington, DC 20546 USA. RP Edwards, CD (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM chad.edwards@jpl.nasa.gov NR 17 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 9 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303089 ER PT J AU Enger, S Deininger, WD Mitchell, S Soto, JC Kendall, M Unruh, B McGuire, ML AF Enger, Scott Deininger, William D. Mitchell, Scott Soto, J. C. Kendall, Martha Unruh, Bryce McGuire, Melissa L. GP IEEE TI Solar Electric Propulsion on ESPA-Class Satellite SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Ball Aerospace & Technologies Corp participated in a Space Act Agreement with NASA GRC to determine the feasibility of accommodating enough Solar Electric Propulsion (SEP) on the Ball ESPA-class bus to result in a mission of interest to Ball customers. The baseline for the study was the ESPA-class BCP-100 bus. Since the BCP-100 bus has flight heritage on USAF programs, the approach for the study was to use the existing bus design and minimize changes to only those necessary to accommodate the SEP system. This approach maintains high heritage and minimizes the amount of Non-Recurring Engineering required for the bus. High heritage components were also selected for the SEP system when available, including an off-the-shelf Xenon tank, existing cathode, HET thruster and Xenon feed control, allowing future development funding to be focused on a PPU compatible with the existing BCP-100 28 V power bus. The results of the study show that while meeting the ESPA envelope and mass requirements, the BCP-I00 can accommodate enough SEP capability to allow the orbit to be raised or lowered anywhere within LEO or change the inclination up to 10 degrees from a LEO starting point. From a GTO starting point, an elliptical orbit with apogee at GEO is also possible. C1 [Enger, Scott; Deininger, William D.; Mitchell, Scott; Soto, J. C.; Kendall, Martha; Unruh, Bryce] Ball Aerosp & Technol Corp, 1600 Commerce St, Boulder, CO 80301 USA. [McGuire, Melissa L.] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Enger, S (reprint author), Ball Aerosp & Technol Corp, 1600 Commerce St, Boulder, CO 80301 USA. EM senger@ball.com; wdeining@ball.com; smitchel@ball.com; jsoto@ball.com; mkendall@ball.com; bunruh@ball.com; melissa.l.mcguire@nasa.gov NR 20 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 10 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302042 ER PT J AU Fanchiang, C Marquez, JJ Gore, BF Klaus, D AF Fanchiang, Christine Marquez, Jessica J. Gore, Brian F. Klaus, David GP IEEE TI Survey and Assessment of Crew Performance Evaluation Methods Applicable to Human Spacecraft Design SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Space is an unforgiving environment where the actions of the crew play a critical role in their health and safety. Given the limited number of crewmembers typically onboard a spacecraft and the multitude of complex systems they must operate, the performance of each individual is of paramount importance. Spacecraft habitat layout and operations are two main drivers affecting crew performance efficiency. Having the capability to analyze and compare crew performance across various spacecraft configurations can help identify improvements early in the conceptual design process where changes are less costly to implement, ultimately reducing overall project costs and improving long-term operations of the system. Currently, there are few comprehensive methods readily available for evaluating crew integration within a spacecraft in the conceptual design phase. In order to address this shortcoming, the goal of this work was to analyze various specialized evaluation methods found in analogous industries that have potential application to human spacecraft design. A survey of more than 400 human performance evaluation methods was completed. Over twenty different attributes were identified for each method and a variety of analyses were conducted to characterize and evaluate their potential use for assessing human spacecraft design options. The analysis revealed a particular deficiency of quantitative evaluation methods that are applicable early in the systems engineering design phase. It also identified five existing methods that could be supplemented to achieve the needs of an early design evaluation method. Additional discussion describes potential issues that must be overcome when developing a method specific for use in human spacecraft evaluations. C1 [Fanchiang, Christine; Klaus, David] Univ Colorado, Boulder, CO 80303 USA. [Marquez, Jessica J.; Gore, Brian F.] NASA, Ames Res Ctr, Moffett Field, CA USA. RP Fanchiang, C (reprint author), Univ Colorado, Boulder, CO 80303 USA. EM fanchian@colorado.edu; jessica.j.marquez@nasa.gov; brian.f.gore@nasa.gov; klaus@colorado.edu NR 23 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 10 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300052 ER PT J AU Farnocchia, D Chesley, SR AF Farnocchia, Davide Chesley, Steven R. GP IEEE TI Apophis: Complex Rotation and Hazard Assessment SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT ID ASTEROID 99942 APOPHIS; SPIN-STATE; YARKOVSKY; EARTH; HAYABUSA; ITOKAWA; ASTROMETRY; HERSCHEL AB We present an updated hazard assessment for near-Earth asteroid (99942) Apophis. The stiff dynamics and the high precision of the trajectory of Apophis call for the most accurate dynamical model. In particular, the dominant source of ephemeris prediction uncertainty is the Yarkovsky effect. We include the Yarkovsky perturbation in the force model by numerically computing the related thermal recoil accelerations. These acceleration are statistically computed according to the known physical properties of Apophis and their uncertainties. Special effort is required to account for the non-principal axis rotation state of Apophis. Finally, we generated Monte Carlo samples to capture the uncertainty in both the orbital elements and the Yarkovsky accelerations and compute the probability of future Earth impacts. Whereas collisions with Earth before 2060 are ruled out, impacts are still possible starting in 2060. The highest impact probability is seven in a million for the April 2068 Earth encounter. C1 [Farnocchia, Davide; Chesley, Steven R.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Farnocchia, D (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. EM Davide.Farnocchia@jpl.nasa.gov; Steve.Chesley@jpl.nasa.gov NR 34 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 7 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302072 ER PT J AU Gal-Edd, J Cheuvront, A AF Gal-Edd, Jonathan Cheuvront, Allan GP IEEE TI The OSIRIS-REx Asteroid Sample Return Mission Operations Design SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB OSIRIS-REx is an acronym that captures the scientific objectives: Origins, Spectral Interpretation, Resource Identification, and Security square Regolith Explorer. OSIRIS-REx will thoroughly characterize near-Earth asteroid Bennu (previously known as 1019551999 RQ36). The OSIRIS-REx Asteroid Sample Return Mission delivers its science using five instruments and radio science along with the Touch-and-Go Sample Acquisition Mechanism (TAGSAM). All of the instruments and data analysis techniques have direct heritage from flown planetary missions. The OSIRIS-REx mission employs a methodical, phased approach to ensure success in meeting the mission's science requirements. OSIRIS-REx launches in September 2016, with a backup launch period occurring one year later. Sampling occurs in 2019. The departure burn from Bennu occurs in March 2021. On September 24, 2023, the Sample Return Capsule (SRC) lands at the Utah Test and Training Range (UTTR). Stardust heritage procedures are followed to transport the SRC to Johnson Space Center, where the samples are removed and delivered to the OSIRIS-REx curation facility. After a six-month preliminary examination period the mission will produce a catalog of the returned sample, allowing the worldwide community to request samples for detailed analysis. Traveling to and returning samples from an asteroid that has not been explored before requires unique operations consideration. The Design Reference Mission (DRM) ties together spacecraft, instrument, and operation scenarios. Asteroid Touch-and-Go (TAG) has various options varying from ground only to fully automated (natural feature tracking). Spacecraft constraints such as thermodynamics and high gain antenna pointing impact the timeline. The mission is sensitive to navigation errors, so a late command update has been implemented. The project implemented lessons learned from other "small body" missions. The key lesson learned was "expect the unexpected" and implement planning tools early in the lifecycle. This paper summarizes the ground and spacecraft design as presented at OSIRIS-REx Critical Design Review (CDR) held April 2014. C1 [Gal-Edd, Jonathan] Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Cheuvront, Allan] Gen Dynam C4 Syst, Seabrook, MD 20706 USA. RP Gal-Edd, J (reprint author), Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. EM jonathan.s.gal-edd@nasa.gov; allan.cheuvront@gd-ms.com NR 2 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 9 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300009 ER PT J AU Gaskin, J Elsner, R Ramsey, B Wilson-Hodge, C Tennant, A Christe, S Shih, A Kilaru, K Swartz, D Seller, P Wilson, M Stuchlik, D Weddendorf, B AF Gaskin, Jessica Elsner, Ronald Ramsey, Brian Wilson-Hodge, Colleen Tennant, Allyn Christe, Steven Shih, Albert Kilaru, Kiranmayee Swartz, Douglas Seller, Paul Wilson, Matthew Stuchlik, David Weddendorf, Bruce GP IEEE TI SuperHERO: Design of a New Hard-X-Ray Focusing Telescope SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT ID 1ST IMAGES; DETECTORS AB SuperHERO is a hard x-ray (20-75 keV) balloon-borne telescope, currently in its proposal phase, that will utilize high angular-resolution grazing-incidence optics, coupled to novel CdTe multi-pixel, fine-pitch (250 mu m) detectors. The high-resolution electroformed-nickel, grazing-incidence optics were developed at MSFC, and the detectors were developed at the Rutherford Appleton Laboratory in the UK, and are being readied for flight at GSFC. SuperHERO will use two active pointing systems; one for carrying out astronomical observations and another for solar observations during the same flight. The telescope will reside on a light-weight, carbon-composite structure that will integrate the Wallops Arc Second Pointer into its frame, for arcsecond or better pointing. This configuration will allow for Long Duration Balloon flights that can last up to 4 weeks. This next generation design, which is based on the High Energy Replicated Optics (HERO) and HERO to Explore the Sun (HEROES) payloads, will be discussed, with emphasis on the core telescope components. C1 [Gaskin, Jessica; Elsner, Ronald; Ramsey, Brian; Wilson-Hodge, Colleen; Tennant, Allyn] NASA, Marshall Space Flight Ctr, Huntsville, AL 35811 USA. [Christe, Steven; Shih, Albert] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Kilaru, Kiranmayee; Swartz, Douglas] Univ Space Res, Huntsville, AL 35805 USA. [Seller, Paul; Wilson, Matthew] Rutherford Appleton Lab, Sci & Technol Facil Council, Harwell Campus, Didcot OX11 0QX, Oxon, England. [Stuchlik, David] NASA, Goddard Space Flight Ctr, Wallops Isl, VA 23337 USA. [Weddendorf, Bruce] Weddendorf Design Inc, Huntsville, AL 35803 USA. RP Gaskin, J (reprint author), NASA, Marshall Space Flight Ctr, Huntsville, AL 35811 USA. EM Jessica.Gaskin@nasa.gov; Steven.d.Christe@nasa.gov; kiranmayee.kilaru-1@nasa.gov; paul.seller@stfc.ac.uk; david.w.stuchlik@nasa.gov; bruce@weddendorf.com NR 37 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 15 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302033 ER PT J AU Gates, M Mazanek, D Muirhead, B Stich, S Naasz, B Chodas, P McDonald, M Reuter, J AF Gates, Michele Mazanek, Dan Muirhead, Brian Stich, Steve Naasz, Bo Chodas, Paul McDonald, Mark Reuter, Jim GP IEEE TI NASA's Asteroid Redirect Mission Concept Development Summary SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB This paper summarizes key findings of Asteroid Redirect Mission pre-formulation concept development efforts, including mission architecture and design drivers, flight system concepts and trades, advanced solar electric propulsion component and system options, and asteroid capture option trades and risk reduction efforts. This paper also provides a summary of concept development findings with a focus on extensibility to future mission applications and risk reduction and early testing of astronaut extra-vehicular activities. C1 [Gates, Michele] NASA Headquarters, 300 E St SW, Washington, DC 20546 USA. [Mazanek, Dan] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Muirhead, Brian; Chodas, Paul] Jet Prop Lab, Pasadena, CA 91109 USA. [Stich, Steve; McDonald, Mark] NASA, Johnson Space Ctr, Houston, TX 77058 USA. [Naasz, Bo] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Reuter, Jim] NASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Gates, M (reprint author), NASA Headquarters, 300 E St SW, Washington, DC 20546 USA. EM Michele.M.Gates@nasa.gov; Daniel.D.Mazanek@nasa.gov; Brian.K.Muirhead@jpl.nasa.gov; J.S.Stich@nasa.gov; Bo.J.Naasz@nasa.gov; Paul.W.Chodas@nasa.gov; Mark.A.Mcdonald@nasa.gov; Jim.L.Reuter@nasa.gov NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 12 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302096 ER PT J AU Gershman, B Howe, S Lantoine, G Love, S Hopkins, J Drever, M AF Gershman, Bob Howe, Scott Lantoine, Gregory Love, Stan Hopkins, Josh Drever, Mike GP IEEE TI Human-Assisted Mars Sample Return SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Any Mars Sample Return campaign must assure a very low probability of inadvertent release of Mars material into the Earth's biosphere in order to provide protection against the extremely unlikely possibility of biological hazards in the returned material. Containment assurance requires breaking the chain of contact with Mars: any Mars material reaching Earth must be inside a sealed sample container. Then the integrity of the sample container must be maintained (with an unprecedented degree of confidence) until delivered to a secure receiving facility on Earth. Earth entry poses a challenge to sample container integrity. In most studies this challenge is met by developing a new, highly-robust, robotic Earth entry vehicle; but NASA's plans for future human space activities offer other possibilities. These plans for the next couple of decades include options for crewed operations in lunar and Mars orbits. This paper describes the results of a study of options for having robotic spacecraft deliver samples to these locations for handoff to the crewed vehicle followed by return to Earth with the crew. Conceptual designs for several options are presented and pros and cons relative to the completely robotic campaign are discussed. C1 [Gershman, Bob; Howe, Scott; Lantoine, Gregory] Jet Prop Lab, Pasadena, CA 91109 USA. [Love, Stan] NASA JSC, Houston, TX USA. [Hopkins, Josh; Drever, Mike] Lockheed Martin Corp, Denver, CO USA. RP Gershman, B (reprint author), Jet Prop Lab, Pasadena, CA 91109 USA. EM Robert.Gershman@jpl.nasa.gov; A.Scott.Howe@jpl.nasa.gov; Gregory.Lantoine@jpl.nasa.gov; Stanley.G.Love@nasa.gov; Josh.B.Hopkins@lmco.com; Mike.Drever@lmco.com NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 10 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302040 ER PT J AU Gibson, C Bonnici, M Castet, JF AF Gibson, Corrina Bonnici, Michael Castet, Jean-Francois GP IEEE TI Model-based Spacecraft Fault Management Design & Formal Validation SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB A model-based method of software system logical design and formal validation will be discussed for the application of fault management throughout the project lifecycle. We have demonstrated that when modeling fault protection system behaviors during the design phases of a project, the expected behavior can be verified early on by executing the model. Correctly capturing the expected behavior in the model improves the system design so that is better defined and complete upon implementation. Additionally, performing model checking formally validates the behavior model against properties of correctness (assertions). The potential to generate and link additional model-based fault management products from the fault protection logical behavior model is key to projects adopting model driven design and retaining a single source of truth. When modeling heritage systems or if a dictionary-type database is needed, a standard for machine-readable import/export of fault management parameters allows for easier integration between flight software and the model-based products. Depending on if there is fault management information available while developing a behavior model, a method for auto-generating the model can be used that reduces human errors and speeds up the modeling process. C1 [Gibson, Corrina; Bonnici, Michael; Castet, Jean-Francois] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Gibson, C (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Corrina.L.Gibson@jpl.nasa.gov; Michael.F.Bonnici@jpl.nasa.gov; JeanFrancois.Castet@jpl.nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 12 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302046 ER PT J AU Gingerich, D Balke, J Sanders, S Hughes, N Mumaw, S King, MD Niebur, D Potts, C Bezjak, K Tietz, J Wynn, J AF Gingerich, Dave Balke, John Sanders, Steve Hughes, Noel Mumaw, Sue King, Matthew D. Niebur, Doug Potts, Chris Bezjak, Kelly Tietz, John Wynn, Jason GP IEEE TI Verification of Mars Odyssey All-Stellar Attitude Determination Ten Years After Launch SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB This paper describes the process used in 2012 by a combined mission Operations Team from the Jet Propulsion Lab and Lockheed Martin Civil Space to successfully upgrade and certify all-stellar attitude determination flight software first included in the as-launched, flight software image of Mars Odyssey 2001. It provides background on why this attitude determination flight software was not completely verified prior to launch and yet had prudently been included in the as-launched FSW image. All-stellar attitude determination was re-considered in 2012 as an alternative to gyro-based attitude determination after the A-side inertial measurement unit's laser intensity monitor exhibited a typical, near-end-of-life signature. After several reviews of the original all-stellar requirements, software design and test results, mission operations engineers concluded that the all-stellar flight software had successfully completed requirements, design, code, and unit testing but had been intentionally and with customer approval, de-scoped prior to completing system verification. This paper also relates how that while completing the previously de-scoped system verification tests of all-stellar AD, the Operations Team discovered a design defect in the original flight software as well as limitations with the star camera which is the primary component for All-Stellar. It describes the rigorous process followed by the Operations Team to build and test a patch to the Odyssey flight software that enabled the successful transition from gyro-based to all-stellar attitude determination. Subsequently, the A-side inertial measurement unit was powered off, prolonging the life of this spacecraft component. The paper concludes with a discussion of how the operations model employed by the combined mission Operations Teams enabled the successful, albeit unorthodox, correction and verification of previously descoped flight software included in an as-launched, but never completely verified flight software image. C1 [Gingerich, Dave; Balke, John; Sanders, Steve; Hughes, Noel; Mumaw, Sue; King, Matthew D.; Niebur, Doug] Lockheed Martin Space Syst Co, Mail Stop S8700,POB 179, Denver, CO 80201 USA. [Potts, Chris] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. [Bezjak, Kelly] Red Canyon Software, Denver, CO 80201 USA. [Tietz, John] MEI Technol Inc, Vista, CA 92081 USA. [Wynn, Jason] Adv Solut Inc, Littleton, CO 80127 USA. RP Gingerich, D (reprint author), Lockheed Martin Space Syst Co, Mail Stop S8700,POB 179, Denver, CO 80201 USA. EM David.E.Gingerich@lmco.com; John.Balke@lmco.com; Stephen.S.Sanders@lmco.com; Noel.H.Hughes@lmco.com; Susan.J.Mumaw@lmco.com; Matthew.D.King@lmco.com; Doug.Niebur@lmco.com; Christopher.L.Potts@jpl.nasa.gov; Kelly.J.Bezjak@lmco.com; John.C.Tietz@gmail.com; JWynn@go-asi.com NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 21 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501301032 ER PT J AU Gomez-Rosa, C Cifuentes, J Wasiak, F Alfonzo, A AF Gomez-Rosa, Carlos Cifuentes, Juan Wasiak, Francis Alfonzo, Agustin GP IEEE TI Essentials for Team Based Rehearsals and the Differences between Earth Orbiting and Deep Space Missions SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB The mission readiness environment is where spacecraft and ground systems converge to form the entire as built flight system for the final phase of operationally-themed testing. For most space missions, this phase starts between nine to twelve months prior to the planned launch. In the mission readiness environment, the goal is to perform sufficient testing to exercise the flight teams and systems through all mission phases in order to demonstrate that all elements are ready to support. As part of the maturation process, a mission rehearsal program is introduced to focus on team processes within the final flight system, in a more realistic operational environment. The overall goal for a mission rehearsal program is to: 1) ensure all flight system elements are able to meet mission objectives as a cohesive team; 2) reduce the risk in space based operations due to deficiencies in people, processes, procedures, or systems; and 3) instill confidence in the teams that will execute these first time flight activities. A good rehearsal program ensures critical events are exercised, discovers team or flight system nuances whose impact were previously unknown, and provides a real-time environment in which to interact with the various teams and systems. For flight team members, the rehearsal program provides experience and training in the event of planned (or unplanned) flight contingencies. To preserve the essence for team based rehearsals, this paper will explore the important elements necessary for a successful rehearsal program, document differences driven by Earth Orbiting (Aqua, Aura, Suomi-National Polar-orbiting Partnership (NPP)) and Deep Space missions (New Horizons, Mars Atmosphere and Volatile EvolutioN (MAVEN)) and discuss common challenges to both mission types. In addition, large scale program considerations and enhancements or additional steps for developing a rehearsal program will also be considered. For NASA missions, the mission rehearsal phase is a key milestone for predicting and ensuring on-orbit success. C1 [Gomez-Rosa, Carlos] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Cifuentes, Juan; Wasiak, Francis; Alfonzo, Agustin] Gen Dynam Miss Syst, Seabrook, MD USA. RP Gomez-Rosa, C (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 8 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303053 ER PT J AU Greenbaum, A Slagowski, S Dyrud, L Landis, D Hilker, T Joiner, J Schaire, S Colvin, M Crum, G Noto, J Watchorn, S Lee, JE Berry, J AF Greenbaum, Adam Slagowski, Stefan Dyrud, Lars Landis, Dave Hilker, Thomas Joiner, Joanna Schaire, Scott Colvin, Matthew Crum, Gary Noto, John Watchorn, Steve Lee, Jung-eun Berry, Joe GP IEEE TI The Earth Photosynthesis Imaging Constellation: Measuring Photosynthesis with a CubeSat Platform SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT ID LIGHT-USE EFFICIENCY; TERRESTRIAL CHLOROPHYLL FLUORESCENCE; SPACE; CLIMATE; MODELS; SINKS; GOSAT AB In response to NASA's Earth Venture Instrument-2 call, we proposed the Earth Photosynthesis Imaging Constellation (EPIC) mission. With EPIC, we will, for the first time, be able to provide the scientific community with global, spatially, and temporally explicit estimates of Photosynthesis, also known as Gross Primary Production (GPP) directly from satellite observations. Understanding the significance of terrestrial GPP for the global carbon, water, and energy balance, as well as its spatiotemporal dynamics is one of the key goals of Earth system science. Our proposed method is based on first principles of plant physiology and radiative transfer theory and has been demonstrated by the science team members in theoretical and experimental research. We expect EPIC to fundamentally change and improve our understanding of global photosynthesis and provide entirely new avenues for modeling and predicting Earth system behavior globally. The EPIC mission consists of four, 3-axis stabilized 6U CubeSats flown in pairs to enable multi-angle measurements. The two pairs may be launched on the same launch vehicle or on separate vehicles as necessitated by availability and destination orbits. If launched on the same vehicle, the two pairs can be spaced out via differential drag separation within a matter of months. To lower overall spacecraft costs, the CubeSats leverage existing off the shelf technologies as much as possible. Each EPIC spacecraft host an Integrated Vegetation Interferometer Spectrometer (IVIS) instrument. The highly compact IVIS consists of two primary sensors with separate, co-aligned optics: a spatial-heterodyne-spectrometer (IVIS/SHS) and hyperspectral imager (IVIS/HSI). The IVIS/HSI was specifically designed to implement a multi-angle measurement technique to determine the photosynthetic rate of vegetation (hereafter Hall-Hilker technique); the IVIS/SHS is designed to narrowly peer into a Fraunhofer line at high spectral resolution to obtain solar induced chlorophyll fluorescence (hereafter referred to as Joiner-Frankenberg technique). This paper will provide a description of the EPIC mission and science goals, details of the EPIC team, details of the science techniques to be implemented, and demonstrate how the design of the proposed EPIC CubeSat spacecraft and integrated IVIS instrument enable the proposed science at a fraction of the cost of larger systems. C1 [Greenbaum, Adam; Slagowski, Stefan; Dyrud, Lars; Landis, Dave] Charles Stark Draper Lab, 555 Technol Sq, Cambridge, MA 02139 USA. [Hilker, Thomas] Oregon State Univ, Coll Forestry, Corvallis, OR 97331 USA. [Joiner, Joanna; Schaire, Scott; Colvin, Matthew; Crum, Gary] NASA, GSFC, Greenbelt, MD 20771 USA. [Noto, John; Watchorn, Steve] Sci Solut Inc, North Chelmsford, MA 01863 USA. [Lee, Jung-eun] Brown Univ, Providence, RI 02912 USA. [Berry, Joe] Carnegie Inst Sci, Dept Global Ecol, Stanford, CA 94305 USA. RP Greenbaum, A (reprint author), Charles Stark Draper Lab, 555 Technol Sq, Cambridge, MA 02139 USA. EM agreenbaum@draper.com; thomas.hilker@oregonstate.edu; Joanna.Joiner@nasa.gov; steve@sci-sol.com; Jung-Eun_Lee@brown.edu; jberry@dge.stanford.edu NR 30 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 12 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501301029 ER PT J AU Greenbaum, A Brady, T Dennehy, C Airey, SP Roelke, E Judd, SB AF Greenbaum, Adam Brady, Tye Dennehy, Cornelius Airey, Stephen P. Roelke, Evan Judd, Samuel Brady GP IEEE TI Understanding International GNC Hardware Trends SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB An industry wide survey of GNC sensors, namely star trackers, gyros, and sun sensors was undertaken last year, in which size, mass, power, and various performance metrics were recorded for each category. A multidimensional analysis was performed, looking at the spectrum of available sensors, with the intent of identifying gaps in the available capability range. Mission types that are not currently well served by the available components were discussed, as well as some missions that would be enabled by filling gaps in the component space. This paper continues that study, with a focus on reaction wheels and magnetometers, as well as with updates to the listings of star trackers, gyros, and sun sensors. Additionally, a framework for making the database available to the community at large, as well as the continued maintenance of this database and the analysis of its contents, is discussed. C1 [Greenbaum, Adam; Brady, Tye] Charles Stark Draper Lab, 555 Technol Sq, Cambridge, MA 02139 USA. [Dennehy, Cornelius] NASA, Engn & Safety Ctr, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Airey, Stephen P.] ESTEC, ESA, NL-2200 AG Noordwijk, Netherlands. [Roelke, Evan] Brown Univ, Providence, RI 02912 USA. [Judd, Samuel Brady] MIT, Cambridge, MA 02139 USA. RP Greenbaum, A (reprint author), Charles Stark Draper Lab, 555 Technol Sq, Cambridge, MA 02139 USA. EM Agreenbaum@draper.com; Tye@draper.com; Cornelius.j.dennehy@nasa.gov; Stephen.Airey@esa.int; Eval_Roelke@Brown.edu; Samjudd@mit.edu NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 9 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300046 ER PT J AU Hadjimichael, TJ Coulter, P Gum, JS Hylan, JE Madison, TJ Miner, L Ohl, RG Redman, K Hayden, JE Wenzel, GW Mclean, KF Khreishi, M Young, J AF Hadjimichael, Theodore J. Coulter, Philip Gum, Jeffrey S. Hylan, Jason E. Madison, Timothy J. Miner, Linda Ohl, Raymond G. Redman, Kevin Hayden, Joseph E. Wenzel, Greg W. Mclean, Kyle F. Khreishi, Manal Young, Jerrod GP IEEE TI Large Volume, Optical and Opto-Mechanical Metrology Techniques for ISIM on JWST SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB The final, flight build of the Integrated Science Instrument Module (ISIM) element of the James Webb Space Telescope is the culmination of years of work across many disciplines and partners. This paper covers the large volume, ambient, optical and opto-mechanical metrology techniques used to verify the mechanical integration of the flight instruments in ISIM, including optical pupil alignment. We present an overview of ISIM's integration and test program, which is in progress, with an emphasis on alignment and optical performance verification. This work is performed at NASA Goddard Space Flight Center, in close collaboration with the European Space Agency, the Canadian Space Agency, and the Mid-Infrared Instrument European Consortium. C1 [Hadjimichael, Theodore J.; Coulter, Philip; Gum, Jeffrey S.; Hylan, Jason E.; Madison, Timothy J.; Miner, Linda; Ohl, Raymond G.; Khreishi, Manal; Young, Jerrod] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Redman, Kevin; Wenzel, Greg W.] Sierra Lobo, Greenbelt, MD 20770 USA. [Hayden, Joseph E.] Sigma Space Corp, Seabrook, MD 20706 USA. [Mclean, Kyle F.] Pinnacle Engn & Management Solut, Prince Anne, MD USA. RP Hadjimichael, TJ (reprint author), NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. EM theodore.j.hadjimichael@nasa.gov; phillip.coulter@nasa.gov; jeffery.s.gum@nasa.gov; jason.e.hylan@nasa.gov; timothy.j.madison@nasa.gov; linda.a.miner@nasa.gov; raymond.g.ohl@nasa.gov; kevin.w.redman@nasa.gov; joseph.hayden@nasa.gov; greg.w.wenzel@nasa.gov; kyle.f.mclean@nasa.gov; manal.a.khreishi@nasa.gov; jerrod.l.young@nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 15 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501304052 ER PT J AU Hagopian, J Evans, T Bolcar, M Eegholm, B De Leon, E Thompson, P Vaughnn, D AF Hagopian, John Evans, Tyler Bolcar, Matt Eegholm, Bente De Leon, Erich Thompson, Patrick Vaughnn, David GP IEEE TI ICESat-2 ATLAS Telescope Testing SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT ID LASER TRANSMITTER; ALTIMETER AB Many lessons were learned in the comprehensive testing of the one meter Beryllium flight telescope for the ICESat-2 mission. This paper will focus on testing areas of encircled energy analysis, plate scale measurements, and boresight alignment for alignment of fiber optic cables. The Optical Development System Lab (ODSL) at NASA's Goddard Space Flight Center (GSFC) was developed to build up experience using engineering test units. This experience was applied to testing the flight telescope. Several tests were able to be performed on the telescope itself, helping drive down risk, cost, and schedule during the integration phase of the telescope onto the instrument and box structure. The main ICESat-2 instrument is the Advanced Topographic Laser Altimeter System (ATLAS). It measures ice elevation by transmitting laser pulses, and collecting the reflection in a telescope. Because so few photons return from each pulse, the alignment of each receiver channel fiber is critical as well as minimizing the distortion. The lab consisted of a clean room with a one meter parabola collimator system with a point source fiber-coupled 532nm laser and a CCD detector. This was used to feed collimated light into the telescope that was recorded with a CCD detector in the telescope focal plane. A large one meter flat mirror was used to certify the collimator system. Fiber optic cables were also used to back-illuminate the telescope and image in the collimator focal plane. The telescope was mounted in a gimbal that allowed for three degrees of rotational freedom allowing the telescope to be steered to each respective science field point. The setup worked well for accomplishing the testing. Through well written procedures and prior experience, the testing was carried out according to plan and on schedule despite obstacles along the way such as late ground support equipment and tests that needed to be repeated. The objective of this paper is to share those lessons learned for optical alignment of a receiver telescope assembly to promote future mission success. C1 [Hagopian, John; Bolcar, Matt; Eegholm, Bente; De Leon, Erich; Thompson, Patrick; Vaughnn, David] Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Evans, Tyler] SGT Inc, Greenbelt, MD 20770 USA. RP Hagopian, J (reprint author), Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 7 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501301038 ER PT J AU Hardash, J Decker, B Landegger, A Thompson, V AF Hardash, Jill Decker, Brady Landegger, Alexandra Thompson, Victor GP IEEE TI Translating Technology Taxonomies to Facilitate Cross-Industry Innovation SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB The Government technology innovation network-Innovate.Gov-is a cross-government extension of the Innovate. NASA (https://innovate.nasa.gov) platform, which was designed to crowdsource new opportunities for NASA technology. Innovate.Gov is a virtual collaboration platform to share technology across Federal agencies and serves as a unified hub for the public to access and innovate with government technology. Using this platform, government agencies share out technology information and engage the public to innovate with these inventions. The Innovate.Gov community collaborates to design improvements and integrations to revitalize these inventions, or propose new applications for these technologies (within and outside of their respective agencies). Innovate.Gov targets participants across a full range of organizations, professions, and areas of expertise, including: government, academia, research labs, private industry, and independent innovators. In order to fulfill the Innovate.Gov mission, technology information posted to the website must be made accessible to this diverse group of participants by applying a universal technology taxonomy. This paper explores our approach, challenges and solutions to translate the language of each agency's technology across multiple disciplines to enable Innovate.Gov to tap into the power of open innovation. This paper describes our approach, which begins with the collection and synthesis of existing taxonomies across our partner government agencies, including the technology categorizations described in their strategic, planning and outreach documents (e.g. the 2012 NASA Space Technology Roadmaps, NASA Tech Briefs). Evaluations of technology discussions across social media were used to augment understanding of the informal taxonomy used by a broader group. This paper describes our solution to build a new taxonomy consistent with our government partners' technology languages that simultaneously represents the full range of the rest of the participant community. Specifically, we created a technology translation matrix to identify the major categories (buckets) of technology (e.g. robotics, materials) and align these overarching terms to agency-specific taxonomies. This matrix creates back-end connections between technologies and various tags to enable a seamless user experience on the Innovate.Gov site. It also automates cross-discipline translation that is individualized to each user and improves the site's search capabilities. This paper also describes our approach to promote the wide spread adoption of the matrix through the creation of a social media strategy and program-specific taxonomy. Furthermore, this paper outlines the unique virtual showcase developed for the technology, which was designed to appeal to participants across multiple industries. For example, one technique entailed the development of "common language" titles to describe technologies by focusing on their function, regardless of their application. Finally, this paper describes the important role that a shared technology taxonomy can play in technological innovation. This new universal technology linguistics tool translation across agencies will promote increased cross-disciplinary collaboration, reduce duplication of efforts across agencies and the private sector, and support innovation and technology infusion across industry and academia. C1 [Hardash, Jill] Booz Allen Hamilton, 5220 Pacific Concourse Dr, Los Angeles, CA 90045 USA. [Decker, Brady; Thompson, Victor] NASA, Headquarters ITCD, Washington, DC 20546 USA. [Landegger, Alexandra] Booz Allen Hamilton, Washington, DC 20005 USA. RP Hardash, J (reprint author), Booz Allen Hamilton, 5220 Pacific Concourse Dr, Los Angeles, CA 90045 USA. EM Hardash_JiII@bah.com; Brady.w.Decker@nasa.gov; Landegger_Alexandra@bah.com; Victor.Thompson-l@nasa.gov NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 8 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302057 ER PT J AU Hayhurst, MR Bitten, RE Eftekharzadeh, S Kellogg, RC Roeum, V Shinn, S AF Hayhurst, Marc R. Bitten, Robert E. Eftekharzadeh, Shirin Kellogg, Robert C. Roeum, Voleak Shinn, Steve GP IEEE TI Calculating Reserves on Schedule-to-Go (STG) Based on Historical Data SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB NASA Center guidance typically requires that a mission hold increasing schedule reserves on schedule-to-go (STG) as the project matures. This approach makes intuitive sense as history has shown that project development schedules typically grow beyond their initial planned schedule. This fact begs the question, are the schedule reserve guidelines adequate relative to the experience of historical missions? This study examines current schedule guidelines and actual historical mission data. Additionally external factors that have caused schedule growth are considered and adjustments are made for them. The results can potentially be used to inform NASA Center and Headquarters guidelines for reserves on STG to set more robust guidance for future missions. C1 [Hayhurst, Marc R.; Bitten, Robert E.; Eftekharzadeh, Shirin; Kellogg, Robert C.] Aerosp Corp, M4-949,PO 92957, Los Angeles, CA 90009 USA. [Roeum, Voleak] NASA Headquarters, Sci Mission Directorate, Washington, DC 20546 USA. [Shinn, Steve] Goddard Space Flight Ctr, Flight Projects Directorate, Greenbelt, MD 20771 USA. RP Hayhurst, MR (reprint author), Aerosp Corp, M4-949,PO 92957, Los Angeles, CA 90009 USA. EM marc.r.hayhurst@aero.org; robert.e.bitten@aero.org; shirin.eftekharzadeh@aero.org; robert.c.kellogg@aero.org; vroeum@nasa.gov; stephen.a.shinn@nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 9 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300033 ER PT J AU Hennawy, J Adams, N Sanchez, E Srinivasan, D Hamkins, J Vilnrotter, V Xie, H Kinman, P AF Hennawy, Joseph Adams, Norman Sanchez, Erika Srinivasan, Dipak Hamkins, Jon Vilnrotter, Victor Xie, Hua Kinman, Peter GP IEEE TI Telemetry Ranging Using Software-Defined Radios SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Telemetry ranging is a technique that inserts ranging data measured by the spacecraft into the downlink telemetry stream, thereby avoiding the need to allocate downlink power for a ranging signal. This technique has many benefits depending on the mission profile, including increased data return, operational simplification, and spectrum efficiency. The present study considers a variation to the ranging technique presented in [1] in order to facilitate implementation in a software-defined radio (SDR). This implementation tracks an uplink PN range code and measures the code phase coincident with the start of downlink telemetry frames. The phase is then embedded in subsequent telemetry frames. The method is implemented in the JHU/APL Frontier Radio and leverages the PN ranging design from the NASA New Horizons communications system. Initial test results are summarized and indicate that the method is viable for space exploration. C1 [Hennawy, Joseph; Adams, Norman; Sanchez, Erika; Srinivasan, Dipak] Johns Hopkins Univ, Appl Phys Lab, Baltimore, MD 21218 USA. [Hamkins, Jon; Vilnrotter, Victor; Xie, Hua] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. [Kinman, Peter] Calif State Univ, Long Beach, CA USA. RP Hennawy, J (reprint author), Johns Hopkins Univ, Appl Phys Lab, Baltimore, MD 21218 USA. EM Joseph.Hennawy@jhuapl.edu; Norman.Adams@jhuapl.edu; Erika.Sanchez@jhuapl.edu; Dipak.Srinivasan@jhuapl.edu; Jon.Hamkins@jpl.nasa.gov; Victor.Vilnrotter@jpl.nasa.gov; Hua.Xie@jpl.nasa.gov; pkinman@csufresno.edu NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 14 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303004 ER PT J AU Hilliard, L Racette, P Blackwell, W Galbraith, C Thompson, E AF Hilliard, Lawrence Racette, Paul Blackwell, William Galbraith, Christopher Thompson, Erik GP IEEE TI Hyperspectral Microwave Atmospheric Sounder (HyMAS) - new capability in the CoSMIR/CoSSIR scanhead SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB MIT Lincoln Laboratory and NASA's Goddard Space Flight Center have teamed to adapt an existing instrument platform, the CoSMIR/CoSSIR system for atmospheric sensing, to develop and demonstrate a new capability in a hyperspectral microwave atmospheric sounder (HyMAS). This new sensor comprises a highly innovative intermediate frequency processor (IFP), that provides the filtering and digitization of 52 radiometric channels and the interoperable remote component (IRC) adapted to CoSMIR, CoSSIR, and HyMAS that stores and archives the data with time tagged calibration and navigation data. The first element of the work is the demonstration of a hyperspectral microwave receiver subsystem that was recently shown using a comprehensive simulation study to yield performance that substantially exceeds current state-of-the-art. Hyperspectral microwave sounders with similar to 100 channels offer temperature and humidity sounding improvements similar to those obtained when infrared sensors became hyperspectral. Hyperspectral microwave operation is achieved using independent RF antenna/receiver arrays that sample the same area/volume of the Earth's surface/atmosphere at slightly different frequencies and therefore synthesize a set of dense, finely spaced vertical weighting functions. The second, enabling element is the development of a compact 52-channel Intermediate Frequency processor module. A principal challenge of a hyperspectral microwave system is the size of the IF filter bank required for channelization. Large bandwidths are simultaneously processed, thus complicating the use of digital back-ends with associated high complexities, costs, and power requirements. Our approach involves passive filters implemented using low-temperature co-fired ceramic (LTCC) technology to achieve an ultra-compact module that can be easily integrated with existing RF front-end technology. This IF processor is applicable to other microwave sensing missions requiring compact IF spectrometry. The unit produces 52 channels of spectral data in a highly compact volume (<100cm3) with low mass (<300g) and linearity better than 0.3% over a 330K dynamic range. C1 [Hilliard, Lawrence; Racette, Paul] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Blackwell, William; Galbraith, Christopher; Thompson, Erik] MIT, Lincoln Lab, Lexington, MA 02420 USA. RP Hilliard, L (reprint author), NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. EM Lawrence.M.Hilliard@NASA.gov; Paul.E.Racette@NASA.gov; wjb@ll.mit.edu; chris.galbraith@ll.mit.edu; Erik.Thompson@ll.mit.edu NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 9 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302008 ER PT J AU Hoffman, JP Ghaemi, H Horst, S AF Hoffman, James P. Ghaemi, Hirad Horst, Stephen GP IEEE TI Digital Calibration System for the Proposed NISAR (NASA/ISRO) Mission SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB The Synthetic Aperture Radar (SAR) instrument for the proposed NASA/ISRO mission would utilize a distributed architecture dubbed SweepSAR. This real-time On-orbit digital beamforming, combined with lightweight, large aperture reflectors, promises significant increases in instrument capability for solid earth and biomass remote sensing. These new instrument concepts require new methods for calibrating the multiple channels, which are combined onboard, in real-time. The benefit of this effort is that it enables a new class of lightweight radar architecture, Digital Beamforming with SweepSAR, providing significantly larger swath coverage than conventional SAR architectures for reduced mass and cost. C1 [Hoffman, James P.; Ghaemi, Hirad; Horst, Stephen] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Hoffman, JP (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM James.P.Hoffman@jpl.nasa.gov; Hirad.Ghaemi@jpl.nasa.gov; Stephen.J.Horst@jpl.nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 7 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302084 ER PT J AU Hogie, K Criscuolo, E Dissanayake, A Flanders, B Safavi, H Lubelczyk, J AF Hogie, Keith Criscuolo, Edward Dissanayake, Asoka Flanders, Bruce Safavi, Haleh Lubelczyk, Jeffry GP IEEE TI TDRSS Demand Access System Augmentation SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB The Demand Access System ( DAS) of the Tracking and Data Relay Satellite System ( TDRSS) enables space borne and ground based Space Network ( SN) customers to send their telemetry and science data 24 hours a day without having to schedule network services. DAS uses Tracking and Data Relay Satellite ( TDRS) Multiple Access ( MA) antennas and spread spectrum modulation. The current DAS system, installed in 2004, is limited in several ways and becoming obsolete due to outdated technology. A new DAS concept that takes advantage of newer technologies and low-cost components to provide enhanced customer service has been developed as a potential replacement of the existing system. The new concept does away with the hardware resource limitations of the previous system, and its performance is limited only by the self-interference generated by the MA users. In contrast to the previous system, which is largely a custom design, the new system makes use of Commercial-Off-The-Shelf ( COTS) products and offers additional features such as seamless TDRS handovers and TDRS arraying. The system is self-contained in terms of handling all user interactions, and can be updated easily without impacting the rest of the SN infrastructure; backward compatibility is also maintained. Plans are underway to demonstrate the initial concept at the White Sands Complex ( WSC) ground terminal by shadowing several orbiting DAS customers. Details of the system architecture, and design approach are presented. C1 [Hogie, Keith] Comp Sci Corp, 12401 Mt Pleasant Dr, Laurel, MD 20708 USA. [Criscuolo, Edward] Comp Sci Corp, Laurel, MD 20707 USA. [Dissanayake, Asoka] Exelis Inc, Greenbelt, MD 20770 USA. [Flanders, Bruce] Exelis Inc, Herndon, VA 20170 USA. [Safavi, Haleh; Lubelczyk, Jeffry] NASA, GSFC, Greenbelt, MD 20771 USA. RP Hogie, K (reprint author), Comp Sci Corp, 12401 Mt Pleasant Dr, Laurel, MD 20708 USA. EM Keith.Hogie@nasa.gov; Edward.L.Criscuolo@nasa.gov; Asoka.Dissanayake@execlisinc.com; Bruce.Flanders@exelisinc.com; Haleh.Safavi@nasa.gov; Jeffrey.T.Lubelczyk@nasa.gov NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 9 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303088 ER PT J AU Hopkins, GD Skala, JR Revier, DL James, MW Simmons, DE Ruf, CS Baileys, MC AF Hopkins, Glenn D. Skala, James R. Revier, Daniel L. James, Mark W. Simmons, David E. Ruf, Christopher S. Baileys, M. C. GP IEEE TI Beam Former Development for the NASA Hurricane Imaging Radiometer SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT DE Tropical Cyclone; Imager; Aperture Synthesis Microwave Radiometer; Thinned Array Antenna; Analog Array Beam Former AB The Hurricane Imaging Radiometer (HIRAD) is an airborne passive microwave synthetic aperture radiometer designed to provide high resolution, wide swath imagery of surface wind speed in tropical cyclones from a low profile planar array antenna. This paper will present the array radiometer system concept and summarize its development, including multiple flight tests on NASA's Genesis and Rapid Intensification Processes (GRIP, 2010) and Hurricane and Severe Storm Sentinel (HS3, 2012) campaigns. The paper will focus on the design goals, trades, and approach for the array antenna along-track beam former. The paper presents details of the beam former design, implementation, integration approach, and measured performance. The paper concludes with a description of planned improvements for the next generation dual-polarized HIRAD antenna and the resulting impacts on the beam former design and integration. C1 [Hopkins, Glenn D.; Skala, James R.; Revier, Daniel L.] Georgia Inst Technol, Georgia Tech Res Inst, Atlanta, GA 30332 USA. [James, Mark W.] NASA, Marshall Space Flight Ctr, Huntsville, AL USA. [Simmons, David E.] Univ Alabama, Huntsville, AL USA. [Ruf, Christopher S.] Univ Michigan, Space Phys Res Lab, Ann Arbor, MI 48109 USA. [Baileys, M. C.] Appl EM Inc, Hampton, VA USA. RP Hopkins, GD (reprint author), Georgia Inst Technol, Georgia Tech Res Inst, Atlanta, GA 30332 USA. EM glenn.hopkins@gtri.gatech.edu; mark.w.james@nasa.gov; david.e.simmons@nasa.gov; cruf@umich.edu; m.c.bailey@cox.net NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 14 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303014 ER PT J AU Horner, MD Eremenko, AE AF Horner, Matthew D. Eremenko, Alexander E. GP IEEE TI Europa Clipper Instrument Accommodation in the Proposal Phase SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB The proposed Europa Clipper mission would send a suite of instruments to Jupiter's Europa moon. The scope of these instruments objectives would range from gravity science, high resolution imaging of the icy surface, thermal and topographical imaging/mapping; to plasma science, neutral mass spectrometry and infrared spectroscopy, and perhaps most importantly ice penetrating radar capability used for examining the potential liquid water ocean beneath the icy outer shell. Perhaps the largest test is solving these challenges in the proposal phase of the mission. In the pre-project timeframe, and nearly a year from instrument selection, broad assumptions must be made and used to drive the system design and implementation. Considerations include: optical fields of view of instruments (both direct and stray light), instrument thermal radiative fields of view (to other structures and to space), co-bore-sight requirements between instruments, and instrument stability over the life of the mission. Many of these items are addressed with the implementation of a dedicated instrument mounting platform, kinematically mounted to the avionics module of the spacecraft. This approach helps deal with the above considerations by placing the instruments outside the spacecraft avionics module in the Nadir direction. This allows for greater control of field of view obstructions (both optical and thermal) by moving instruments away from other structures. It also gives greater stability to instruments with coupled optical alignment requirements (i.e. the Short Wave Infrared Spectrometer and the High Resolution Reconnaissance Camera). Kinematic mounting also ensures that moments are not introduced into the mounting plate structure due to thermal gradients. Instrument envelope approximations are made by comparison to previously flown instruments, and through ongoing discussion between the mechanical and instrument teams to determine approximate sizes and needs for baffles, deployable covers, radiation and thermal shielding, etc. These challenges are all met with a newly developed system modeling approach that combines inputs from many of the stakeholders (science, flight system, mechanical, etc.) and presents them in a common view form. C1 [Horner, Matthew D.; Eremenko, Alexander E.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr M-S 303-410, Pasadena, CA 91109 USA. RP Horner, MD (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr M-S 303-410, Pasadena, CA 91109 USA. EM mhorner@jpl.nasa.gov; Alexander.E.Eremenko@jpl.nasa.gov NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 9 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501301088 ER PT J AU Howe, AS Simon, M Smitherman, D Howard, R Toups, L Hoffman, SJ AF Howe, A. Scott Simon, Matthew Smitherman, David Howard, Robert Toups, Larry Hoffman, Stephen J. GP IEEE TI Mars Surface Habitability Options SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB This paper reports on current habitability concepts for an Evolvable Mars Campaign (EMC) prepared by the NASA Human Spaceflight Architecture Team (HAT). For many years NASA has investigated alternative human Mars missions, examining different mission objectives, trajectories, vehicles, and technologies; the combinations of which have been referred to as reference missions or architectures. At the highest levels, decisions regarding the timing and objectives for a human mission to Mars continue to evolve while at the lowest levels, applicable technologies continue to advance. This results in an on-going need for assessments of alternative system designs such as the habitat, a significant element in any human Mars mission scenario, to provide meaningful design sensitivity characterizations to assist decision-makers regarding timing, objectives, and technologies. As a subset of the Evolvable Mars Campaign activities, the habitability team builds upon results from past studies and recommends options for Mars surface habitability compatible with updated technologies. C1 [Howe, A. Scott] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Simon, Matthew] NASA, Langley Res Ctr, Washington, DC 20546 USA. [Smitherman, David] NASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USA. [Howard, Robert; Toups, Larry] NASA, Johnson Space Ctr, Houston, TX 77058 USA. [Hoffman, Stephen J.] Sci Applicat Int, Houston, TX 77058 USA. RP Howe, AS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM a.scott.howe@jpl.nasa.gov; matthew.a.simon@nasa.gov; david.smitherman@nasa.gov; robert.l.howard@nasa.gov; larry.toups-1@nasa.gov; stephen.j.hoffman@nasa.gov NR 24 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 9 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501304007 ER PT J AU Jamnejad, V Long, E Durden, S AF Jamnejad, Vahraz Long, Ezra Durden, Stephen GP IEEE TI Design of a Quasi Optical Transmission Line for Cloud and Precipitation Radar System of ACE Mission SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB We outline the design and test of a new quasi-optical transmission line (QOTL) for feeding the reflector system in an optional instrument for deployment on the Aerosol/Cloud/Ecosystems (ACE) mission. The QOTL used to connect the transmitter and receiver to the antenna is designed for operation at W-band (94 GHz) frequency. A test-bed has been developed for the various critical components of the radar system. The challenge in using quasi-optics for ACERAD is that it must accommodate dual-polarized operation. We have developed a way to accomplish this that extends the design implemented in CloudSat radar jointly developed by JPL/NASA, Canadian Space Agency and other agencies. The new design has been prototyped using various components on a laboratory optical bench. Critical components of the QOTL have been fabricated and tested. Some results are presented. C1 [Jamnejad, Vahraz; Long, Ezra; Durden, Stephen] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Jamnejad, V (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Vahraz.Jamnejad@jpl.nasa.gov NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 6 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302068 ER PT J AU Jones, DL Lazio, TJW Burns, JO AF Jones, Dayton L. Lazio, T. Joseph W. Burns, Jack O. GP IEEE TI Dark Ages Radio Explorer Mission: Probing the Cosmic Dawn SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB The period between the creation of the cosmic microwave background at a redshift of similar to 1000 and the formation of the first stars and black holes that re-ionize the intergalactic medium at redshifts of 10-20 is currently unobservable. The baryonic component of the universe during this period is almost entirely neutral hydrogen, which falls into local regions of higher dark matter density. This seeds the formation of large-scale structures including the cosmic web that we see today in the filamentary distribution of galaxies and clusters of galaxies. The only detectable signal from these dark ages is the 21-cm spectral line of hydrogen, redshifted down to frequencies of approximately 10-100 MHz. Space-based observations of this signal will allow us to determine the formation epoch and physics of the first sources of ionizing radiation, and potentially detect evidence for the decay of dark matter particles. JPL is developing deployable low frequency antenna and receiver prototypes and calibration techniques to enable both all-sky spectral measurements of neutral hydrogen and ultimately to map the spatial distribution of the signal as a function of redshift. Such observations must be done from space because of Earth's ionosphere and ubiquitous radio interference. Both lunar orbiting and lunar surface based instruments are under development. A specific application of these technologies is the Dark Ages Radio Explorer (DARE) mission. This small Explorer class mission is designed to measure the sky-averaged hydrogen signal from the shielded region above the far side of the Moon. Observations of neutral hydrogen from the dark ages and the cosmic dawn (when light from the first generation of stars appeared) will provide unique and critical information on the early evolution of the universe. These data will complement ground-based radio observations of the final stages of intergalactic re-ionization at higher frequencies. DARE will also serve as a scientific percursor for space-based interferometry missions to image the distirbution of hydrogen during the cosmic dark ages. C1 [Jones, Dayton L.; Lazio, T. Joseph W.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Burns, Jack O.] Univ Colorado, CASA, UCB 593, Boulder, CO 80309 USA. RP Jones, DL (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM dayton.jones@jpl.nasa.gov; joseph.lazio@jpl.nasa.gov; jack.burns@colorado.edu NR 23 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 7 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300066 ER PT J AU Joosten, BK White, HG AF Joosten, B. Kent White, Harold G.Sonny GP IEEE TI Human Outer Solar System Exploration via Q-Thruster Technology SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Propulsion technology development efforts at the NASA Johnson Space Center continue to advance the understanding of the quantum vacuum plasma thruster (Q-Thruster), a form of electric propulsion. Through the use of electric and magnetic fields, a Q-thruster pushes quantum particles (electrons/positrons) in one direction, while the Q-thruster recoils to conserve momentum. This principle is similar to how a submarine uses its propeller to push water in one direction, while the submarine recoils to conserve momentum. Based on laboratory results and theoretical analysis, it appears that continuous specific thrust levels of 0.4 - 4.0 N/kWe may be achievable with essentially no onboard propellant consumption. To evaluate the potential of this technology, a mission analysis tool was developed utilizing the Generalized Reduced Gradient non-linear parameter optimization engine contained in the Microsoft Excel (R) platform. This tool allowed very rapid assessments of "Q-Ship" minimum time transfers from earth to the outer planets and back utilizing parametric variations in thrust acceleration while enforcing constraints on planetary phase angles and minimum heliocentric distances. A speculative Q-Thruster specific thrust assumption (0.4 N/kWe) combined with "moderate" levels of space nuclear power (1 - 2 MWe) and vehicle specific mass (45 - 55 kg/kWe) results in continuous milli-g thrust acceleration, opening up realms of human spaceflight performance completely unattainable by any current systems or near-term proposed technologies. Minimum flight times to Mars are predicted to be as low as 75 days, but perhaps more importantly new "retro-phase" and "gravity-augmented" trajectory shaping techniques were revealed which overcome adverse planetary phasing and allow virtually unrestricted departure and return opportunities. Even more impressively, the Jovian and Saturnian systems would be opened up to human exploration with round-trip times of 21 and 32 months respectively including 6 to 12 months of exploration at the destinations. Finally, interstellar trip times are assessed at milli-g acceleration levels. C1 [Joosten, B. Kent] MBO Partners Inc, 2383 York Harbour Ct, League City, TX 77573 USA. [White, Harold G.Sonny] NASA, Johnson Space Ctr, Houston, TX 77058 USA. RP Joosten, BK (reprint author), MBO Partners Inc, 2383 York Harbour Ct, League City, TX 77573 USA. EM kent.joosten@icloud.com; harold.white-1@nasa.gov NR 15 TC 0 Z9 0 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 14 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300019 ER PT J AU Kacpura, TJ Eddy, WM Smith, CR Liebetreu, J AF Kacpura, Thomas J. Eddy, Wesley M. Smith, Carl R. Liebetreu, John GP IEEE TI Software Defined Radio Architecture Contributions to Next Generation Space Communications SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Space communications architecture concepts, comprising the elements of the system, the interactions among them, and the principles that govern their development, are essential factors in developing National Aeronautics and Space Administration (NASA) future exploration and science missions. Accordingly, vital architectural attributes encompass flexibility, the extensibility to insert future capabilities, and to enable evolution to provide interoperability with other current and future systems. Space communications architectures and technologies for this century must satisfy a growing set of requirements, including those for Earth sensing, collaborative observation missions, robotic scientific missions, human missions for exploration of the Moon and Mars where surface activities require supporting communications, and in-space observatories for observing the earth, as well as other star systems and the universe. An advanced, integrated, communications infrastructure will enable the reliable, multipoint, high-data-rate capabilities needed on demand to provide continuous, maximum coverage for areas of concentrated activity. Importantly, the cost/value proposition of the future architecture must be an integral part of its design; an affordable and sustainable architecture is indispensable within anticipated future budget environments. Effective architecture design informs decision makers with insight into the capabilities needed to efficiently satisfy the demanding space-communication requirements of future missions and formulate appropriate requirements. A driving requirement for the architecture is the extensibility to address new requirements and provide low-cost on-ramps for new capabilities insertion, ensuring graceful growth as new functionality and new technologies are infused into the network infrastructure. In addition to extensibility, another key architectural attribute of the space communication equipment is interoperability with other NASA communications systems, as well as those communications and navigation systems operated by international space agencies and civilian and government agencies. The structure of candidate next-generation integrated communication architectures for space communications and navigation address technologies, architectural attributes, mission services, and communications capabilities is improved by using software defined radios (SDRs). Evaluating lessons learned from development and operation of the early space SDRs on the NASA Space Communications and Navigation (SCaN) Testbed on the International Space Station (ISS) provide feedback for defining the communications architecture. An important attribute is leveraging SDR reconfigurability, which can change the way that operations are conducted. C1 [Kacpura, Thomas J.] NASA, Glenn Res Ctr, MS 54-1,21000 Brookpk Rd, Cleveland, OH 44135 USA. [Eddy, Wesley M.] NASA, Glenn Res Ctr, MTI Syst, Cleveland, OH 44135 USA. [Smith, Carl R.; Liebetreu, John] Gen Dynam Adv Informat Syst, Scottsdale, AZ 85257 USA. RP Kacpura, TJ (reprint author), NASA, Glenn Res Ctr, MS 54-1,21000 Brookpk Rd, Cleveland, OH 44135 USA. EM thomas.j.kacpura@nasa.gov; wesley.m.eddy@nasa.gov; Carl.Smith@gd-ais.com; John.Liebetreu@gd-ais.com NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 12 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300002 ER PT J AU Kerczewski, RJ Bishop, WD Hoder, DJ Shalkhauser, KA Wilson, JD AF Kerczewski, Robert J. Bishop, William D. Hoder, Douglas J. Shalkhauser, Kurt A. Wilson, Jeffrey D. GP IEEE TI Impact of Co-Site Interference on L/C-Band Spectrum for VAS Control and Non-Payload Communications SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB In order to provide for the safe integration of unmanned aircraft systems into the National Airspace System, the control and non-payload communications (CNPC) link connecting the ground-based pilot with the unmanned aircraft must be highly reliable. A specific requirement is that it must operate using aviation safety radiofrequency spectrum. The 2012 World Radiocommunication Conference (WRC-12) provided a potentially suitable allocation for LOS CNPC spectrum in C-Band at 5030-5091 MHz band which, when combined with a previous allocation in L-Band (960-1164 MHz) may satisfy the LOS spectrum requirement and provide for high reliability through dual-band redundancy. However, the L-Band spectrum hosts a number of aeronautical navigation systems which require high-power transmitters on-board the aircraft. These high-power transmitters co-located with sensitive CNPC receivers operating in the same frequency band have the potential to create co-site interference, reducing the performance of the CNPC receivers and ultimately reducing the usability of the L-Band for CNPC. This paper examines the potential for co-site interference, as highlighted in recent flight tests, and discusses the impact on the UAS CNPC spectrum availability and requirements for further testing and analysis. C1 [Kerczewski, Robert J.; Hoder, Douglas J.; Shalkhauser, Kurt A.; Wilson, Jeffrey D.] NASA, Glenn Res Ctr, 21000 Brookpark Rd,MS 54-1, Cleveland, OH 44135 USA. [Bishop, William D.] Jacobs Engn, Cleveland, OH 44135 USA. RP Kerczewski, RJ (reprint author), NASA, Glenn Res Ctr, 21000 Brookpark Rd,MS 54-1, Cleveland, OH 44135 USA. EM rkerczewski@nasa.gov; william.d.bishop@nasa.gov; douglas.j.hoder@nasa.gov; kurt.a.shalkhauser@nasa.gov; jeffrey.d.wilson@nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 12 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501301090 ER PT J AU Kremic, T Cheng, AF Hibbitts, K Young, EF Ansari, RR Dolloff, MD Landis, RR AF Kremic, Tibor Cheng, Andrew F. Hibbitts, Karl Young, Eliot F. Ansari, Rafat R. Dolloff, Matthew D. Landis, Rob R. GP IEEE TI Stratospheric Balloons for Planetary Science and the Balloon Observation Platform for Planetary Science (BOPPS) Mission Summary SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB NASA and the planetary science community have been exploring the potential contributions of stratospheric balloons to decadal class planetary science. Previous studies of the similar to 200 questions raised in the Decadal Survey have identified about 45 topics that are potentially suitable for addressing by stratospheric balloon platforms. A stratospheric balloon mission was flown in the fall of 2014 called BOPPS, Balloon Observation Platform for Planetary Science. This mission observed a number of planetary targets including two Oort cloud comets. The optical system and instrumentation payload was able to provide unique measurements of the intended targets and increase our understanding of these primitive bodies and their implications for us here on Earth. This paper will discuss the mission, instrumentation and initial results and how these may contribute to the broader planetary science objectives of NASA and the scientific community. This paper will also identify how the instrument platform on BOPPS may be able to contribute to future balloon-based science. Finally the paper will address potential future enhancements and the expected science impacts should those enhancements be implemented. C1 [Kremic, Tibor; Ansari, Rafat R.; Dolloff, Matthew D.] NASA, Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. [Cheng, Andrew F.; Hibbitts, Karl] JHU Appl Phys Lab, Laurel, MD 20723 USA. [Young, Eliot F.] SW Res Inst, Boulder, CO 80302 USA. [Landis, Rob R.] NASA, Wallops Flight Facil, Wallops, VA 23337 USA. RP Kremic, T (reprint author), NASA, Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. EM Tibor.Kremic@nasa.gov; Andy.Cheng@jhuapl.edu; Karl.Hibbitts@jhuapl.edu; efy@boulder.swri.edu; Rafat.R.Ansari@nasa.gov; matthew.d.dolloff@nasa.gov; Rob.R.Landis@nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 10 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501301039 ER PT J AU Leung, BC Goeser, NR Miller, LA Gonzalez, S AF Leung, Braven C. Goeser, Nicholas R. Miller, Larry A. Gonzalez, Sonia GP IEEE TI Validation of Electroadhesion as a Docking Method for Spacecraft and Satellite Servicing SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB An electrostatic gripping force is created when a non-conducting dielectric is placed between a conducting material and a series of oppositely charged monopolar electrodes. Given the non-uniformity of satellites and their typical lack of docking structures, electrostatic gripping is a promising option for docking to satellites for servicing and refueling. This research investigates the effectiveness of a high voltage electrostatic gripper in vacuum to validate its use as a docking method in space. Five linear actuators were mounted inside a vacuum chamber to create a 5 DOF test stand to examine normal, shear, peeling, and twisting forces on various test materials. To further assess the feasibility of the gripping system in docking operations, the gripper was mounted to a robotic arm atop a free-floating frictionless base on a special flat floor in the NASA MSFC Flight Robotics Laboratory to test satellite docking and capture maneuvers utilizing electroadhesion. C1 [Leung, Braven C.] Univ Illinois, Urbana, IL 61801 USA. [Leung, Braven C.; Goeser, Nicholas R.; Miller, Larry A.; Gonzalez, Sonia] NASA, Marshall Space Flight Ctr, Huntsville, AL USA. [Goeser, Nicholas R.] Univ Michigan, Ann Arbor, MI 48109 USA. [Miller, Larry A.] Univ Alabama, Huntsville, AL 35899 USA. [Gonzalez, Sonia] Univ Calif Davis, Davis, CA USA. RP Leung, BC (reprint author), Univ Illinois, Urbana, IL 61801 USA. EM leung27@illinois.edu; ngoeser@umich.edu; larry.miller.hsv@gmail.com; sgonzalez@ucdavis.edu NR 2 TC 0 Z9 0 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 8 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501304017 ER PT J AU Li, X Uckert, K Getty, S Grubisic, A Brinckerhoff, W Cornish, T Ecelberger, S Chanover, N AF Li, Xiang Uckert, Kyle Getty, Stephanie Grubisic, Andrej Brinckerhoff, William Cornish, Timothy Ecelberger, Scott Chanover, Nancy GP IEEE TI Analysis of Aqueous Environments by Laser Desorption/Ionization Time-of-Flight Mass Spectrometry SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT DE hydrous minerals; laser desorption; mass spectrometry; time-of-flight ID MARS AB Laser desorption/ionization time-of-flight mass spectrometry (LD-TOF-MS) has been developed and used to characterize different groups of hydrous minerals. We have advanced the technique by including reversed polarity, precision ion gating, and a curved field reflectron mass analyzer. Reversed polarity provides capabilities in achieving complementary compositional information of the materials, and ion gating enhances the selectivity and sensitivity in specific mass ranges. Representative reference minerals including sulfates, clays, serpentine, and naturally collected complex samples have been analyzed by LD-TOF-MS as well as infrared (IR) spectroscopy, to provide supporting information. We demonstrate that mass spectrometry can identify water in mineral species, and reveal the presence of aqueous environments. Miniaturized LD-TOF-MS is a valuable instrument technique for the in situ characterization and analysis of samples as part of future landed planetary missions and astrobiology explorations. C1 [Li, Xiang] Univ Maryland Baltimore Cty, Baltimore, MD 21250 USA. [Uckert, Kyle; Chanover, Nancy] New Mexico State Univ, Las Cruces, NM 88003 USA. [Getty, Stephanie; Brinckerhoff, William] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Grubisic, Andrej] Univ Maryland, College Pk, MD 20742 USA. [Cornish, Timothy; Ecelberger, Scott] C&E Res Inc, Columbia, MD 21045 USA. RP Li, X (reprint author), Univ Maryland Baltimore Cty, Baltimore, MD 21250 USA. EM xiang.li@nasa.gov RI Li, Xiang/F-4539-2012 NR 22 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 10 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302024 ER PT J AU Limes, G Christa, S Pires, C Gundy-Burlet, K AF Limes, Greg Christa, Scott Pires, Craig Gundy-Burlet, Karen GP IEEE TI EDAC Events during the LADEE Mission SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB The purpose of the Lunar Atmosphere Dust Environment Explorer (LADEE) mission was to measure the density, composition and time variability of the lunar dust environment. The spacecraft was designed with modular common structural components that could be connected together to form the spacecraft. Spacecraft components were largely chosen from "off-the-shelf" sensors, actuators and avionics. The flight software was also designed using a layered modular approach leveraging model-based design concepts. High-level spacecraft control modules were autocoded from Simulink and integrated with reused executive and services modules and a small number of new hand-coded elements such as the software to control memory scrub hardware. The successful mission launched Sept 6, 2013 and was de-orbited and impacted the moon's surface on April 18, 2014. The spacecraft had 3 primary science instruments, the Lunar Dust Experiment, Neutral Mass Spectrometer, and the Ultra Violet Spectrometer. The mission also had a Laser Communications payload that set a record download rate of 622 MPS from the moon orbit. Over the course of the mission, LADEE had to tolerate a varying space radiation environment during a period of relative solar maximum and multiple passes through the Earth's Van Allen Radiation Belt. In order to mitigate this challenging environment, the Integrated Avionics Unit (IAU) chosen for the mission (a Broadreach Engineering RAD-750) implemented memory scrub in hardware. Software developed for the mission initialized and controlled the Error Detection and Correction (EDAC) circuitry and categorized and reported on errors that occurred during flight. The payloads, sensors and actuators each had varying degrees of tolerance to space radiation events, and events on these pieces of hardware were also tracked. This paper discusses the avionics and software for resilience to radiation events, and characterized the types of events during the course of LADEE's mission. C1 [Limes, Greg] NASA, SGT Inc, Ames Res Ctr, Moffett Field, CA 94035 USA. [Christa, Scott] NASA, Ames Res Ctr, AerospaceComp Inc, Moffett Field, CA 94035 USA. [Pires, Craig; Gundy-Burlet, Karen] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Limes, G (reprint author), NASA, SGT Inc, Ames Res Ctr, Moffett Field, CA 94035 USA. EM gregory.limes@nasa.gov; scott.e.christa@nasa.gov; craig.r.pires@nasa.gov; karen.gundy-burlet@nasa.gov NR 14 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 8 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302043 ER PT J AU Lin, H Long, E Sosnowski, J Jamnejad, V AF Lin, Hungsheng Long, Ezra Sosnowski, John Jamnejad, Vahraz GP IEEE TI Design of a New Smaller Lighter Faraday Rotator for ACERAD Radar QOTL SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB We describe a new Faraday rotator as part of the Quasi Optical Transmission Line (QOTL) on the Aerosol/Cloud/Ecosystems (ACE) mission. A QOTL design has been completed and laboratory tested and is the subject of a separate paper. A major component of the QOTL is a Faraday Rotator used in the simultaneous transmit and receive operation. It rotates the polarization of the transmitted and received signals by 45 degrees in opposite directions, thus creating a 90 degree polarization difference which is utilized by a linear polarizer to separate the two. This paper describes the design of a new rotator which is substantially lighter and smaller than a previous one used in the CloudSat radar jointly developed by JPL/NASA, Canadian Space Agency and other agencies. This is achieved by using better ferrite materials and a higher degree of optimization in the design. The weight and volume of the rotator have been substantially reduced to less than one third of the original. Furthermore, the RF performance of the new magnet design is much better than original design in the 94 GHz range. The new Faraday Rotator has been fabricated and tested with very good results. C1 [Lin, Hungsheng; Long, Ezra; Sosnowski, John; Jamnejad, Vahraz] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Lin, H (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Vahraz.Jamnejad@jpl.nasa.gov NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 7 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302069 ER PT J AU Little, JM Majerowicz, W Shinn, SA AF Little, Jonathan M. Majerowicz, Walt Shinn, Stephen A. GP IEEE TI Implementing Quantitative Schedule Performance Metrics at NASA Goddard Space Flight Center SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB For the past several years, NASA Goddard Space Flight Center's Flight Projects Directorate (FPD) spearheaded the Business Change Initiative (BCI) to improve program planning and control practices to enhance cost and schedule performance. One outcome of the BCI is a renewed emphasis on schedule in the form of a directive to plan, assess, and measure schedule performance. A guideline with accompanying procedures was developed and released to institute the implementation and adoption of three essential schedule performance metrics: baseline execution index (BEI), hit-miss index (HMI), and current execution index (CEI). These metrics aid project management by quantifying schedule performance against both the schedule baseline as well as the current operating schedule. To enable Goddard's projects to generate and report the new performance metrics on a monthly basis, FPD designed and developed the Goddard Schedule Analysis Tool (GSAT), which when added to MS Project, can calculate BEI, HMI, and CEI, as well as produce associated trend reports. GSAT also provides a drill-down capability to better understand variances at lower levels of the work breakdown structure. This tool dramatically decreases the time programs and projects would normally devote to generating BEI, HMI, and CEI performance metrics, and improves the consistency in reporting for internal reviews. Prior to formal deployment, FPD surveyed its project portfolio to assess the current status of all projects and determine the appropriate scope for applicability and required adoption. To date, the requirements have been published, the tool has been deployed to all identified projects, and all projects report on the performance metrics monthly at directorate-level tag-ups. These metrics have been beneficial to the discussion and review of mission success. This paper summarizes Goddard's BCI progress to date and introduces the BEI, HMI, and CEI metrics and how these metrics can be used to monitor project schedule performance and trends. It also highlights programmatic and technical challenges associated with measuring schedule performance with these indices. An examination of the cultural resistance to the metrics and how we worked with stakeholders to understand and address their concerns are also described. Results of some initial "back-testing" of the metrics on completed projects are highlighted and actual GSAT report examples are included. C1 [Little, Jonathan M.; Majerowicz, Walt; Shinn, Stephen A.] Goddard Space Flight Ctr, 8800 Greenbelt Rd,Code 452, Greenbelt, MD 20771 USA. RP Little, JM (reprint author), Goddard Space Flight Ctr, 8800 Greenbelt Rd,Code 452, Greenbelt, MD 20771 USA. EM jonathan.m.little@nasa.gov; walt.majerowicz@nasa.gov; stephen.a.shinn@nasa.gov NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 11 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302051 ER PT J AU Lopez, P Schultz, E Mattfeld, B Stromgren, C Goodliff, K AF Lopez, Pedro, Jr. Schultz, Eric Mattfeld, Bryan Stromgren, Chel Goodliff, Kandyce GP IEEE TI Logistics Needs for Potential Deep Space Mission Scenarios Post Asteroid Redirect Crewed Mission SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB The Asteroid Redirect Mission (ARM) is currently being explored as the next step towards deep space human exploration, with the ultimate goal of reaching Mars. NASA is currently investigating a number of potential human exploration missions, which will progressively increase the distance and duration that humans spend away from Earth. Missions include extended human exploration in cis-lunar space which, as conceived, would involve durations of around 60 days, and human missions to Mars, which are anticipated to be as long as 1000 days. The amount of logistics required to keep the crew alive and healthy for these missions is significant. It is therefore important that the design and planning for these missions include accurate estimates of logistics requirements. This paper provides a description of a process and calculations used to estimate mass and volume requirements for crew logistics, including consumables, such as food, personal items, gasses, and liquids. Determination of logistics requirements is based on crew size, mission duration, and the degree of closure of the environmental control life support system (ECLSS). Details are provided on the consumption rates for different types of logistics and how those rates were established. Results for potential mission scenarios are presented, including a breakdown of mass and volume drivers. Opportunities for mass and volume reduction are identified, along with potential threats that could possibly increase requirements. C1 [Lopez, Pedro, Jr.; Schultz, Eric] NASA, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. [Mattfeld, Bryan; Stromgren, Chel] Binera Inc, Silver Spring, MD 20910 USA. [Goodliff, Kandyce] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Lopez, P (reprint author), NASA, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. EM pedro.lopez-1@nasa.gov; eric.d.schultz@nasa.gov; b.mattfeld@binera.com; c.stromgren@binera.com; kandyce.e.goodliff@nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 10 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302094 ER PT J AU Malekpour, MR AF Malekpour, Mahyar R. GP IEEE TI A Self-Stabilizing Hybrid Fault-Tolerant Synchronization Protocol SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT ID CLOCK SYNCHRONIZATION AB This paper presents a strategy for solving the Byzantine general problem for self-stabilizing a fully connected network from an arbitrary state and in the presence of any number of faults with various severities including any number of arbitrary (Byzantine) faulty nodes. The strategy consists of two parts: first, converting Byzantine faults into symmetric faults, and second, using a proven symmetric-fault tolerant algorithm to solve the general case of the problem. A protocol (algorithm) is also present that tolerates symmetric faults, provided that there are more good nodes than faulty ones. The solution applies to realizable systems, while allowing for differences in the network elements, provided that the number of arbitrary faults is not more than a third of the network size. The only constraint on the behavior of a node is that the interactions with other nodes are restricted to defined links and interfaces. The solution does not rely on assumptions about the initial state of the system and no central clock nor centrally generated signal, pulse, or message is used. Nodes are anonymous, i.e., they do not have unique identities. A mechanical verification of a proposed protocol is also present. A bounded model of the protocol is verified using the Symbolic Model Verifier (SMV). The model checking effort is focused on verifying correctness of the bounded model of the protocol as well as confirming claims of determinism and linear convergence with respect to the self-stabilization period. C1 [Malekpour, Mahyar R.] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Malekpour, MR (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM Mahyar.R.Malekpour@nasa.gov NR 26 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 11 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302103 ER PT J AU Marquez, JJ AF Marquez, Jessica J. GP IEEE TI Integrating Human Performance Measures into Space Operations: Beyond Our Scheduling Capabilities? SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT ID CIRCADIAN-RHYTHMS; SLEEP; FATIGUE AB Current planning and scheduling software tools for International Space Station (ISS) support different flight controller teams as they plan daily space operations. Planning and scheduling tools capabilities include integrating digitized ISS state inputs, evaluating their expected future states, and propagating them over time. Extensive, custom-made computational models of operations, of objectives, and of operational constraints help ISS flight controllers identify where scheduled events violate constraints. Based on the current capabilities of these tools, this paper proposes how human performance measures could be better integrated into planning and scheduling tools for space mission operations. Future integration of human performance measures could be applied to state inputs (in this case, the astronaut's state) and to modeling human performance operational constraints & operational objectives (i.e., assigned activities) with parameters that are relevant to human performance measures. Gaps between the state-of-the-art for human performance modeling and planning tools for future exploration missions are identified. C1 [Marquez, Jessica J.] NASA, Ames Res Ctr, M-S 262-2,Bldg 262,Rm 132,POB 1, Moffett Field, CA 94035 USA. RP Marquez, JJ (reprint author), NASA, Ames Res Ctr, M-S 262-2,Bldg 262,Rm 132,POB 1, Moffett Field, CA 94035 USA. EM Jessica.J.Marquez@nasa.gov NR 27 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 9 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302048 ER PT J AU Mattfeld, B Stromgren, C Shyface, H Cirillo, W Goodliff, K AF Mattfeld, Bryan Stromgren, Chel Shyface, Hilary Cirillo, William Goodliff, Kandyce GP IEEE TI Developing a Crew Time Model for Human Exploration Missions to Mars SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Candidate human missions to Mars require mission lengths that could extend beyond those that have previously been demonstrated during crewed Lunar (Apollo) and International Space Station (ISS) missions. The nature of the architectures required for deep space human exploration will likely necessitate major changes in how crews operate and maintain the spacecraft. The uncertainties associated with these shifts in mission constructs - including changes to habitation systems, transit durations, and system operations raise concerns as to the ability of the crew to complete required overhead activities while still having time to conduct a set of robust exploration activities. This paper will present an initial assessment of crew operational requirements for human missions to the Mars surface. The presented results integrate assessments of crew habitation, system maintenance, and utilization to present a comprehensive analysis of potential crew time usage. Destination operations were assessed for a short (similar to 50 day) and long duration (similar to 500 day) surface habitation case. Crew time allocations are broken out by mission segment, and the availability of utilization opportunities was evaluated throughout the entire mission progression. To support this assessment, the integrated crew operations model (ICOM) was developed. ICOM was used to parse overhead, maintenance and system repair, and destination operations requirements within each mission segment outbound transit, Mars surface duration, and return transit to develop a comprehensive estimation of exploration crew time allocations. Overhead operational requirements included daily crew operations, health maintenance activities, and down time. Maintenance and repair operational allocations are derived using the Exploration Maintainability and Analysis Tool (EMAT) to develop a probabilistic estimation of crew repair time necessary to maintain systems functionality throughout the mission. C1 [Mattfeld, Bryan; Stromgren, Chel] Binera Inc, 8455 Colesville Rd,Suite 1075, Silver Spring, MD 20910 USA. [Shyface, Hilary] Analyt Mech Associates Inc, Hampton, VA 23666 USA. [Cirillo, William; Goodliff, Kandyce] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Mattfeld, B (reprint author), Binera Inc, 8455 Colesville Rd,Suite 1075, Silver Spring, MD 20910 USA. EM b.mattfeld@binera.com; c.stromgren@binera.com; h.shyface@ama-inc.com; william.m.cirillo@nasa.gov; kandyce.e.goodliff@nasa.gov NR 6 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 16 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303068 ER PT J AU McGhan, CLR Murray, RM Serra, R Ingham, MD Ono, M Estlin, T Williams, BC AF McGhan, Catharine L. R. Murray, Richard M. Serra, Romain Ingham, Michel D. Ono, Masahiro Estlin, Tara Williams, Brian C. GP IEEE TI A Risk-Aware Architecture for Resilient Spacecraft Operations SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB In this paper we discuss a resilient, risk-aware software architecture for onboard, real-time autonomous operations that is intended to robustly handle uncertainty in spacecraft behavior within hazardous and unconstrained environments, without unnecessarily increasing complexity. This architecture, the Resilient Spacecraft Executive (RSE), serves three main functions: (1) adapting to component failures to allow graceful degradation, (2) accommodating environments, science observations, and spacecraft capabilities that are not fully known in advance, and (3) making risk-aware decisions without waiting for slow ground-based reactions. This RSE is made up of four main parts: deliberative, habitual, and reflexive layers, and a state estimator that interfaces with all three. We use a risk-aware goal-directed executive within the deliberative layer to perform risk-informed planning, to satisfy the mission goals (specified by mission control) within the specified priorities and constraints. Other state-of-the-art algorithms to be integrated into the RSE include correct-by-construction control synthesis and model-based estimation and diagnosis. We demonstrate the feasibility of the architecture in a simple implementation of the RSE for a simulated Mars rover scenario. C1 [McGhan, Catharine L. R.; Murray, Richard M.] CALTECH, Dept Control & Dynam Syst, 1200 E Calif Blvd,Mail Code 107-81, Pasadena, CA 91125 USA. [Serra, Romain] Univ Toulouse, LAAS CNRS, F-31031 Toulouse 4, France. [Ingham, Michel D.; Ono, Masahiro; Estlin, Tara] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. [Williams, Brian C.] MIT, Dept Aeronaut & Astronaut, Cambridge, MA 02139 USA. RP McGhan, CLR (reprint author), CALTECH, Dept Control & Dynam Syst, 1200 E Calif Blvd,Mail Code 107-81, Pasadena, CA 91125 USA. EM cmcghan@cms.caltech.edu; murray@cds.caltech.edu; serra@laas.fr; Michel.D.Ingham@jpl.nasa.gov; Masahiro.Ono@jpl.nasa.gov; Tara.A.Estlin@jpl.nasa.gov; williams@csail.mit.edu NR 37 TC 0 Z9 0 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 15 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501301066 ER PT J AU Mercury, M Drouin, B Brageot, E Beatty, R Green, R Mouroulis, P Stephens, G Duren, R Rogers, WF Rosen, H Gerwe, D AF Mercury, Michael Drouin, Brian Brageot, Emily Beatty, Richard Green, Robert Mouroulis, Pantazis Stephens, Graeme Duren, Riley Rogers, W. Ford Rosen, Harold Gerwe, David GP IEEE TI Monitoring Earth's Shortwave Reflectance: LEO and GEO System Architectures SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT ID CLOUDS AB Monitoring the Earth's shortwave reflectance with persistent, sub-diurnal, cloud-resolved sampling would improve understanding of key climate system processes and track geo-engineering efforts. Current measurement systems do not provide the spatial, spectral or temporal sampling to distinguish between natural variability and anthropogenic modification, so this paper presents Low Earth Orbit (LEO) and Geosynchronous Earth Orbit (GEO) system architectures that would provide these monitoring capabilities. The LEO system concept would be a constellation of sixteen microsatellites in four orbit planes with a miniature push-broom Dyson spectrometer providing a 709 km swath. The satellite would be a Boeing microsat that builds on heritage of recent Boeing Space Environmental NanoSat Experiment (SENSE) mission. The GEO system concept would be a scanning Offner spectrometer on a constellation of six satellites launched from a single EELV class launch vehicle. Both systems would provide a two hour revisit, globally, at 1 km spatial resolution and 10 nm spectral resolution between 380 nm and 2510 nm. C1 [Mercury, Michael; Drouin, Brian; Brageot, Emily; Beatty, Richard; Green, Robert; Mouroulis, Pantazis; Stephens, Graeme; Duren, Riley] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Rogers, W. Ford; Rosen, Harold; Gerwe, David] Boeing Space & Intelligence Syst, El Segundo, CA 90245 USA. RP Mercury, M (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Michael.B.Mercury@jpl.nasa.gov; Ford.Rogers@boeing.com NR 13 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 9 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501301019 ER PT J AU Merrill, RG Strange, N Qu, M Hatten, N AF Merrill, Raymond G. Strange, Nathan Qu, Min Hatten, Noble GP IEEE TI Mars Conjunction Crewed Missions with a Reusable Hybrid Architecture SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB A new crew Mars architecture has been developed that provides many potential benefits for NASA-led human Mars moons and surface missions beginning in the 2030s or 2040s. By using both chemical and electric propulsion systems where they are most beneficial and maintaining as much orbital energy as possible, the Hybrid spaceship that carries crew round trip to Mars is pre-integrated before launch and can be delivered to orbit by a single launch. After check-out on the way to cis-lunar space, it is refueled and can travel round trip to Mars in less than 1100 days, with a minimum of 300 days in Mars vicinity (opportunity dependent). The entire spaceship is recaptured into cis-lunar space and can be reused. The spaceship consists of a habitat for 4 crew attached to the Hybrid propulsion stage which uses long duration electric and chemical in-space propulsion technologies that are in use today. The hybrid architecture's con-ops has no in-space assembly of the crew transfer vehicle and requires only rendezvous of crew in a highly elliptical Earth orbit for arrival at and departure from the spaceship. The crew transfer vehicle does not travel to Mars so it only needs be able to last in space for weeks and re-enter at lunar velocities. The spaceship can be refueled and resupplied for multiple trips to Mars (every other opportunity). The hybrid propulsion stage for crewed transits can also be utilized for cargo delivery to Mars every other opportunity in a reusable manner to pre-deploy infrastructure required for Mars vicinity operations. Finally, the Hybrid architecture provides evolution options for mitigating key long-duration space exploration risks, including crew microgravity and radiation exposure. C1 [Merrill, Raymond G.] NASA, Langley Res Ctr, 1 North Dryden St MS 462, Hampton, VA 23681 USA. [Strange, Nathan] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. [Qu, Min] AMA Inc, Hampton, VA 23666 USA. [Hatten, Noble] Univ Texas Austin, Dept Aerosp Engn & Engn Mech, Austin, TX 78712 USA. RP Merrill, RG (reprint author), NASA, Langley Res Ctr, 1 North Dryden St MS 462, Hampton, VA 23681 USA. EM Raymond.G.Merrill@nasa.gov; Nathan.J.Strange@nasa.gov; M.Qu-1@nasa.gov; Noble.Hatten@gmail.com NR 17 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 13 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300080 ER PT J AU Miller, MJ McGuire, KM Feigh, KM AF Miller, Matthew J. McGuire, Kerry M. Feigh, Karen M. GP IEEE TI Information Flow Model of Human Extravehicular Activity Operations SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Future human spaceflight missions will face the complex challenge of performing human extravehicular activity (EVA) beyond the low Earth orbit (LEO) environment. Astronauts will become increasingly isolated from Earth-based mission support and thus will rely heavily on their own decision-making capabilities and onboard tools to accomplish proposed EVA mission objectives. To better address time delay communication issues, EVA characters, e.g. flight controllers, astronauts, etc., and their respective work practices and roles need to be better characterized and understood. This paper presents the results of a study examining the EVA work domain and the personnel that operate within it. The goal is to characterize current and historical roles of ground support, intravehicular (IV) crew and EV crew, their communication patterns and information needs. This work provides a description of EVA operations and identifies issues to be used as a basis for future investigation. C1 [Miller, Matthew J.; Feigh, Karen M.] Georgia Inst Technol, 270 Ferst Dr,Room 416, Atlanta, GA 30332 USA. [McGuire, Kerry M.] NASA, Johnson Space Ctr, Houston, TX 77058 USA. RP Miller, MJ (reprint author), Georgia Inst Technol, 270 Ferst Dr,Room 416, Atlanta, GA 30332 USA. EM mmiller@gatech.edu; kerry.m.mcguire@nasa.gov; karen.feigh@gatech.edu NR 34 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 15 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300067 ER PT J AU Moore, EC Ryder, J AF Moore, E. Cherice Ryder, Jeff GP IEEE TI Planning for Crew Exercise for Deep Space Mission Scenarios SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT ID LONG-DURATION SPACEFLIGHT; RESISTANCE EXERCISE; MUSCLE VOLUME; FIBERS; SIZE; BONE AB Exercise which is necessary for maintaining crew health on-orbit and preparing the crew for return to 1G can be challenging to incorporate into spaceflight vehicles. Deep space missions will require further understanding of the physiological response to microgravity, understanding appropriate mitigations, and designing the exercise systems to effectively provide mitigations, and integrating effectively into vehicle design with a focus to support planned mission scenarios. Recognizing and addressing the constraints and challenges can facilitate improved vehicle design and exercise system incorporation. C1 [Moore, E. Cherice] Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. [Ryder, Jeff] Univ Space Res Assoc, Houston, TX 77058 USA. RP Moore, EC (reprint author), Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. EM cherice.moore-1@nasa.gov; jeffrey.ryder-1@nasa.gov NR 14 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 9 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302097 ER PT J AU Moore, J Calvert, D Frady, G Chavers, G Hull, P Lowery, E Farmer, J Trinh, H Rojdev, K Piatek, I Ess, K Vitalpur, S Dunn, K AF Moore, Josh Calvert, Derek Frady, Greg Chavers, Greg Hull, Patrick Lowery, Eric Farmer, Jeff Huu Trinh Rojdev, Kristina Piatek, Irene Ess, Kim Vitalpur, Sharada Dunn, Kevin GP IEEE TI Resource Prospector Lander: Architecture and Trade Studies SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB NASA's Resource Prospector (RP) is a multi-center and multi-institution collaborative project to investigate the polar regions of the Moon in search of volatiles. The mission is rated Class D and the duration is approximately 10 days. The RP vehicle comprises three elements: the Lander, the Rover, and the Payload. The Payload is housed on the Rover and the Rover is on top of the Lander. The focus of this paper is on the Lander element for the RP vehicle. The design of the Lander was requirements-driven and focused on a low-cost approach. To arrive at the final configuration, several multi-disciplinary trade studies were conducted. There were several primary trade studies that were instrumental in determining the final design. This paper will discuss six of these trades in further detail and show how these trades led to the final architecture of the RP Lander. C1 [Moore, Josh; Calvert, Derek; Frady, Greg; Chavers, Greg; Hull, Patrick; Lowery, Eric; Farmer, Jeff; Huu Trinh] NASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USA. [Rojdev, Kristina; Piatek, Irene; Ess, Kim; Vitalpur, Sharada; Dunn, Kevin] NASA, Johnson Space Ctr, Houston, TX 77058 USA. RP Moore, J (reprint author), NASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USA. EM Joshua.moore@nasa.gov; Kristina.rojdev-1@nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 15 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501301024 ER PT J AU Morgan, PS AF Morgan, Paula S. GP IEEE TI Cassini Mission-to-Saturn Spacecraft Overview & CDS Preparations for End-of-Mission Proximal Orbits SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB In November 2016, the Cassini Mission-to-Saturn Spacecraft will enter a new mission regime, bringing the orbiter closer to Saturn's gaseous surface than ever before. This unique orbital profile will call for the vehicle to fly at very high speeds in a ballistic trajectory with shorter orbits than previously flown, within the vicinity of the "F" and "D" Rings of the Saturn ian system. This mission phase is called the "F-Ring/Proximal Orbit" segment where a close flyby of Saturn's moon Titan will place the spacecraft in an orientation which resides near the outside edge of Saturn's F-Ring, positioning the vehicle in the proper flight path to complete the final 42 orbits of Cassini's mission. After 20 F-Ring orbits, a second close flyby of Titan will place the spacecraft between the innermost D-Ring and Saturn, where it will continue to collect new and unique science data for the remaining 22 orbits, before a third and final distant flyby of this moon alters Cassini's flight path to an impact trajectory with Saturn's surface, plunging the vehicle into the planet's atmosphere and ending the spacecraft's very successful 20-year mission, on September 15, 2017. Environmental assessments indicate that the D-Ring contains a significantly higher dust level than previously encountered by the spacecraft, while the F-Ring contains relatively little dust. Although Cassini was built to withstand dust and micro meteoroid impacts, high dust levels still pose a hazard to the vehicle during ring flyby events, and also cause a higher incidence of "bit flips" on the spacecraft's two Solid State Recorders (SSR) within the Command & Data Subsystem (CDS). Since these devices contain copies of the computer and instrument flight software (FSW), in addition to stored (recorded) science data, bit flip occurrences are autonomously repaired where possible. A high incidence of flipped bits could corrupt the SSR's stored science data significantly, and cause autonomous repairs in the FSW region, which if activated often [GRAPHICS] enough, can interrupt science data collection to a significant degree and inhibit instrument FSW load retrieval from the SSR when required, as well as contribute to the likelihood of SSR memory failures. Additionally, cosmic ray-induced bit flips can occur on uplinked commands sent from the Ground to the spacecraft, such as the November 2010 Safing event where Cassini executed its Spacecraft Safing Response upon receipt of a corrupted uplink command, causing the autonomous Fault Protection (FP) to activate, which consumes a portion of Cassini's carefully budgeted propellant residual. Also of concern for the Proximal Orbits is the possibility of high radiation levels which contribute to Solid State Power Switch trips on the 192 switches aboard Cassini; several of which activate FP. In the presence of this adverse environment where very short orbits require minimized fault recovery time to maximize science capture, preparatory measures have been taken to address anomalous events quickly and are detailed in this paper.(1) C1 [Morgan, Paula S.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Morgan, PS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Paula.S.Morgan@jpl.nasa.gov NR 15 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 17 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300037 ER PT J AU Murray, A Clark, K AF Murray, Alex Clark, Ken GP IEEE TI The Use of UML for Software Requirements Expression and Management SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB It is common practice to write English-language "shall" statements to embody detailed software requirements in aerospace software applications. This paper explores the use of the UML language as a replacement for the English language for this purpose. Among the advantages offered by the Unified Modeling Language (UML) is a high degree of clarity and precision in the expression of domain concepts as well as architecture and design. Can this quality of UML be exploited for the definition of software requirements? While expressing logical behavior, interface characteristics, timeliness constraints, and other constraints on software using UML is commonly done and relatively straight-forward, achieving the additional aspects of the expression and management of software requirements that stakeholders expect, especially traceability, is far less so. These other characteristics, concerned with auditing and quality control, include the ability to trace a requirement to a parent requirement (which may well be an English "shall" statement), to trace a requirement to verification activities or scenarios which verify that requirement, and to trace a requirement to elements of the software design which implement that requirement. UML Use Cases, designed for capturing requirements, have not always been satisfactory. Some applications of them simply use the Use Case model element as a repository for English requirement statements. Other applications of Use Cases, in which Use Cases are incorporated into behavioral diagrams that successfully communicate the behaviors and constraints required of the software, do indeed take advantage of UML's clarity, but not in ways that support the traceability features mentioned above. Our approach uses the Stereotype construct of UML to precisely identify elements of UML constructs, especially behaviors such as State Machines and Activities, as requirements, and also to achieve the necessary mapping capabilities. We describe this approach in the context of a space-based software application currently under development at the Jet Propulsion Laboratory. C1 [Murray, Alex; Clark, Ken] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Murray, A (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM alex.murray@jpl.nasa.gov; kenneth.c.clark@jpl.nasa.gov NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 9 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300026 ER PT J AU Nag, S LeMoigne, J Miller, DW de Weck, O AF Nag, Sreeja LeMoigne, Jacqueline Miller, David W. de Weck, Olivier GP IEEE TI A Framework for Orbital Performance Evaluation in Distributed Space Missions for Earth Observation SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT ID CONSTELLATIONS AB Distributed Space Missions (DSMs) are gammg momentum in their application to earth science missions owing to their unique ability to increase observation sampling in angular, spatial, spectral and temporal dimensions simultaneously. DSM architectures have a large number of design variables and since they are expected to increase mission flexibility, scalability, evolvability and robustness, their design is a complex problem with many variables and objectives affecting performance. There are few open-access tools available to explore the tradespace of variables which allow performance assessment and are easy to plug into science goals, and therefore select the most optimal design. This paper presents a software framework developed on the MATLAB engine interfacing with STK, for DSM orbit design and selection. The associated tool is capable of generating thousands of homogeneous constellation or formation flight architectures based on pre-defined design variable ranges and sizing those architectures in terms of pre-defined performance metrics. The metrics can be input into observing system simulation experiments, as available from the science teams, allowing dynamic coupling of science and engineering designs. Design variables include constellation type, formation flight type, instrument view, altitude and inclination of chief orbits, differential orbital elements, leader satellites, latitudes or regions of interest, planes and satellite numbers. Intermediate performance metrics include angular coverage, number of accesses, revisit coverage, access deterioration over time at every point of the Earth's grid. The orbit design process can be streamlined and variables more bounded along the way, owing to the availability of low fidelity and low complexity models such as corrected HCW equations up to high precision STK models with J2 and drag. The tool can thus help any scientist or program manager select pre-Phase A, Pareto optimal DSM designs for a variety of science goals without having to delve into the details of the engineering design process. This paper uses cases measurements for multi-angular earth observation to demonstrate the applicability of the tool. C1 [Nag, Sreeja; Miller, David W.; de Weck, Olivier] MIT, Cambridge, MA 02139 USA. [LeMoigne, Jacqueline] NASA, Goddard Space Flight Ctr, Software Engn Div, Greenbelt, MD 20771 USA. [Miller, David W.] NASA HQ, Cambridge, MA 02139 USA. RP Nag, S (reprint author), MIT, Cambridge, MA 02139 USA. EM sreeja_n@mit.edu; Jacqueline.LeMoigne@nasa.gov; millerd@mit.edu; deweck@mit.edu NR 45 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 20 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303052 ER PT J AU Nessel, J Morse, J Zemba, M Riva, C Luini, L AF Nessel, James Morse, Jacquelynne Zemba, Michael Riva, Carlo Luini, Lorenzo GP IEEE TI Performance of the NASA Beacon Receiver for the Alphasat Aldo Paraboni TDP5 Propagation Experiment SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT ID ATTENUATION AB NASA Glenn Research Center (GRC) and the Politecnico di Milano (POLIMI) have initiated a joint propagation campaign within the framework of the Alphasat propagation experiment to characterize rain attenuation, scintillation, and gaseous absorption effects of the atmosphere in the 40 GHz band. NASA GRC has developed and installed a K/Q-band (20/40 GHz) beacon receiver at the POLIMI campus in Milan, Italy, which receives the 20/40 GHz signals broadcast from the Alphasat Aldo Paraboni Technology Demonstration Payload (TDP) #5 beacon payload. The primary goal of these measurements is to develop a physical model to improve predictions of communications systems performance within the Q-band. Herein, we describe the design and preliminary performance of the NASA propagation terminal, which has been installed and operating in Milan since June 2014. The receiver is based upon a validated Fast Fourier Transform (FFT) I/Q digital design approach utilized in other operational NASA propagation terminals, but has been modified to employ power measurement via a frequency estimation technique and to coherently track and measure the amplitude of the 20/40 GHz beacon signals. The system consists of a 1.2-m K-band and a 0.6-m Q-band Cassegrain reflector employing synchronous open-loop tracking to track the inclined orbit of the Alphasat satellite. An 8 Hz sampling rate is implemented to characterize scintillation effects, with a 1-Hz measurement bandwidth dynamic range of 45 dB. A weather station with an optical disdrometer is also installed to characterize rain drop size distribution for correlation with physical based models. C1 [Nessel, James; Morse, Jacquelynne; Zemba, Michael] NASA, Glenn Res Ctr 4800, 21000 Brookpark Rd,MS 54-1, Cleveland, OH 44135 USA. [Riva, Carlo; Luini, Lorenzo] Politecn Milan, I-20133 Milan, Italy. RP Nessel, J (reprint author), NASA, Glenn Res Ctr 4800, 21000 Brookpark Rd,MS 54-1, Cleveland, OH 44135 USA. EM james.a.nessel@nasa.gov; carlo.riva@polimi.it NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 7 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501304045 ER PT J AU Ni, JJ Lansdowne, C AF Ni, Jianjun Lansdowne, Chatwin GP IEEE TI Robust Low-Density-Parity-Check Decoder Design to Mitigate Pulsed Radio Frequency Interference SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Low-Density Parity-Check (LDPC) codes are a class of forward error correction (FEC) linear block codes which provide near-capacity performance for power-efficient communications. Optimum decoding requires accurate combining ratio estimation to scale the input signal in an additive white Gaussian noise channel (AWGN). Test data and analysis show that the performance of the optimal LDPC decoding algorithm is severely degraded when encountering pulsed radio frequency interference (RFI) from sources such as ground based radars. This research effort first reveals that the LDPC performance degradation under pulsed RFI is not due to the burst of errors but to the inaccurate combining ratio estimation. Although an ideal combining ratio estimator (symbol-wise) could mitigate the degradation caused by pulsed RFI, it is not practical for implementation. Some near optimal LDPC decoding algorithms which do not require combining ratio estimation are investigated. One near optimum decoding algorithm "min-scale" is proposed in the robust decoder design to mitigate pulsed RFI. Analysis shows that "min-scale" only loses about 0.2 dB performance compared to the optimal decoding algorithm under nominal condition; in a pulsed RFI environment, the designed performance can be achieved if the system design has adequate margin. Without combining ratio estimation, the decoder design complexity is reduced and the risk of performance degradation due to combining ratio estimation error is eliminated. This robust decoder design enables reliable communications to space vehicles which may encounter strong pulsed RFI signals from high power radar systems. C1 [Ni, Jianjun] MRI Technol JETS, 2101 NASA Pkwy, Houston, TX 77058 USA. [Lansdowne, Chatwin] NASA, Johnson Space Ctr, Houston, TX 77058 USA. RP Ni, JJ (reprint author), MRI Technol JETS, 2101 NASA Pkwy, Houston, TX 77058 USA. EM david.ni-1@nasa.gov; chatwin.lansdowne@nasa.gov NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 6 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303025 ER PT J AU Oberhettinger, D AF Oberhettinger, David GP IEEE TI The PRACA System as an 'Incubator' for Lessons Learned SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Although NASA has an established process for documenting lessons learned from development and operation of its complex and challenging missions, a recent audit of the NASA lessons learned program found that most NASA Centers have made few contributions to the NASA lessons learned repository in recent years. Among the NASA Centers, the NASA/Caltech Jet Propulsion Laboratory (JPL) has a relatively mature lesson learned process. Based on his experience managing the JPL lessons learned process, the author suggests that organizations lacking sources of lessons learned content may find excellent pre-screened material in their equivalent of the Laboratory's problem/failure reporting system. JPL confidence in the value and veracity of its lesson learned submissions is enhanced by an extensive periodic review of Problem Reporting and Corrective Action (PRACA) reports from JPL spaceflight projects. A standard practice of most engineering organizations throughout the system development life cycle, this formal anomaly reporting may reveal enterprise-wide process deficiencies or other issues worthy of documentation as lessons learned. Valid lesson learned topics are derived from various sources, including word-of-mouth. But when a lesson learned is supported by information from the PRACA system, it benefits from the rigorous PRACA vetting process that includes formal analysis of proximate cause and root cause. A "well-incubated" PRACA report-i.e., one that has benefitted from thousands of labor dollars worth of engineering analysis and reflection and has been signed off by the appropriate engineering authorities-may provide ample objective evidence of a lesson that needs to be learned. C1 [Oberhettinger, David] CALTECH, NASA, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Oberhettinger, D (reprint author), CALTECH, NASA, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM davido@jpl.nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 8 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300006 ER PT J AU Ong, J Remolina, E Prompt, A Robinson, P Sweet, A Nishikawa, D AF Ong, James Remolina, Emilio Prompt, Axel Robinson, Peter Sweet, Adam Nishikawa, David GP IEEE TI Software Testbed for Developing and Evaluating Integrated Autonomous Systems SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB To implement fault tolerant autonomy in future space systems, it will be necessary to integrate planning, adaptive control, and state estimation subsystems. However, integrating these subsystems is difficult, time-consuming, and error-prone. This paper describes Intelliface/ADAPT, a software testbed that helps researchers develop and test alternative strategies for integrating planning, execution, and diagnosis subsystems more quickly and easily. The testbed's architecture, graphical data displays, and implementations of the integrated subsystems support easy plug and play of alternate components to support research and development in fault-tolerant control of autonomous vehicles and operations support systems. Intelliface/ADAPT controls NASA's Advanced Diagnostics and Prognostics Testbed ( ADAPT), which comprises batteries, electrical loads ( fans, pumps, and lights), relays, circuit breakers, invertors, and sensors. During plan execution, an experimentor can inject faults into the ADAPT testbed by tripping circuit breakers, changing fan speed settings, and closing valves to restrict fluid flow. The diagnostic subsystem, based on NASA's Hybrid Diagnosis Engine ( HyDE), detects and isolates these faults to determine the new state of the plant, ADAPT. Intelliface/ADAPT then updates its model of the ADAPT system's resources and determines whether the current plan can be executed using the reduced resources. If not, the planning subsystem generates a new plan that reschedules tasks, reconfigures ADAPT, and reassigns the use of ADAPT resources as needed to work around the fault. The resource model, planning domain model, and planning goals are expressed using NASA's Action Notation Modeling Language ( ANML). Parts of the ANML model are generated automatically, and other parts are constructed by hand using the Planning Model Integrated Development Environment, a visual Eclipse-based IDE that accelerates ANML model development. Because native ANML planners are currently under development and not yet sufficiently capable, the ANML model is translated into the New Domain Definition Language ( NDDL) and sent to NASA's EUROPA planning system for plan generation. The adaptive controller executes the new plan, using augmented, hierarchical finite state machines to select and sequence actions based on the state of the ADAPT system. Real-time sensor data, commands, and plans are displayed in information-dense arrays of timelines and graphs that zoom and scroll in unison. A dynamic schematic display uses color to show the real-time fault state and utilization of the system components and resources. An execution manager coordinates the activities of the other subsystems. The subsystems are integrated using the Internet Communications Engine ( ICE), an object-oriented toolkit for building distributed applications. C1 [Ong, James; Remolina, Emilio; Prompt, Axel] Stottler Henke Associates Inc, 1670 S Amphlett Blvd,Suite 310, San Mateo, CA 94402 USA. [Robinson, Peter; Sweet, Adam; Nishikawa, David] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Ong, J (reprint author), Stottler Henke Associates Inc, 1670 S Amphlett Blvd,Suite 310, San Mateo, CA 94402 USA. EM ong@stottlerhenke.com; remolina@stottlerhenke.com; aprompt@stottlerhenke.com; peter.i.robinson@nasa.gov; adam.sweet@nasa.gov; david.nishikawa@nasa.gov NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 12 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303073 ER PT J AU Ono, M Nicholas, A Alibay, F Parrish, J AF Ono, Masahiro Nicholas, Austin Alibay, Farah Parrish, Joseph GP IEEE TI SMART: a Propositional Logic-Based Trade Analysis and Risk Assessment Tool for a Complex Mission SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT ID APPROXIMATE INCLUSION-EXCLUSION AB This paper introduces a new trade analysis software called the Space Mission Architecture and Risk Analysis Tool (SMART). This tool supports a high-level system trade study on a complex mission, such as a potential Mars Sample Return (MSR) mission, in an intuitive and quantitative manner. In a complex mission, a common approach to increase the probability of success is to have redundancy and prepare backups. Quantitatively evaluating the utility of adding redundancy to a system is important but not straightforward, particularly when the failure of parallel subsystems are correlated. SMART offers the unique capability of handling correlated redundancies and accurately evaluating the probability of mission success as well as its sensitivity to the reliability of mission components. It can also perform Monte-Carlo analysis to find the confidence interval of the success probability, total mission cost, and total mass. Additionally, SMART provides a GUI interface based on Matlab/Simulink that allows users to graphically define mission architecture as well as the logical relationship between mission components and outcomes. These analysis capabilities enable to answer questions such as: "for a given upper bound on total cost and mass, on which subsystem should we implement redundancy to maximize the chance of mission success?" Although the focus of SMART is high-level trade analysis, it also provides an interface to detailed models of mission components, allowing to perform an integrated analysis that covers from low-level details to high-level architecture. The analysis capabilities are enabled by our unique propositional logic-based approach. SMART translates the graphical mission model to a propositional logic representation through symbolic computation. We demonstrate SMART's analysis capabilities on a MSR model as well as a model of a fictional mission. C1 [Ono, Masahiro; Nicholas, Austin; Alibay, Farah; Parrish, Joseph] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Ono, M (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Masahiro.Ono@jpl.nasa.gov; Austin.K.Nicholas@jpl.nasa.gov; Farah.Alibay@jpl.nasa.gov; Joseph.C.Parrish@jpl.nasa.gov NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 15 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501301052 ER PT J AU Ono, M Fuchs, TJ Steffy, A Maimone, M Yen, J AF Ono, Masahiro Fuchs, Thoams J. Steffy, Amanda Maimone, Mark Yen, Jeng GP IEEE TI Risk-aware Planetary Rover Operation: Autonomous Terrain Classification and Path Planning SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Identifying and avoiding terrain hazards (e.g., soft soil and pointy embedded rocks) are crucial for the safety of planetary rovers. This paper presents a newly developed ground-based Mars rover operation tool that mitigates risks from terrain by automatically identifying hazards on the terrain, evaluating their risks, and suggesting operators safe paths options that avoids potential risks while achieving specified goals. The tool will bring benefits to rover operations by reducing operation cost, by reducing cognitive load of rover operators, by preventing human errors, and most importantly, by significantly reducing the risk of the loss of rovers. The risk-aware rover operation tool is built upon two technologies. The first technology is a machine learning-based terrain classification that is capable of identifying potential hazards, such as pointy rocks and soft terrains, from images. The second technology is a risk-aware path planner based on rapidly-exploring random graph (RRG) and the A* search algorithms, which is capable of avoiding hazards identified by the terrain classifier with explicitly considering wheel placement. We demonstrate the integrated capability of the proposed risk-aware rover operation tool by using the images taken by the Curiosity rover. C1 [Ono, Masahiro; Fuchs, Thoams J.; Steffy, Amanda; Maimone, Mark; Yen, Jeng] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Ono, M (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Masahiro.Ono@jpl.nasa.gov; Thomas.Fuchs@jpl.nasa.gov; Amanda.C.Steffy@jpl.nasa.gov; Mark.W.Maimone@jpl.nasa.gov; Jeng.Yen@jpl.nasa.gov NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 10 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501301053 ER PT J AU Owens, BD Crocker, AR AF Owens, Brandon D. Crocker, Alan R. GP IEEE TI SimSup's Loop: A Control Theory Approach to Spacecraft Operator Training SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT ID SYSTEMS; SAFETY AB Immersive simulation is a staple of training for many complex system operators, including astronauts and ground operators of spacecraft. However, while much has been written about simulators, simulation facilities, and operator certification programs, the topic of how one develops simulation scenarios to train a spacecraft operator is relatively understated in the literature. In this paper, an approach is presented for using control theory as the basis for developing the immersive simulation scenarios for a spacecraft operator training program. The operator is effectively modeled as a high level controller of lower level hardware and software control loops that affect a select set of system state variables. Simulation scenarios are derived from a STAMP-based hazard analysis of the operator's high and low level control loops. The immersive simulation aspect of the overall training program is characterized by selecting a set of scenarios that expose the operator to the various inadequate control actions that stem from control flaws and inadequate control executions in the different sections of the typical control loop. Results from the application of this approach to the Lunar Atmosphere and Dust Environment Explorer (LADEE) mission are provided through an analysis of the simulation scenarios used for operator training and the actual anomalies that occurred during the mission. The simulation scenarios and in flight anomalies are mapped to specific control flaws and inadequate control executions in the different sections of the typical control loop to illustrate the characteristics of anomalies arising from the different sections of the typical control loop (and why it is important for operators to have exposure to these characteristics). Additionally, similarities between the simulation scenarios and inflight anomalies are highlighted to make the case that the simulation scenarios prepared the operators for the mission. C1 [Owens, Brandon D.] NASA, Ames Res Ctr, Stinger Ghaffarian Technol, Mail Stop 240-2, Moffett Field, CA 94035 USA. [Crocker, Alan R.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Owens, BD (reprint author), NASA, Ames Res Ctr, Stinger Ghaffarian Technol, Mail Stop 240-2, Moffett Field, CA 94035 USA. EM brandon.d.owens@nasa.gov; alan.r.crocker@nasa.gov NR 36 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 17 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300047 ER PT J AU Percy, T McGuire, M Polsgrove, T AF Percy, Tom McGuire, Melissa Polsgrove, Tara GP IEEE TI Combining Solar Electric Propulsion and Chemical Propulsion for Crewed Missions to Mars SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB This paper documents the results of an investigation of human Mars mission architectures that leverage near-term technology investments and infrastructures resulting from the planned Asteroid Redirect Robotic Mission (ARRM), including high-power Solar Electric Propulsion (SEP) and a human presence in Lunar Distant Retrograde Orbit (LDRO). The architectures investigated use a combination of SEP and chemical propulsion elements. Through this combination of propulsion technologies, these architectures take advantage of the high efficiency SEP propulsion system to deliver cargo, while maintaining the faster trip times afforded by chemical propulsion for crew transport. Evolved configurations of the Asteroid Redirect Vehicle (ARV) are considered for cargo delivery. Sensitivities to SEP system design parameters, including power level and propellant quantity, are presented. For the crew delivery, liquid oxygen and methane stages were designed using engines common to future human Mars landers. Impacts of various Earth departure orbits, Mars loiter orbits, and Earth return strategies are presented. The use of the Space Launch System for delivery of the various architecture elements was also investigated and launch vehicle manifesting, launch scheduling and mission timelines are also discussed. The study results show that viable Mars architecture can be constructed using LDRO and SEP in order to take advantage of investments made in the ARRM mission. C1 [Percy, Tom] Jacobs ESSSA Grp SAIC, 6723 Odyssey Dr, Huntsville, AL 35806 USA. [McGuire, Melissa] NASA, Cleveland, OH 44135 USA. [Polsgrove, Tara] NASA, MSFC, Huntsville, AL 35812 USA. RP Percy, T (reprint author), Jacobs ESSSA Grp SAIC, 6723 Odyssey Dr, Huntsville, AL 35806 USA. EM Thomas.K.Percy@nasa.gov; Melissa.L.McGuire@nasa.gov; Tara.Polsgrove@nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 10 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501304023 ER PT J AU Ponchak, DS Apaza, RD Wichgers, JM Haynes, B Roy, A AF Ponchak, Denise S. Apaza, Rafael D. Wichgers, Joel M. Haynes, Brian Roy, Aloke GP IEEE TI A Study of Future Communications Concepts and Technologies for the National Airspace System-Part IV SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB The National Aeronautics and Space Administration (NASA) Glenn Research Center (GRC) is investigating current and anticipated wireless communications concepts and technologies that the National Airspace System (NAS) may need in the next 50 years. NASA has awarded three NASA Research Announcements (NAR) studies with the objective to determine the most promising candidate technologies for air-to-air and air-to-ground data exchange and analyze their suitability in a post-NextGen NAS environment. This paper will present the final results describing the communications challenges and opportunities that have been identified as part of the study. C1 [Ponchak, Denise S.; Apaza, Rafael D.] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. [Wichgers, Joel M.] Rockwell Collins, Cedar Rapids, IA USA. [Haynes, Brian] Xcelar, Hopkins, MN USA. [Roy, Aloke] Honeywell Int Inc, Columbia, MD USA. RP Ponchak, DS (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. EM Denise.S.Ponchak@nasa.gov; Rafael.D.Apaza@nasa.gov; Joel.Wichgers@rockwellcollins.com; brian.haynes@xcelar.com; aloke.roy@honeywell.com NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 13 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300059 ER PT J AU Randolph, TM Mullenax, R Schwantes, C Sell, SW Ball, DRJ AF Randolph, Thomas M. Mullenax, Robert Schwantes, Christopher Sell, Steven W. Ball, Danny R. J. GP IEEE TI The First Balloon Flight of the Low Density Supersonic Decelerator Technology Demonstration Mission SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB To improve the state of the art in Mars supersonic decelerator technology, the Low Density Supersonic Decelerator (LDSD) technology demonstration mission has embarked upon a series of high altitude balloon lofted, rocket propelled, supersonic reentry tests. Similar to Mars reentry technology tests performed in the 1970s, including the Planetary Entry Parachute Program (PEPP) and the Balloon Launch Decelerator Test (BLDT), LDSD relies on a zero pressure balloon to deliver the test vehicle to its high altitude initial conditions. The test architecture was successfully demonstrated in the first test flight of the project from the Pacific Missile Range Facility (PMRF) in Kauai on June 28th, 2014. In adapting this test architecture from the 1970s to today, many new developments were made to the balloon system including: a new balloon static launch technique and new balloon trajectory predictive capabilities. Additional diagnostic tools, intended for characterization of the test vehicle flight, were also available to characterize the balloon flight including: meteorological rockets for atmospheric characterization and the test vehicle's inertial measurement unit, which was able to measure the dynamic rates of the suspended payload. These results provided the test architecture validation and data necessary for the LDSD flights planned in 2015. C1 [Randolph, Thomas M.; Sell, Steven W.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Mullenax, Robert; Schwantes, Christopher; Ball, Danny R. J.] CSBF NMSU, Phys Sci Lab, Palestine, TX 75803 USA. RP Randolph, TM (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM thomas.m.randolph@jpl.nasa.gov; robert.mullenax@csbf.nasa.gov; chris.schwantes@csbf.nasa.gov; steven.w.sell@jpl.nasa.gov; danny.ball@csbf.nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 12 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303037 ER PT J AU Robinson, D Tonn, S AF Robinson, David Tonn, Synthia GP IEEE TI Mechanical Aspects of the Thermal Infrared System (TIRS) on Landsat 8 SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB The Thermal InfraRed Sensor (TIRS) instrument was launched into space on board Landsat 8 in February 2013. This instrument was added to Landsat 8 to measure water evaporation and transpiration as well as provide two thermal infrared bands to complement the optical suite. TIRS has a refractive telescope which focuses a light onto a focal plane cooled to 43K with a two-stage cryocooler. This paper will detail the mechanical aspects of TIRS including a description of its composite honeycomb box design, flexures, large deployable earth shield, and accommodations for the telescope, detector, and cryocooler. The design, build, test, and delivery of TIRS was accomplished in three years on an accelerated schedule at NASA Goddard Space Flight Center. The assembly and test flow are discussed including qualification of the structure in vibration and acoustic tests. C1 [Robinson, David; Tonn, Synthia] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP Robinson, D (reprint author), NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. EM david.w.robinson@nasa.gov; synthia.1.tonn@nasa.gov NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 10 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303022 ER PT J AU Rose, R Ruf, C Scherrer, J Wells, J AF Rose, Randy Ruf, Chris Scherrer, John Wells, James GP IEEE TI The CYGNSS Flight Segment; Mainstream Science on a Micro-Budget SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB NASA's first Earth Venture mission, the NASA EVM-1 Cyclone Global Navigation Satellite System (CYGNSS), is designed to provide data that will enable the study of the relationship between ocean surface properties, moist atmospheric thermodynamics and convective dynamics. These relationships are postulated to be intrinsic to the genesis and intensification of tropic storms. Key information about the ocean surface under and around a tropical storm is hidden from existing space borne observatories because the intense precipitation degrades the frequency bands in which they operate, obscuring the ocean's surface. GNSS-based bi-static scatterometry performed by a constellation of micro-satellites offers remote sensing of ocean waves and wind with unprecedented temporal resolution and spatial coverage across the full dynamic range of ocean wind speeds in all precipitating conditions. A better understanding of these relationships and their effects will advance our ability to forecast tropical storm intensity and storm surge. Achieving the required temporal and spatial resolution for tropical cyclone remote sensing has not been possible previously due to technology and cost limitations. Modeling techniques developed over the past 20 years combined with recent developments in nano-satellite technology and an increased risk tolerance by NASA have enabled the CYGNSS mission. CYGNSS consists of 8 GPS bi-static radar receivers deployed on 8 separate micro-satellites to be launched in October 2016. The mission is cost capped at $102M exclusive of launch vehicle. It is being developed as a Category 3 mission (per NPR 7120.5D NID) with Class D payloads (per NPR 8705.4). This paper will present an overview of the CYGNSS flight segment implementation and how our Class D approach allows the development to meet cost constraints. C1 [Rose, Randy; Scherrer, John] Southwest Res Inst, 6220 Culebra Rd, San Antonio, TX 78238 USA. [Ruf, Chris] Univ Michigan, Ann Arbor, MI 48109 USA. [Wells, James] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Rose, R (reprint author), Southwest Res Inst, 6220 Culebra Rd, San Antonio, TX 78238 USA. EM rrose@swri.org; cruf@umich.edu; jscherrer@swri.edu; James.E.Wells@nasa.gov NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 10 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303042 ER PT J AU Sankararaman, S Teubert, C AF Sankararaman, Shankar Teubert, Christopher GP IEEE TI Impact of Uncertainty on the Diagnostics and Prognostics of a Current-Pressure Transducer SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Current-Pressure (I/P) transducers are effective pressure regulators that can vary the output pressure depending on the supplied electrical current signal, and are commonly used in pneumatic actuators and valves. Faults in current-pressure transducers have a significant impact on the regulation mechanism; therefore, it is important to perform diagnosis to identify such faults and estimate their effect on the remaining useful life of the transducer. However, there are different sources of uncertainty that significantly affect the diagnostics procedure, and therefore, it may not be possible to perform fault diagnosis and prognosis accurately, with complete confidence. These sources of uncertainty include natural variability, sensor errors (gain, bias, noise), model uncertainty, etc. This paper presents a computational methodology to quantify the uncertainty and thereby estimate the confidence in the fault diagnosis of a current-pressure transducer. Further, the effect of diagnostic uncertainty on prognostics and remaining useful life prediction are also quantified. First, experiments are conducted to study the nominal and off-nominal behavior of the I/P transducer; however, sensor measurements are not fast enough to capture brief transient states that are indicative of wear, and hence, steady-state measurements are directly used for fault diagnosis. Second, the results of these experiments are used to train a Gaussian process model using machine learning principles. Finally, a Bayesian inference methodology is developed to quantify the uncertainty in fault diagnosis by systematically accounting for the aforementioned sources of uncertainty, and in turn, the uncertainty in prognostics is also estimated. C1 [Sankararaman, Shankar; Teubert, Christopher] NASA, SGT Inc, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Sankararaman, S (reprint author), NASA, SGT Inc, Ames Res Ctr, Moffett Field, CA 94035 USA. EM shankar.sankararaman@nasa.gov; christopher.a.teubert@nasa.gov NR 19 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 10 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302016 ER PT J AU Scott, DW Curreri, PA Ferguson, CK Nall, ME Tinker, ML Wright, GM AF Scott, David W. Curreri, Peter A. Ferguson, Cynthia K. Nall, Mark E. Tinker, Michael L. Wright, Gregory M. GP IEEE TI Germinating the 2050 Cis-Lunar Econosphere SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB In early 2013, Marshall Space Flight Center's upper management chartered a diverse team for a six-week "sprint" to speculate ( in a disciplined manner) and paint ( with broad brush strokes) a picture of how earth, space, and public/ private entities might be operating and relating to each other. in the year 2100. Two 12-person groups of civil servants, one with members having 15 years or less of NASA experience and the other with more senior members, worked independently and then compared and integrated their conclusions. In 2014, the " Space 2100" team, with some new team members and different group boundaries, ran a longer sprint to a) develop more detailed estimates of the operations and economics of space activities in the vicinity of the Earth and Moon in the 2050 time frame, b) identify evolutionary paths, barriers, and opportunities, and c) suggest actions and philosophies to enable and invigorate progress towards the vision. This paper explores Space 2100's first two sprints and their projections of NASA's role in what will likely be a highly networked, international space industry and cis-lunar infrastructure.(1) C1 [Scott, David W.; Curreri, Peter A.; Ferguson, Cynthia K.; Nall, Mark E.; Tinker, Michael L.; Wright, Gregory M.] NASA, MSFC, Huntsville, AL 35812 USA. RP Scott, DW (reprint author), NASA, MSFC, Huntsville, AL 35812 USA. EM scotty@nasa.gov; peter.a.curreri@nasa.gov; tia.ferguson@nasa.gov; mark.e.nall@nasa.gov; mike.tinker@nasa.gov; greg.wright@nasa.gov NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 16 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303080 ER PT J AU Seery, B Barbee, B Nuth, J Oman, L Boslough, M Miller, P Plesko, C Weaver, R AF Seery, Bernard Barbee, Brent Nuth, Joseph Oman, Luke Boslough, Mark Miller, Paul Plesko, Catherine Weaver, Robert GP IEEE TI INVESTIGATIONS OF SHORT WARNING TIME RESPONSE OPTIONS FOR HAZARDOUS NEAR-EARTH OBJECTS SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB This paper describes an assessment of capabilities for two planetary defense techniques: Kinetic Energy Impactors (KEIs) and Nuclear Explosive Devices (NEDs), including both Near Earth Asteroid (NEA) deflection and disruption. These studies will help us understand how energetic systems affect asteroidal (or cometary) bodies, and how to deliver energetic payloads to target objects under short warning time conditions, accounting for real-life constraints including payload integration and spacecraft Iifecycle. Techniques for spacecraft trajectory optimization and mission design, scientific knowledge of asteroid and comet characteristics and chemistry, and energetic systems modeling will be combined to produce designs and strategies that will inform effective, reliable responses to short warning time NEA impact scenarios. C1 [Seery, Bernard; Barbee, Brent; Nuth, Joseph; Oman, Luke] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Boslough, Mark] Sandia Natl Labs, Livermore, CA 94550 USA. [Miller, Paul] Lawrence Livermore Natl Lab, Lawrence, KS USA. [Plesko, Catherine; Weaver, Robert] Los Alamos Natl Lab, Los Alamos, NM USA. RP Seery, B (reprint author), NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. EM bernard.d.seery@nasa.gov NR 25 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 12 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300084 ER PT J AU Shinn, SA Lunz, VA AF Shinn, Stephen A. Lunz, Val A. GP IEEE TI Managing Cost, Schedule, and Technical Performance through a Sustained Change Framework SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Operating a world-renowned space flight mission portfolio under tight policy, fiscal scrutiny, and increased competition makes open communication, visible performance data, and streamlined processes challenging. To respond to these challenges and meet cost and schedule commitments, Goddard Space Flight Center's Flight Projects Directorate employed a Business Change Initiative (BCI) to infuse a series of activities coordinated to drive process improvement across Goddard's missions. The result is a framework that sustains continuous, lasting change, which actively educates and consistently applies program planning and control (PP&C) techniques to launch on time and on budget, and achieve mission success. The BCI formed an integrated community of flight projects that openly shares and applies best practices to ensure cost effective, on-time delivery for all missions. The BCI team employed a five-phase change framework to structure, guide, and respond to needed improvements and policy changes. To date, the team utilizes cross-cutting assessments of the space flight mission portfolio to envision opportunities that reinforce strengths and improve weaknesses and threats. Once these opportunities are defined, subject matter experts design, develop, and deploy changes that are scaled up or down for adoption, depending on mission requirements, and drive compliance and improve performance. Over 100 major changes were deployed from 2012-2014 spanning various PP&C disciplines to include: schedule, cost, earned value, risk, and configuration management, as well as project coordination, reporting, performance analysis, and employee education. These changes were the basis to improve cost and schedule management as well as to ensure compliance to federal and commercial policies and regulations. This paper will assess how a sustaining change framework provides a long-term strategy to maintain organization responsiveness and to continuously seek refinements and updates to tools and resources to meet cost and schedule commitments while maintaining technical excellence. This paper will also recommend how similar adoption in government and industry space agencies and companies will assist to collaborate across boundaries and build strategic relationships to achieve common goals in aerospace. C1 [Shinn, Stephen A.; Lunz, Val A.] Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP Shinn, SA (reprint author), Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. EM Stephen.A.Shinn@nasa.gov; Val.Lunz@nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 13 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302052 ER PT J AU Sindoni, G Pavlis, EC AF Sindoni, Giampiero Pavlis, Erricos C. GP IEEE TI LARES Mission Operations SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT ID LASER-RANGED SATELLITES; GENERAL-RELATIVITY; INERTIAL FRAMES; TIME-DELAY; SPIN; GRAVITY; LAGEOS; EARTH AB LAser RElativity Satellite (LARES) is an Italian Space Agency mission that started operations on February 2012 after a successful launch on ESA's VEGA qualification flight. The satellite is covered with retroreflectors that allow accurate laser ranging tracking from the stations of the International Laser Ranging Service. Data of laser ranged satellites are publicly available for scientific analysis and in the case of LARES are being used mainly for testing general relativity and in particular the Lense-Thirring effect due to the rotation of Earth. Although designed for fundamental physics, the LARES mission is also very useful for geodesy and geodynamics and it will provide, among other things, improvement of the International Terrestrial Reference Frame. After a description of the scientific objectives and of the satellite, the paper will focus on the operations required to run the mission. C1 [Sindoni, Giampiero] Univ Roma La Sapienza, DIAEE & SIA, Via Salaria 851, I-00141 Rome, Italy. [Pavlis, Erricos C.] Univ Maryland Baltimore Cty, Goddard Earth Sci & Technol Ctr, GEST UMBC, Baltimore, MD 21250 USA. [Pavlis, Erricos C.] NASA Goddard, Baltimore, MD 21250 USA. RP Sindoni, G (reprint author), Univ Roma La Sapienza, DIAEE & SIA, Via Salaria 851, I-00141 Rome, Italy. EM giampiero.sindoni@uniroma1.it; epavlis@umbc.edu NR 60 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 9 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302082 ER PT J AU Smith, B Cassell, A Kruger, C Venkatapathy, E Kazemba, C Simonis, K AF Smith, Brandon Cassell, Alan Kruger, Carl Venkatapathy, Ethiraj Kazemba, Cole Simonis, Kyle GP IEEE TI Nano-ADEPT: An Entry System for Secondary Payloads SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Small spacecraft have emerged in recent years from a niche academic pursuit to a platform for governments and corporations to perform scientific and commercial ventures in space at much lower cost. Simultaneously, the field of Entry, Descent, and Landing (EDL) is rapidly maturing a number of technologies geared toward delivering ever-larger payloads to destinations across our solar system, with the culminating event being safe transport of human beings to the surface of Mars. One of these technologies for landing large payloads, known as the Adaptable, Deployable Entry and Placement Technology (ADEPT), uses a mechanical skeleton to deploy a revolutionary carbon fabric system that serves as both heat shield and primary structure during atmospheric entry. This paper explores the application of a Nano-ADEPT entry system for delivery of very small payloads (< 5 kg) to locations of interest in an effort to leverage low-cost platforms to rapidly mature the technology while simultaneously delivering high-value science. It is shown that secondary payload missions to Mars as well as entry from low Earth orbit are feasible. Secondary payload missions to Venus at small scale present a greater challenge and may only be feasible if the system can be designed with exceptionally low mass. The technology maturation strategy for Nano-ADEPT is described. Four test campaigns underway at the time of writing are discussed in detail, including deployment testing, wind tunnel testing, system-level arc jet testing, and a sounding rocket flight test. To conclude, a mission opportunity is described to demonstrate Nano-ADEPT from the International Space Station. C1 [Smith, Brandon; Cassell, Alan; Kruger, Carl; Venkatapathy, Ethiraj] NASA, Ames Res Ctr, M-S 229-1, Moffett Field, CA 94104 USA. [Kazemba, Cole] NASA, Ames Res Ctr, STC Inc, Moffett Field, CA 94104 USA. [Simonis, Kyle] Georgia Inst Technol, Atlanta, GA 30332 USA. RP Smith, B (reprint author), NASA, Ames Res Ctr, M-S 229-1, Moffett Field, CA 94104 USA. EM Brandon.P.Smith@nasa.gov; Cole.D.Kazemba@nasa.gov; ksimonis3@gatech.edu NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 11 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302031 ER PT J AU Sosland, R Seibert, M Ferguson, E Steele, R Zittle, K AF Sosland, Rebekah Seibert, Michael Ferguson, Eric Steele, Robert Zittle, Kyle GP IEEE TI Getting Back on the Road: Reformatting Flash Memory On-board the Mars Exploration Rover Opportunity SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB In early 2011, NASA's Mars Exploration Rover ( MER) Opportunity began experiencing intermittent errors when writing data products to Flash memory. Similar errors occurred with increasing frequency in early 2013 and many were accompanied by unexpected resets of the rover's flight computer ( warm reboots). Depending on timing, warm reboots occasionally caused communication faults. Although these errors subsided in mid-2013, they returned at an increasing rate in mid-2014. The MER team developed techniques to mitigate the effects of infrequent warm reboots but these became ineffective as the rate and severity of the errors increased. Faced with these more frequent errors, the MER team decided to reformat the Flash memory. Using lessons learned from reformatting the Flash file system on the Spirit rover and implementing some new techniques, the MER team was able to reformat Flash and resume science operations much more quickly than anticipated. This paper will discuss the history of Flash related anomalies, suspect cause, initial operational mitigations, and the ultimate Flash reformat strategy and rover recovery activities. C1 [Sosland, Rebekah; Seibert, Michael; Ferguson, Eric; Steele, Robert; Zittle, Kyle] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Sosland, R (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM rebekah.f.sosland@jpl.nasa.gov; michael.a.seibert@jpl.nasa.gov; eric.w.ferguson@jpl.nasa.gov; robert.d.steele@jpl.nasa.gov; kyle.a.zittle@jpl.nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 11 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303082 ER PT J AU Spangelo, S Landau, D Johnson, S Arora, N Randolph, T AF Spangelo, Sara Landau, Damon Johnson, Shawn Arora, Nitin Randolph, Thomas GP IEEE TI Defining the Requirements for the Micro Electric Propulsion Systems for Small Spacecraft Missions SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT ID CUBESATS AB Recent technology advancements in Micro Electric Propulsion (MEP) will enable the next generation of small spacecraft to perform trajectory and attitude maneuvers with significant Delta V requirements, provide thrust over long mission durations, and replace reaction wheels for attitude control. These advancements will open up the class of mission architectures achievable by small spacecraft to include formation flying, proximity operations, and precision pointing missions in both LEO and interplanetary destinations. The goal of this study is to establish the optimal performance parameters for future MEP technology that are applicable to a broad range of flight demonstration platforms (e.g. dedicated 3-12U CubeSats to ESPA-class spacecraft), for a variety of applications, including LEO and Earth escape orbit transfers, travel to interplanetary destinations, hover and drag make-up missions, and performing reaction wheel-free attitude control. An integrated systems-level model for propulsion, spacecraft (power, data, telecommunication, thermal management), and orbit and attitude maneuvers is developed to support solution space exploration. MEP system performance parameters are derived that maximize the performance capability subject to realistic system-level constraints in the context of upcoming mission opportunities where MEP is enabling or advantageous relative to other technologies. C1 [Spangelo, Sara; Landau, Damon; Johnson, Shawn; Arora, Nitin; Randolph, Thomas] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Spangelo, S (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 37 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 16 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303067 ER PT J AU Spaulding, M Eremenko, A AF Spaulding, Matthew Eremenko, Alexander GP IEEE TI Europa Clipper Vault Shielding Optimization Approach SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB In the effort to further understanding of the Jovian moon Europa, a Jet Propulsion Laboratory (JPL) and Applied Physics Laboratory (APL) joint team are developing the Europa Clipper spacecraft concept that would provide multiple flybys of Europa during its tour. During the flyby maneuvers, the proposed Europa Clipper spacecraft would be required to operate within the high radiation environment. In order to protect the sensitive electronics of the spacecraft, the current radiation protection approach is to locate these electronics within a radiation vault. This paper documents the study performed addressing the construction and geometry of this electronics radiation vault. The method of development incorporated analytical base panels of various thicknesses comprised of standard aerospace materials (aluminum and titanium). These panels were then subjected to a range of seed loads in order to create a preliminary rib pattern. Panels where the baseline thickness is not adequate to provide the necessary shielding will then have additional shielding applied in the form of Tantalum sheet added to either the internal or external faces in order to account for the capability differences. Further vetting of the panel geometries will then take into account factors such as manufacturability, flexibility to late shielding requirement changes, assembly mass, and additional design requirements finally selecting a baseline configuration to be implemented in the flight design. Detailed analysis will be performed for an idealized panel which will not be required to support any additional components; however aspects such as harness pass-through, thermal impacts, and accessibility will be addressed. C1 [Spaulding, Matthew; Eremenko, Alexander] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Spaulding, M (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Matthew.D.Spaulding@jpl.nasa.gov; Alexander.E.Eremenko@jpl.nasa.gov NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 6 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302002 ER PT J AU Stapelfeldt, K AF Stapelfeldt, Karl CA Exo-C Sci & Technol Definition Tea Exo-C Engn Design Team GP IEEE TI Exo-C: A Space Mission for Direct Imaging and Spectroscopy of Extrasolar Planetary Systems SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Exo-C is NASAs first community study of a modest aperture space telescope designed for high contrast observations of exoplanetary systems. The mission will be capable of taking optical spectra of nearby exoplanets in reflected light, discovering previously undetected planets, and imaging structure in a large sample of circumstellar disks. It will obtain unique science results on planets down to super-Earth sizes and serve as a technology pathfinder toward an eventual flagship-class mission to find and characterize habitable Earth-like exoplanets. We present the mission/payload design and highlight steps to reduce mission cost/risk relative to previous mission concepts. Key elements are an unobscured telescope aperture, an internal coronagraph with deformable mirrors for precise wavefront control, and an orbit and observatory design chosen for high thermal stability. Exo-C has a similar telescope aperture, orbit, lifetime, and spacecraft bus requirements to the highly successful Kepler mission (which is our cost reference). The needed technology development is on-course for a possible mission start in 2017. This paper summarizes the study final report completed in January 2015. During 2015 NASA will make a decision on its potential development. C1 [Stapelfeldt, Karl] NASA, Goddard Space Flight Ctr, Exoplanets & Stellar Astrophys Lab, Code 667, Greenbelt, MD 20771 USA. RP Stapelfeldt, K (reprint author), NASA, Goddard Space Flight Ctr, Exoplanets & Stellar Astrophys Lab, Code 667, Greenbelt, MD 20771 USA. EM karl.r.stapelfeldt@nasa.gov NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 10 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303011 ER PT J AU Stephens, SK AF Stephens, Stuart K. GP IEEE TI The Juno Mission to Jupiter: Lessons from Cruise and Plans for Orbital Operations and Science Return SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB This paper describes the Juno mission, including its experience during 3+ years of cruise, and focuses on plans for its orbital mission and science return at Jupiter. Previous papers focused on the history of the mission, development, launch, and early cruise, or on spacecraft operations lessons learned. Juno is a NASA New Frontiers spacecraft currently enroute to Jupiter where it will enter a polar orbit in July 2016 with 9 instruments to study its atmospheric composition and structure, magnetic and gravity fields, and polar magnetosphere. Juno's prime science goal is to understand the origin and evolution of Jupiter, thereby shedding light on the formation of the Earth and other planets. Its science objectives are designed to be satisfied with 30 orbits, a spin-stabilized solar powered spacecraft with radiation shielding, and a unique payload including microwave receivers, X- and Ka-band gravity science hardware, magnetometers, low- and high-energy particle detectors, and UV and IR spectroscopic imagers. Observations are made in two primary orientations, one for gravity science (spacecraft spin axis and main antenna pointing to Earth), and the other for microwave atmospheric sounding (spin axis perpendicular to orbit plane to allow nadir pointing in spin plane). All other investigations work in either one or both orientations. Primary science data are collected within 3 hours of closest approach, although calibrations, occasional remote sensing, and magneto-spheric observations are planned throughout the orbits. Since launch in August 2011, the Juno ops team has exercised the instruments with occasional checkouts, periodic maintenance, compatibility tests, and an Earth Flyby in October 2013 (Figure 1). This paper discusses lessons learned from using the instruments and from challenges faced as a result of anomalies, with an emphasis on applications to orbital operations. It also focuses on mission plan details for the science orbits as well as on key work and remaining decisions, including recent evaluation of trajectory alternatives for the initial large capture orbit and primary science orbits, and preliminary development of a tactical playbook to facilitate contingency response in the orbital mission. C1 [Stephens, Stuart K.] CALTECH, NASA, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91009 USA. RP Stephens, SK (reprint author), CALTECH, NASA, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91009 USA. EM stuart.k.stephens@jpl.nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 20 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501301004 ER PT J AU Stone, T Murbach, M Alema, R Gilstrap, R AF Stone, Thom Murbach, Marcus Alema, Richard Gilstrap, Ray GP IEEE TI SOAREX-8 Suborbital Experiments 2015-A New Paradigm for Small Spacecraft Communication SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB In 2015 NASA plans to launch a payload to 280 Km altitude on a sounding rocket from the Wallops Flight Facility. This payload will contain several novel technologies that work together to demonstrate methodologies for space sample return missions and for nanosatellite communications in general. The payload will deploy and test an Exo-Brake, which slows the payload aerodynamically, providing eventual de-orbit and recovery of future ISS samples through a Small Payload Quick Return project. In addition, this flight addresses future Mars mission entry technology, space-to-space communications using the Iridium Short Messaging Service (SMS), GPS tracking, and wireless sensors using the ZigBee protocol. SOAREX-8 is being assembled and tested at Ames Research Center (ARC) and the NASA Engineering and Safety Center (NESC) is funding sensor and communications work. Open source Arduino technology and software are used for system control. The ZigBee modules used are XBee units that connect analog sensors for temperature, air pressure and acceleration measurement wirelessly to the payload telemetry system. Our team is developing methods for power distribution and module mounting, along with software for sensor integration, data assembly and downlink. We have demonstrated relaying telemetry to the ground using the Iridium satellite constellation on a previous flight, but the upcoming flight will be the first time we integrate useful flight test data from a ZigBee wireless sensor network. Wireless sensor data will measure the aerodynamic efficacy of the Exo-Brake permitting further on-orbit flight tests of improved designs. The Exo-Brake is 5 m(2) in area and will be stored in a container and deployed during ascent once the payload is jettisoned from the launch vehicle. We intend to further refine the hardware and continue testing on balloon launches, future sounding rocket flights and on nanosatellite missions. The use of standards-based and open-source hardware/software has allowed for this project to be completed with a very modest budget and a challenging schedule. There is a wealth of hardware and software available for both the Arduino platform and the XBee, all low-cost or open-source. Along with the Exo-Brake hardware and deployment discussion, this paper will describe in detail the system architecture emphasizing the successful use of open-source hardware and software to minimize effort and cost. Testing procedures, radio frequency interference (RFI) mitigation, success criteria and expected results will also be discussed. The use of Iridium short messaging capability for space-to-space links, standards-based wireless sensor networks, and other innovative communications technology are also presented. C1 [Stone, Thom] NASA, Ames Res Ctr, Comp Sci Corp, Moffett Field, CA 94035 USA. [Murbach, Marcus; Alema, Richard; Gilstrap, Ray] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Stone, T (reprint author), NASA, Ames Res Ctr, Comp Sci Corp, Moffett Field, CA 94035 USA. EM Thom.Stone@nasa.gov; marcus.s.murbach@nasa.gov; richard.l.alena@nasa.gov; ray.gilstrap@nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 7 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303023 ER PT J AU Sturm, E Manor-Chapman, E AF Sturm, Erick Manor-Chapman, Emily GP IEEE TI Laying Down Tracks: DSN Planning for Cassini's Final Mission Phase SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB The Cassini Mission is in the final years of its second extension, the Cassini Solstice Mission (CSM). Nine months prior to the end-of-mission, the spacecraft will embark on its final mission phase, the F-ring and Proximal Orbits (FRPO). These orbits will bring the spacecraft closer to Saturn than ever before, allowing for the collection of some of the most unprecedented, imperative, and profuse science of the entire mission. A key challenge during this phase is identifying viable spacecraft downlink opportunities given the reduced orbital period and the temporal 'balancing act' that must be maintained between science data acquisition, orbit trim maneuvers (OTMs), orbital geometry, other missions' events, and Deep Space Network (DSN) downtimes. This paper describes the development of the DSN straw-man for the FRPO phase of the Cassini mission, starting with the constraints identified from the above sources, then the process followed to select DSN passes given those constraints, and finally the products produced to summarize the selected passes and verify their compliance with the constraints. Ultimately, the DSN straw-man included 286 selected passes, of which only 44 had conflicts with constraints. C1 [Sturm, Erick; Manor-Chapman, Emily] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Sturm, E (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Erick.J.Sturm@jpl.nasa.gov; Emily.A.Manor@jpl.nasa.gov NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 10 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501301047 ER PT J AU Sturm, EJ Barber, TJ Roth, D AF Sturm, Erick J., II Barber, Todd J. Roth, Duane GP IEEE TI Ensuring Cassini's End-of-Mission Propellant Margins SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB The Cassini spacecraft is in its final years. On September 15, 2017, Cassini will plunge deep into Saturn's atmosphere never to reemerge; thus concluding its second extended mission and 13 years in orbit around the ringed planet. As of October 2014, the spacecraft is four years in to its seven-year, second extended mission, the Cassini Solstice Mission (CSM). With three years left and only 2.5% of its loaded bipropellant and 37% of its loaded monopropellant remaining, the Cassini project actively manages the predicted end-of-mission propellant margins to maintain a high confidence in the spacecraft's ability to complete the CSM as designed. Accurate spacecraft navigation, rigorous remaining-propellant estimation, and frequent future propellant consumption prediction have resulted in efficient propellant use and a probability of sufficient propellant margin greater than 99%. C1 [Sturm, Erick J., II; Barber, Todd J.; Roth, Duane] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Sturm, EJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Erick.J.Sturm@jpl.nasa.gov; Todd.J.Barber@jpl.nasa.gov; Duane.C.Roth@jpl.nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 9 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501301046 ER PT J AU Tabirian, N HaiqingXianyu Serabyn, E AF Tabirian, Nelson HaiqingXianyu Serabyn, Eugene GP IEEE TI Liquid Crystal Polymer Vector Vortex Waveplates with Sub-micrometer Singularity SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Small singularity size is critical for achieving low light loss and high contrast for vector vortex waveplate (VVW) based coronagraph. In the opto-mechanical system for recording VVW with photoalignment, reshaping the center light intensity distribution and precision alignment can effectively decrease singularity size. We have developed methods for redistributing the light intensity near the singularity. A new direct alignment method is introduced. This method helps in reaching the optimized alignment position by allowing to depict the beam profile at the photoalignment surface. Employing these techniques and new liquid crystal polymer materials, we have fabricated VVWs with sub-micrometer defect size for UV, and subs-wavelength defect size for 1.5 micrometer wavelength range. Inversely twisted layers method was used for fabrication of broadband VVW for the near infrared region. C1 [Tabirian, Nelson; HaiqingXianyu] BEAM Engn Adv Measurements Co, 809 S Orlando Ave,Suite 1, Winter Pk, FL 32789 USA. [Serabyn, Eugene] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Tabirian, N (reprint author), BEAM Engn Adv Measurements Co, 809 S Orlando Ave,Suite 1, Winter Pk, FL 32789 USA. EM nelson@beamco.com; haiqing@beamco.com; eserabyn@s383.jpl.nasa.gov NR 4 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 9 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302101 ER PT J AU Takamura, E Mangum, K Wasiak, F Gomez-Rosa, C AF Takamura, Eduardo Mangum, Kevin Wasiak, Fran Gomez-Rosa, Carlos GP IEEE TI Information Security Considerations for Protecting NASA Mission Operations Centers (MOCs) SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT DE access control; asset protection; automation; change control; connection protection; continuous diagnostics and mitigation; continuous monitoring; ground segment; ground system; incident handling; information assurance; information security; information security leadership; information technology leadership; infrastructure protection; IT security metrics; least privilege; logical security; mission assurance; mission operations; mission operations center; NASA; network security; personnel screening; policies and procedures; physical security; risk management; scheduling restrictions; security controls; security hardening; software updates; system cloning and software licenses; system security; system security life cycle; unauthorized change detection; unauthorized change deterrence; unauthorized change prevention AB In NASA space flight missions, the Mission Operations Center (MOC) is often considered "the center of the (ground segment) universe," at least by those involved with ground system operations. It is at and through the MOC that spacecraft is commanded and controlled, and science data acquired. This critical element of the ground system must be protected to ensure the confidentiality, integrity and availability of the information and information systems supporting mission operations. This paper identifies and highlights key information security aspects affecting MOCs that should be taken into consideration when reviewing and/or implementing protecting measures in and around MOCs. It stresses the need for compliance with information security regulation and mandates, and the need for the reduction of IT security risks that can potentially have a negative impact to the mission if not addressed. This compilation of key security aspects was derived from numerous observations, findings, and issues discovered by IT security audits the authors have conducted on NASA mission operations centers in the past few years. It is not a recipe on how to secure MOCs, but rather an insight into key areas that must be secured to strengthen the MOC, and enable mission assurance. Most concepts and recommendations in the paper can be applied to non-NASA organizations as well. Finally, the paper emphasizes the importance of integrating information security into the MOC development life cycle as configuration, risk and other management processes are tailored to support the delicate environment in which mission operations take place. C1 [Takamura, Eduardo; Mangum, Kevin; Wasiak, Fran] Gen Dynam Miss Syst, Seabrook, MD USA. [Gomez-Rosa, Carlos] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. RP Takamura, E (reprint author), Gen Dynam Miss Syst, Seabrook, MD USA. NR 13 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 14 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303032 ER PT J AU Terrile, RJ Doumani, FG Ho, GY Jackson, BL AF Terrile, Richard J. Doumani, Fred G. Ho, Gary Y. Jackson, Byron L. GP IEEE TI Calibrating the Technology Readiness Level (TRL) Scale Using NASA Mission Data SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB This paper seeks to assess the qualitative and quantitative aspects of the Technology Readiness Level (TRL) scale in order to understand its ability to provide estimates of the forward costs of developing a new technology to a state of flight readiness. TRLs are in common use throughout NASA, industry and military organizations and are characterized by being easy to determine using a set of well-defined parameters. However, the TRL scale is not calibrated to any consistent unit and the relative size of TRL steps are not linear and can vary for different technologies. We use archived cost data from a variety of recent NASA flight missions and from several technology-heavy instrument suites on the Mars Science Laboratory (MSL). Development costs are extracted at the time of several NASA life cycle review milestones. We relate the project requirements associated with these defined milestones with approximate TRL steps and use the cost data as a proxy for TRL step costs. When corrected for programmatic variations in time spent at each TRL step, the NASA mission data demonstrated a 30% reduction in variability, illustrating how unexpected events mask a more stable progression of technology development. A calibrated TRL scale is determined with an "S-curve" shape to TRL growth. The steepest step sizes are in the TRL 6 to 8 range, matching the region of technology maturation known to be a difficult barrier to traverse. C1 [Terrile, Richard J.; Doumani, Fred G.; Ho, Gary Y.; Jackson, Byron L.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Terrile, RJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Rich.Terrile@jpl.nasa.gov; Fred.G.Doumani@jpl.nasa.gov; Gary.Y.Ho@jpl.nasa.gov; Byron.L.Jackson@jpl.nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 9 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501304047 ER PT J AU Toups, L Brown, K Hoffman, SJ AF Toups, Larry Brown, Kendall Hoffman, Stephen J. GP IEEE TI Transportation-Driven Mars Surface Operations Supporting an Evolvable Mars Campaign SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB This paper describes the results of a study evaluating options for supporting a series of human missions to a single Mars surface destination. In this scenario the infrastructure emplaced during previous visits to this site is leveraged in following missions. The goal of this single site approach to Mars surface infrastructure is to enable "Steady State" operations by at least 4 crew for up to 500 sols at this site. These characteristics, along with the transportation system used to deliver crew and equipment to and from Mars, are collectively known as the Evolvable Mars Campaign (EMC). Information in this paper is presented in the sequence in which it was accomplished. First, a logical buildup sequence of surface infrastructure was developed to achieve the desired "Steady State" operations on the Mars surface. This was based on a concept of operations that met objectives of the EMC. Second, infrastructure capabilities were identified to carry out this concept of operations. Third, systems (in the form of conceptual elements) were identified to provide these capabilities. This included top-level mass, power and volume estimates for these elements. Fourth, the results were then used in analyses to evaluate three options (18t, 27t, and 40t landed mass) of Mars Lander delivery capability to the surface. Finally, Mars arrival mass estimates were generated based upon the entry, descent, and landing requirements for inclusion in separate assessments of in-space transportation capabilities for the EMC. C1 [Toups, Larry] NASA, Johnson Space Ctr, NASA Rd 1, Houston, TX 77058 USA. [Brown, Kendall] NASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USA. [Hoffman, Stephen J.] Sci Applicat Int Corp, Houston, TX 77058 USA. RP Toups, L (reprint author), NASA, Johnson Space Ctr, NASA Rd 1, Houston, TX 77058 USA. EM larry.toups-1@nasa.gov; kendall.brown@nasa.gov; stephen.j.hoffman@nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 14 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501304006 ER PT J AU van Harmelen, C Soriano, M AF van Harmelen, Chris Soriano, Melissa GP IEEE TI Development of the Science Data System for the International Space Station Cold Atom Lab SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Cold Atom Laboratory (CAL) is a facility that will enable scientists to study ultra-cold quantum gases in a microgravity environment on the International Space Station (ISS) beginning in 2016. The primary science data for each experiment consists of two images taken in quick succession. The first image is of the trapped cold atoms and the second image is of the background. The two images are subtracted to obtain optical density. These raw Level 0 atom and background images are processed into the Level 1 optical density data product, and then into the Level 2 data products: atom number, Magneto-Optical Trap (MOT) lifetime, magnetic chip-trap atom lifetime, and condensate fraction. These products can also be used as diagnostics of the instrument health. With experiments being conducted for 8 hours every day, the amount of data being generated poses many technical challenges, such as downlinking and managing the required data volume. A parallel processing design is described, implemented, and benchmarked. In addition to optimizing the data pipeline, accuracy and speed in producing the Level 1 and 2 data products is key. Algorithms for feature recognition are explored, facilitating image cropping and accurate atom number calculations. C1 [van Harmelen, Chris; Soriano, Melissa] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP van Harmelen, C (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM chrisv1@stanford.edu; Melissa.A.Soriano@jpl.nasa.gov NR 6 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 7 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300053 ER PT J AU Weisbin, C Lincoln, W Wilcox, B Brophy, J Chodas, P Muirhead, B AF Weisbin, Charles Lincoln, William Wilcox, Brian Brophy, John Chodas, Paul Muirhead, Brian GP IEEE TI Comparative Analysis of Asteroid-Deflection Approaches SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Five potential methods of preventing an asteroid from colliding with Earth-Kinetic Impactor (KI), Ion Beam Deflection (IBD), Gravity Tractor (GT), Enhanced Gravity Tractor (EGT), and Laser Ablation (LA)-are compared, with the objective of helping to inform a NASA decision regarding which technology or technologies could be demonstrated in space on the proposed 2019 Asteroid Robotic Redirect Mission (ARRM). Three design blocks are considered, which differ in the power available to the deflection technology and the mass at low-Earth orbit. We plot the required warning time (up to 30 years between discovery of the hazard and potential collision with Earth) vs. asteroid diameter for each of four technologies (gravity tractor without enhancement is considered only as a trim/verification candidate) under each design block, and illustrate sensitivities of results to important parameters. Under assumptions detailed in the study, we find the following: For asteroids up to about 200-300 meters in diameter (depending on design block), KI achieves the desired deflection with the least amount of warning time required, and its range of applicability increases to about 500-600 meters with a series of (e.g., three) missions. Terminal guidance capability required to ensure that a sufficiently massive impactor can reliably be made to collide with a relatively small asteroid at high speed can be accommodated via judicious camera selection and guidance-and-control parameter adjustment (along with sufficient rocket performance), and does not require further technology development. But KI's deflection capability lacks the precision that may be needed to avoid pushing an asteroid into a gravitational "keyhole" that would cause the asteroid to intercept Earth at another time. It has long been recognized that KI would require implementation of a second spacecraft to rendezvous with the threat object, enable precision tracking after the kinetic impact, and provide secondary precision deflection to assure keyhole avoidance. No primary deflection can be considered successful unless keyhole avoidance can be guaranteed. ARRM provides a good opportunity to use its high-power Solar-Electric ion-Propulsion (SEP) system to perform a secondary deflection demonstration for late final adjustments and/or avoidance of keyholes. For larger asteroids, LA shows the best performance under the single-mission scenarios, but its relatively low technology readiness level (TRL) requires further work to validate key assumptions in the analysis. In addition, LA may not work well on all asteroid types. For example, an asteroid composed primarily of nickel-iron might conduct away most of the laser's heat instead of ablating. Nevertheless, if sufficient resources are available, testing the laser-ablation technique during ARRM is an attractive option since LA has a very broad range of applicability, potential performance well exceeding that of either IBD or EGT, and can act both as a trim technique and a primary-deflection method. It should be recognized at the outset that such a compressed schedule (2019 launch) would probably preclude full proof of this capability, but would likely provide enough real data to affirm or deny the potential of what appears to be a significant and heretofore unexplored option for planetary defense. C1 [Weisbin, Charles; Lincoln, William; Wilcox, Brian; Brophy, John; Chodas, Paul; Muirhead, Brian] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Weisbin, C (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM charles.r.weisbin@jpl.nasa.gov; william.lincoln@jpl.nasa.gov; brian.h.wilcox@jpl.nasa.gov; john.r.brophy@jpl.nasa.gov; paul.w.chodas@jpl.nasa.gov; brian.k.muirhead@jpl.nasa.gov NR 14 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 16 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300064 ER PT J AU Wells, J Scherrer, J Van Noord, J Law, R AF Wells, James Scherrer, John Van Noord, Jonathan Law, Richard GP IEEE TI Early Development of the First Earth Venture Mission: How CYGNSS is Using Engineering Models to Validate the Design SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB In response to the recommendations made in the National Research Council's Earth Science and Applications 2007 Decadal Survey, NASA has initiated the Earth Venture line of mission opportunities. The first orbital mission chosen for this competitively selected, cost and schedule constrained, Principal Investigator-led opportunity is the CYclone Global Navigation Satellite System (CYGNSS). The goal of CYGNSS is to understand the coupling between ocean surface properties, moist atmospheric thermodynamics, radiation, and convective dynamics in the inner core of a tropical cyclone. The CYGNSS mission is comprised of eight Low Earth Observing (LEO) microsatellites that use GPS bi-static scatterometry to measure ocean surface winds. As specified in the selecting Announcement of Opportunity, the Principal Investigator (PI) for CYGNSS is held responsible for successfully achieving the science objectives of the selected mission and the management approach that he chooses to obtain those results has a significant amount of freedom as long as it meets the intent of key NASA guidance. The development approach chosen for the implementation of CYGNSS has several facets. One foundational tenant of the Class D approach chosen by CYGNSS was to maximize the use of off-the-shelf components and then offset this higher mission risk posture by early and thorough testing of multiple Engineering Models. This not only tested hardware and software but it allowed for exercising of Assembly, Integration, and Test (AI&T) processes and procedures before ever building the flight units. The CYGNSS team is currently in Phase C of the Project Life Cycle. Not only is the design continuing to mature but AI&T of three microsatellite engineering models, each with its own objectives, are in progress. Testing of the Engineering Model (EM), the Structural Thermal Model (STM), and the Radio Frequency Model (RFM) has commenced and a discussion on the purpose and progress made to date of each of these engineering models as well as some associated lessons learned is presented in this paper. C1 [Wells, James; Law, Richard] NASA, Langley Res Ctr, 9A Langley Blvd, Hampton, VA 23681 USA. [Scherrer, John] Southwest Res Inst, San Antonio, TX 78238 USA. [Van Noord, Jonathan] Univ Michigan, Space Phys Res Lab, Ann Arbor, MI 48109 USA. RP Wells, J (reprint author), NASA, Langley Res Ctr, 9A Langley Blvd, Hampton, VA 23681 USA. EM James.E.Wells@nasa.gov; jscherrer@swri.edu; noord@umich.edu; Richard.C.Law@nasa.gov NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 8 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501301027 ER PT J AU Wettemann, T Ehrenwinkler, R Johnson, TE Maschmann, M Mosner, P te Plate, M Rodel, A AF Wettemann, Thomas Ehrenwinkler, Ralf Johnson, Thomas E. Maschmann, Marc Mosner, Peter te Plate, Maurice Roedel, Andreas GP IEEE TI The NIRSpec Assembly Integration and Test Status SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB The Near-Infrared Spectrograph (NIRSpec) is one of the four instruments on the James Webb Space Telescope (JWST) scheduled for launch in 2018. NIRSpec has been manufactured and tested by an European industrial consortium led by Airbus Defence and Space and delivered to the European Space Agency (ESA) and NASA in September 2013. Since then it has successfully been integrated onto the JWST Integrated Science Instrument Module (ISIM) and has completed ISIM Cryo-Vacuum Test#2. Since two of its most important assemblies, the Focal Plane Assembly (FPA) and the Micro-Shutter Assembly (MSA) need to be replaced by new units, we will present the status of the instrument, the status of its new flight assemblies and give an outlook on the planned exchange activities and the following instrument reverification. C1 [Wettemann, Thomas; Ehrenwinkler, Ralf; Maschmann, Marc; Mosner, Peter; Roedel, Andreas] AIRBUS DS GmbH, D-81663 Munich, Germany. [Johnson, Thomas E.] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. [te Plate, Maurice] ESA, Estec, NL-2200 AG Noordwijk, Netherlands. RP Wettemann, T (reprint author), AIRBUS DS GmbH, D-81663 Munich, Germany. EM Thomas.Wettemann@astrium.eads.net NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 8 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501304055 ER PT J AU Winternitz, LMB Hassouneh, MA Mitchell, JW Valdez, JE Price, SR Semper, SR Yu, WH Ray, PS Wood, KS Arzoumanian, Z Gendreau, KC AF Winternitz, Luke M. B. Hassouneh, Munther A. Mitchell, Jason W. Valdez, Jennifer E. Price, Samuel R. Semper, Sean R. Yu, Wayne H. Ray, Paul S. Wood, Kent S. Arzoumanian, Zaven Gendreau, Keith C. GP IEEE TI X-ray Pulsar Navigation Algorithms and Testbed for SEXTANT SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT ID TIMING PACKAGE; TEMPO2 AB The Station Explorer for X-ray Timing and Navigation Technology (SEXTANT) is a NASA funded technology-demonstration. SEXTANT will, for the first time, demonstrate real-time, on-board X-ray Pulsar-based Navigation (XNAV), a significant milestone in the quest to establish a GPS-Iike navigation capability available throughout our Solar System and beyond. This paper describes the basic design of the SEXTANT system with a focus on core models and algorithms, and the design and continued development of the GSFC X-ray Navigation Laboratory Testbed (GXLT) with its dynamic pulsar emulation capability. We also present early results from GXLT modeling of the combined NICER X-ray timing instrument hardware and SEXTANT flight software algorithms. C1 [Winternitz, Luke M. B.; Hassouneh, Munther A.; Mitchell, Jason W.; Valdez, Jennifer E.; Price, Samuel R.; Semper, Sean R.; Yu, Wayne H.; Gendreau, Keith C.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Ray, Paul S.; Wood, Kent S.] Naval Res Lab, Washington, DC 20375 USA. [Arzoumanian, Zaven] NASA, GSFC, USRA, Greenbelt, MD 20771 USA. RP Winternitz, LMB (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM luke.b.winternitz@nasa.gov NR 31 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 14 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300061 ER PT J AU Woolley, R AF Woolley, Ryan GP IEEE TI A Simple Analytic Model for Estimating Mars Ascent Vehicle Mass and Performance SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB The Mars Ascent Vehicle (MAV) is a crucial component in any sample return campaign. In this paper we present a universal model for a two-stage MAV along with the analytic equations and simple parametric relationships necessary to quickly estimate MAV mass and performance. Ascent trajectories can be modeled as two-burn transfers from the surface with appropriate loss estimations for finite burns, steering, and drag. Minimizing lift-off mass is achieved by balancing optimized staging and an optimized path-to-orbit. This model allows designers to quickly find optimized solutions and to see the effects of design choices. C1 [Woolley, Ryan] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Woolley, R (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Ryan.C.Woolley@jpl.nasa.gov NR 12 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 10 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303057 ER PT J AU Xaypraseuth, P Satish, R Chatterjee, A AF Xaypraseuth, Peter Satish, R. Chatterjee, Alok GP IEEE TI NISAR Spacecraft Concept Overview: Design challenges for a proposed flagship dual-frequency SAR Mission SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB NISAR (NASA-ISRO Synthetic Aperture Radar) would be the inaugural collaboration between National Aeronautics and Space Administration (NASA) and Indian Space Research Organization (ISRO) on an Earth Science mission, which would feature an L-Band SAR instrument and an S-Band SAR instrument. As partners, NASA and ISRO would each contribute different engineering elements to help achieve the proposed scientific objectives of the mission. ISRO-Vikram Sarabhai Space Centre would provide the GSLV-Mark II launch vehicle, which would deliver the spacecraft into the desired orbit. ISRO-Satellite Centre would provide the spacecraft based on its I3K structural bus, a commonly used platform for ISRO's communication satellite missions, which would provide the resources necessary to operate the science payload. NASA would augment the spacecraft capabilities with engineering payload systems to help store, and transmit the large volume of science data. The combination of two SAR instruments on one platform would challenge the capabilities of both ISRO and NASA. The following are some of the challenges that will be discussed in the paper. The desire to operate both radars simultaneously would lead to a several-kilowatt power system design. The need to point the radar antenna to within a tenth of a degree would drive the attitude control system design. At peak rates, each instrument would produce data at gigabit per second speeds, which would drive the data transfer and storage capabilities. Furthermore, these data volumes would require the transition from an X-Band telecommunication system to Ka-Band, which could support multi-gigabit data rates. C1 [Xaypraseuth, Peter; Chatterjee, Alok] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Satish, R.] ISRO, Satellite Ctr, Bangalore 560017, Karnataka, India. RP Xaypraseuth, P (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Peter.Xaypraseuth@jpl.nasa.gov; RSatish@isac.gov.in; Alok.Chatterjee@jpl.nasa.gov NR 2 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 10 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300060 ER PT J AU Yerdon, M Cook, B AF Yerdon, Mark Cook, Brant GP IEEE TI Mass Properties Analysis and Measurements of a High Altitude Supersonic Decelerator Test Vehicle SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB The mass properties of the Low Density Supersonic Decelerator (LDSD) Supersonic Flight Dynamics Test Vehicle (SFDTV) were analyzed and measured to ensure a successful test flight and allow for accurate post-flight reconstruction. This paper covers the methods used for analytical estimates of the mass properties throughout the design process, balancing and ballasting design, mass trends, measurements performed to verify the analytical models, and issues found. The test vehicle analyzed and measured is a full scale 4.7 m diameter, 3085 kg, high altitude test vehicle. Brought to Mars-like test conditions in Earth's atmosphere at 180,000 ft and Mach 4 by a balloon and solid rocket motor, the spin stabilized vehicle deploys a parachute and inflatable toroid for enhanced Mars landings in the future. Control of mass, center of mass, and products of inertia were critical for stable and predictable flight conditions. Accurate knowledge of mass, center of mass, and inertias throughout all the changing states of the test flight were required for post-flight reconstruction of the performance achieved by the inflatable decelerator and parachute. A component-level line item Monte Carlo method was used to predict the mass properties and associated uncertainties. Spin table measurements of two components of center of mass, one moment of inertia, and two products of inertia were used to reduce the uncertainties of the mass properties. Spin table measured values matched pre-measurement predictions closely, providing validation of the analytical model. Ultimately the center of mass was controlled to within 3 mm of the geometric center of the vehicle, and the spin axis products of inertia were zeroed out to within 4 kg-m(2) at launch. Uncertainties for mass properties throughout all phases of flight, balloon drop through motor burnout and parachute deployment, were 10.8 kg for mass, 25 mm for center of mass, 1.6% for moments of inertia, and 10 kg-m(2) for products of inertia, satisfying requirements for post-flight reconstruction. C1 [Yerdon, Mark; Cook, Brant] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Yerdon, M (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Mark.J.Yerdon@jpl.nasa.gov; Brant.T.Cook@jpl.nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 10 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501300063 ER PT J AU Yiu, P Iturbe, X Keymeulen, D Berisford, D Hand, K Carlson, R Wadsworth, W Dybwad, JP Levy, R AF Yiu, Patrick Iturbe, Xabier Keymeulen, Didier Berisford, Dan Hand, Kevin Carlson, Robert Wadsworth, Winthrop Dybwad, Jens Peter Levy, Ralph GP IEEE TI Adaptive Controller for a Fourier Transform Spectrometer with Space Applications SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB This paper presents an adaptive controller for CIRIS (Compositional InfraRed Interferometric Spectrometer) implemented on a stand-alone field programmable gate array (FPGA) architecture with emphasis on space applications in radiation environments such as Europa. CIRIS is a novel take on traditional Fourier Transform Spectrometers (FTS) and replaces linearly moving mirrors (characteristic of Michelson interferometers) with a constant-velocity rotating refractor to variably phase shift and alter the path length of incoming light. This design allows for a compact and robust device, making it ideal for spaceborne measurements in the near-IR to thermal-IR band (2-12 mu m) on planetary exploration missions. The instrument's embedded microcontroller is implemented on a VIRTEX-5 FPGA and a PowerPC with the aim of sampling the instrument's detector and optical rotary encoder in order to construct an interferogram. Subsequent signal processing provides spectral immunity from the noise effects of radiation encountered during space flight to destinations such as Europa. A variety of signal processing techniques, including radiation peak removal, resampling, Fast Fourier Transform (FFT), filtering, dispersion correction, and spectral calibration processes are applied in real-time to compose the sample spectrum. The instrument's FPGA controller is demonstrated with the FTS to highlight its suitability for implementation in space systems. C1 [Yiu, Patrick; Iturbe, Xabier] CALTECH, Pasadena, CA 91125 USA. [Keymeulen, Didier; Berisford, Dan; Hand, Kevin; Carlson, Robert] CALTECH, Jet Prop Lab, NASA, Pasadena, CA 91109 USA. [Wadsworth, Winthrop; Dybwad, Jens Peter] Designs & Prototypes Ltd, Nashua, NH 03060 USA. [Levy, Ralph] Quant Engn LLC, Doylestown, PA 18902 USA. RP Yiu, P (reprint author), CALTECH, Pasadena, CA 91125 USA. EM Patrick_Yiu@caltech.edu NR 25 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 7 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302034 ER PT J AU Zacny, K Yaggi, B Chu, P Johnson, J Kulchitsky, A Hedlund, M Davis, K Hermalyn, B Lee, P Paulsen, G Abrashkin, J AF Zacny, Kris Yaggi, Bryan Chu, Phil Johnson, Jerome Kulchitsky, Anton Hedlund, Magnus Davis, Kiel Hermalyn, Brendan Lee, Pascal Paulsen, Gale Abrashkin, John GP IEEE TI Thumper and Shotgun: Low Velocity Kinetic Penetrometers to Estimate Regolith and Rock Properties for NASA's Asteroid Redirect Mission (ARM) SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB NASA's Asteroid Redirect Mission (ARM) is a challenging mission to capture and bring back either an entire asteroid (Option A) or a large boulder from the surface of an asteroid (Option B) to a cislunar orbit. Options A and B have a range of risks; one of them relates to the unknown strength of the asteroid or boulder. This paper describes methods of estimating asteroid regolith strength and density, and the strength of boulders, using kinetic impactors: Thumpers and Shotgun. Thumpers are large, instrumented kinetic impactors specifically designed to measure regolith strength during impact deceleration. The Shotgun system, on the other hand, uses a large number of small projectiles ("balls") fired at low velocity at the surface of the asteroid or at the boulder. If a ball impacts regolith, it will create a crater whose size is a function of regolith strength and density. If a ball impacts a coherent boulder, it will bounce back at a certain speed, whose value is proportional to rock strength. If the rebound speed cannot be measured, hollow balls packed with retroretlectors could be used instead (similar to paintballs). The shell of balls can be designed to crack open and release retroretlectors when impacting rock above the threshold strength required for successful boulder retrieval. This paper describes the concepts of Thumpers and Shotgun and demonstrates their feasibility through a series of experiments. These methods leverage many of the advantages of in-situ measurements of target properties-particularly the ability to accurately determine geotechnical measurements-at a considerably reduced cost and implementation effort, and will enable significant risk buy-down on the scope of the ARM mission. C1 [Zacny, Kris; Yaggi, Bryan; Chu, Phil; Hedlund, Magnus; Paulsen, Gale] Honeybee Robot, 398 W Washington Blvd,Suite 200, Pasadena, CA 91103 USA. [Johnson, Jerome; Kulchitsky, Anton] Univ Alaska, Inst Northern Engn, Fairbanks, AK 99701 USA. [Davis, Kiel; Abrashkin, John] Honeybee Robot, New York, NY 10001 USA. [Hermalyn, Brendan] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Lee, Pascal] SETI Inst, Mountain View, CA 94043 USA. RP Zacny, K (reprint author), Honeybee Robot, 398 W Washington Blvd,Suite 200, Pasadena, CA 91103 USA. EM zacny@honeybeerobotics.com; yaggi@honeybeerobotics.com; chu@honeybeerobotics.com; jerome.b.johnson@alaska.edu; anton.kulchitsky@alaska.edu; hedlund@honeybeeroboties.com; davis@honeybeerobotics.com; brendan.hermalyn@nasa.gov; pascal.lee@marsinstitute.net; paulsen@honeybeerobotics.com; abrashkin@honeybeerobotics.com NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 12 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303058 ER PT J AU Zarifian, P Imken, T Matousek, SE Moeller, RC Bennett, MW Norton, CD Rosenberg, L Alibay, F Spangelo, S Banazadeh, P Casillas, RP Kawata, J AF Zarifian, Pez Imken, Travis Matousek, Steve E. Moeller, Robert C. Bennett, Matthew W. Norton, Charles D. Rosenberg, Leigh Alibay, Farah Spangelo, Sara Banazadeh, Payam Casillas, Raul Polit Kawata, Jessie GP IEEE TI Team Xc: JPL's Collaborative Design Team for Exploring CubeSat, NanoSat, and SmallSat-based Mission Concepts SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB Recently there has been an increasing demand for a rapid mission concept generation capability for CubeSats, NanoSats, and SmallSats at JPL and in the broader community in the Concept Maturity Level (CML) 2-5 range. To help address these needs, JPL's Innovation Foundry has extended its long-standing advanced concepts concurrent engineering team, Team X, with a new, agile, and collaborative design capability called Team Xc. This concurrent team-based approach provides rapid turnaround for small spacecraft mission and system early concept studies. The process is adaptable to a wide variety of CubeSat, NanoSat, and SmallSat customers and mission applications. Team Xc design and analysis services include feasibility assessments, trade space exploration studies, and point design studies, commensurate with the level of maturity of the mission concept. The team is assembled with experts experienced in designing, building, launching, and operating CubeSats; leaders in mission architecture, spacecraft design, and concurrent engineering methods; and subject matter experts tailored to the specific needs of each study and customer. The Team Xc capability has been applied to several studies and extended to cover a large breadth of missions spanning applications including Earth science, planetary science, astrophysics, and technology demonstration. Team Xc draws from Team X, JPL, and external subject matter experts to produce quick-turnaround reports targeted to each customer's needs. C1 [Zarifian, Pez; Imken, Travis; Matousek, Steve E.; Moeller, Robert C.; Bennett, Matthew W.; Norton, Charles D.; Rosenberg, Leigh; Alibay, Farah; Spangelo, Sara; Banazadeh, Payam; Casillas, Raul Polit; Kawata, Jessie] Jet Prop Lab, Pasadena, CA 91109 USA. RP Zarifian, P (reprint author), Jet Prop Lab, Pasadena, CA 91109 USA. EM Pezhman.Zarifian@jpl.nasa.gov; Travis.Imken@jpl.nasa.gov; Steven.E.Matousek@jpl.nasa.gov; Robert.C.Moeller@jpl.nasa.gov; Matthew.W.Bennett@jpl.nasa.gov; Charles.D.Norton@jpl.nasa.gov; Leigh.S.Rosenberg@jpl.nasa.gov; Farah.Alibay@jpl.nasa.gov; Sara.Spangelo@jpl.nasa.gov; Payam.Banazadeh@jpl.nasa.gov; Raul.Polit-Casillas@jpl.nasa.gov; Jessie.M.Kawata@jpl.nasa.gov NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 10 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501303046 ER PT J AU Zhang, SJ Acikmese, B Swei, SSM Prabhu, D AF Zhang, Serena Jing Acikmese, Behcet Swei, Sean Shan-Min Prabhu, Dinesh GP IEEE TI Convex Programming Approach to Real-time Trajectory Optimization for Mars Aerocapture SO 2015 IEEE AEROSPACE CONFERENCE LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 07-14, 2015 CL Big Sky, MT AB This paper is to develop a robust guidance and control (G&C) system and corresponding real-time algorithms for ADEPT (Adaptable Deployable Entry Placement Technology) planetary entry vehicle for Mars aerocapture mission with large payloads. The convex optimization based guidance approach is proposed that enables the real-time implementation of the algorithm and increases the predictability and robustness of the closed-loop system. The objective of this study is to utilize ADEPT aeroshell as a controllable G&C effector through active bank angle and angle of attack modulation and convex optimization based control methods for planetary entry maneuvers. A Mars aerocapture case study is simulated to demonstrate the feasibility and efficacy of the proposed guidance concept. C1 [Zhang, Serena Jing; Acikmese, Behcet] Univ Texas Austin, Austin, TX 78712 USA. [Swei, Sean Shan-Min] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Prabhu, Dinesh] NASA, ERC Inc, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Zhang, SJ (reprint author), Univ Texas Austin, Austin, TX 78712 USA. EM serenaj.zhang@gmail.com; behcet@austin.utexas.edu; sean.s.swei@nasa.gov; dinesh.k.prabhu@nasa.gov NR 18 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-5380-6 PY 2015 PG 7 WC Engineering, Aerospace SC Engineering GA BF2UN UT WOS:000380501302047 ER PT J AU Ranganathan, SVS Divsalar, D Wesel, RD AF Ranganathan, Sudarsan V. S. Divsalar, Dariush Wesel, Richard D. GP IEEE TI On the Girth of (3,L) Quasi-Cyclic LDPC Codes based on Complete Protographs SO 2015 IEEE INTERNATIONAL SYMPOSIUM ON INFORMATION THEORY (ISIT) SE IEEE International Symposium on Information Theory LA English DT Proceedings Paper CT IEEE International Symposium on Information Theory (ISIT) CY JUN 14-19, 2015 CL Hong Kong, PEOPLES R CHINA SP IEEE, IEEE Informat Theory Soc, HUAWEI, VTECH, Qualcomm, Google, Croucher Fdn, IBM, BROADCOM, Mediatek, iSN State Key Lab, INC, ITS, SENG, Hong Kong Polytechn Univ, K C Wong Educ Fdn, NSF, Hong Kong Univ Sci & Technol, Sch Engn ID PARITY-CHECK CODES; MATRICES; BOUNDS AB We consider the problem of constructing (3,L) quasi-cyclic low-density parity-check (LDPC) codes from complete protographs. A complete protograph is a small bipartite graph with two disjoint vertex sets such that every vertex in the variable-node set is connected to every vertex in the check-node set by a unique edge. This paper analyzes the required lifting factor for achieving girths of six or eight in the resulting quasi-cyclic codes with constraints on lifting. The required lifting factors provide lower bounds on the block-length of such codes. C1 [Ranganathan, Sudarsan V. S.; Wesel, Richard D.] Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90095 USA. [Divsalar, Dariush] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Ranganathan, SVS (reprint author), Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90095 USA. EM sudarsanvsr@ucla.edu; Dariush.Divsalar@jpl.nasa.gov; wesel@ee.ucla.edu NR 14 TC 2 Z9 2 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-7704-1 J9 IEEE INT SYMP INFO PY 2015 BP 431 EP 435 PG 5 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF4GT UT WOS:000380904700086 ER PT J AU Vakilinia, K Divsalar, D Wesel, RD AF Vakilinia, Kasra Divsalar, Dariush Wesel, Richard D. GP IEEE TI RCA Analysis of the Polar Codes and the use of Feedback to aid Polarization at Short Blocklengths SO 2015 IEEE INTERNATIONAL SYMPOSIUM ON INFORMATION THEORY (ISIT) SE IEEE International Symposium on Information Theory LA English DT Proceedings Paper CT IEEE International Symposium on Information Theory (ISIT) CY JUN 14-19, 2015 CL Hong Kong, PEOPLES R CHINA SP IEEE, IEEE Informat Theory Soc, HUAWEI, VTECH, Qualcomm, Google, Croucher Fdn, IBM, BROADCOM, Mediatek, iSN State Key Lab, INC, ITS, SENG, Hong Kong Polytechn Univ, K C Wong Educ Fdn, NSF, Hong Kong Univ Sci & Technol, Sch Engn AB This paper uses an extension of Reciprocal Channel Approximation (RCA) to accurately and efficiently predict the frame error rate (FER) performance of polar codes by analyzing the probability density function (p.d.f) of log likelihood ratios (LLR) associated with information bits. A feedback scheme uses the RCA to predict the p.d.f of LLRs in conjunction with a repetition coding system to decrease the blocklength required for a target FER by a factor of 16. Using a rate-0.5 128-bit polar code as the initially transmitted code, the FER of the system with feedback is obtained by theoretical analysis and verified by simulation. Including the additional incremental transmissions the average blocklength for the system with feedback is 137.55 bits and the rate is 0.4653. Without feedback, a polar code with blocklength 2048 is required to achieve a comparable FER at a comparable rate. Intuitively, feedback allows the polar code to use fewer frozen bits in the initial transmission and then uses repetition codes to provide the needed reliability to resolve unreliable unfrozen bits identified by feedback. C1 [Vakilinia, Kasra; Wesel, Richard D.] Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90095 USA. [Divsalar, Dariush] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Vakilinia, K (reprint author), Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90095 USA. NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-7704-1 J9 IEEE INT SYMP INFO PY 2015 BP 1292 EP 1296 PG 5 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF4GT UT WOS:000380904701069 ER PT J AU Sala, F Schoeny, C Divsalar, D Dolecek, L AF Sala, Frederic Schoeny, Clayton Divsalar, Dariush Dolecek, Lara GP IEEE TI Asymmetric Error -Correcting Codes for Flash Memories in High-Radiation Environments SO 2015 IEEE INTERNATIONAL SYMPOSIUM ON INFORMATION THEORY (ISIT) SE IEEE International Symposium on Information Theory LA English DT Proceedings Paper CT IEEE International Symposium on Information Theory (ISIT) CY JUN 14-19, 2015 CL Hong Kong, PEOPLES R CHINA SP IEEE, IEEE Informat Theory Soc, HUAWEI, VTECH, Qualcomm, Google, Croucher Fdn, IBM, BROADCOM, Mediatek, iSN State Key Lab, INC, ITS, SENG, Hong Kong Polytechn Univ, K C Wong Educ Fdn, NSF, Hong Kong Univ Sci & Technol, Sch Engn DE Coding for memories; Codes for Flash; Algebraic codes; Radiation-induced errors AB Research works exploring coding for Flash memories typically seek to correct errors taking place during normal device operation. In this paper, we study the design of codes that protect Flash devices dealing with the unusual class of errors caused by exposure to large radiation dosages. Significant radiation exposure can take place, for example, when Flash is used as on-board memory in satellites and space probes. We introduce an error model that captures the effects of radiation exposure. Such errors are asymmetric, with the additional feature that the degree (and direction) of asymmetry depends on the stored sequence. We develop an appropriate distance and an upper bound on the sizes of codes which correct such errors. We introduce and analyze several simple code constructions. C1 [Sala, Frederic; Schoeny, Clayton; Dolecek, Lara] Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90095 USA. [Divsalar, Dariush] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Sala, F (reprint author), Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90095 USA. EM fredsala@ucla.edu; cschoeny@ucla.edu; dariush.divsalar@jpl.nasa.gov; dolecek@ee.ucla.edu NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-7704-1 J9 IEEE INT SYMP INFO PY 2015 BP 2096 EP 2100 PG 5 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF4GT UT WOS:000380904702030 ER PT J AU Yoo, J Park, IW To, V Lum, JQH Smith, T AF Yoo, Jongwoon Park, In-Won To, Vinh Lum, Jason Q. H. Smith, Trey GP IEEE TI Avionics and Perching Systems of Free-Flying Robots for the International Space Station SO 2015 IEEE INTERNATIONAL SYMPOSIUM ON SYSTEMS ENGINEERING (ISSE) PROCEEDINGS LA English DT Proceedings Paper CT IEEE International Symposium on Systems Engineering (ISSE) Proceedings CY SEP 28-30, 2015 CL ROME, ITALY SP IEEE, IEEE SYSTEM COUNCIL AB This paper introduces NASA's new free-flying robot, Astrobee, especially focusing on its avionics and perching subsystems. Astrobee is a cube-shaped autonomous robot designed for various missions on the International Space Station (ISS). Its major goal is to offload routine and repetitive work from the ISS crews and assist their science activities. Astrobee is also designed for scientists to use it as a micro-gravity robotics research platform. It can host various science equipment and software, allowing scientists to conduct their experiments using Astrobees on the ISS. The robot has a small compliant, detachable arm with a griper so that it can perch on the ISS wall to support long duration tasks. This arm will grasp ISS handrails to hold its position without using propulsion or navigation subsystems to minimize power consumption. Due to its special missions and operating environment, Astrobee has a set of unique design requirements. This paper gives an overview of Astrobee and the details of its avionics and perching subsystems with distinctive design challenges. We also present the trade studies that we have conducted to decide the critical hardware and software components for the avionics. C1 [Yoo, Jongwoon; Park, In-Won; To, Vinh; Lum, Jason Q. H.; Smith, Trey] NASA, Ames Res Ctr, Intelligent Robot Grp, Mountain View, CA 94035 USA. RP Yoo, J (reprint author), NASA, Ames Res Ctr, Intelligent Robot Grp, Mountain View, CA 94035 USA. EM jongwoon.yoo@nasa.gov; in.w.park@nasa.gov; vinh.to@nasa.gov; jason.q.lum@nasa.gov; trey.smith@nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-1919-2 PY 2015 BP 198 EP 201 PG 4 WC Computer Science, Software Engineering SC Computer Science GA BF3NJ UT WOS:000380559200032 ER PT J AU Gebreyohannes, S Edmonson, W Chenou, J Neogi, N Esterline, A AF Gebreyohannes, Solomon Edmonson, William Chenou, Jules Neogi, Natasha Esterline, Albert GP IEEE TI Formal Requirement Management for the Responsive and Formal Design Process SO 2015 IEEE INTERNATIONAL SYMPOSIUM ON SYSTEMS ENGINEERING (ISSE) PROCEEDINGS LA English DT Proceedings Paper CT IEEE International Symposium on Systems Engineering (ISSE) Proceedings CY SEP 28-30, 2015 CL ROME, ITALY SP IEEE, IEEE SYSTEM COUNCIL AB In this paper, we present the formal requirement management of the Responsive and Formal Design (RFD) process that extracts a formal theory from requirements written in a natural language. The RFD process was developed as a procedure used in designing Cyber-Physical Systems (CPS) and represents an integration of Model-Based Systems Engineering (MBSE) with formal methods to ensure a "correct-by-construction" design. The extraction of a formal theory is based on Channel Theory as developed by Barwise and Seligman, which is established as a framework for the "flow of information" in terms of category theory. A system consists of components connected via channels. Each component is viewed as an information-flow network and mathematically modeled using a notion of a classification. A classification is a table representation of an information-flow network. Regularities (that represent global behavior of the system) of a classification are captured using a theory (a set of formulas or constraints). One goal of the RFD process is to insure that the requirements are formally consistent. In this paper, we develop a set of algorithms that extracts a theory from a classification, though the theory is not necessarily unique. This work is inclusive of an algorithm which checks whether a regular closure (based on structural rules) of a theory is a theory of a given classification. An example of this work is demonstrated through a satellite communication Store and Forward operation. C1 [Gebreyohannes, Solomon; Edmonson, William; Chenou, Jules; Esterline, Albert] NC A&T State Univ, Greensboro, NC 27411 USA. [Neogi, Natasha] NASA, LaRC, Hampton, VA USA. RP Gebreyohannes, S (reprint author), NC A&T State Univ, Greensboro, NC 27411 USA. EM shgebrey@ncat.edu; wwedmons@ncat.edu; jchenou@ncat.edu; natasha.a.neogi@nasa.gov; esterlin@ncat.edu NR 8 TC 0 Z9 0 U1 1 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-1919-2 PY 2015 BP 364 EP 369 PG 6 WC Computer Science, Software Engineering SC Computer Science GA BF3NJ UT WOS:000380559200058 ER PT J AU Trujillo, AC Fan, H Cross, CD Hempley, LE Cichella, V Puig-Navarro, J Mehdi, SB AF Trujillo, Anna C. Fan, Henry Cross, Charles D. Hempley, Lucas E. Cichella, Venanzio Puig-Navarro, Javier Mehdi, Syed Bilal BE Ahram, T Karwowski, W Schmorrow, D TI Operator informational needs for multiple autonomous small vehicles SO 6TH INTERNATIONAL CONFERENCE ON APPLIED HUMAN FACTORS AND ERGONOMICS (AHFE 2015) AND THE AFFILIATED CONFERENCES, AHFE 2015 LA English DT Proceedings Paper CT 6th International Conference on Applied Human Factors and Ergonomics (AHFE) CY JUL 26-30, 2015 CL Las Vegas, NV DE Mission manager; Autonomy; Small unmanned aerial vehicles AB With the anticipated explosion of small unmanned aerial vehicles, it is highly likely that operators will be controlling fleets of autonomous vehicles. To fulfill the promise of autonomy, vehicle operators will not be concerned with manual control of the vehicle; instead, they will deal with the overall mission. Furthermore, the one operator to many vehicles is becoming a constant meme with various industries including package delivery, search and rescue, and utility companies. In order for an operator to concurrently control several vehicles, his station must look and behave very differently than the current ground control station instantiations. Furthermore, the vehicle will have to be much more autonomous, especially during non-normal operations, in order to accommodate the knowledge deficit or the information overload of the operator in charge of several vehicles. The expected usage increase of small drones requires presenting the operational information generated by a fleet of heterogeneous autonomous agents to an operator. NASA Langley Research Center's Autonomy Incubator has brought together researchers in various disciplines including controls, trajectory planning, systems engineering, and human factors to develop an integrated system to study autonomy issues. The initial human factors effort is focusing on mission displays that would give an operator the overall status of all autonomous agents involved in the current mission. This paper will discuss the specifics of the mission displays for operators controlling several vehicles. Published by Elsevier B.V. C1 [Trujillo, Anna C.] NASA Langley Res Ctr, Hampton, VA 23665 USA. [Fan, Henry] Analyt Mech Associates Inc, Hampton, VA USA. [Cross, Charles D.; Hempley, Lucas E.] Northrop Grumman, Hampton, VA 23681 USA. [Cichella, Venanzio; Puig-Navarro, Javier; Mehdi, Syed Bilal] Univ Illinois, Urbana, IL 61801 USA. RP Trujillo, AC (reprint author), NASA Langley Res Ctr, Hampton, VA 23665 USA. EM anna.c.trujillo@nasa.gov NR 34 TC 1 Z9 1 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS PY 2015 BP 936 EP 943 DI 10.1016/j.promfg.2015.07.141 PG 8 WC Behavioral Sciences; Engineering, Multidisciplinary SC Behavioral Sciences; Engineering GA BF6UZ UT WOS:000383740301007 ER PT J AU Kramer, LJ Bailey, RE Ellis, KK AF Kramer, Lynda J. Bailey, Randall E. Ellis, Kyle K. BE Ahram, T Karwowski, W Schmorrow, D TI Using vision system technologies for offset approaches in low visibility operations SO 6TH INTERNATIONAL CONFERENCE ON APPLIED HUMAN FACTORS AND ERGONOMICS (AHFE 2015) AND THE AFFILIATED CONFERENCES, AHFE 2015 LA English DT Proceedings Paper CT 6th International Conference on Applied Human Factors and Ergonomics (AHFE) CY JUL 26-30, 2015 CL Las Vegas, NV DE Enhanced Flight Vision Systems; Synthetic Vision Systems; Head-up display; NextGen AB Flight deck-based vision systems, such as Synthetic Vision Systems (SVS) and Enhanced Flight Vision Systems (EFVS), have the potential to provide additional margins of safety for aircrew performance and enable the implementation of operational improvements for low visibility surface, arrival, and departure operations in the terminal environment with equivalent efficiency to visual operations. Twelve air transport-rated crews participated in a motion-base simulation experiment to evaluate the use of SVS/EFVS in Next Generation Air Transportation System low visibility approach and landing operations at Chicago O'Hare airport. Three monochromatic, collimated head-up display (HUD) concepts (conventional HUD, SVS HUD, and EFVS HUD) and three instrument approach types (straight-in, 3-degree offset, 15-degree offset) were experimentally varied to test the efficacy of the SVS/EFVS HUD concepts for offset approach operations. The findings suggest making offset approaches in low visibility conditions with an EFVS HUD or SVS HUD appear feasible. Regardless of offset approach angle or HUD concept being flown, all approaches had comparable ILS tracking during the instrument segment and were within the lateral confines of the runway with acceptable sink rates during the visual segment of the approach. Published by Elsevier B.V. C1 [Kramer, Lynda J.; Bailey, Randall E.; Ellis, Kyle K.] NASA, Langley Res Ctr, Hampton, VA 23665 USA. RP Kramer, LJ (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. EM lynda.j.kramer@nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS PY 2015 BP 2373 EP 2380 DI 10.1016/j.promfg.2015.07.385 PG 8 WC Behavioral Sciences; Engineering, Multidisciplinary SC Behavioral Sciences; Engineering GA BF6UZ UT WOS:000383740302067 ER PT J AU Monk, KJ Strybel, TZ Vu, KPL Marayong, P Battiste, V AF Monk, Kevin J. Strybel, Thomas Z. Vu, Kim-Phuong L. Marayong, Panadda Battiste, Vernol BE Ahram, T Karwowski, W Schmorrow, D TI Effects of force feedback and distractor location on a CDTI target selection task SO 6TH INTERNATIONAL CONFERENCE ON APPLIED HUMAN FACTORS AND ERGONOMICS (AHFE 2015) AND THE AFFILIATED CONFERENCES, AHFE 2015 LA English DT Proceedings Paper CT 6th International Conference on Applied Human Factors and Ergonomics (AHFE) CY JUL 26-30, 2015 CL Las Vegas, NV DE Force feedback; Distractor; Haptic; CDTI; Movement task ID PERFORMANCE; INTERFACE AB New flight deck technologies need to be implemented in order to support the projected rises in traffic levels. Future cockpit displays of traffic information(CDTIs) shall accommodate the altered responsibilities of pilots by facilitating more efficient routes and minimizing conflicts. However, the unstable nature of the cockpit may present challenges when precise inputs are required. The present study investigated the effects of force feedback and distractors on point-and-click movement times in a CDTI environment. Participants performed target selection tasks with multiple levels of force feedback and distractor location. Results implied that force feedback failed to benefit movement times relative to the standard computer mouse. However, substantial interactions between distractor effects, force levels, and other target characteristics are explored. (C) 2015 Published by Elsevier B.V. C1 [Monk, Kevin J.; Battiste, Vernol] NASA Ames Res Ctr, Moffett Field, CA 94035 USA. [Strybel, Thomas Z.; Vu, Kim-Phuong L.; Marayong, Panadda] Calif State Univ Long Beach, Long Beach, CA 90840 USA. RP Monk, KJ (reprint author), NASA Ames Res Ctr, Moffett Field, CA 94035 USA. EM kevin.j.monk@nasa.gov NR 25 TC 0 Z9 0 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS PY 2015 BP 2395 EP 2402 DI 10.1016/j.promfg.2015.07.388 PG 8 WC Behavioral Sciences; Engineering, Multidisciplinary SC Behavioral Sciences; Engineering GA BF6UZ UT WOS:000383740302070 ER PT J AU Sturre, LK Kozon, TE Verma, SA Jung, J Zelinski, SJ AF Sturre, Lindsay K. Kozon, Thomas E. Verma, Savita A. Jung, Jaewoo Zelinski, Shannon J. BE Ahram, T Karwowski, W Schmorrow, D TI Human factors assessment of disturbances to scheduled performance-based navigation arrival operations SO 6TH INTERNATIONAL CONFERENCE ON APPLIED HUMAN FACTORS AND ERGONOMICS (AHFE 2015) AND THE AFFILIATED CONFERENCES, AHFE 2015 LA English DT Proceedings Paper CT 6th International Conference on Applied Human Factors and Ergonomics (AHFE) CY JUL 26-30, 2015 CL Las Vegas, NV DE Workload; Scheduled arrival operations; Performance-Based Navigation AB The introduction of Performance-Based Navigation (PBN) specifications to air traffic management has resulted in many benefits during nominal operations, including shorter flight paths, reduced fuel costs, and improved terminal area arrival rates. However, these benefits become less noticeable during off-nominal operations where aircraft are routinely interrupted from staying on PBN procedures due to disturbances such as missed approaches. This human-in-the-loop (HITL) study used multiple types of disturbance events to perturb the arrival schedule. Perturbed schedules were managed with different types of schedule adjustments, including a condition with no adjustments. The study collected data on a host of dependent variables, including human factors measures on controller workload and system performance measures such as schedule nonconformance (nc). Initial analyses showed strong correlations between aggregated controller workload and aggregated nc, as well as benefits of both automatic and manual schedule adjustments for increasing system performance, such as reduced PBN procedure interruptions. The goal of this paper is to further test these initial findings. The results indicated that an increase in schedule nonconformance correlated with an increase in controller workload at specific time intervals, and automated schedule adjustments consistently reduced controller workload associated with nonconformance. Published by Elsevier B.V. C1 [Sturre, Lindsay K.; Kozon, Thomas E.] Univ Calif Santa Cruz, Santa Cruz, CA 95064 USA. [Verma, Savita A.; Jung, Jaewoo; Zelinski, Shannon J.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Sturre, LK (reprint author), Univ Calif Santa Cruz, Santa Cruz, CA 95064 USA. EM lindsay.k.sturre@nasa.gov NR 17 TC 0 Z9 0 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS PY 2015 BP 2442 EP 2449 DI 10.1016/j.promfg.2015.07.504 PG 8 WC Behavioral Sciences; Engineering, Multidisciplinary SC Behavioral Sciences; Engineering GA BF6UZ UT WOS:000383740302076 ER PT J AU Bakowski, DL Hooey, BL Foyle, DC Wolter, CA AF Bakowski, Deborah L. Hooey, Becky L. Foyle, David C. Wolter, Cynthia A. BE Ahram, T Karwowski, W Schmorrow, D TI NextGen Surface Trajectory-Based Operations (STBO): Evaluating conformance to a four-dimensional trajectory (4DT) SO 6TH INTERNATIONAL CONFERENCE ON APPLIED HUMAN FACTORS AND ERGONOMICS (AHFE 2015) AND THE AFFILIATED CONFERENCES, AHFE 2015 LA English DT Proceedings Paper CT 6th International Conference on Applied Human Factors and Ergonomics (AHFE) CY JUL 26-30, 2015 CL Las Vegas, NV DE NextGen; STBO; 4D Trajectory (4DT); Surface operations; Taxi; Displays AB A pilot-in-the-loop simulation was conducted to assess the feasibility of a Surface Trajectory-Based Operations (STBO) concept [1]. The STBO concept was investigated from the pilot perspective by evaluating pilot conformance to a four-dimensional trajectory (4DT) while taxiing under manual control. Simulation conditions included a Current-Day Equipage condition; a verbal Speed-Advisory condition, which represented a near-term condition in which pilots were provided with verbal speed guidance from ATC, but not provided with any additional flight-deck tools by which to support schedule conformance; and two NextGen 4DT conditions in which the pilots were provided with flight deck displays to support conformance to the 4DT at two different levels, +/- 30 sec (4DT(30)) and +/- 15 sec (4DT(15)). In the NextGen 4DT conditions, pilots were presented with a graphical representation of the 4DT on an Airport Moving Map (AMM). Results showed that both the 4DT30 and 4DT15 conditions afforded more than 99% conformance to the 4DT across the entire route. An evaluation of the time of arrival (TOA) at the end-point revealed significantly less TOA error in the 4DT30 and 4DT15 conditions as compared to the Speed-Advisory condition. Although eye-tracking data revealed an increase in eyes-in time in the 4DT-display conditions, pilots rated this increase as acceptable. The results of this pilot-in-the-loop simulation demonstrated that the NextGen 4DT displays afforded high conformance with a substantial increase in predictability throughout the entire taxi route and at the runway queue. Pilots also rated that conforming to a speed profile, during taxi, was acceptable and safe. Published by Elsevier B.V. C1 [Bakowski, Deborah L.; Hooey, Becky L.; Wolter, Cynthia A.] San Jose State Univ, Moffett Field, CA USA. [Foyle, David C.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Bakowski, DL (reprint author), San Jose State Univ, Moffett Field, CA USA. EM deborah.bakowski@nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS PY 2015 BP 2458 EP 2465 DI 10.1016/j.promfg.2015.07.506 PG 8 WC Behavioral Sciences; Engineering, Multidisciplinary SC Behavioral Sciences; Engineering GA BF6UZ UT WOS:000383740302078 ER PT J AU Koltz, MT Roberts, ZS Sweet, J Battiste, H Cunningham, J Battiste, V Vu, KPL Strybel, TZ AF Koltz, Martin T. Roberts, Zachary S. Sweet, John Battiste, Henri Cunningham, James Battiste, Vernol Vu, Kim-Phuong L. Strybel, Thomas Z. BE Ahram, T Karwowski, W Schmorrow, D TI An investigation of the harbor pilot concept for single pilot operations SO 6TH INTERNATIONAL CONFERENCE ON APPLIED HUMAN FACTORS AND ERGONOMICS (AHFE 2015) AND THE AFFILIATED CONFERENCES, AHFE 2015 LA English DT Proceedings Paper CT 6th International Conference on Applied Human Factors and Ergonomics (AHFE) CY JUL 26-30, 2015 CL Las Vegas, NV DE Single pilot operations; Workload; Harbor pilot AB Commercial aviation is expected to see an average growth of 3.7% per year over the next five years. At the same time, regional airlines are expressing concerns that they are unable to find a sufficient number of pilots who meet the minimum number of required flight hours and certifications. One option for handling the increased demand for, and reduced supply of, pilots is to better distribute the pilots already employed. This could be accomplished by reducing the number of required crewmembers on the flight deck from two to one. However, a significant challenge to the implementation of a single pilot crew is the increase in workload a single pilot would face especially in complex airspace. The harbor pilot is one concept of operations that has been proposed to deal with the potentially serious problem. In this concept, the harbor pilot is a ground operator whose job it is to help arriving single pilot aircraft navigate the complex terminal area airspace. The purpose of the present study was to investigate the feasibility of the harbor pilot concept by measuring the workload and performance of harbor pilots during a series of back-to-back simulated arrival procedures. Preliminary results show that harbor pilots rate their workload generally low and indicate that the maximum consecutive normal approaches that they are able to complete in a row is about four to six, provided they are not emergency situations. (C) 2015 The Authors. Published by Elsevier B.V. C1 [Koltz, Martin T.; Roberts, Zachary S.; Sweet, John; Battiste, Henri; Cunningham, James; Vu, Kim-Phuong L.; Strybel, Thomas Z.] Calif State Univ Long Beach, Long Beach, CA 90840 USA. [Battiste, Vernol] San Jose State Univ, San Jose, CA 95192 USA. [Battiste, Vernol] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Koltz, MT (reprint author), Calif State Univ Long Beach, Long Beach, CA 90840 USA. NR 7 TC 0 Z9 0 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS PY 2015 BP 2937 EP 2944 DI 10.1016/j.promfg.2015.07.948 PG 8 WC Behavioral Sciences; Engineering, Multidisciplinary SC Behavioral Sciences; Engineering GA BF6UZ UT WOS:000383740303008 ER PT J AU Cunningham, JC Battiste, H Curtis, S Hallett, EC Koltz, M Brandt, SL Lachter, J Battiste, V Johnson, WW AF Cunningham, James C. Battiste, Henri Curtis, Sam Hallett, Elyse C. Koltz, Martin Brandt, Summer L. Lachter, Joel Battiste, Vernol Johnson, Walter W. BE Ahram, T Karwowski, W Schmorrow, D TI Measuring Situation Awareness with probe questions: Reasons for not answering the probes SO 6TH INTERNATIONAL CONFERENCE ON APPLIED HUMAN FACTORS AND ERGONOMICS (AHFE 2015) AND THE AFFILIATED CONFERENCES, AHFE 2015 LA English DT Proceedings Paper CT 6th International Conference on Applied Human Factors and Ergonomics (AHFE) CY JUL 26-30, 2015 CL Las Vegas, NV DE Situation Awareness; Situation Present Assessment Method; SPAM; Single pilot operations; SPO; Reduced crew operations; RCO; Response time-out; Question time-out AB Situation Awareness (SA) refers to an individual's understanding of what is happening in their environment, and what is likely to happen in the near future [1]. SA is an important construct to study in aviation because lower levels of SA are associated with increased aviation accidents and mishaps [2]. One technique to measure operator SA is through the use of online probe questions, where operators are queried about their task environment at various intervals while performing the task. The current study used the Situation Present Assessment Method (SPAM) [3] for administering online probes. With SPAM, a ready prompt appears on a panel and participants are instructed to accept the prompt when workload permits to be presented with a SA probe question. Latencies in accepting the ready prompt are indicative of the operator's workload level at that time. When ready prompts go unanswered, (ready time-outs; RTO), it is assumed workload is too high. When a prompt is accepted, probe questions are presented for a limited time (60 seconds in this study). Thus it is possible they too will go unanswered by timing out (question time-out; QTO). QTOs can occur for the following reasons: 1) operator did not know the answer, 2) due to the dynamic changes in the task, the operator workload became too high to devote resources to answering the question, 3) question was unanswerable due to the current context, or 4) question required more time to answer than allowed. In the present study, we analyzed a subset of the data from a larger study (see Brandt et al. [4]) to examine reasons for why probe questions go unanswered. For QTOs, the majority of questions went unanswered because the operator did not know how to answer the question, or because the operator was dealing with high workload. RTOs, which occurred more frequently, were normally due to task/workload. (C) 2015 The Authors. Published by Elsevier B.V. C1 [Cunningham, James C.; Battiste, Henri; Curtis, Sam; Hallett, Elyse C.; Koltz, Martin] Calif State Univ Long Beach, 1250 Bellflower Blvd, Long Beach, CA 90840 USA. [Brandt, Summer L.; Lachter, Joel; Battiste, Vernol] San Jose State Univ, NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Brandt, Summer L.; Lachter, Joel; Battiste, Vernol; Johnson, Walter W.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Cunningham, JC (reprint author), Calif State Univ Long Beach, 1250 Bellflower Blvd, Long Beach, CA 90840 USA. NR 10 TC 0 Z9 0 U1 1 U2 2 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS PY 2015 BP 2982 EP 2989 DI 10.1016/j.promfg.2015.07.840 PG 8 WC Behavioral Sciences; Engineering, Multidisciplinary SC Behavioral Sciences; Engineering GA BF6UZ UT WOS:000383740303014 ER PT J AU Martin, L Nguyen, J Lin, M Sharma, S Witzberger, K AF Martin, Lynne Nguyen, Jimmy Lin, Melody Sharma, Shivanjli Witzberger, Kevin BE Ahram, T Karwowski, W Schmorrow, D TI Accommodating off nominal conditions when working to a metered schedule SO 6TH INTERNATIONAL CONFERENCE ON APPLIED HUMAN FACTORS AND ERGONOMICS (AHFE 2015) AND THE AFFILIATED CONFERENCES, AHFE 2015 LA English DT Proceedings Paper CT 6th International Conference on Applied Human Factors and Ergonomics (AHFE) CY JUL 26-30, 2015 CL Las Vegas, NV DE Terminal Sequencing and Spacing; Workload; Aircraft management AB In a schedule based Air Traffic Management (ATM) system, minor disruptions to the traffic flow could have a wider impact than would be expected as aircraft are linked temporally. However, given the frequency of these minor disruptions, the extent of their impact on operations needs to be scoped. In a human-in-the-loop (HITL) simulation, four TRACON controllers worked arrival traffic to Phoenix airport (PHX), aided by a schedule and controller sequencing and spacing tools. In approximately two-thirds of the runs, either one or two disrupting events that were local or global in nature, were set in motion. Controllers were asked to manage the disruptions and bring the traffic back onto the schedule. The research questions were exploratory: to observe the impact of the disruption, watch how controllers solved these problems and whether the controller tools assisted them. Global events were observed to have a greater impact on TRACON operations than local events as they led to a greater mean path length flown by aircraft through the TRACON and, although reported workload levels remained manageable overall global events created higher reported loads. Controller strategies for resolving events followed a similar pattern: with controllers often solving local problems with speed and moving to using vectors more often during global events. Controllers used their tools in a similar manner to those observed in nominal-operations studies, with the slot marker being the preferred aid regardless of the event. However, due to the range of factors influencing the event, e.g., environmental conditions, aircraft density in the TRACON, etc., sometimes the plan required revision and occasionally events had a wide-reaching effect. (C) 2015 The Authors. Published by Elsevier B.V. C1 [Martin, Lynne] San Jose State Univ, NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Nguyen, Jimmy; Lin, Melody] Optimal Synth, Los Gatos, CA 94035 USA. [Sharma, Shivanjli; Witzberger, Kevin] NASA, Ames Res Ctr, Mountain View, CA 94035 USA. RP Martin, L (reprint author), San Jose State Univ, NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM lynne.martin@nasa.gov NR 12 TC 0 Z9 0 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS PY 2015 BP 2990 EP 2997 DI 10.1016/j.promfg.2015.07.842 PG 8 WC Behavioral Sciences; Engineering, Multidisciplinary SC Behavioral Sciences; Engineering GA BF6UZ UT WOS:000383740303015 ER PT J AU Brandt, SL Lachter, J Battiste, V Johnson, W AF Brandt, Summer L. Lachter, Joel Battiste, Vernol Johnson, Walter BE Ahram, T Karwowski, W Schmorrow, D TI Pilot situation awareness and its implications for single pilot operations: Analysis of a human-in-the-loop study SO 6TH INTERNATIONAL CONFERENCE ON APPLIED HUMAN FACTORS AND ERGONOMICS (AHFE 2015) AND THE AFFILIATED CONFERENCES, AHFE 2015 LA English DT Proceedings Paper CT 6th International Conference on Applied Human Factors and Ergonomics (AHFE) CY JUL 26-30, 2015 CL Las Vegas, NV DE Single pilot operations (SPO); Reduced crew operations (RCO); Remote pilot support; Ground station; Situation awareness (SA) AB In 2012, NASA began exploring the feasibility of single pilot/reduced crew operations in the context of scheduled air carrier operations. The current study examined how important it was for ground-based personnel providing support to single piloted aircraft (ground operators) to have opportunities to acquire situation awareness (SA) prior to being called on to assist an aircraft. We looked at two distinct concepts of operation, which varied in how much information was available to ground operators prior to being called on to assist a critical event (no vs. some Situation Preview). Thirty-five commercial pilots participated in the current study. Results suggested that a ground operators' lack of initial SA when called on for dedicated assistance is not an issue, at least when the ground operator station displays environmental and systems data which are important to gaining overall SA of the specified aircraft. With appropriate displays, ground operators were able to provide immediate assistance, even if they had minimal SA prior to getting a request. (C) 2015 The Authors. Published by Elsevier B.V. C1 [Brandt, Summer L.; Lachter, Joel; Battiste, Vernol] San Jose State Univ, NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Brandt, Summer L.; Lachter, Joel; Battiste, Vernol; Johnson, Walter] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Brandt, SL (reprint author), San Jose State Univ, NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM summer.l.brandt@nasa.gov NR 9 TC 2 Z9 2 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS PY 2015 BP 3017 EP 3024 DI 10.1016/j.promfg.2015.07.846 PG 8 WC Behavioral Sciences; Engineering, Multidisciplinary SC Behavioral Sciences; Engineering GA BF6UZ UT WOS:000383740303019 ER PT J AU Dao, AQV Koltai, K Cals, SD Brandt, SL Lachter, J Matessa, M Smith, DE Battiste, V Johnson, WW AF Dao, Arik-Quang V. Koltai, Kolina Cals, Samantha D. Brandt, Summer L. Lachter, Joel Matessa, Michael Smith, David E. Battiste, Vernol Johnson, Walter W. BE Ahram, T Karwowski, W Schmorrow, D TI Evaluation of a recommender system for single pilot operations SO 6TH INTERNATIONAL CONFERENCE ON APPLIED HUMAN FACTORS AND ERGONOMICS (AHFE 2015) AND THE AFFILIATED CONFERENCES, AHFE 2015 LA English DT Proceedings Paper CT 6th International Conference on Applied Human Factors and Ergonomics (AHFE) CY JUL 26-30, 2015 CL Las Vegas, NV DE Single pilot operations; Transparency; Trust; Recommender system; Emergency landing; Ground station; Simulation ID TRUST; RELIANCE; AUTOMATION AB This paper discusses the quality of a recommender system implemented in a simulation to assist with choosing a diversionary airport for distressed aircraft. In the third of the series of studies investigating the feasibility of ground-supported single pilot operations (SPO) a recommender system was used by 35 airline pilots as an aid for selecting diversionary airports. These pilots, acting as ground operators, used the recommender system from a ground station when off-nominal events required them to provide ground support to a single piloted aircraft. The unique circumstances imposed by each of the scenarios required the ground operators, together with the recommender system, to consider the relative importance of different factors when recommending an airport. Post-trial questionnaires were used to evaluate the recommender system. Results indicated that the pilots did not find the recommender system very transparent and did not always trust its initial recommendation. However, pilots did appear to find the recommender system to be effective in supporting them with the high workload in off nominal situations, and interactions with the system appear to have been satisfactory. Pilots also reported in post simulation surveys a desire to have better explanations for those recommendations. Findings will inform the development of future iterations of the recommender system, as well as influence SPO procedures and further development of a prototype ground station. (C) 2015 The Authors. Published by Elsevier B.V. C1 [Dao, Arik-Quang V.; Brandt, Summer L.; Lachter, Joel; Battiste, Vernol] San Jose State Univ, San Jose, CA 95112 USA. [Koltai, Kolina; Cals, Samantha D.] Calif State Univ Northridge, Northridge, CA 91330 USA. [Matessa, Michael] Rockwell Collins, Cedar Rapids, IA 52498 USA. [Dao, Arik-Quang V.; Brandt, Summer L.; Lachter, Joel; Smith, David E.; Battiste, Vernol; Johnson, Walter W.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Dao, AQV (reprint author), San Jose State Univ, San Jose, CA 95112 USA. EM quang.v.dao@nasa.gov NR 21 TC 0 Z9 0 U1 3 U2 3 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS PY 2015 BP 3070 EP 3077 DI 10.1016/j.promfg.2015.07.853 PG 8 WC Behavioral Sciences; Engineering, Multidisciplinary SC Behavioral Sciences; Engineering GA BF6UZ UT WOS:000383740303026 ER PT J AU Schulze, C Lindvall, M Bjorgvinsson, S Wiegand, R AF Schulze, Christoph Lindvall, Mikael Bjorgvinsson, Sigurthor Wiegand, Robert GP IEEE TI Model Generation to support Model-based Testing Applied on the NASA DAT Web-application -an Experience Report SO 2015 IEEE 26TH INTERNATIONAL SYMPOSIUM ON SOFTWARE RELIABILITY ENGINEERING (ISSRE) LA English DT Proceedings Paper CT IEEE 26th International Symposium on Software Reliability Engineering (ISSRE 2015) CY NOV 02-05, 2015 CL Gaithersbury, MD DE Model-based Testing; Model Generation; State Machines AB Model-based Testing (MBT), where a model of the system under test's (SUT) behavior is used to automatically generate executable test cases, is a promising and versatile testing technology. Nevertheless, adoption of MBT technologies in industry is slow and many testing tasks are performed via manually created executable test cases (i.e. test programs such as RI nit). In order to adopt MBT, testers must learn how to construct models and use these models to generate test cases, which might be a hurdle. An interesting observation in our previous work is that the existing manually created test cases often provided invaluable insights for the manual creation of the testing models of the system. In this paper we present an approach that allows the tester to first create and debug a set of test cases. When the tester is happy with the test cases, the next step is to automatically generate a model from the test cases. The generated model is derived from the test cases, which are actions that the system can perform (e.g. a button clicks) and their expected outputs in form of assert statements (e.g. assert data entered). The model is a Finite State Machine (FSM) model that can be employed with little or no manual changes to generate additional test cases for the SUT. We successfully applied the approach in a feasibility study to the NASA Data Access Toolkit (DAT), which is a web-based GUI. One compelling finding is that the test cases that were generated from the automatically generated models were able to detect issues that were not detected by the original set of manually created test cases. We present the findings from the case study and discuss best practices for incorporating model generation techniques into an existing testing process. C1 [Schulze, Christoph; Lindvall, Mikael; Bjorgvinsson, Sigurthor] Fraunhofer Ctr Expt Software Engn, College Pk, MD 20740 USA. [Wiegand, Robert] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. RP Schulze, C (reprint author), Fraunhofer Ctr Expt Software Engn, College Pk, MD 20740 USA. EM cschulze@fc-md.umd.edu; mlindvall@fc-md.umd.edu; sbjorgvinsson@fc-md.umd.edu; robert.e.wiegand@nasa.gov NR 18 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-5090-0406-5 PY 2015 BP 77 EP 87 PG 11 WC Computer Science, Software Engineering; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF3XS UT WOS:000380604200008 ER PT J AU Vakilinia, K Divsalar, D Wesel, RD AF Vakilinia, Kasra Divsalar, Dariush Wesel, Richard D. GP IEEE TI Protograph-Based Raptor-Like LDPC Codes for the Binary Erasure Channel SO 2015 INFORMATION THEORY AND APPLICATIONS WORKSHOP (ITA) LA English DT Proceedings Paper CT Information Theory and Applications Workshop (ITA) CY FEB 01-06, 2015 CL Univ California, San Diego, CA HO Univ California ID PARITY-CHECK CODES; COMPLEXITY; CAPACITY; CONSTRUCTION; PERFORMANCE; DESIGN AB This paper designs protograph-based Raptor-like (PBRL) codes as a class of rate-compatible (RC) LDPC codes for binary-erasure channels (BEC). Similar to the Raptor Codes, the RC property is achieved by X-OR operations of the precoded bits. The additional parity bits, which lower the rate, are selected such that their connections in the protograph optimize the density evolution threshold. In order to avoid problematic graphical objects in the CPEG lifted bipartite graph and guarantee the linear growth distance property some constraints are imposed in the threshold optimization algorithm. Simulation results are presented for information block sizes of k = 1032, and k = 16384. These results are compared with finite blocklength bounds of Polyanskiy, Poor, Verdu (PPV) as well as several asymptotic bounds. The k = 1032 code family operates at various rates in the range of 8/9 to 8/48 and has an average normalized threshold gap of 5.56% from capacity. The k = 16384 code family operates at rates 8/10 to 8/32 and has an average normalized threshold gap of 3.27% from capacity. C1 [Vakilinia, Kasra; Wesel, Richard D.] Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90024 USA. [Divsalar, Dariush] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Vakilinia, K (reprint author), Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90024 USA. EM vakiliniak@ucla.edu; Dariush.Divsalar@jpl.nasa.gov; wesel@ee.ucla.edu NR 28 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-7195-4 PY 2015 BP 240 EP 246 PG 7 WC Computer Science, Information Systems; Computer Science, Theory & Methods SC Computer Science GA BF3SJ UT WOS:000380573200037 ER PT B AU Ahmad, IAD AF Ahmad, Imad-ad-Dean BE Ali, AJ TI Individual rights and responsibilities, morality, relativism and self-interest SO HANDBOOK OF RESEARCH ON ISLAMIC BUSINESS ETHICS LA English DT Article; Book Chapter C1 [Ahmad, Imad-ad-Dean] Minaret Freedom Inst, Washington, DC 20540 USA. [Ahmad, Imad-ad-Dean] Wesley Theol Seminary, Washington, DC USA. [Ahmad, Imad-ad-Dean] Univ Maryland, College Pk, MD 20742 USA. [Ahmad, Imad-ad-Dean] Georgetown Univ, Washington, DC 20057 USA. [Ahmad, Imad-ad-Dean] Johns Hopkins Univ, Baltimore, MD 21218 USA. [Ahmad, Imad-ad-Dean] Foreign Serv Inst, Islam, New Delhi, India. [Ahmad, Imad-ad-Dean] Harvard, Astron, Cambridge, MA USA. [Ahmad, Imad-ad-Dean] Univ Maryland, Astron, College Pk, MD 20742 USA. [Ahmad, Imad-ad-Dean] Goddard Space Flight Ctr, Greenbelt, MD USA. [Ahmad, Imad-ad-Dean] Amer Univ, Washington, DC 20016 USA. [Ahmad, Imad-ad-Dean] Dar Adh Dhikr Mosque, Bethesda, MD USA. [Ahmad, Imad-ad-Dean] Islamic Amer Zakat Fdn, Bethesda, MD USA. [Ahmad, Imad-ad-Dean] Coordinating Council Muslim Org Greater Washingto, Bethesda, MD USA. RP Ahmad, IAD (reprint author), Minaret Freedom Inst, Washington, DC 20540 USA. NR 10 TC 0 Z9 0 U1 0 U2 0 PU EDWARD ELGAR PUBLISHING LTD PI CHELTENHAM PA GLENSANDA HOUSE, MONTPELLIER PARADE, CHELTENHAM GL50 1UA, GLOS, ENGLAND BN 978-1-78100-945-1; 978-1-78100-944-4 PY 2015 BP 32 EP 45 D2 10.4337/9781781009451 PG 14 WC Business; Ethics; Religion SC Business & Economics; Social Sciences - Other Topics; Religion GA BF8KG UT WOS:000385140000003 ER PT J AU Wu, GF Tang, X Meyyappan, M Lai, KWC AF Wu, Guangfu Tang, Xin Meyyappan, M. Lai, King W. C. GP IEEE TI Chemical Functionalization of Graphene with Aromatic Molecule SO 2015 IEEE 15TH INTERNATIONAL CONFERENCE ON NANOTECHNOLOGY (IEEE-NANO) LA English DT Proceedings Paper CT IEEE NANO 2015 15th INTERNATIONAL CONFERENCE ON NANOTECHNOLOGY CY JUL 27-30, 2015 CL ROME, ITALY SP Univ di Roma, SAPIENZA UNIV DI ROMA, IEEE, IEEE NANO, USN DEPT OF THE NAVY SCI & TECHNOL, ISTITUTO ITALIANO DI TECNOLOGIA, CAMBRIDGE UNIV PRESS, Centro Studi e Documentazione sulla Sensoristica, FEI, Nanoscale Horizons, UNIV NOTRE DAME DE chemical functionalization; graphene; aromatic; pi-pi stacking ID FIELD-EFFECT TRANSISTORS; DERIVATIVES; SENSORS; SHEETS AB We investigated the doping effects of chemical functionalization on graphene field-effect transistors (G-FETs). A pyrene backbone with an electron-withdrawing group (1-pyrenebutanoic acid succinimidyl ester, PBASE) and DMF acting as a solvent were used. The pyrene derivative was stably immobilized onto the graphene surface via pi-pi stacking between the two highly conjugated systems, confirmed by electric measurements with different incubation times and linker molecule concentrations. Dimethyl formamide (DMF) can decrease the conductivity of the FET devices and showed an n-doping effect while the pyrene derivative showed a p-doping effect. Because of this, the functionalization with PBASE in DMF could be regarded as a competitive process. This study provides a new insight into chemical functionalization with aromatic molecule, and understanding of doping effects about electron donor and electron acceptor on graphene during the functionalization process. C1 [Wu, Guangfu; Tang, Xin; Lai, King W. C.] City Univ Hong Kong, Dept Mech & Biomed Engn, Hong Kong, Hong Kong, Peoples R China. [Meyyappan, M.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Wu, GF (reprint author), City Univ Hong Kong, Dept Mech & Biomed Engn, Hong Kong, Hong Kong, Peoples R China. EM kinglai@cityu.edu.hk NR 24 TC 0 Z9 0 U1 2 U2 4 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-8155-0 PY 2015 BP 1324 EP 1327 PG 4 WC Engineering, Electrical & Electronic; Nanoscience & Nanotechnology SC Engineering; Science & Technology - Other Topics GA BF3AF UT WOS:000380515200258 ER PT J AU Park, C Meyyappan, M Kim, K Kim, D Hong, N Lee, JS AF Park, ChanOh Meyyappan, Meyya Kim, Kihyun Kim, DongHoon Hong, Nanki Lee, Jeong-Soo GP IEEE TI Effects of Buffer Concentration on Sensing Performances of Ion-Sensitive Field-Effect Transistors wth Si-Nanowires SO 2015 IEEE 15TH INTERNATIONAL CONFERENCE ON NANOTECHNOLOGY (IEEE-NANO) LA English DT Proceedings Paper CT IEEE NANO 2015 15th INTERNATIONAL CONFERENCE ON NANOTECHNOLOGY CY JUL 27-30, 2015 CL ROME, ITALY SP Univ di Roma, SAPIENZA UNIV DI ROMA, IEEE, IEEE NANO, USN DEPT OF THE NAVY SCI & TECHNOL, ISTITUTO ITALIANO DI TECNOLOGIA, CAMBRIDGE UNIV PRESS, Centro Studi e Documentazione sulla Sensoristica, FEI, Nanoscale Horizons, UNIV NOTRE DAME DE Nanosensors; Nanofabrication; Silicon nanoelectronics; buffer concentration; Debye length ID LABEL-FREE DETECTION; CARDIAC TROPONIN-I; BIOSENSORS AB We have experimentally investigated the effect of buffer-dilution on sensing characteristics of the Si-nanowire (SiNW) ion-sensitive field-effect transistors (ISFETs). Phosphate-buffered saline (PBS) with various buffer concentrations was prepared. The result showed that the sensitivity increases as the buffer concentration decreases for bio-molecule detection, while the pH sensitivity of the Si-NW FETs is insensitive to the buffer solutions. The Debye length of the buffer solution can be a crucial factor to detect biomolecules using FET sensors. For the buffer solution with high ionic strength, the Debye length becomes shorter than the distance between the sensing membrane and the target-molecules so that the charges of target-molecules are screened out. For the pH sensing, however, small hydrogen ions can be bound close to the channel surface and thus little dependence on the buffer concentration. C1 [Park, ChanOh] POSTECH, Div IT Convergence Engn, Pohang, South Korea. [Meyyappan, Meyya] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Kim, Kihyun] POSTECH, Dept Creat IT Engn, Pohang, South Korea. [Kim, Kihyun] POSTECH, Future IT Innovat Lab, Pohang, South Korea. [Kim, DongHoon; Hong, Nanki; Lee, Jeong-Soo] POSTECH, Dept Elect Engn, Pohang, South Korea. RP Meyyappan, M (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM m.meyyappan@nasa.gov; ljs6951@postech.ac.kr NR 16 TC 0 Z9 0 U1 1 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-8155-0 PY 2015 BP 1335 EP 1338 PG 4 WC Engineering, Electrical & Electronic; Nanoscience & Nanotechnology SC Engineering; Science & Technology - Other Topics GA BF3AF UT WOS:000380515200261 ER PT S AU Taylor, MGGT Escoubet, CP Laakso, H Masson, A Hapgood, M Dimbylow, T Volpp, J Sangiorgi, S Goldstein, ML AF Taylor, Matthew G. G. T. Escoubet, C. Philippe Laakso, Harri Masson, Arnaud Hapgood, Mike Dimbylow, Trevor Volpp, Juergen Sangiorgi, Silvia Goldstein, Melvyn L. BE Southwood, D Cowley, SWH Mitton, S TI The Science of the Cluster Mission SO MAGNETOSPHERIC PLASMA PHYSICS: THE IMPACT OF JIM DUNGEY'S RESEARCH SE Astrophysics and Space Science Proceedings LA English DT Article; Book Chapter ID MAGNETOTAIL CURRENT SHEET; CURLOMETER TECHNIQUE; CURRENT-DENSITY; SOLAR-WIND; MAGNETOPAUSE; RECONNECTION; SPACECRAFT; MAGNETOSPHERE; OSCILLATIONS; ORIENTATION AB In 1966, in the concluding part of his inaugural lecture at Imperial College London, Jim Dungey discussed the future of magnetospheric physics, in particular indicating that progress in the field required "bunches" of satellites. Indeed, the previous year Dungey had submitted a proposal to the European Space Agency's predecessor ESRO (European Space Research Organisation) proposing the launch of bunches of spacecraft into the magnetosphere. However it was not until 2000, following the successful 1982 proposal led by G. Haerendel, that the first four spacecraft mission, Cluster, was initiated. This paper provides a select few highlights of the Cluster mission related specifically to some objectives presented in the 1960s by Dungey. In addition, we will indicate future prospects for Cluster, in particular coordination of a number of multi-spacecraft missions-Cluster, THEMIS, Van Allen Probes and Swarm, approaching "bunches of bunches" of satellites. C1 [Taylor, Matthew G. G. T.; Escoubet, C. Philippe; Laakso, Harri; Masson, Arnaud] ESA ESTEC, D SRE, Keplerlaan 1, NL-2200 AG Noordwijk, Netherlands. [Hapgood, Mike; Dimbylow, Trevor] RAL Space STFC, Oxford, England. [Volpp, Juergen; Sangiorgi, Silvia] ESA ESOC, Darmstadt, Germany. [Goldstein, Melvyn L.] NASA GSFC, Greenbelt, MD 20771 USA. RP Taylor, MGGT (reprint author), ESA ESTEC, D SRE, Keplerlaan 1, NL-2200 AG Noordwijk, Netherlands. EM mtaylor@esa.int NR 53 TC 0 Z9 0 U1 1 U2 1 PU SPRINGER PI NEW YORK PA 233 SPRING STREET, NEW YORK, NY 10013, UNITED STATES SN 1570-6591 BN 978-3-319-18359-6; 978-3-319-18358-9 J9 ASTROPHYSICS SPACE PY 2015 VL 41 BP 159 EP 179 DI 10.1007/978-3-319-18359-6_8 D2 10.1007/978-3-319-18359-6 PG 21 WC Astronomy & Astrophysics; Geosciences, Multidisciplinary SC Astronomy & Astrophysics; Geology GA BF7FT UT WOS:000384054600009 ER PT J AU Basu, C Koehler, C Das, K Dey, AK AF Basu, Chandrayee Koehler, Christian Das, Kamalika Dey, Anind K. GP ACM TI PerCCS: Person-Count from Carbon dioxide using Sparse Non-negative Matrix Factorization SO PROCEEDINGS OF THE 2015 ACM INTERNATIONAL JOINT CONFERENCE ON PERVASIVE AND UBIQUITOUS COMPUTING (UBICOMP 2015) LA English DT Proceedings Paper CT ACM International Joint Conference on Pervasive and Ubiquitous Computing (UbiComp) CY SEP 07-11, 2015 CL Osaka, JAPAN SP Assoc Comp Machinery, ACM SIGCHI, ACM SIGMOBILE, Panasonic, Bell Labs, Microsoft, Google, Yahoo Japan, KDDI, FXPAL, Rakuten Inst Technol, ISTC PC, NTT DOCOMO, Telefonica Investigac & Desarrollo DE Building energy efficiency; Machine Learning AB Occupancy count in rooms is valuable for applications such as room utilization, opportunistic meeting support, and efficient heating-cooling operations. Few buildings, however, have the means of knowing occupancy beyond simple binary presence-absence. In this paper we present the PerCCS algorithm that explores the possibility of estimating person count from CO2 sensors already integrated in everyday room airconditioning infrastructure. PerCSS uses task-driven Sparse Non-negative Matrix Factorization (SNMF) to learn a nonnegative low-dimensional representation of the CO2 data in the preprocessing stage. This denoised CO2 acts as the predictor variable for estimating occupancy count using Ensemble Least Square Regression. We tested the algorithm to estimate 15 minutes average occupancy count from a classroom of capacity 42 and compared its performance against existing methods from the literature. PerCSS estimates occupancy with a normalized mean squared error (NMSE) of 0.075 and outperformed our comparative methods in predicting occupancy count with 91 % and 15 % for exact occupancy estimation, when the room was unoccupied and occupied respectively, whereas the competing methods failed mostly. C1 [Basu, Chandrayee] Univ Calif Merced, Merced, CA 95340 USA. [Koehler, Christian; Dey, Anind K.] Carnegie Mellon Univ, Pittsburgh, PA 15213 USA. [Das, Kamalika] NASA, Ames Res Ctr, UARC, Moffett Field, CA 94035 USA. RP Basu, C (reprint author), Univ Calif Merced, Merced, CA 95340 USA. EM basu.chandrayee@gmail.com; christiankoehler81@icloud.com; kamalika.das@nasa.gov; anind@cs.cmu.edu NR 33 TC 1 Z9 1 U1 0 U2 0 PU ASSOC COMPUTING MACHINERY PI NEW YORK PA 1515 BROADWAY, NEW YORK, NY 10036-9998 USA BN 978-1-4503-3574-4 PY 2015 BP 987 EP 998 DI 10.1145/2750858.2807525 PG 12 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF6WQ UT WOS:000383742200090 ER PT J AU Frank, J AF Frank, Jeremy BE Lalanda, P Diaconescu, A Cherkasova, L Kounev, S TI Reflecting on Planning Models: A Challenge for Self-Modeling Systems SO 2015 IEEE INTERNATIONAL CONFERENCE ON AUTONOMIC COMPUTING LA English DT Proceedings Paper CT IEEE International Conference on Autonomic Computing CY JUL 07-10, 2015 CL Grenoble, FRANCE SP IEEE, usenix, Univ Joseph Fourier, Telecom ParisTech, Spec, GRENOBLE ALPLES METROPOLE, VILLE CRENOBOLE, MINALOGIC, CPS, IEEE COMPUTER SOC, hp, Google, orange, FOCAS, INRIA INVENTORS DIGITAL WORLD AB We discuss the opportunities for autonomous systems to perform reflection on their planners by adapting the models used to build plans. We first describe model-based planning systems, a form of automated planning system driven by declarative models of the planning domain. These models include descriptions of the conditions and effects of actions on the state of the world. When planning the activities of cyber-physical systems, the command and data representation of the system must be formally abstracted to the actions and states described in the planning system model. When the execution of a plan either fails or produces unexpected outcomes, the execution trace can be abstracted and compared to the predicted state according to the planning model, producing a list of discrepancies; these discrepancies can then be used to fix the model. This provides part of a reflection capability, namely, a set of well-formed problems with the domain model, the abstractions, or both. The challenge lies in the rest of the reflection capability, namely, a set of techniques for changing the models or the abstractions. We discuss these challenges and describe some of the options for addressing them. C1 [Frank, Jeremy] NASA, Ames Res Ctr, Mail Stop N269-3, Moffett Field, CA 94035 USA. RP Frank, J (reprint author), NASA, Ames Res Ctr, Mail Stop N269-3, Moffett Field, CA 94035 USA. NR 12 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-6971-8 PY 2015 BP 255 EP 260 DI 10.1109/ICAC.2015.72 PG 6 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF3RK UT WOS:000380570700048 ER PT S AU Annuar, A Gandhi, P Alexander, D Lansbury, G Harrison, F Stern, D AF Annuar, Adlyka Gandhi, Poshak Alexander, Dave Lansbury, George Harrison, Fiona Stern, Daniel CA NuSTAR Sci Team BE Singh, M Mansor, MF Suparta, W Bahari, SA Shariff, ARM TI Constraining the Population of Compton-Thick AGN and N-H Distribution in the Local Universe SO 2015 INTERNATIONAL CONFERENCE ON SPACE SCIENCE AND COMMUNICATION (ICONSPACE) SE International Conference on Space Science and Communication LA English DT Proceedings Paper CT 4th International Conference on Space Science and Communication (IconSpace) CY AUG 10-12, 2015 CL Langkawi, MALAYSIA SP IEEE Commun Soc, Malaysia Chapter, IEEE, Univ Kebangsaan Malaysia, Univ Kebangsaan Malaysia, ANGKASA, IEEE Vehicular Technol Soc, Malaysia Chapter, IEEE Geoscience & Remote Sensing Soc DE astrophysics; galaxies: active; X-ray astronomy ID SEYFERT 2 GALAXIES AB Compton-thick active galactic nuclei (CTAGN) are defined as AGN that are obscured along our line-of-sight by absorbing gas with a column density of N-H greater than or similar to 10(24) cm(-2). This is what makes it difficult to identify them at X-ray energies E < 10 keV, where the direct emission from the AGN is severely absorbed by the obscuring gas. Because of this, a large fraction of the CTAGN population is believed to be missed by current low X-ray energy observations. In this paper, we present updated results from an ongoing project to form the most unbiased census of CTAGN population in the local universe, using a sample of mid-infrared (mid-IR) selected AGN within D < 15 Mpc. We find that 20% of the AGN in the sample has been confirmed to be CT from current hard X-ray studies (E greater than or similar to 10 keV). More candidates are then selected using multiwavelength techniques, i.e. optical [OIII]lambda 5007: X-ray and mid-IR: X-ray flux ratios. Based on these analyses, we initially find a further 25% of potential candidates. NuSTAR (Nuclear Spectroscopic Telescope Array) recently observed two of these candidates at high X-ray energies and is able to confirm one of them, NGC 5643, as a CTAGN and rule out the other one as an obscured AGN. This constrains the total CTAGN population in the sample to 25-40%, though it could also be as high as 65% accounting for those that we still lack data. Finally, we use these results to estimate the intrinsic N-H distribution of the local AGN population. C1 [Annuar, Adlyka; Gandhi, Poshak; Alexander, Dave; Lansbury, George] Univ Durham, Dept Phys, Ctr Extragalact Astron, South Rd, Durham DH1 3LE, England. [Gandhi, Poshak] Univ Southampton, Fac Phys Sci & Engn, Dept Phys & Astron, Southampton SO17 1BJ, Hants, England. [Harrison, Fiona] CALTECH, Cahill Ctr Astron & Astrophys, Pasadena, CA 91125 USA. [Stern, Daniel] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Annuar, A (reprint author), Univ Durham, Dept Phys, Ctr Extragalact Astron, South Rd, Durham DH1 3LE, England. EM n.a.b.ainul-annuar@durham.ac.uk NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2165-4301 BN 978-1-4799-1940-6 J9 INT CONF SPACE SCI PY 2015 BP 329 EP + PG 3 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BF6CS UT WOS:000382974000067 ER PT S AU Fuyi, T Balarabe, MA Abdullah, K Lim, HS Brent, H AF Fuyi, T. Balarabe, M. A. Abdullah, K. Lim, H. S. Brent, H. BE Singh, M Mansor, MF Suparta, W Bahari, SA Shariff, ARM TI An Analysis of Aerosol Types in Southeast Asia SO 2015 INTERNATIONAL CONFERENCE ON SPACE SCIENCE AND COMMUNICATION (ICONSPACE) SE International Conference on Space Science and Communication LA English DT Proceedings Paper CT 4th International Conference on Space Science and Communication (IconSpace) CY AUG 10-12, 2015 CL Langkawi, MALAYSIA SP IEEE Commun Soc, Malaysia Chapter, IEEE, Univ Kebangsaan Malaysia, Univ Kebangsaan Malaysia, ANGKASA, IEEE Vehicular Technol Soc, Malaysia Chapter, IEEE Geoscience & Remote Sensing Soc DE aerosol optical depth; Angstrom exponent; aerosol type ID TROPICAL COASTAL STATION; OPTICAL DEPTH; MARITIME CONTINENT; TEMPORAL HETEROGENEITY; ANGSTROM EXPONENT; AERONET; TRANSPORT; CLIMATOLOGY; RETRIEVALS; NETWORK AB Aerosol study in Southeast Asia is one of the hottest issues in the globe. Southeast Asia (SEA) region hosts one of the most complex meteorological and environment conditions. Therefore, determining temporal and spatial aerosol distribution pattern in Southeast Asia are essential for better understanding the role of aerosol in the global climate and environmental assessments. The dominant aerosol types distributed in 14 sites over SEA in different seasonal monsoon are determined. The dominant aerosol types are identified by aerosol classification method based on several threshold criteria suggested by different researchers. Seasonal monsoons cause to various dominant aerosol type in SEA regions during a different season. This study can give a better understanding of the aerosol distribution in SEA in term of temporal and spatial. C1 [Fuyi, T.; Balarabe, M. A.; Abdullah, K.; Lim, H. S.] Univ Sains Malaysia, Sch Phys, George Town, Malaysia. [Brent, H.] NASA Goddard Space Flight Ctr, Greenbelt, MD USA. RP Fuyi, T (reprint author), Univ Sains Malaysia, Sch Phys, George Town, Malaysia. EM fuyitan@yahoo.com RI Lim, Hwee San/F-6580-2010 OI Lim, Hwee San/0000-0002-4835-8015 NR 28 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2165-4301 BN 978-1-4799-1940-6 J9 INT CONF SPACE SCI PY 2015 BP 473 EP 478 PG 6 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BF6CS UT WOS:000382974000099 ER PT J AU Lee, C Chattopadhyay, G Decrossas, E Peralta, A Mehdi, I Leal-Sevillano, CA Pino, MA Llombart, N AF Lee, Choonsup Chattopadhyay, Goutam Decrossas, Emmanuel Peralta, Alex Mehdi, Imran Leal-Sevillano, Carlos A. Pino, M. AlonsoDel Llombart, N. GP IEEE TI Terahertz Antenna Arrays with Silicon Micromachined-Based Microlens Antenna and Corrugated Horns SO 2015 INTERNATIONAL WORKSHOP ON ANTENNA TECHNOLOGY (IWAT) LA English DT Proceedings Paper CT International Workshop on Antenna Technology (iWAT) CY MAR 04-06, 2015 CL Seoul, SOUTH KOREA DE antenna; silicon micromachining; THz; array AB We report on two silicon based antennas for future large-format THz focal plane imaging arrays. The silicon-based corrugated horn antenna shows return loss below 15 dB and antenna gain over 20 dB in the 320-360 GHz frequency band. The 1.9 THz silicon microlens antenna has been designed and microfabricated. The simulated 1.9 THz antenna shows good 2-D beam radiation pattern and aperture efficiencies around 85%. It is clear that the silicon-based corrugated horn antenna will work well below 1 THz. However, it would be difficult to fabricate such antennas at frequencies beyond 1 THz due to the requirement of thin silicon wafers which is difficult to handle during the microfabrication. On the other hand, silicon microlens antennas can work in the frequency range of 300 GHz - 2 THz or even higher because of the excellent tolerances achievable with microfabrication techniques. One major advantage of these batch processing techniques is that one can get hundreds of antennas on a single microfabrication run, thus reducing fabrication cost and time. C1 [Lee, Choonsup; Chattopadhyay, Goutam; Decrossas, Emmanuel; Peralta, Alex; Mehdi, Imran] CALTECH, NASA, Jet Prop Lab, Pasadena, CA 91125 USA. [Leal-Sevillano, Carlos A.] Univ Politecn Madrid, Madrid, Spain. [Pino, M. AlonsoDel; Llombart, N.] Delft Univ Technol, Delft, Netherlands. RP Lee, C (reprint author), CALTECH, NASA, Jet Prop Lab, Pasadena, CA 91125 USA. EM Choonsup.Lee@jpl.nasa.gov NR 12 TC 1 Z9 1 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-7717-8 PY 2015 BP 70 EP 73 PG 4 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BF5LH UT WOS:000382198700021 ER PT J AU Chattopadhyay, G AF Chattopadhyay, Goutam GP IEEE TI Terahertz Antennas and Related Optical Components SO 2015 INTERNATIONAL WORKSHOP ON ANTENNA TECHNOLOGY (IWAT) LA English DT Proceedings Paper CT International Workshop on Antenna Technology (iWAT) CY MAR 04-06, 2015 CL Seoul, SOUTH KOREA C1 [Chattopadhyay, Goutam] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Chattopadhyay, G (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-7717-8 PY 2015 BP 75 EP 76 PG 2 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BF5LH UT WOS:000382198700022 ER PT S AU Buchwitz, M Reuter, M Schneising, O Boesch, H Aben, I Alexe, M Armante, R Bergamaschi, P Bovensmann, H Brunner, D Buchmann, B Burrows, JP Butz, A Chevallier, F Chedin, A Crevoisier, CD Gonzi, S De Maziere, M De Wachter, E Detmers, R Dils, B Frankenberg, C Hahne, P Hasekamp, OP Hewson, W Heymann, J Houweling, S Hilker, M Kaminski, T Kuhlmann, G Laeng, A van Leeuwen, TT Lichtenberg, G Marshall, J Noel, S Notholt, J Palmer, P Parker, R Scholze, M Stiller, GP Warneke, T Zehner, C AF Buchwitz, M. Reuter, M. Schneising, O. Boesch, H. Aben, I. Alexe, M. Armante, R. Bergamaschi, P. Bovensmann, H. Brunner, D. Buchmann, B. Burrows, J. P. Butz, A. Chevallier, F. Chedin, A. Crevoisier, C. D. Gonzi, S. De Maziere, M. De Wachter, E. Detmers, R. Dils, B. Frankenberg, C. Hahne, P. Hasekamp, O. P. Hewson, W. Heymann, J. Houweling, S. Hilker, M. Kaminski, T. Kuhlmann, G. Laeng, A. v Leeuwen, T. T. Lichtenberg, G. Marshall, J. Noel, S. Notholt, J. Palmer, P. Parker, R. Scholze, M. Stiller, G. P. Warneke, T. Zehner, C. BE Schreier, G Skrovseth, PE Staudenrausch, H TI THE GREENHOUSE GAS PROJECT OF ESA'S CLIMATE CHANGE INITIATIVE (GHG-CCI): OVERVIEW, ACHIEVEMENTS AND FUTURE PLANS SO 36TH INTERNATIONAL SYMPOSIUM ON REMOTE SENSING OF ENVIRONMENT SE International Archives of the Photogrammetry Remote Sensing and Spatial Information Sciences LA English DT Proceedings Paper CT 36th International Symposium on Remote Sensing of the Environment (ISRSE) CY MAY 11-15, 2015 CL Berlin, GERMANY DE Climate change; carbon cycle; greenhouse gases; emissions; satellites; remote sensing; SCIAMACHY; GOSAT ID COLUMN OBSERVING NETWORK; ATMOSPHERIC CO2; RETRIEVAL ALGORITHM; SURFACE MEASUREMENTS; METHANE EMISSIONS; SOLAR OCCULTATION; CARBON-CYCLE; THIN CLOUDS; IN-SITU; SCIAMACHY AB The GHG-CCI project (http://www.esa-ghg-cci.org/) is one of several projects of the European Space Agency's (ESA) Climate Change Initiative (CCI). The goal of the CCI is to generate and deliver data sets of various satellite-derived Essential Climate Variables (ECVs) in line with GCOS (Global Climate Observing System) requirements. The "ECV Greenhouse Gases" (ECV GHG) is the global distribution of important climate relevant gases - namely atmospheric CO2 and CH4 - with a quality sufficient to obtain information on regional CO2 and CH4 sources and sinks. The main goal of GHG-CCI is to generate long-term highly accurate and precise time series of global near-surface-sensitive satellite observations of CO2 and CH4, i.e., XCO2 and XCH4, starting with the launch of ESA's ENVISAT satellite. These products are currently retrieved from SCIAMACHY/ENVISAT (2002-2012) and TANSO-FTS/GOSAT (2009-today) nadir mode observations in the near-infrared/shortwave-infrared spectral region. In addition, other sensors (e.g., IASI and MIPAS) and viewing modes (e.g., SCIAMACHY solar occultation) are also considered and in the future also data from other satellites. The GHG-CCI data products and related documentation are freely available via the GHG-CCI website and yearly updates are foreseen. Here we present an overview about the latest data set (Climate Research Data Package No. 2 (CRDP#2)) and summarize key findings from using satellite CO2 and CH4 retrievals to improve our understanding of the natural and anthropogenic sources and sinks of these important atmospheric greenhouse gases. We also shortly mention ongoing activities related to validation and initial user assessment of CRDP#2 and future plans. C1 [Buchwitz, M.; Reuter, M.; Schneising, O.; Bovensmann, H.; Burrows, J. P.; Heymann, J.; Hilker, M.; Noel, S.; Notholt, J.; Warneke, T.] Univ Bremen, Inst Environm Phys IUP, Bremen, Germany. [Boesch, H.; Hewson, W.; Parker, R.] Univ Leicester, Leicester, Leics, England. [Aben, I.; Detmers, R.; Hasekamp, O. P.; Houweling, S.; v Leeuwen, T. T.] SRON Netherlands Inst Space Res, Utrecht, Netherlands. [Alexe, M.; Bergamaschi, P.; Hilker, M.] European Commiss, Joint Res Ctr, IES, Air & Climate Unit, Ispra, Italy. [Armante, R.; Chedin, A.; Crevoisier, C. D.] LMD, Palaiseau, France. [Brunner, D.; Buchmann, B.; Kuhlmann, G.] Swiss Fed Labs Mat Sci & Technol Empa, Dubendorf, Switzerland. [Butz, A.; Hahne, P.; Laeng, A.; Stiller, G. P.] KIT, Karlsruhe, Germany. [Chevallier, F.] LSCE, Gif Sur Yvette, France. [Gonzi, S.; Palmer, P.] Univ Edinburgh, Edinburgh, Midlothian, Scotland. [De Maziere, M.; De Wachter, E.; Dils, B.] Belgian Inst Space Aeron BIRA, Brussels, Belgium. [Frankenberg, C.] Jet Prop Lab, Pasadena, CA USA. [Kaminski, T.] Invers Lab, Hamburg, Germany. [Lichtenberg, G.] Deutsch Zentrum Luft & Raumfahrt DLR, Oberpfaffenhofen, Germany. [Marshall, J.] Max Planck Inst Biogeochem MPI BGC, Jena, Germany. [Scholze, M.] Lund Univ, Lund, Sweden. [Zehner, C.] ESRIN, ESA, Frascati, Italy. RP Buchwitz, M (reprint author), Univ Bremen, Inst Environm Phys IUP, Bremen, Germany. EM Michael.Buchwitz@iup.physik.uni-bremen.de; mreuter@iup.physik.uni-bremen.de; schneising@iup.physik.uni-bremen.de; hb100@leicester.ac.uk; E.A.A.Aben@sron.nl; Mihai.Alexe@jrc.ec.europa.eu; Raymond.Armante@lmd.polytechnique.fr; Peter.Bergamaschi@jrc.ec.europa.eu; bovensmann@iup.physik.uni-bremen.de; Dominik.Brunner@empa.ch; Brigitte.Buchmann@empa.ch; burrows@iup.physik.uni-bremen.de; Andre.Butz@kit.edu; Frederic.Chevallier@lsce.ipsl.fr; Chedin@lmd.polytechnique.fr; Cyril.Crevoisier@lmd.polytechnique.fr; sgonzi@ed.ac.uk; Martine.DeMaziere@aeronomie.be; Evelyn.DeWachter@aeronomie.be; R.G.Detmers@sron.nl; Bart.Dils@aeronomie.be; Christian.Frankenberg@jpl.nasa.gov; Philipp.Hahne@kit.edu; O.P.Hasekamp@sron.nl; wh76@leicester.ac.uk; heymann@iup.physik.uni-bremen.de; S.Houweling@sron.nl; mhilker@iup.physik.uni-bremen.de; Thomas.Kaminski@Inversion-Lab.com; Gerrit.Kuhlmann@empa.ch; Alexandra.Laeng@kit.edu; T.T.van.Leeuwen@sron.nl; Guenter.Lichtenberg@dlr.de; marshall@bgc-jena.mpg.de; noel@iup.physik.uni-bremen.de; jnotholt@iup.physik.uni-bremen.de; Paul.Palmer@ed.ac.uk; rjp23@leicester.ac.uk; Marko.Scholze@nateko.lu.se; Gabriele.Stiller@kit.edu; warneke@iup.physik.uni-bremen.de; Claus.Zehner@esa.int RI Bovensmann, Heinrich/P-4135-2016; Brunner, Dominik/A-1255-2009; Boesch, Hartmut/G-6021-2012; Kuhlmann, Gerrit/E-9697-2016; Frankenberg, Christian/A-2944-2013; Notholt, Justus/P-4520-2016; Burrows, John/B-6199-2014; OI Bovensmann, Heinrich/0000-0001-8882-4108; Brunner, Dominik/0000-0002-4007-6902; Kuhlmann, Gerrit/0000-0002-7021-4712; Frankenberg, Christian/0000-0002-0546-5857; Notholt, Justus/0000-0002-3324-885X; Burrows, John/0000-0002-6821-5580; Buchmann, Brigitte/0000-0002-3449-9642; Marshall, Julia/0000-0003-2648-128X NR 82 TC 0 Z9 0 U1 3 U2 3 PU COPERNICUS GESELLSCHAFT MBH PI GOTTINGEN PA BAHNHOFSALLE 1E, GOTTINGEN, 37081, GERMANY SN 2194-9034 J9 INT ARCH PHOTOGRAMM PY 2015 VL 47 IS W3 BP 165 EP 172 DI 10.5194/isprsarchives-XL-7-W3-165-2015 PG 8 WC Environmental Sciences; Geography, Physical; Remote Sensing; Imaging Science & Photographic Technology SC Environmental Sciences & Ecology; Physical Geography; Remote Sensing; Imaging Science & Photographic Technology GA BF3EG UT WOS:000380531900025 ER PT S AU Leckey, J AF Leckey, J. BE Schreier, G Skrovseth, PE Staudenrausch, H TI CLIMATE ABSOLUTE RADIANCE AND REFRACTIVITY OBSERVATORY (CLARREO) SO 36TH INTERNATIONAL SYMPOSIUM ON REMOTE SENSING OF ENVIRONMENT SE International Archives of the Photogrammetry Remote Sensing and Spatial Information Sciences LA English DT Proceedings Paper CT 36th International Symposium on Remote Sensing of Environment CY MAY 11-15, 2015 CL Berlin, GERMANY DE Infrared; Far-Infrared; Radiance; Climate; Atmosphere AB The Climate Absolute Radiance and Refractivity Observatory (CLARREO) is a mission, led and developed by NASA, that will measure a variety of climate variables with an unprecedented accuracy to quantify and attribute climate change. CLARREO consists of three separate instruments: an infrared (IR) spectrometer, a reflected solar (RS) spectrometer, and a radio occultation (RO) instrument. The mission will contain orbiting radiometers with sufficient accuracy, including on orbit verification, to calibrate other space-based instrumentation, increasing their respective accuracy by as much as an order of magnitude. The IR spectrometer is a Fourier Transform spectrometer (FTS) working in the 5 to 50 mu m wavelength region with a goal of 0.1 K (k = 3) accuracy. The FTS will achieve this accuracy using phase change cells to verify thermistor accuracy and heated halos to verify blackbody emissivity, both on orbit. The RS spectrometer will measure the reflectance of the atmosphere in the 0.32 to 2.3 mu m wavelength region with an accuracy of 0.3% (k = 2). The status of the instrumentation packages and potential mission options will be presented. C1 [Leckey, J.] NASA, Langley Res Ctr LARC, Bldg 1202,MS 468, Hampton, VA 23681 USA. RP Leckey, J (reprint author), NASA, Langley Res Ctr LARC, Bldg 1202,MS 468, Hampton, VA 23681 USA. EM john.p.leckey@nasa.gov NR 6 TC 0 Z9 0 U1 4 U2 4 PU COPERNICUS GESELLSCHAFT MBH PI GOTTINGEN PA BAHNHOFSALLE 1E, GOTTINGEN, 37081, GERMANY SN 2194-9034 J9 INT ARCH PHOTOGRAMM PY 2015 VL 47 IS W3 BP 213 EP 217 DI 10.5194/isprsarchives-XL-7-W3-213-2015 PG 5 WC Environmental Sciences; Geography, Physical; Remote Sensing; Imaging Science & Photographic Technology SC Environmental Sciences & Ecology; Physical Geography; Remote Sensing; Imaging Science & Photographic Technology GA BF3EG UT WOS:000380531900032 ER PT S AU Hosford, S Proy, C Giros, A Eddy, A Petiteville, I Ishida, C Gaetani, F Frye, S Zoffoli, S Danzeglocke, J AF Hosford, Steven Proy, Catherine Giros, Alain Eddy, Andrew Petiteville, Ivan Ishida, Chu Gaetani, Francesco Frye, Stuart Zoffoli, Simona Danzeglocke, Jens BE Schreier, G Skrovseth, PE Staudenrausch, H TI THE CEOS RECOVERY OBSERVATORY PILOT SO 36TH INTERNATIONAL SYMPOSIUM ON REMOTE SENSING OF ENVIRONMENT SE International Archives of the Photogrammetry Remote Sensing and Spatial Information Sciences LA English DT Proceedings Paper CT 36th International Symposium on Remote Sensing of Environment CY MAY 11-15, 2015 CL Berlin, GERMANY DE Earth Observation; post-disaster recovery; disaster management cycle AB Over the course of the last decade, large populations living in vulnerable areas have led to record damages and substantial loss of life in mega-disasters ranging from the deadly Indian Ocean tsunami of 2004 and Haiti earthquake of 2010; the catastrophic flood damages of Hurricane Katrina in 2005 and the Tohoku tsunami of 2011, and the astonishing extent of the environmental impact of the Deepwater Horizon explosion in 2009. These major catastrophes have widespread and long-lasting impacts with subsequent recovery and reconstruction costing billions of euros and lasting years. While satellite imagery is used on an ad hoc basis after many disasters to support damage assessment, there is currently no standard practice or system to coordinate acquisition of data and facilitate access for early recovery planning and recovery tracking and monitoring. CEOS led the creation of a Recovery Observatory Oversight Team, which brings together major recovery stakeholders such as the UNDP and the World Bank/Global Facility for Disaster Reduction and Recovery, value-adding providers and leading space agencies. The principal aims of the Observatory are to: 1. Demonstrate the utility of a wide range of earth observation data to facilitate the recovery and reconstruction phase following a major catastrophic event; 2. Provide a concrete case to focus efforts in identifying and resolving technical and organizational obstacles to facilitating the visibility and access to a relevant set of EO data; and 3. Develop dialogue and establish institutional relationships with the Recovery phase user community to best target data and information requirements; The paper presented here will describe the work conducted in preparing for the triggering of a Recovery Observatory including support to rapid assessments and Post Disaster Needs Assessments by the EO community. C1 [Hosford, Steven; Proy, Catherine; Giros, Alain] CNES, 18 Ave Edouard Belin, F-31401 Toulouse, France. [Eddy, Andrew] Athena Global, F-04150 La Frouste, Simiane La Roto, France. [Petiteville, Ivan] ESA, ESRIN, I-00044 Frascati, Italy. [Ishida, Chu] Japan Aerosp Explorat Agcy JAXA, Tsukuba Space Ctr, Tsukuba, Ibaraki 3058505, Japan. [Gaetani, Francesco] Grp Earth Observat GEO Secretariat, CH-1211 Geneva 2, Switzerland. [Frye, Stuart] NASA, Godard Space Flight Ctr, Greenbelt, MD 20771 USA. [Zoffoli, Simona] ASI, I-00133 Rome, Italy. [Danzeglocke, Jens] German Aerosp Ctr DLR, Space Adm, Earth Observat, Bonn, Germany. RP Hosford, S (reprint author), CNES, 18 Ave Edouard Belin, F-31401 Toulouse, France. EM steven.hosford@cnes.fr; catherine.proy@cnes.fr; alain.giros@cnes.fr; andrew.eddy@athenaglobal.com; ivan.petiteville@esa.int; ishida.chu@jaxa.jp; fgaetani@geosec.org; stuart.w.frye@nasa.gov; simona.zoffoli@asi.it; jens.danzeglocke@dlr.de OI Zoffoli, Simona/0000-0003-3573-9051 NR 1 TC 0 Z9 0 U1 0 U2 0 PU COPERNICUS GESELLSCHAFT MBH PI GOTTINGEN PA BAHNHOFSALLE 1E, GOTTINGEN, 37081, GERMANY SN 2194-9034 J9 INT ARCH PHOTOGRAMM PY 2015 VL 47 IS W3 BP 815 EP 818 DI 10.5194/isprsarchives-XL-7-W3-815-2015 PG 4 WC Environmental Sciences; Geography, Physical; Remote Sensing; Imaging Science & Photographic Technology SC Environmental Sciences & Ecology; Physical Geography; Remote Sensing; Imaging Science & Photographic Technology GA BF3EG UT WOS:000380531900121 ER PT S AU Petiteville, I Ishida, C Danzeglocke, J Eddy, A Gaetani, F Frye, S Kuligowski, B Zoffoli, S Poland, M Jones, B AF Petiteville, Ivan Ishida, Chu Danzeglocke, Jens Eddy, Andrew Gaetani, Francesco Frye, Stuart Kuligowski, Bob Zoffoli, Simona Poland, Michael Jones, Brenda BE Schreier, G Skrovseth, PE Staudenrausch, H TI WCDRR AND THE CEOS ACTIVITIES ON DISASTERS SO 36TH INTERNATIONAL SYMPOSIUM ON REMOTE SENSING OF ENVIRONMENT SE International Archives of the Photogrammetry Remote Sensing and Spatial Information Sciences LA English DT Proceedings Paper CT 36th International Symposium on Remote Sensing of Environment CY MAY 11-15, 2015 CL Berlin, GERMANY DE satellite; international cooperation; disaster risk reduction AB Agencies from CEOS (Committee on Earth Observation Satellites) have traditionally focused their efforts on the response phase. Rapid urbanization and increased severity of weather events has led to growing economic and human losses from disasters, requiring international organisations to act now in all disaster risk management (DRM) phases, especially through improved disaster risk reduction policies and programmes. As part of this effort, CEOS agencies have initiated a series of actions aimed at fostering the use of Earth observation (EO) data to support disaster risk reduction and at raising the awareness of policy and decision-makers and major stakeholders of the benefits of using satellite EO in all phases of DRM. CEOS is developing a long-term vision for sustainable application of satellite EO to all phases of DRM. CEOS is collaborating with regional representatives of the DRM user community, on a multi-hazard project involving three thematic pilots (floods, seismic hazards and volcanoes) and a Recovery Observatory that supports resilient recovery from one major disaster. These pilot activities are meant as trail blazers that demonstrate the potential offered by satellite EO for comprehensive DRM. In the framework of the 2015 3rd World Conference on Disaster Risk Reduction (WCDRR), the CEOS space agencies intend to partner with major stakeholders, including UN organizations, the Group on Earth Observations (GEO), international relief agencies, leading development banks, and leading regional DRM organisations, to define and implement a 15-year plan of actions (20152030) that responds to high-level Post-2015 Framework for Disaster Risk Reduction priorities. This plan of action will take into account lessons learned from the CEOS pilot activities. C1 [Petiteville, Ivan] European Space Agcy, ESRIN, Via G Galilei,CP 64, I-00044 Frascati, Italy. [Ishida, Chu] Japan Aerosp Explorat Agcy JAXA, Tsukuba Space Ctr, Tsukuba, Ibaraki 3058505, Japan. [Danzeglocke, Jens] German Aerosp Ctr DLR, Space Adm, Earth Observat, Bonn, Germany. [Danzeglocke, Jens] Athena Global, F-04150 La Frouste, Simiane La Roto, France. [Gaetani, Francesco] Grp Earth Observat GEO Secretariat, CH-1211 Geneva 2, Switzerland. [Frye, Stuart] NASA, NASA Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Kuligowski, Bob] NOAA, NCWCP E RA2, College Pk, MD 20740 USA. [Zoffoli, Simona] Agenzia Spaziale Italiana, Osservaz Terra, I-00133 Rome, Italy. [Poland, Michael] USGS, Hawaiian Volcano Observ, Hawaii Natl Pk, HI 96718 USA. [Jones, Brenda] USGS, USGS EROS Ctr, Sioux Falls, SD 57198 USA. RP Petiteville, I (reprint author), European Space Agcy, ESRIN, Via G Galilei,CP 64, I-00044 Frascati, Italy. EM Ivan.Petiteville@esa.int; ishida.chu@jaxa.jp; jens.danzeglocke@dlr.de; andrew.eddy@athenaglobal.com; fgaetani@geosec.org; stuart.frye@nasa.gov; Bob.Kuligowski@noaa.gov; simona.zoffoli@asi.it; mpoland@usgs.gov; bkjones@usgs.gov RI Kuligowski, Robert/C-6981-2009; OI Kuligowski, Robert/0000-0002-6909-2252; Zoffoli, Simona/0000-0003-3573-9051; Poland, Michael/0000-0001-5240-6123 NR 2 TC 0 Z9 0 U1 1 U2 1 PU COPERNICUS GESELLSCHAFT MBH PI GOTTINGEN PA BAHNHOFSALLE 1E, GOTTINGEN, 37081, GERMANY SN 2194-9034 J9 INT ARCH PHOTOGRAMM PY 2015 VL 47 IS W3 BP 845 EP 850 DI 10.5194/isprsarchives-XL-7-W3-845-2015 PG 6 WC Environmental Sciences; Geography, Physical; Remote Sensing; Imaging Science & Photographic Technology SC Environmental Sciences & Ecology; Physical Geography; Remote Sensing; Imaging Science & Photographic Technology GA BF3EG UT WOS:000380531900126 ER PT S AU Stefanov, WL Evans, CA AF Stefanov, W. L. Evans, C. A. BE Schreier, G Skrovseth, PE Staudenrausch, H TI DATA COLLECTION FOR DISASTER RESPONSE FROM THE INTERNATIONAL SPACE STATION SO 36TH INTERNATIONAL SYMPOSIUM ON REMOTE SENSING OF ENVIRONMENT SE International Archives of the Photogrammetry Remote Sensing and Spatial Information Sciences LA English DT Proceedings Paper CT 36th International Symposium on Remote Sensing of the Environment (ISRSE) CY MAY 11-15, 2015 CL Berlin, GERMANY DE Space Station; Hyperspectral; Imager; Astronaut; Hazards; International Charter AB Remotely sensed data acquired by orbital sensor systems has emerged as a vital tool to identify the extent of damage resulting from a natural disaster, as well as providing near-real time mapping support to response efforts on the ground and humanitarian aid efforts. The International Space Station (ISS) is a unique terrestrial remote sensing platform for acquiring disaster response imagery. Unlike automated remote-sensing platforms it has a human crew; is equipped with both internal and externally-mounted remote sensing instruments; and has an inclined, low-Earth orbit that provides variable views and lighting (day and night) over 90 percent of the inhabited surface of the Earth. As such, it provides a useful complement to autonomous sensor systems in higher altitude polar orbits. NASA remote sensing assets on the station began collecting International Charter, Space and Major Disasters, also known informally as the International Disaster Charter (IDC) response data in May 2012. Since the start of IDC response in 2012, and as of late March 2015, there have been 123 IDC activations; NASA sensor systems have collected data for thirty-four of these events. Of the successful data collections, eight involved two or more ISS sensor systems responding to the same event. Data has also been collected by International Partners in response to natural disasters, most notably JAXA and Roscosmos/Energia through the Urugan program. C1 [Stefanov, W. L.] NASA Johnson Space Ctr, Int Space Stn Program, Sci Off, Houston, TX 77058 USA. [Stefanov, W. L.; Evans, C. A.] NASA Johnson Space Ctr, Astromat Res & Explorat Sci Div, Explorat Integrat & Sci Directorate, Houston, TX 77058 USA. RP Stefanov, WL (reprint author), NASA Johnson Space Ctr, Int Space Stn Program, Sci Off, Houston, TX 77058 USA. EM william.l.stefanov@nasa.gov; cindy.evans-1@nasa.gov NR 5 TC 0 Z9 0 U1 3 U2 3 PU COPERNICUS GESELLSCHAFT MBH PI GOTTINGEN PA BAHNHOFSALLE 1E, GOTTINGEN, 37081, GERMANY SN 2194-9034 J9 INT ARCH PHOTOGRAMM PY 2015 VL 47 IS W3 BP 851 EP 855 DI 10.5194/isprsarchives-XL-7-W3-851-2015 PG 5 WC Environmental Sciences; Geography, Physical; Remote Sensing; Imaging Science & Photographic Technology SC Environmental Sciences & Ecology; Physical Geography; Remote Sensing; Imaging Science & Photographic Technology GA BF3EG UT WOS:000380531900127 ER PT S AU Albertson, R Schoenung, S Fladeland, M Cutler, F Tagg, B AF Albertson, Randal Schoenung, Susan Fladeland, Matt Cutler, Frank Tagg, Bruce BE Schreier, G Skrovseth, PE Staudenrausch, H TI ENABLING EARTH SCIENCE MEASUREMENTS WITH NASA UAS CAPABILITIES SO 36TH INTERNATIONAL SYMPOSIUM ON REMOTE SENSING OF ENVIRONMENT SE International Archives of the Photogrammetry Remote Sensing and Spatial Information Sciences LA English DT Proceedings Paper CT 36th International Symposium on Remote Sensing of Environment CY MAY 11-15, 2015 CL Berlin, GERMANY DE NASA; UAS; UAV; airborne; aircraft; Earth Science AB NASA's Airborne Science Program (ASP) maintains a fleet of manned and unmanned aircraft for Earth Science measurements and observations. The unmanned aircraft systems (UAS) range in size from very large (Global Hawks) to medium (SIERRA, Viking) and relatively small (DragonEye). UAS fly from very low (boundary layer) to very high altitude (stratosphere). NASA also supports science and applied science projects using UAS operated by outside companies or agencies. The aircraft and accompanying data and support systems have been used in numerous investigations. For example, Global Hawks have been used to study both hurricanes and atmospheric composition. SIERRA has been used to study ice, earthquake faults, and coral reefs. DragonEye is being used to measure volcanic emissions. As a foundation for NASA's UAS work, Altair and Ikhana not only flew wildfires in the US, but also provided major programs for the development of real-time data download and processing capabilities. In 2014, an advanced L-band Synthetic Aperture Radar flew for the first time on Global Hawk, demonstrating UAVSAR, which has been flying successfully on a manned aircraft. This paper focuses on two topics: 1) results of a NASA program called UAS-Enabled Earth Science, in which three science teams flew UAS to demonstrate platform and sensor performance, airspace integration, and applied science results from the data collected; 2) recent accomplishments with the high altitude, long-duration Global Hawks. The challenges experienced with flying UAS are discussed. Recent upgrades to data processing, communications, tracking and flight planning systems are described. C1 [Albertson, Randal; Cutler, Frank] NASA, Armstrong Flight Res Ctr, Edwards AFB, CA 93523 USA. [Schoenung, Susan] Longitude 122 West Inc, 885 Oak Grove Ave, Menlo Pk, CA 94025 USA. [Fladeland, Matt] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Tagg, Bruce] NASA, Airborne Sci Program, Washington, DC 20546 USA. RP Schoenung, S (reprint author), Longitude 122 West Inc, 885 Oak Grove Ave, Menlo Pk, CA 94025 USA. EM randal.t.albertson@nasa.gov; susan.schoenung@gmail.com; matthew.m.fladeland@nasa.gov; frank.w.cutler@nasa.gov; bruce.a.tagg@nasa.gov NR 11 TC 0 Z9 0 U1 1 U2 1 PU COPERNICUS GESELLSCHAFT MBH PI GOTTINGEN PA BAHNHOFSALLE 1E, GOTTINGEN, 37081, GERMANY SN 2194-9034 J9 INT ARCH PHOTOGRAMM PY 2015 VL 47 IS W3 BP 1111 EP 1117 DI 10.5194/isprsarchives-XL-7-W3-1111-2015 PG 7 WC Environmental Sciences; Geography, Physical; Remote Sensing; Imaging Science & Photographic Technology SC Environmental Sciences & Ecology; Physical Geography; Remote Sensing; Imaging Science & Photographic Technology GA BF3EG UT WOS:000380531900165 ER PT S AU Dunagan, S Fladeland, M Ippolito, C Knudson, M Young, Z AF Dunagan, S. Fladeland, M. Ippolito, C. Knudson, M. Young, Z. BE Schreier, G Skrovseth, PE Staudenrausch, H TI MISSION ADAPTIVE UAS CAPABILITIES FOR EARTH SCIENCE AND RESOURCE ASSESSMENT SO 36TH INTERNATIONAL SYMPOSIUM ON REMOTE SENSING OF ENVIRONMENT SE International Archives of the Photogrammetry Remote Sensing and Spatial Information Sciences LA English DT Proceedings Paper CT 36th International Symposium on Remote Sensing of Environment CY MAY 11-15, 2015 CL Berlin, GERMANY DE remote sensing; UAS; autopilot; flight control; sensors; hyperspectral; radiometry; magnetometry AB Unmanned aircraft systems (UAS) are important assets for accessing high risk airspace and incorporate technologies for sensor coordination, onboard processing, tele-communication, unconventional flight control, and ground based monitoring and optimization. These capabilities permit adaptive mission management in the face of complex requirements and chaotic external influences. NASA Ames Research Center has led a number of Earth science remote sensing missions directed at the assessment of natural resources and here we describe two resource mapping problems having mission characteristics requiring a mission adaptive capability extensible to other resource assessment challenges. One example involves the requirement for careful control over solar angle geometry for passive reflectance measurements. This constraint exists when collecting imaging spectroscopy data over vegetation for time series analysis or for the coastal ocean where solar angle combines with sea state to produce surface glint that can obscure the signal. Furthermore, the primary flight control imperative to minimize tracking error should compromise with the requirement to minimize aircraft motion artifacts in the spatial measurement distribution. A second example involves mapping of natural resources in the Earth's crust using precision magnetometry. In this case the vehicle flight path must be oriented to optimize magnetic flux gradients over a spatial domain having continually emerging features, while optimizing the efficiency of the spatial mapping task. These requirements were highlighted in recent Earth Science missions including the OCEANIA mission directed at improving the capability for spectral and radiometric reflectance measurements in the coastal ocean, and the Surprise Valley Mission directed at mapping sub-surface mineral composition and faults, using high-sensitivity magnetometry. This paper reports the development of specific aircraft control approaches to incorporate the unusual and demanding requirements to manage solar angle, aircraft attitude and flight path orientation, and efficient (directly geo-rectified) surface and sub-surface mapping, including the near-time optimization of these sometimes competing requirements. C1 [Dunagan, S.; Fladeland, M.; Ippolito, C.; Knudson, M.; Young, Z.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Dunagan, S (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM stephen.e.dunagan@nasa.gov; matthew.m.fladeland@nasa.gov; corey.a.ippolito@nasa.gov; matt.knudson@nasa.gov; zion.w.young@nasa.gov NR 18 TC 0 Z9 0 U1 1 U2 1 PU COPERNICUS GESELLSCHAFT MBH PI GOTTINGEN PA BAHNHOFSALLE 1E, GOTTINGEN, 37081, GERMANY SN 2194-9034 J9 INT ARCH PHOTOGRAMM PY 2015 VL 47 IS W3 BP 1163 EP 1170 DI 10.5194/isprsarchives-XL-7-W3-1163-2015 PG 8 WC Environmental Sciences; Geography, Physical; Remote Sensing; Imaging Science & Photographic Technology SC Environmental Sciences & Ecology; Physical Geography; Remote Sensing; Imaging Science & Photographic Technology GA BF3EG UT WOS:000380531900173 ER PT S AU Srinivasan, M Andral, A Dejus, M Hossain, F Peterson, C Beighley, E Pavelsky, T Chao, Y Doorn, B Bronner, E Houpert, L AF Srinivasan, M. Andral, A. Dejus, M. Hossain, F. Peterson, C. Beighley, E. Pavelsky, T. Chao, Y. Doorn, B. Bronner, E. Houpert, L. BE Schreier, G Skrovseth, PE Staudenrausch, H TI ENGAGING THE APPLICATIONS COMMUNITY OF THE FUTURE SURFACE WATER AND OCEAN TOPOGRAPHY (SWOT) MISSION SO 36TH INTERNATIONAL SYMPOSIUM ON REMOTE SENSING OF ENVIRONMENT SE International Archives of the Photogrammetry Remote Sensing and Spatial Information Sciences LA English DT Proceedings Paper CT 36th International Symposium on Remote Sensing of Environment CY MAY 11-15, 2015 CL Berlin, GERMANY DE Applications; Hydrology; Oceanography; Operational; SWOT AB NASA and the French space agency, CNES, with contributions from the Canadian Space Agency ( CSA) and United Kingdom Space Agency ( UKSA) are developing new wide swath altimetry technology that will cover most of the world's ocean and surface freshwater bodies. The proposed Surface Water and Ocean Topography ( SWOT) mission will have the capability to make observations of surface water ( lakes, rivers, wetland) heights and measurements of ocean surface topography with unprecedented spatial coverage, temporal sampling, and spatial resolution compared to existing technologies. These data will be useful for monitoring the hydrologic cycle, flooding, and characterizing human impacts on a changing environment. The applied science community is a key element in the success of the SWOT mission, demonstrating the high value of the science and data products in addressing societal issues and needs. The SWOT applications framework includes a working group made up of applications specialists, SWOT science team members, academics and SWOT Project members to promote applications research and engage a broad community of potential SWOT data users. A defined plan and a guide describing a program to engage early adopters in using proxies for SWOT data, including sophisticated ocean and hydrology simulators, an airborne analogue for SWOT ( AirSWOT), and existing satellite datasets, are cornerstones for the program. A user survey is in development and the first user workshop was held in 2015, with annual workshops planned. The anticipated science and engineering advances that SWOT will provide can be transformed into valuable services to decision makers and civic organizations focused on addressing global disaster risk reduction initiatives and potential science-based mitigation activities for water resources challenges of the future. With the surface water measurements anticipated from SWOT, a broad range of applications can inform inland and coastal managers and marine operators of terrestrial and oceanic phenomena relevant to their work. C1 [Srinivasan, M.] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. [Andral, A.; Dejus, M.; Bronner, E.; Houpert, L.] CNES, Toulouse, France. [Hossain, F.] Univ Washington, Seattle, WA 98195 USA. [Peterson, C.] MSU Sci & Technol Ctr, Stennis Space Ctr, MS USA. [Beighley, E.] Northeastern Univ, Boston, MA 02115 USA. [Pavelsky, T.] Univ N Carolina, Chapel Hill, NC USA. [Chao, Y.] Remote Sensing Solut, Pasadena, CA USA. [Doorn, B.] NASA, Washington, DC 20546 USA. RP Srinivasan, M (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. EM margaret.srinivasan@jpl.nasa.gov; alice.andral@cnes.fr; michel.dejus@cnes.fr; fhossain@uw.edu; craigp@gri.msstate.edu; r.beighley@neu.edu; pavelsky@unc.edu; ychao001@gmail.com; bradley.doorn@nasa.gov; emilie.bronner@cnes.fr; laurence.houpert@cnes.fr NR 15 TC 0 Z9 0 U1 2 U2 2 PU COPERNICUS GESELLSCHAFT MBH PI GOTTINGEN PA BAHNHOFSALLE 1E, GOTTINGEN, 37081, GERMANY SN 2194-9034 J9 INT ARCH PHOTOGRAMM PY 2015 VL 47 IS W3 BP 1497 EP 1504 DI 10.5194/isprsarchives-XL-7-W3-1497-2015 PG 8 WC Environmental Sciences; Geography, Physical; Remote Sensing; Imaging Science & Photographic Technology SC Environmental Sciences & Ecology; Physical Geography; Remote Sensing; Imaging Science & Photographic Technology GA BF3EG UT WOS:000380531900221 ER PT S AU Basu, S DiBiano, R Karki, M Stagg, M Weltman, J Mukhopadhyay, S Ganguly, S AF Basu, Saikat DiBiano, Robert Karki, Manohar Stagg, Malcolm Weltman, Jerry Mukhopadhyay, Supratik Ganguly, Sangram BE Ahamed, SI Chang, CK Chu, W Crnkovic, I Hsiung, PA Huang, G Yang, J TI An Agile Framework for Real-Time Motion Tracking SO IEEE 39TH ANNUAL COMPUTER SOFTWARE AND APPLICATIONS CONFERENCE WORKSHOPS (COMPSAC 2015), VOL 3 SE Proceedings International Computer Software and Applications Conference LA English DT Proceedings Paper CT 39th IEEE Annual International Computer Software and Applications Conference Workshops (COMPSAC) CY JUL 01-05, 2015 CL Taichung, TAIWAN SP IEEE, IEEE Comp Soc, IEEE Big Data, IEEE Cloud Comp, IPS, Korean Inst Informat Scientists & Engineers, CCF, Natl Cent Univ, Natl Chung cheng Univ, Natl Chung Hsing Univ, Feng Chia Univ, Natl Ilan Univ, Iowa State Univ Sci & Technol, Marquette Univ, Natl Tsing hua univ, Natl Taichung Univ Sci & Technol, Tunghai Univ, Minist Ssci & Technol, Minist Econ Affairs, R O C, Minist Educ, Unison Healthcare Grp, Inventec, Academia Sinica, Natl Appl Res Labs DE Full Motion Video; object tracking; Confidence-based spatio-temporal filtering; Agile tracking; Ensemble algorithm AB We present an agile framework for automated tracking of moving objects in full motion video (FMV). The framework is robust, being able to track multiple foreground objects of different types (e.g., person, vehicle) having disparate motion characteristics (like speed, uniformity) simultaneously in real time under changing lighting conditions, background, and disparate dynamics of the camera. It is able to start tracks automatically based on a confidence-based spatio-temporal filtering algorithm and is able to follow objects through occlusions. Unlike existing tracking algorithms, with high likelihood, it does not lose or switch tracks while following multiple similar closely-spaced objects. The framework is based on an ensemble of tracking algorithms that are switched automatically for optimal performance based on a performance measure without losing state. Only one of the algorithms, that has the best performance in a particular state is active at any time providing computational advantages over existing ensemble frameworks like boosting. A C++ implementation of the framework has outperformed existing visual tracking algorithms on most videos in the Video Image Retrieval and Analysis Tool (VIRAT: www.viratdata.org) and the Tracking-Learning-Detection data-sets. C1 [Basu, Saikat; DiBiano, Robert; Karki, Manohar; Stagg, Malcolm; Weltman, Jerry; Mukhopadhyay, Supratik] Sch Elect Engn & Comp Sci, Baton Rouge, LA 70803 USA. [Ganguly, Sangram] NASA, Ames Res Ctr, Bay Area Environm Res Inst, Moffett Field, CA 94035 USA. RP Basu, S (reprint author), Sch Elect Engn & Comp Sci, Baton Rouge, LA 70803 USA. EM sbasu8@lsu.edu NR 18 TC 2 Z9 2 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0730-3157 BN 978-1-4673-6563-5 J9 P INT COMP SOFTW APP PY 2015 BP 205 EP 210 DI 10.1109/COMPSAC.2015.231 PG 6 WC Computer Science, Software Engineering; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF4RB UT WOS:000381598900036 ER PT S AU Pool, DM Zaal, PMT AF Pool, Daan M. Zaal, Peter M. T. GP IEEE TI Between-Subject Variability in Transfer-of-Training of Skill-Based Manual Control Behavior SO 2015 IEEE INTERNATIONAL CONFERENCE ON SYSTEMS, MAN, AND CYBERNETICS (SMC 2015): BIG DATA ANALYTICS FOR HUMAN-CENTRIC SYSTEMS SE IEEE International Conference on Systems Man and Cybernetics Conference Proceedings LA English DT Proceedings Paper CT IEEE International Conference on Systems, Man, and Cybernetics (SMC) CY OCT 09-12, 2015 CL City Univ Hong Kong, Hong Kong, PEOPLES R CHINA SP IEEE, IEEE Comp Soc, IEEE Syst Man & Cybernet Soc, Hong Kong Polytechn Univ, K C Wong Fdn HO City Univ Hong Kong ID MOTION CUES; FLIGHT; PITCH; TASK AB This paper describes a new approach for analyzing training effectiveness in transfer-of-training experiments, by considering the between-subject variability of post-transfer changes in task performance and control activity of individual trained pilots. First, exponential learning curve models were fit on experimental data of individual pilots. Second, curve parameters were used to analyze the immediate changes in task performance and control gain following transfer, and the correlation between immediate changes in task performance and continued learning rate after transfer. Data from two experiments with different experimental designs were compared using the new approach. The method revealed similar post-transfer effects in the immediate changes in task performance and control gain following transfer between the two experiments when pilots trained without motion. However, differences in post-transfer effects were found when comparing the correlations between the immediate change in task performance and learning rate. In addition, differences were found between participant groups training with different levels of flight simulator motion fidelity. C1 [Pool, Daan M.] Delft Univ Technol, Delft, Netherlands. [Zaal, Peter M. T.] San Jose State Univ, NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Pool, DM (reprint author), Delft Univ Technol, Delft, Netherlands. EM d.m.pool@tudelft.nl; peter.m.t.zaal@nasa.gov NR 12 TC 0 Z9 0 U1 0 U2 0 PU IEEE COMPUTER SOC PI LOS ALAMITOS PA 10662 LOS VAQUEROS CIRCLE, PO BOX 3014, LOS ALAMITOS, CA 90720-1264 USA SN 1062-922X BN 978-1-4799-8696-5 J9 IEEE SYS MAN CYBERN PY 2015 BP 1094 EP 1099 DI 10.1109/SMC.2015.196 PG 6 WC Computer Science, Cybernetics; Computer Science, Information Systems; Computer Science, Theory & Methods SC Computer Science GA BE2BU UT WOS:000368940201028 ER PT J AU Borges, M Filieri, A d'Amorim, M Pasareanu, CS AF Borges, Mateus Filieri, Antonio d'Amorim, Marcelo Pasareanu, Corina S. BE DiNitto, E Harman, M Heymans, P TI Iterative Distribution-Aware Sampling for Probabilistic Symbolic Execution SO 2015 10TH JOINT MEETING OF THE EUROPEAN SOFTWARE ENGINEERING CONFERENCE AND THE ACM SIGSOFT SYMPOSIUM ON THE FOUNDATIONS OF SOFTWARE ENGINEERING (ESEC/FSE 2015) PROCEEDINGS LA English DT Proceedings Paper CT 10th Joint Meeting of the European Software Engineering Conference (ESEC) / ACM SIGSOFT Symposium on the Foundations of Software Engineering (FSE) CY AUG 30-SEP 04, 2015 CL Bergamo, ITALY SP ACM SIGSOFT, ABB, Microsoft Res, Fujitsu, CEFRIEL, Google, BTO, ITA STQB & Engn DE Symbolic Execution; Monte Carlo Sampling; Probabilistic Analysis AB Probabilistic symbolic execution aims at quantifying the probability of reaching program events of interest assuming that program inputs follow given probabilistic distributions. The technique collects constraints on the inputs that lead to the target events and analyzes them to quantify how likely it is for an input to satisfy the constraints. Current techniques either handle only linear constraints or only support continuous distributions using a "discretization" of the input domain, leading to imprecise and costly results. We propose an iterative distribution-aware sampling approach to support probabilistic symbolic execution for arbitrarily complex mathematical constraints and continuous input distributions. We follow a compositional approach, where the symbolic constraints are decomposed into sub-problems whose solution can be solved independently. At each iteration the convergence rate of the computation is increased by automatically refocusing the analysis on estimating the sub-problems that mostly affect the accuracy of the results, as guided by three different ranking strategies. Experiments on publicly available benchmarks show that the proposed technique improves on previous approaches in terms of scalability and accuracy of the results. C1 [Borges, Mateus; Filieri, Antonio] Univ Stuttgart, Stuttgart, Germany. [Borges, Mateus; d'Amorim, Marcelo] Univ Fed Pernambuco, Recife, PE, Brazil. [Pasareanu, Corina S.] CMU SV, NASA, Ames Res Ctr, Moffett Field, CA USA. RP Borges, M (reprint author), Univ Stuttgart, Stuttgart, Germany. NR 28 TC 0 Z9 0 U1 0 U2 0 PU ASSOC COMPUTING MACHINERY PI NEW YORK PA 1515 BROADWAY, NEW YORK, NY 10036-9998 USA BN 978-1-4503-3675-8 PY 2015 BP 866 EP 877 DI 10.1145/2786805.2786832 PG 12 WC Computer Science, Software Engineering; Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF5SI UT WOS:000382568700074 ER PT J AU Akay, IG Kaymaz, Z Sibeck, DG Angelopoulos, V AF Akay, Iklim Gencturk Kaymaz, Zerefsan Sibeck, David G. Angelopoulos, Vassilis BE Hacioglu, A Ince, F Kaynak, O Unal, MF Basturk, S TI Investigating Magnetic Field Structure at Moon Distance: A Single Pass Example SO 2015 7TH INTERNATIONAL CONFERENCE ON RECENT ADVANCES IN SPACE TECHNOLOGIES (RAST) LA English DT Proceedings Paper CT 7th International Conference on Recent Advances in Space Technologies (RAST) CY JUN 16-19, 2015 CL Istanbul, TURKEY SP IEEE, AIAA, URSI, AESS, GRSS, EARSeL, ISPRS, Turkish Air Force Acad, Istanbul Tech Univ, Bogazici Univ, Middle E Tech Univ, Yildiz Tech Univ, Roketsan, Havelsan, Turksat, Aselsan, TAI, Tusas Engine Ind Inc, Petlas, ALP Havacilik, Mitsubishi Elect, Space & Defence Technologies, ThalesAlenia Space, Savunma Havacilik, MSI DE magnetotail; ARTEMIS; magnetic field mapping; topology; MHD models ID MAGNETOTAIL AB Since 2011, ARTEMIS spacecraft 1 and 2 take observations in the solar wind and magnetotail as they orbit around the Moon at +/-60 Re. With the state-of-the-art magnetic field and plasma instruments, they perform the first systematic, two-point observations of the mid-to-distant tail and give an opportunity for the scientist to study the detailed structure of the mid-to-distant tail at -60 Re as well as the tail dynamics since the era of ISEE-3 and Wind in 1970s and mid-1990s. In this study, we use magnetic field observations to perform vector mappings of the magnetotail structure in xy-, xz, and yz- planes. We present our preliminary results based on the investigation of four trajectory passes. The one of the example pass we present here corresponds to the IMF orientation in -y direction. Even it is a single pass, we can see the IMF By effect on the orientation of the magnetic field vectors within the magnetotail. Mapping along the trajectory also shows several unexpected tail magnetic field orientations within the central magnetotail which we attribute to the fact that it is a single pass and thus it may reflect the singular, local short term variations occurred in the central tail as the spacecraft moves. We run MHD model, SWMF-BATSRUS, at CCMC for this single pass to see how much temporally the model and observations agree. The results will be discussed in the frame of understanding the magnetotail behavior in response to the IMF By on a temporal scale. C1 [Akay, Iklim Gencturk; Kaymaz, Zerefsan] Istanbul Tech Univ, Fac Aeronaut & Astronaut, Istanbul, Turkey. [Sibeck, David G.] NASA, Space Weather Lab, GSFC, Greenbelt, MD USA. [Angelopoulos, Vassilis] UCLA, Dept Earth Planetary & Space Sci, Los Angeles, CA USA. RP Akay, IG (reprint author), Istanbul Tech Univ, Fac Aeronaut & Astronaut, Istanbul, Turkey. EM gencturk@itu.edu.tr; zerefsan@itu.edu.tr; david.g.sibeck@nasa.gov; vassilis@ucla.edu NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-7697-3 PY 2015 BP 505 EP 508 PG 4 WC Engineering, Aerospace; Engineering, Electrical & Electronic SC Engineering GA BF4RN UT WOS:000381627000083 ER PT J AU Wie, B Barbee, B AF Wie, Bong Barbee, Brent BE Hacioglu, A Ince, F Kaynak, O Unal, MF Basturk, S TI An Optimal Mitigation Strategy Against the Asteroid Impact Threat with Short Warning Time SO 2015 7TH INTERNATIONAL CONFERENCE ON RECENT ADVANCES IN SPACE TECHNOLOGIES (RAST) LA English DT Proceedings Paper CT 7th International Conference on Recent Advances in Space Technologies (RAST) CY JUN 16-19, 2015 CL Istanbul, TURKEY SP IEEE, AIAA, URSI, AESS, GRSS, EARSeL, ISPRS, Turkish Air Force Acad, Istanbul Tech Univ, Bogazici Univ, Middle E Tech Univ, Yildiz Tech Univ, Roketsan, Havelsan, Turksat, Aselsan, TAI, Tusas Engine Ind Inc, Petlas, ALP Havacilik, Mitsubishi Elect, Space & Defence Technologies, ThalesAlenia Space, Savunma Havacilik, MSI DE NEO impact threat mitigation; planetary defense; nuclear subsurface explosions; hypervelocity asteroid intercept vehicle (HAIV) ID FLIGHT VALIDATION MISSION; INTERCEPT VEHICLE; CONCEPTUAL DESIGN; SPACECRAFT; TRACTOR AB This paper presents the results of a NASA Innovative Advanced Concept (NIAC) Phase 2 study entitled "An Innovative Solution to NASA's Near-Earth Object (NEO) Impact Threat Mitigation Grand Challenge and Flight Validation Mission Architecture Development." This NIAC Phase 2 study was conducted at the Asteroid Deflection Research Center (ADRC) of Iowa State University in 2012-2014. The study objective was to develop an innovative yet practically implementable mitigation strategy for the most probable impact threat of an asteroid or comet with short warning time (<5 years). The mitigation strategy described in this paper is intended to optimally reduce the severity and catastrophic damage of the NEO impact event, especially when we don't have sufficient warning times for non-disruptive deflection of a hazardous NEO. This paper provides an executive summary of the NIAC Phase 2 study results. C1 [Wie, Bong] Iowa State Univ, Asteroid Deflect Res Ctr, Ames, IA 50011 USA. [Barbee, Brent] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Wie, B (reprint author), Iowa State Univ, Asteroid Deflect Res Ctr, Ames, IA 50011 USA. EM bongwie@iastate.edu; brent.w.barbee@nasa.gov NR 27 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-7697-3 PY 2015 BP 539 EP 544 PG 6 WC Engineering, Aerospace; Engineering, Electrical & Electronic SC Engineering GA BF4RN UT WOS:000381627000089 ER PT S AU Filieri, A Pasareanu, CS Yang, GW AF Filieri, Antonio Pasareanu, Corina S. Yang, Guowei BA Cohen, M Grunske, L Whalen, M BF Cohen, M Grunske, L Whalen, M TI Quantification of Software Changes through Probabilistic Symbolic Execution SO 2015 30TH IEEE/ACM INTERNATIONAL CONFERENCE ON AUTOMATED SOFTWARE ENGINEERING (ASE) SE IEEE ACM International Conference on Automated Software Engineering LA English DT Proceedings Paper CT 30th IEEE/ACM International Conference on Automated Software Engineering Workshops (ASEW) CY NOV 09-13, 2015 CL Lincoln, NE SP IEEE, IEEE Comp Soc, ACM, ACM Special Interest Grp Software Engn, IEEE Comp Soc Tech Council Software Engn, ACM SIGAI AB Characterizing software changes is fundamental for software maintenance. However existing techniques are imprecise leading to unnecessary maintenance efforts. We introduce a novel approach that computes a precise numeric characterization of program changes, which quantifies the likelihood of reaching target program events (e.g., assert violations or successful termination) and how that evolves with each program update, together with the percentage of inputs impacted by the change. This precise characterization leads to a natural ranking of different program changes based on their probability of execution and their impact on target events. The approach is based on model counting over the constraints collected with a symbolic execution of the program, and exploits the similarity between program versions to reduce cost and improve the quality of analysis results. We implemented our approach in the Symbolic PathFinder tool and illustrate it on several Java case studies, including the evaluation of different program repairs, mutants used in testing, or incremental analysis after a change. C1 [Filieri, Antonio] Univ Stuttgart, Stuttgart, Germany. [Pasareanu, Corina S.] NASA Ames, Carnegie Mellon Silicon Valley, Moffett Field, CA USA. [Yang, Guowei] Texas State Univ, San Marcos, TX USA. RP Filieri, A (reprint author), Univ Stuttgart, Stuttgart, Germany. EM filieri@informatik.uni-stuttgart.de; corina.s.pasareanu@nasa.gov; gyang@txstate.edu NR 22 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1527-1366 BN 978-1-5090-0025-8 J9 IEEE INT CONF AUTOM PY 2015 BP 703 EP 708 DI 10.1109/ASE.2015.78 PG 6 WC Computer Science, Software Engineering SC Computer Science GA BF5OE UT WOS:000382380700069 ER PT J AU Ahmad, T Bebis, G Nicolescu, M Nefian, A Fong, T AF Ahmad, Touqeer Bebis, George Nicolescu, Monica Nefian, Ara Fong, Terry GP IEEE TI Fusion of Edge-less and Edge-based Approaches for Horizon Line Detection SO 2015 6TH INTERNATIONAL CONFERENCE ON INFORMATION, INTELLIGENCE, SYSTEMS AND APPLICATIONS (IISA) LA English DT Proceedings Paper CT 6th International Conference on Information, Intelligence, Systems and Applications (IISA) CY JUL 06-08, 2015 CL Corfu, GREECE SP Inst Elect & Elect Engineers, Biol & Artificial Intelligence Fdn, Univ Piraeus, Ionian Univ ID SCALE AB Horizon line detection requires finding a boundary which segments an image into sky and non-sky regions. It has many applications including visual geo-localization and geo-tagging, robot navigation/localization, and ship detection and port security. Recently, two machine learning based approaches have been proposed for horizon line detection: one relying on edge classification and the other relying on pixel classification. In the edge-based approach, a classifier is used to refine the edge map by removing non-horizon edges. The refined edge map is then used to form a multi-stage graph where dynamic programming is applied to extract the horizon line. In the edge-less approach, classification is used to obtain a confidence of horizon-ness at each pixel location. The horizon line is then extracted by applying dynamic programming on the resultant dense classification map rather than on the edge map. Both approaches have shown to outperform the classical approach where dynamic programming is applied on the non-refined edge map. In this paper, we provide a comparison between the edge-less and edge-based approaches using two challenging data sets. Moreover, we propose fusing the information about the horizon-ness and edge-ness of each pixel. Our experimental results illustrate that the proposed fusion approach outperforms both the edge-based and edge-less approaches. C1 [Ahmad, Touqeer; Bebis, George; Nicolescu, Monica] Univ Nevada, Dept Comp Sci & Engn, Reno, NV 89557 USA. [Nefian, Ara; Fong, Terry] NASA, Ames Res Ctr, Washington, DC 20546 USA. RP Ahmad, T (reprint author), Univ Nevada, Dept Comp Sci & Engn, Reno, NV 89557 USA. EM ahmad@cse.unr.edu; bebis@cse.unr.edu; monica@cse.unr.edu; ara.nefian@nasa.gov; terry.fong@nasa.gov NR 23 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA PY 2015 PG 6 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic; Telecommunications SC Computer Science; Engineering; Telecommunications GA BF4QJ UT WOS:000381572400035 ER PT S AU Brassitos, E Dubowsky, S AF Brassitos, Elias Dubowsky, Steven GP IEEE TI Compact Drive System for Planetary Rovers and Space Manipulators SO 2015 IEEE/ASME INTERNATIONAL CONFERENCE ON ADVANCED INTELLIGENT MECHATRONICS (AIM) SE IEEE ASME International Conference on Advanced Intelligent Mechatronics LA English DT Proceedings Paper CT IEEE/ASME International Conference on Advanced Intelligent Mechatronics (AIM) CY JUL 07-11, 2015 CL Busan, SOUTH KOREA SP IEEE, ASME, Natl Robot Res Ctr, IEEE Ind Elect Soc, IEEE Robot & Automat Soc, ASME Dynam Syst & Control Div, Korea Robot Soc, Soc Instrument and Control Engineers, Inst Control Robot & Syst, JSME, IEEJ, JSPE, Robot Soc Japan, Creat Adv Robot Educ & Res Consortium, Busan Tourism Org, Korea Tourism Org DE manipulator joint; compact actuators; mechanisms AB Space robotics requires a new generation of actuators that have high torque densities and high efficiencies, high positioning resolutions, high torque capacities and torsional stiffnesses. Ideally they should be lightweight and low-cost. This paper presents a new hardware actuator technology concept to address the above needs. In the concept, a compact integrated motor-transmission-joint mechanism is optimized for size and torque density, while providing good joint support. This is achieved by novel arrangement of multifunction mechanical components and external-rotor motor technology and advantageous use of structural symmetry. Finite element results show the potential to deliver more than 200 Nm of continuous torque at 50 Deg/s in a package as small as a human elbow joint. With its small size and weight and its large torque output, the proposed actuator concept could benefit numerous applications, ranging from space manipulators to actuated prosthetics and medical devices. C1 [Brassitos, Elias] Jet Prop Lab, Pasadena, CA 91109 USA. [Brassitos, Elias] Northeastern Univ, Boston, MA 02115 USA. [Dubowsky, Steven] MIT, Field & Space Robot Lab, Cambridge, MA 02139 USA. RP Brassitos, E (reprint author), Jet Prop Lab, Pasadena, CA 91109 USA. EM Elias.brassitos@jpl.nasa.gov; Dubowsky@mit.edu NR 12 TC 1 Z9 1 U1 3 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2159-6255 BN 978-1-4673-9107-8 J9 IEEE ASME INT C ADV PY 2015 BP 664 EP 669 PG 6 WC Engineering, Electrical & Electronic; Robotics SC Engineering; Robotics GA BF4OK UT WOS:000381493900116 ER PT J AU Iturbe, X Keymeulen, D Ozer, E Yiu, P Berisford, D Hand, K Carlson, R AF Iturbe, Xabier Keymeulen, Didier Ozer, Emre Yiu, Patrick Berisford, Daniel Hand, Kevin Carlson, Robert GP IEEE TI An Integrated SoC for Science Data Processing in Next-Generation Space Flight Instruments Avionics SO 2015 IFIP/IEEE INTERNATIONAL CONFERENCE ON VERY LARGE SCALE INTEGRATION (VLSI-SOC) LA English DT Proceedings Paper CT 23rd IFIP/IEEE International Conference on Very Large Scale Integration (VLSI-SoC) CY OCT 05-07, 2015 CL Daejeon, SOUTH KOREA SP Int Federat Informat Proc, Inst Elect & Elect Engineers, Korea Adv Inst Sci & Technol, Seoul Natl Univ, Embedded Syst Res Ctr, IEEE Council Elect Design Automat, IEEE Circuits & Syst Soc, Korean Inst Informat Scientists & Engineers, ACM Special Interest Grp Design Automat DE SoC; RHBD; Avionics; Instrumentation AB We present here an integrated SoC platform, called APEX-SoC, that is aimed at speeding-up the design of next-generation space flight instruments avionics by providing a convenient infrastructure for hardware and software based science data processing. We use a case-study drawn from the JPL Compositional Infrared Imaging Spectrometer (CIRIS) to illustrate the process of integrating instrument-dependent data acquisition and processing stages in this platform. In order to enable the use of APEX-SoC-based instruments in deep space missions, the platform implements Radiation Hardening By Design (RHBD) techniques and offers support for instantiating multiple processing stages that can be used at runtime to increase reliability or performance, based on the requirements of the mission at each particular stage. Finally, in the specific case of CIRIS, the data processing includes a stage to cope with radiation affecting the instrument photo-detector. C1 [Iturbe, Xabier; Yiu, Patrick] CALTECH, Pasadena, CA 91125 USA. [Iturbe, Xabier; Keymeulen, Didier; Berisford, Daniel; Hand, Kevin; Carlson, Robert] CALTECH, NASA Jet Prop Lab, Pasadena, CA 91125 USA. [Iturbe, Xabier; Ozer, Emre] ARM R&D, Cambridge, England. RP Iturbe, X (reprint author), CALTECH, Pasadena, CA 91125 USA. EM xabier.iturbe@jpl.nasa.gov NR 26 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-9140-5 PY 2015 BP 134 EP 141 PG 8 WC Computer Science, Hardware & Architecture; Engineering, Electrical & Electronic; Telecommunications SC Computer Science; Engineering; Telecommunications GA BF5OP UT WOS:000382398500025 ER PT S AU Gilbert, A Mesmer, B Watson, MD AF Gilbert, Andrew Mesmer, Bryan Watson, Michael D. GP IEEE TI Exergy Analysis of Rocket Systems SO 2015 9TH ANNUAL IEEE INTERNATIONAL SYSTEMS CONFERENCE (SYSCON) SE Annual IEEE Systems Conference LA English DT Proceedings Paper CT 9th Annual IEEE International Systems Conference (SysCon) CY APR 13-16, 2015 CL Vancouver, CANADA SP IEEE, IEEE Syst Council DE exergy; exergy analysis; rocket systems; system efficiency; attribute trade space; value-driven design ID POWER-PLANTS AB Exergy is defined as the useful work available from a system in a specified environment. Exergy analysis allows for comparison between different system designs, and allows for comparison of subsystem efficiencies within system designs. This paper explores the relationship between the fundamental rocket equation and an exergy balance equation. A previously derived exergy equation related to rocket systems is investigated, and a higher fidelity analysis is derived. The exergy assessments will enable informed, value-based decision making when comparing alternative rocket system designs, and will allow the most efficient configuration among candidate configurations to be determined. C1 [Gilbert, Andrew; Mesmer, Bryan] Univ Alabama, Ind & Syst Engn & Engn Management, Huntsville, AL 35899 USA. [Watson, Michael D.] NASA, Marshall Space Flight Ctr, Syst Engn Management Off, Chief Engineers Off, Huntsville, AL USA. RP Gilbert, A (reprint author), Univ Alabama, Ind & Syst Engn & Engn Management, Huntsville, AL 35899 USA. NR 20 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1944-7620 BN 978-1-4799-5927-3 J9 ANN IEEE SYST CONF PY 2015 BP 283 EP 288 PG 6 WC Engineering, Multidisciplinary SC Engineering GA BF3FS UT WOS:000380537800045 ER PT J AU Saini, S Jin, HQ Jespersen, D Cheung, S Djomehri, J Chang, J Hood, R AF Saini, Subhash Jin, Haoqiang Jespersen, Dennis Cheung, Samson Djomehri, Jahed Chang, Johnny Hood, Robert GP IEEE TI Early Multi-Node Performance Evaluation of a Knights Corner (KNC) Based NASA Supercomputer SO 2015 IEEE 29TH INTERNATIONAL PARALLEL AND DISTRIBUTED PROCESSING SYMPOSIUM WORKSHOPS LA English DT Proceedings Paper CT 29th IEEE International Parallel and Distributed Processing Symposium (IPDPS) CY MAY 25-29, 2015 CL Hyderabad, INDIA SP IEEE, IEEE Comp Soc DE Benchmarking; Performance; WRF, OVERFLOW AB We have conducted performance evaluation of a dual-rail Fourteen Data Rate (FDR) InfiniBand (IB) connected cluster, where each node has two Intel Xeon E5-2670 (Sandy Bridge) processors and two Intel Xeon Phi coprocessors. The Xeon Phi, based on the Many Integrated Core (MIC) architecture, is of the Knights Corner (KNC) generation. We used several types of benchmarks for the study. We ran the MPI and multi-zone versions of the NAS Parallel Benchmarks (NPB)-both original and optimized for the Xeon Phi. Among the full-scale benchmarks, we ran two versions of WRF, including one optimized for the MIC, and used a 12 Km Continental U. S (CONUS) data set. We also used original and optimized versions of OVERFLOW and ran with four different datasets to understand scaling in symmetric mode and related load-balancing issues. We present performance for the four different modes of using the host + MIC combination: native host, native MIC, offload, and symmetric. We also discuss the various optimization techniques used in optimizing two of the NPBs for offload mode as well as WRF and OVERFLOW. WRF 3.4 optimized for MIC runs 47% faster than the original NCAR WRF 3.4. The optimized version of OVERFLOW runs 18% faster on the host and the load-balancing strategy used improves the performance on MIC by 5% to 36% depending on the data size. In addition, we discuss the issues related to offload mode and load balancing in symmetric mode. C1 [Saini, Subhash; Jin, Haoqiang; Jespersen, Dennis] NASA, NASA Adv Supercomp NAS Div, NASA Ames Res Ctr, Moffett Field, CA 94035 USA. [Cheung, Samson; Djomehri, Jahed; Chang, Johnny; Hood, Robert] Comp Sci Corp, Cincinnati, OH 45202 USA. RP Saini, S (reprint author), NASA, NASA Adv Supercomp NAS Div, NASA Ames Res Ctr, Moffett Field, CA 94035 USA. EM subhash.saini@nasa.gov; haoqiang.jin@nasa.gov; dennis.jespersen@nasa.gov; samson.h.cheung@nasa.gov; jahed.djomehri@nasa.gov; johnny.chang@nasa.gov; robert.hood@nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-7684-6 PY 2015 BP 57 EP 67 PG 11 WC Computer Science, Hardware & Architecture; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF2ME UT WOS:000380479800006 ER PT J AU Whalen, MW Person, S Rungta, N Staats, M Grijincu, D AF Whalen, Michael W. Person, Suzette Rungta, Neha Staats, Matt Grijincu, Daniela GP IEEE TI A Flexible and Non-intrusive Approach for Computing Complex Structural Coverage Metrics SO 2015 IEEE/ACM 37TH IEEE INTERNATIONAL CONFERENCE ON SOFTWARE ENGINEERING, VOL 1 LA English DT Proceedings Paper CT 2015 IEEE ACM 37th IEEE International Conference on Software Engineering CY MAY 16-24, 2015 CL Florence, ITALY SP IEEE Comp Soc ID TEST SUITES AB Software analysis tools and techniques often leverage structural code coverage information to reason about the dynamic behavior of software. Existing techniques instrument the code with the required structural obligations and then monitor the execution of the compiled code to report coverage. Instrumentation based approaches often incur considerable runtime overhead for complex structural coverage metrics such as Modified Condition/Decision (MC/DC). Code instrumentation, in general, has to be approached with great care to ensure it does not modify the behavior of the original code. Furthermore, instrumented code cannot be used in conjunction with other analyses that reason about the structure and semantics of the code under test. In this work, we introduce a non-intrusive preprocessing approach for computing structural coverage information. It uses a static partial evaluation of the decisions in the source code and a source-to-bytecode mapping to generate the information necessary to efficiently track structural coverage metrics during execution. Our technique is flexible; the results of the preprocessing can be used by a variety of coverage-driven software analysis tasks, including automated analyses that are not possible for instrumented code. Experimental results in the context of symbolic execution show the efficiency and flexibility of our non-intrusive approach for computing code coverage information. C1 [Whalen, Michael W.] Univ Minnesota, Minneapolis, MN 55455 USA. [Person, Suzette] NASA, Langley Res Ctr, Hampton, VA 23665 USA. [Rungta, Neha] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Staats, Matt] Google Inc, Zurich, Switzerland. [Grijincu, Daniela] Univ St Andrews, St Andrews KY16 9AJ, Fife, Scotland. RP Whalen, MW (reprint author), Univ Minnesota, Minneapolis, MN 55455 USA. EM whalen@cs.umn.edu; suzette.person@nasa.gov; neha.s.rungta@nasa.gov; staatsm@gmail.com; dana.grijincu@gmail.com NR 35 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-1934-5 PY 2015 BP 506 EP 516 DI 10.1109/ICSE.2015.68 PG 11 WC Computer Science, Software Engineering; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF3SL UT WOS:000380573400047 ER PT J AU Dieumegard, A Garoche, PL Kahsai, T Taillar, A Thirioux, X AF Dieumegard, Arnaud Garoche, Pierre-Loic Kahsai, Temesghen Taillar, Alice Thirioux, Xavier BE Shin, D TI Compilation of Synchronous Observers as Code Contracts SO 30TH ANNUAL ACM SYMPOSIUM ON APPLIED COMPUTING, VOLS I AND II LA English DT Proceedings Paper CT 30th ACM Symposium on Applied Computing (SAC) CY APR 13-17, 2015 CL Salamanca, SPAIN SP ACM, ACM Special Interest Grp Appl Comp, Telefonica, IBM ID SYSTEMS; VERIFICATION AB Synchronous languages have long been the standard formalism for modeling and implementing embedded control software in critical domains like avionics, automotive or railway system development. Those languages are equipped with qualified compilers that generate the target final embedded code. An extensively used technique to de fine the expected behavior is the use of synchronous observers. Those observers are typically used for simulation and testing purposes. However, the information contained in those observers is lost during the compilation process. This makes the verification of expected behavior at code level difficult, since it requires the re-specification of the observer. In this paper, we propose an integrated process in which functional properties expressed at the model level through synchronous observers are compiled as code-level contracts. We also show how these specifications, both at model level and code level could be analyzed via SMT-based model checking, static analysis and runtime verification. We have implemented these techniques in a tool chain targeting embedded systems modeled in Simulink. C1 [Dieumegard, Arnaud; Taillar, Alice; Thirioux, Xavier] INPT, ENSEEIHT, Toulouse, France. [Garoche, Pierre-Loic] Off Natl Etud & Rech Aerosp, French Aerosp Lab, Toulouse, France. [Kahsai, Temesghen] CMU, NASA Ames, Pittsburgh, PA USA. RP Dieumegard, A (reprint author), INPT, ENSEEIHT, Toulouse, France. NR 24 TC 0 Z9 0 U1 0 U2 0 PU ASSOC COMPUTING MACHINERY PI NEW YORK PA 1515 BROADWAY, NEW YORK, NY 10036-9998 USA PY 2015 BP 1933 EP 1939 DI 10.1145/2695664.2695819 PG 7 WC Computer Science, Interdisciplinary Applications SC Computer Science GA BF4IX UT WOS:000381029800305 ER PT S AU Josset, D Hou, W Pelon, J Hu, Y Tanelli, S Ferrare, R Burton, S Pascal, N AF Josset, D. Hou, W. Pelon, J. Hu, Y. Tanelli, S. Ferrare, R. Burton, S. Pascal, N. CA ICARE Team BE Hou, WW Arnone, RA TI Ocean and Polarization observations from active remote sensing: Atmospheric and Ocean science applications SO OCEAN SENSING AND MONITORING VII SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Ocean Sensing and Monitoring VII CY APR 21-22, 2015 CL Baltimore, MD SP SPIE DE Lidar; Remote Sensing; Ocean; Aerosols; Clouds ID AEROSOL OPTICAL DEPTH; WATER CLOUDS; LIDAR RATIO; RETRIEVAL; DEPOLARIZATION; BACKSCATTER; PRODUCTS; CALIOP AB In the past few years, we have demonstrated how the surface return measured by the active instruments onboard CloudSat and CALIPSO could be used to retrieve the optical depth and backscatter phase function (lidar ratio) of aerosols and ice clouds. This methodology lead to the development of a data fusion product publicly available at the ICARE archive center using the Synergized Optical Depth of Aerosols and Ice Clouds (SODA & ICE) algorithm(1). This algorithm, also allowing to derive ocean surface wind speed, has been extended to include dense cloud surface return to analyze aerosol and cloud properties above such clouds. This low level data fusion of CALIPSO and CloudSat ocean surface echoes has been used by several researchers to explore different research paths. Among them, we can cite: A new characterization of the lidar ratio of cirrus clouds(2) The analysis of the precipitable water and development of a new Millimeter-Wave Propagation Model for the W-Band observations (EMPIRIMA(3)) The analysis of the lidar ratio of sea-spray aerosols(4), and of Aerosol multilayer lidar ratio and extinction(5) A contribution to the retrieval of the subsurface particulate backscatter coefficients of phytoplankton particles(6) In this paper, we present the main features of SODA & ICE, summarizing some of the results obtained. C1 [Josset, D.; Hou, W.] Naval Res Lab, Stennis Space Ctr, MS 39529 USA. [Pelon, J.] LATMOS IPSL, Paris, France. [Hu, Y.; Ferrare, R.; Burton, S.] NASA Langley Res Ctr, Atmospher Composit Branch, Hampton, VA 23681 USA. [Tanelli, S.] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. [Pascal, N.] ICARE Univ Lille 1, Lille, France. RP Josset, D (reprint author), Naval Res Lab, Stennis Space Ctr, MS 39529 USA. RI Hu, Yongxiang/K-4426-2012 NR 30 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-62841-575-9 J9 PROC SPIE PY 2015 VL 9459 AR UNSP 94590N DI 10.1117/12.2181544 PG 14 WC Remote Sensing; Optics SC Remote Sensing; Optics GA BD0SJ UT WOS:000357647400014 ER PT S AU Haldeman, CD Schofield, O Webb, DC Valdez, TI Jones, JA AF Haldeman, Clinton D., III Schofield, Oscar Webb, Douglas C. Valdez, Thomas I. Jones, Jack A. GP IEEE TI Implementation of Energy Harvesting System for Powering Thermal Gliders for Long Duration Ocean Research SO OCEANS 2015 - MTS/IEEE WASHINGTON SE OCEANS-IEEE LA English DT Proceedings Paper CT OCEANS MTS/IEEE Conference CY OCT 19-22, 2015 CL Washington, DC SP MTS, IEEE DE glider; thermal glider; thermal recharging AB The exploration of the Earth's oceans is aided by autonomous underwater vehicles (AUVs). AUVs in use today include floats and gliders; they can be deployed to profile salinity, temperature and pressure of the ocean at depths of up to 2 km. Both the floats and gliders typically control buoyancy by filling and deflating an external bladder with a hydraulic fluid delivered by an electrical pump. The operation time of an AUV is limited by energy storage. For floats, such as the Argo float, the operating duration is approximately 5 years with the capability to dive once every 10 days. For electric gliders, such as the deep G2 Slocum, the mission duration can be up to one year with lithium primary batteries. An energy storage system has been developed that can harvest energy from the temperature differences at various depths of the ocean. This system was demonstrated on an Argo style float and has been implemented in a thermal version of the Slocum glider. The energy harvesting system is based on a phase change material with a freeze thaw cycle that pressurizes hydraulic oil that is converted to electrical energy. The thermal Slocum glider does not use an electrical pump, but harvested thermal energy to control buoyancy. The goal for the thermal Slocum glider is for persistent ocean operation for a duration of up to 10 years. A thermal powered glider with an energy harvesting system as described can collect conductivity, temperature, and pressure data and deliver it to the National Data Buoy Center (NDBC) Glider Data Monitoring System and the World Meteorological Organization (WMO) Global Telecommunications System (GTS). Feeding into operational modeling centers such as the National Centers for Environmental Prediction (NCEP) and the U.S. Naval Observatory (NAVO), this data will enable advanced climate predictions over a timespan not currently achievable with present technology. Current testing of the thermal powered Slocum glider is to determine the durability of the technology and quantify the glider system design. Previous issues with this technology included energy storage system management and glider mechanical limitations. Our objective is to learn how to fly an energy harvesting thermal glider that interacts with the ocean environment efficiently. We would also like to establish the latitudinal range of operation. This thermal powered Slocum glider, dubbed Clark, after the famous explorer duo Lewis and Clark, has been deployed off of St. Thomas for flight dynamics and durability testing. The following paper will discuss the deployment and testing of the thermal powered Slocum glider. We will also discuss the advantages of ocean energy harvesting technology for oceanographic research. C1 [Haldeman, Clinton D., III; Schofield, Oscar] Rutgers State Univ, Ctr Ocean Observing Leadership, New Brunswick, NJ 08903 USA. [Webb, Douglas C.] Teledyne Webb Res Corp, N Falmouth, MA USA. [Valdez, Thomas I.; Jones, Jack A.] CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Haldeman, CD (reprint author), Rutgers State Univ, Ctr Ocean Observing Leadership, New Brunswick, NJ 08903 USA. NR 7 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0197-7385 BN 978-0-933957-43-5 J9 OCEANS-IEEE PY 2015 PG 5 WC Engineering, Marine; Engineering, Electrical & Electronic; Oceanography SC Engineering; Oceanography GA BF3JW UT WOS:000380550000392 ER PT S AU Hammond, M Clark, A Mahajan, A Sharma, S Rock, S AF Hammond, Marcus Clark, Ashley Mahajan, Aditya Sharma, Sumant Rock, Stephen GP IEEE TI Automated Point Cloud Correspondence Detection for Underwater Mapping Using AUVs SO OCEANS 2015 - MTS/IEEE WASHINGTON SE OCEANS-IEEE LA English DT Proceedings Paper CT OCEANS MTS/IEEE Conference CY OCT 19-22, 2015 CL Washington, DC SP MTS, IEEE AB An algorithm for automating correspondence detection between point clouds composed of multibeam sonar data is presented. This allows accurate initialization for point cloud alignment techniques even in cases where accurate inertial navigation is not available, such as iceberg profiling or vehicles with low-grade inertial navigation systems. Techniques from computer vision literature are used to extract, label, and match keypoints between "pseudo-images" generated from these point clouds. Image matches are refined using RANSAC and information about the vehicle trajectory. The resulting correspondences can be used to initialize an iterative closest point (ICP) registration algorithm to estimate accumulated navigation error and aid in the creation of accurate, self-consistent maps. The results presented use multibeam sonar data obtained from multiple overlapping passes of an underwater canyon in Monterey Bay, California. Using strict matching criteria, the method detects 23 between-swath correspondence events in a set of 155 pseudo-images with zero false positives. Using less conservative matching criteria doubles the number of matches but introduces several false positive matches as well. Heuristics based on known vehicle trajectory information are used to eliminate these. C1 [Hammond, Marcus; Clark, Ashley; Mahajan, Aditya; Sharma, Sumant; Rock, Stephen] Stanford Univ, Dept Aeronaut & Astronaut, Stanford, CA 94305 USA. [Clark, Ashley] NASA Ames Res Ctr, Mountain View, CA 94035 USA. [Rock, Stephen] Monterey Bay Aquarium Res Inst, Moss Landing, CA 95039 USA. RP Hammond, M (reprint author), Stanford Univ, Dept Aeronaut & Astronaut, Stanford, CA 94305 USA. EM mmh13@stanford.edu; aaclark@stanford.edu; mahajan1@stanford.edu; sharmas@stanford.edu; rock@stanford.edu NR 12 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0197-7385 BN 978-0-933957-43-5 J9 OCEANS-IEEE PY 2015 PG 7 WC Engineering, Marine; Engineering, Electrical & Electronic; Oceanography SC Engineering; Oceanography GA BF3JW UT WOS:000380550000267 ER PT J AU Ghosh, TK Nguyen, LA Quiocho, LJ AF Ghosh, Tushar K. Nguyen, Luong A. Quiocho, Leslie J. BE Bailey, D Gupta, GS Demidenko, S TI An Efficient Solution Method for Multibody Systems with Loops Using Multiple Processors SO PROCEEDINGS OF THE 2015 6TH INTERNATIONAL CONFERENCE ON AUTOMATION, ROBOTICS AND APPLICATIONS (ICARA) LA English DT Proceedings Paper CT 6th International Conference on Automation, Robotics and Applications (ICARA) CY FEB 17-19, 2015 CL Queenstown, NEW ZEALAND SP IEEE NZ Cent Sect, IEEE Instrumentat & Measurement Soc Tech Comm Robot & Automat, IEEE, Massey Univ, Sch Engn & Adv Technol DE Multibody dynamics; multiple processors; divide-and-conquer algorithm; computational efficiency; Order-N ID PARALLEL O(LOG(N)) CALCULATION; ARTICULATED-BODY ALGORITHM; DYNAMICS AB This paper describes a multibody dynamics algorithm formulated for parallel implementation on multiprocessor computing platforms using the divide-and-conquer approach. The system of interest is a general topology of rigid and elastic articulated bodies with or without loops. The algorithm divides the multibody system into a number of smaller sets of bodies in chain or tree structures, called "branches" at convenient joints called "connection points", and uses an Order-N (O (N)) approach to formulate the dynamics of each branch in terms of the unknown spatial connection forces. The equations of motion for the branches, leaving the connection forces as unknowns, are implemented in separate processors in parallel for computational efficiency, and the equations for all the unknown connection forces are synthesized and solved in one or several processors. The performances of two implementations of this divide-and-conquer algorithm in multiple processors are compared with an existing method implemented on a single processor. C1 [Ghosh, Tushar K.; Nguyen, Luong A.] Natl Secur Solut, Commun L 3, Houston, TX 77058 USA. [Quiocho, Leslie J.] NASA, Software Robot & Simulat Div, Johnson Space Ctr, Houston, TX USA. RP Ghosh, TK (reprint author), Natl Secur Solut, Commun L 3, Houston, TX 77058 USA. NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-6466-6 PY 2015 BP 430 EP 436 PG 7 WC Robotics SC Robotics GA BF4QD UT WOS:000381564700072 ER PT S AU Levis, A Schechner, YY Aides, A Davis, AB AF Levis, Aviad Schechner, Yoav Y. Aides, Amit Davis, Anthony B. GP IEEE TI Airborne Three-Dimensional Cloud Tomography SO 2015 IEEE INTERNATIONAL CONFERENCE ON COMPUTER VISION (ICCV) SE IEEE International Conference on Computer Vision LA English DT Proceedings Paper CT IEEE International Conference on Computer Vision CY DEC 11-18, 2015 CL Santiago, CHILE SP Amazon, Microsoft, Sansatime, Baidu, Intel, Facebook, Adobe, Panasonic, 360, Google, Omron, Blippar, iRobot, Hiscene, nVidia, Mvrec, Viscovery, AiCure ID SOLAR-RADIATION MEASUREMENTS; EFFECTIVE PARTICLE RADIUS; OPTICAL-THICKNESS; GAS-FLOWS; AEROSOL; LIGHT; RECONSTRUCTION; SIMULATION; STEREO AB We seek to sense the three dimensional (3D) volumetric distribution of scatterers in a heterogenous medium. An important case study for such a medium is the atmosphere. Atmospheric contents and their role in Earth's radiation balance have significant uncertainties with regards to scattering components: aerosols and clouds. Clouds, made of water droplets, also lead to local effects as precipitation and shadows. Our sensing approach is computational tomography using passive multi-angular imagery. For light-matter interaction that accounts for multiple-scattering, we use the 3D radiative transfer equation as a forward model. Volumetric recovery by inverting this model suffers from a computational bottleneck on large scales, which include many unknowns. Steps taken make this tomography tractable, without approximating the scattering order or angle range. C1 [Levis, Aviad; Schechner, Yoav Y.; Aides, Amit] Technion Israel Inst Technol, Dept Elect Engn, Haifa, Israel. [Davis, Anthony B.] CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Levis, A (reprint author), Technion Israel Inst Technol, Dept Elect Engn, Haifa, Israel. EM levisav@tx.technion.ac.il; yoav@ee.technion.ac.il; amitibo@campus.technion.ac.il; Anthony.B.Davis@jpl.nasa.gov NR 56 TC 0 Z9 0 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1550-5499 BN 978-1-4673-8390-5 J9 IEEE I CONF COMP VIS PY 2015 BP 3379 EP 3387 DI 10.1109/ICCV.2015.386 PG 9 WC Computer Science, Artificial Intelligence SC Computer Science GA BF1NZ UT WOS:000380414100378 ER PT J AU Scardelletti, MC Jordan, JL Ponchak, GE Zorman, CA AF Scardelletti, M. C. Jordan, J. L. Ponchak, G. E. Zorman, C. A. BE Brown, R Abedi, A TI WIRELESS CAPACITIVE PRESSURE SENSOR WITH DIRECTIONAL RF CHIP ANTENNA FOR HIGH TEMPERATURE ENVIRONMENTS SO 2015 IEEE INTERNATIONAL CONFERENCE ON WIRELESS FOR SPACE AND EXTREME ENVIRONMENTS (WISEE) LA English DT Proceedings Paper CT IEEE International Conference on Wireless for Space and Extreme Environments (WiSEE) CY DEC 14-16, 2015 CL Orlando, FL SP IEEE USA, IEEE Canada, UFFC, AESS, RFID, Michigan Tech, Univ Central Florida, CIADI, NASA, ESA, CSA ASC DE Wireless capacitive pressure sensor system; MEMS; chip antenna; passive and active components; high temperature applications; health monitoring AB This paper presents the design, fabrication and characterization of a wireless capacitive pressure sensor with directional RF chip antenna that is envisioned for the health monitoring of aircraft engines operating in harsh environments. The sensing system is characterized from room temperature (25 degrees C) to 300 degrees C for a pressure range from 0 to 100 psi. The wireless pressure system consists of a Clapp-type oscillator design with a capacitive MEMS pressure sensor located in the LC-tank circuit of the oscillator. Therefore, as the pressure of the aircraft engine changes, so does the output resonant frequency of the sensing system. A chip antenna is integrated to transmit the system output to a receive antenna 10 m away. The design frequency of the wireless pressure sensor is 127 MHz and a 2% increase in resonant frequency over the temperature range of 25 to 300 degrees C from 0 to 100 psi is observed. The phase noise is less than-30 dBc/Hz at the 1 kHz offset and decreases to less than-80 dBc/Hz at 10 kHz over the entire temperature range. The RF radiation patterns for two cuts of the wireless system have been measured and show that the system is highly directional and the MEMS pressure sensor is extremely linear from 0 to 100 psi. C1 [Scardelletti, M. C.; Jordan, J. L.; Ponchak, G. E.] NASA, Glenn Res Ctr, Cleveland, OH USA. [Zorman, C. A.] Case Western Reserve Univ, Cleveland, OH USA. RP Scardelletti, MC (reprint author), NASA, Glenn Res Ctr, Cleveland, OH USA. NR 12 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-9946-3 PY 2015 PG 6 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BF2FY UT WOS:000380464200013 ER PT S AU Davoodi, F Asama, J Rais-Zadeh, M Burdick, J Behar, A AF Davoodi, Faranak Asama, Junichi Rais-Zadeh, Mina Burdick, Joel Behar, Alberto GP IEEE TI Moball: An Intelligent Wind-Opportunistic Mobile Sensor to Monitor the Polar Regions SO 2015 IEEE SENSORS SE IEEE Sensors LA English DT Proceedings Paper CT 2015 IEEE SENSORS CY NOV 01-04, 2015 CL Busan, SOUTH KOREA SP IEEE, Sensors Council, Korean Sensors Soc DE Arctic Mapping; Energy Harvesting; Wireless mesh Network of Mobile Sensors; Sensor Networks; Mobile Sensor Networks; Distributed Control System of Moballs; Moball; Moball Network; Moball-buoy; Task sharing and Learning Sensor Network; Intelligent Buoy Network; Spherical Sensors; Wind Energy Harvesting AB Sensors capable of operating in harsh environments for long periods of time and having wireless readout capability are needed for mapping environmental conditions in remote areas, such as polar regions. In this paper, we report the first measured results of an innovative in-situ system of controllable and wind-opportunistic spherical mobile sensors (called Moballs), used to monitor and map various environmental factors in polar areas. To have self-powered controlled motion, Moballs exploit the abundance of wind and a novel dual-functioning mechanical control and linear induction system. Moballs have peer-to-peer and Moball-to-base (e.g. satellite) communication capability, reporting the sensory data back to the base station or other peer Moballs for task sharing decisions, improving area coverage, optimizing system performance, etc. C1 [Davoodi, Faranak] Intelligent Buoy Networks Inc, Pasadena, CA 91101 USA. [Asama, Junichi] Shizuoka Univ, Mech Engn, Shizuoka, Japan. [Rais-Zadeh, Mina] Univ Michigan, Elect Engn, Ann Arbor, MI 48109 USA. [Burdick, Joel] CALTECH, Mech Engn, Pasadena, CA 91125 USA. [Behar, Alberto] Jet Prop Lab, Pasadena, CA USA. RP Davoodi, F (reprint author), Intelligent Buoy Networks Inc, Pasadena, CA 91101 USA. EM Faranak.davoodi@intelligentbuoys.com; asama.junichi@shizuoka.ac.jp; minar@umich.edu; jwb@Caltech.edu NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1930-0395 BN 978-1-4799-8203-5 J9 IEEE SENSOR PY 2015 BP 1437 EP 1440 PG 4 WC Engineering, Electrical & Electronic; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BF1WO UT WOS:000380440800375 ER PT S AU Notardonato, WU AF Notardonato, W. U. BE TerBrake, HJM TenKate, HHJ Vanapalli, S TI Development of a ground operations demonstration unit for liquid hydrogen at Kennedy Space Center SO PROCEEDINGS OF THE 25TH INTERNATIONAL CRYOGENIC ENGINEERING CONFERENCE AND INTERNATIONAL CRYOGENIC MATERIALS CONFERENCE 2014 SE Physics Procedia LA English DT Proceedings Paper CT 25th International Cryogenic Engineering Conference and International Cryogenic Materials Conference CY JUL 07-11, 2014 CL Enschede, NETHERLANDS DE Liquid hydrogen; cryogenic refrigeration; space launch systems AB NASA operations for handling cryogens in ground support equipment have not changed substantially in 50 years, despite major technology advances in the field of cryogenics. NASA loses approximately 50% of the hydrogen purchased because of a continuous heat leak into ground and flight vessels, transient chill down of warm cryogenic equipment, liquid bleeds, and vent losses. NASA Kennedy Space Center (KSC) needs to develop energy-efficient cryogenic ground systems to minimize propellant losses, simplify operations, and reduce cost associated with hydrogen usage. The GODU LH2 project will design, assemble, and test a prototype storage and distribution system for liquid hydrogen that represents an advanced end-to-end cryogenic propellant system for a ground launch complex. The project has multiple objectives and will culminate with an operational demonstration of the loading of a simulated flight tank with densified propellants. The system will be unique because it uses an integrated refrigeration and storage system (IRAS) to control the state of the fluid. The integrated refrigerator is the critical feature enabling the testing of the following three functions: zero-loss storage and transfer, propellant densification/conditioning, and on-site liquefaction. This paper will discuss the test objectives, the design of the system, and the current status of the installation. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/). C1 [Notardonato, W. U.] NASA, Cryogen Test Lab, Kennedy Space Ctr, FL 32899 USA. RP Notardonato, WU (reprint author), NASA, Cryogen Test Lab, Kennedy Space Ctr, FL 32899 USA. EM bill.notardonato@nasa.gov NR 2 TC 0 Z9 0 U1 1 U2 1 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 1875-3892 J9 PHYSCS PROC PY 2015 VL 67 BP 95 EP 100 DI 10.1016/j.phpro.2015.06.017 PG 6 WC Physics, Applied SC Physics GA BF3YX UT WOS:000380607500015 ER PT S AU Shirron, PJ Kimball, MO DiPirro, MJ Bialas, TG AF Shirron, Peter J. Kimball, Mark O. DiPirro, Michael J. Bialas, Thomas G. BE TerBrake, HJM TenKate, HHJ Vanapalli, S TI Performance testing of the Astro-H flight model 3-stage ADR SO PROCEEDINGS OF THE 25TH INTERNATIONAL CRYOGENIC ENGINEERING CONFERENCE AND INTERNATIONAL CRYOGENIC MATERIALS CONFERENCE 2014 SE Physics Procedia LA English DT Proceedings Paper CT 25th International Cryogenic Engineering Conference and International Cryogenic Materials Conference CY JUL 07-11, 2014 CL Enschede, NETHERLANDS DE Astro-H; adiabatic demagnetization refrigerator; space astronomy; x-ray calorimeter AB The Soft X-ray Spectrometer (SXS) is one of four instruments that will be flown on the Japanese Astro-H satellite, planned for launch in late 2015/early 2016. The SXS will perform imaging spectroscopy in the soft x-ray band using a 6x6 array of silicon microcalorimeters operated at 50 mK, cooled by an adiabatic demagnetization refrigerator (ADR). NASA/GSFC is providing the detector array and ADR, and Sumitomo Heavy Industries, Inc. is providing the remainder of the cryogenic system (superfluid helium dewar (< 1.3 K), Stirling cryocoolers and a 4.5 K Joule-Thomson (JT) cryocooler). The ADR is unique in that it is designed to use both the liquid helium and the JT cryocooler as it heat sink. The flight detector and ADR assembly have successfully undergone vibration and performance testing at GSFC, and have now undergone initial performance testing with the flight dewar at Sumitomo Heavy Industries, Inc. in Japan. This paper summaries the performance of the flight ADR in both cryogen-based and cryogen-free operating modes. Published by Elsevier Ltd. C1 [Shirron, Peter J.; Kimball, Mark O.; DiPirro, Michael J.; Bialas, Thomas G.] NASA, Goddard Space Flight Ctr, Cryogen & Fluids Grp, Greenbelt, MD 20771 USA. RP Shirron, PJ (reprint author), NASA, Goddard Space Flight Ctr, Cryogen & Fluids Grp, Greenbelt, MD 20771 USA. EM Peter.Shirron@nasa.gov NR 5 TC 0 Z9 0 U1 1 U2 1 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 1875-3892 J9 PHYSCS PROC PY 2015 VL 67 BP 250 EP 257 DI 10.1016/j.phpro.2015.06.083 PG 8 WC Physics, Applied SC Physics GA BF3YX UT WOS:000380607500041 ER PT S AU Fesmire, JE AF Fesmire, James E. BE TerBrake, HJM TenKate, HHJ Vanapalli, S TI Standardization in cryogenic insulation systems testing and performance data SO PROCEEDINGS OF THE 25TH INTERNATIONAL CRYOGENIC ENGINEERING CONFERENCE AND INTERNATIONAL CRYOGENIC MATERIALS CONFERENCE 2014 SE Physics Procedia LA English DT Proceedings Paper CT 25th International Cryogenic Engineering Conference and International Cryogenic Materials Conference CY JUL 07-11, 2014 CL Enschede, NETHERLANDS DE Thermal insulation; boiloff calorimetry; thermal conductivity; heat flux; multilayer insulation; cryogenic testing; materials; standards AB The close relationship between industrial energy use and cryogenics drives the need for optimized thermal insulation systems. Emerging cryofuels usage is enabled by adequate isolation of the liquid hydrogen or liquefied natural gas from the ambient environment. Thermal performance data for the total insulation system, as rendered, are essential for both engineering designs and cost-benefit decisions involving comparisons among alternatives. These data are obtained through rigorous testing with suitable apparatus and repeatable methods. Properly defined terminology, analysis, and reporting are also vital. Advances in cryogenic insulation test apparatus and methods have led to the recent addition of two new technical standards of ASTM International: C1774 - Standard Guide for Thermal Performance Testing of Cryogenic Insulation Systems and C740 - Standard Guide for Evacuated Reflective Cryogenic Insulation. Among the different techniques described in the new standards is the cylindrical boiloff calorimeter for absolute heat measurement over the full range of vacuum pressure conditions. The details of this apparatus, test method, and data analysis are given. Benchmark thermal performance data, including effective thermal conductivity (k(e)) and heat flux (q) for the boundary temperatures of 293 K and 77 K, are given for a number of different multilayer insulation (MLI) systems in comparison with data for other commonly-used insulation systems including perlite powder, fiberglass, polyurethane foam, and aerogels. Published by Elsevier B.V. C1 [Fesmire, James E.] NASA, Cryogen Test Lab, Kennedy Space Ctr, FL 32899 USA. RP Fesmire, JE (reprint author), NASA, Cryogen Test Lab, Kennedy Space Ctr, FL 32899 USA. EM james.e.fesmire@nasa.gov NR 13 TC 0 Z9 0 U1 4 U2 5 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 1875-3892 J9 PHYSCS PROC PY 2015 VL 67 BP 1089 EP 1097 DI 10.1016/j.phpro.2015.06.205 PG 9 WC Physics, Applied SC Physics GA BF3YX UT WOS:000380607500180 ER PT S AU Thomsen, B Luckow, KS Leth, L Bogholm, T AF Thomsen, Bent Luckow, Kasper Soe Leth, Lone Bogholm, Thomas BE Bodei, C Ferrari, GL Priami, C TI From Safety Critical Java Programs to Timed Process Models SO PROGRAMMING LANGUAGES WITH APPLICATIONS TO BIOLOGY AND SECURITY: ESSAYS DEDICATED TO PIERPAOLO DEGANO ON THE OCCASION OF HIS 65TH BIRTHDAY SE Lecture Notes in Computer Science LA English DT Proceedings Paper CT Colloquium on Programming Languages with Applications to Biology and Security CY JUN 19, 2015 CL Univ Pisa, Dept Comp Sci, Pisa, ITALY HO Univ Pisa, Dept Comp Sci AB The idea of analysing real programs by process algebraic methods probably goes back to the Occam language using the CSP process algebra [43]. In [16,24] Degano et al. followed in that tradition by analysing Mobile Agent Programs written in the Higher Order Functional, Concurrent and Distributed, programming language Facile [47], by equipping Facile with a process algebraic semantics based on true concurrency. This semantics facilitated analysis of programs revealing subtle bugs that would otherwise be very hard to find. Inspired by the idea of translating real programs into process algebraic frameworks, we have in recent years pursued an agenda of translating hard-real-time embedded safety critical programs written in the Safety Critical Java Profile [33] into networks of timed automata [4] and subjecting those to automated analysis using the UPPAAL model checker [10]. Several tools have been built and the tools have been used to analyse a number of systems for properties such as worst case execution time, schedulability and energy optimization [12-14,19,34,36,38]. In this paper we will elaborate on the theoretical underpinning of the translation from Java programs to timed automata models and briefly summarize some of the results based on this translation. Furthermore, we discuss future work, especially relations to the work in [16,24] as Java recently has adopted first class higher order functions in the form of lambda abstractions. C1 [Thomsen, Bent; Leth, Lone; Bogholm, Thomas] Aalborg Univ, Dept Comp Sci, Aalborg, Denmark. [Luckow, Kasper Soe] NASA Ames, Carnegie Mellon Silicon Valley, Moffett Field, CA USA. RP Thomsen, B (reprint author), Aalborg Univ, Dept Comp Sci, Aalborg, Denmark. EM bt@cs.aau.dk NR 45 TC 1 Z9 1 U1 0 U2 0 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 0302-9743 BN 978-3-319-25527-9; 978-3-319-25526-2 J9 LECT NOTES COMPUT SC PY 2015 VL 9465 BP 319 EP 338 DI 10.1007/978-3-319-25527-9_21 PG 20 WC Computer Science, Interdisciplinary Applications; Computer Science, Theory & Methods SC Computer Science GA BF4EJ UT WOS:000380766100021 ER PT S AU Kumar, U Ganguly, S Milesi, C Nemani, RR AF Kumar, Uttam Ganguly, Sangram Milesi, Cristina Nemani, Ramakrishna R. BE Ao, SI Douglas, C Grundfest, WS Burgstone, J TI Fully Constrained Linear Subpixel Classification Algorithms: A Comparative Analysis Based on Heuristic SO WORLD CONGRESS ON ENGINEERING AND COMPUTER SCIENCE, WCECS 2015, VOL II SE Lecture Notes in Engineering and Computer Science LA English DT Proceedings Paper CT World Congress on Engineering and Computer Science CY OCT 21-23, 2015 CL San Francisco, CA SP Int Assoc Engn DE algorithm; constrained model; endmember; linear spectral mixture; mixed pixel ID SPARSE REGRESSION; MODELS AB During the past two and a half decades, many subpixel classification algorithms have been developed to classify multispectral and hyperspectral data for spatiotemporal data mining. The aim of these classification algorithms is to disintegrate a pixel spectrum into its constituent spectra through a mixture model assuming that observed data are linear mixtures of two or more objects, representing a mixed pixel. The linear mixture model allows the presence of a number of target classes with the fractions of their fixed spectrum corresponding to the area occupied by that class in a pixel. The linear model is inverted to produce estimates of those fractional abundances. All of these algorithms are either unconstrained or partially constrained or fully constrained depending on whether the abundance non negativity and abundance sum-to-one constraints are imposed. More often, the constrained algorithms are appropriate for target class quantification and abundance fraction estimation. In this paper, we perform a comparative analysis of five state of the art fully constrained linear subpixel classification algorithms fully constrained least squares (FCLS), modified FCLS (MFCLS), simplex projection unmixing (SPU), constrained sparse unmixing via. variable splitting and augmented Lagrangian (CSUnSAL) and CSUnSAL Total Variation (CSUnSAL TV). The algorithms were tested on computer-simulated data of various signal to noise ratio and Landsat-5 TM data of an agricultural landscape and an urban scenario. The results were validated using descriptive statistics, correlation coefficient, RMSE and probability of success. C1 [Kumar, Uttam; Ganguly, Sangram; Milesi, Cristina; Nemani, Ramakrishna R.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Kumar, U (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM uttam.kumar@nasa.gov; sangram.ganguly@nasa.gov; cristina.milesi@gmail.com; rama.nemani@nasa.gov NR 24 TC 0 Z9 0 U1 0 U2 0 PU INT ASSOC ENGINEERS-IAENG PI HONG KONG PA UNIT 1, 1-F, 37-39 HUNG TO ROAD, KWUN TONG, HONG KONG, 00000, PEOPLES R CHINA SN 2078-0958 BN 978-988-14047-2-5 J9 LECT NOTES ENG COMP PY 2015 BP 764 EP 769 PG 6 WC Computer Science, Theory & Methods; Engineering, Multidisciplinary; Mathematics, Applied SC Computer Science; Engineering; Mathematics GA BF3XM UT WOS:000380591800048 ER PT J AU Rahnamai, K Gray, A AF Rahnamai, Kourosh Gray, Andrew GP IEEE TI Systems Engineering in Industry Internship and Academic Projects SO 2015 10th System of Systems Engineering Conference (SoSE) LA English DT Proceedings Paper CT 10th System of Systems Engineering Conference (SoSE) CY MAY 17-20, 2015 CL San Antonio, TX SP UISA, IEEE, RIT, RELIABILITYSOCIETY, SMC, INCOSE, IEEE SMC SOC, IEEE RELIABILITY SOC, MABL, ROCHESTER I TECHN, ACE, U TEXAS SAN ANTONIO DE Systems engineering; interdisciplinary; industrial projects; systems engineering in academic environment ID MARS AB Large complex Industrial projects most often are interdisciplinary and require a complex systems engineering approach to guarantee success. In this paper we present a successful implementation of a true systems engineering approach to a summer internship program in industry. We exported the methods and lessons learned to an academic environment. For each project a group of six to fifteen students were selected to solve a practical industry problem and produce a detailed design for a specified project. Different aspects of the project plan were assigned to members of each group who were the most qualified or who expressed interest in a specific area of specialization. Three industrial and one academic implementation of this method are explained in this paper. C1 [Rahnamai, Kourosh] Western New England Univ, Dept Elect Engn, Springfield, MA 01119 USA. [Gray, Andrew] Jet Prop Lab, Game Changing Technol Dev Off, Pasadena, CA USA. RP Rahnamai, K (reprint author), Western New England Univ, Dept Elect Engn, Springfield, MA 01119 USA. EM kourosh.rahnamai@wne.edu; Andrew.a.gray@jpl.nasa.gov NR 15 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-7611-9 PY 2015 BP 30 EP 35 PG 6 WC Automation & Control Systems; Engineering, Electrical & Electronic SC Automation & Control Systems; Engineering GA BF3AK UT WOS:000380516100034 ER PT J AU Adirosi, E Baldini, L Roberto, N Gorgucci, E Gatlin, P Tokay, A AF Adirosi, E. Baldini, L. Roberto, N. Gorgucci, E. Gatlin, P. Tokay, A. GP IEEE TI Estimation of raindrop drop size distributions and their vertical profile using ground based disdrometer and FMCW vertically pointing radar SO 2015 1st URSI Atlantic Radio Science Conference (URSI AT-RASC) LA English DT Proceedings Paper CT 1st URSI Atlantic Radio Science Conference (URSI AT-RASC) CY MAY 16-24, 2015 CL Gran Canaria, SPAIN C1 [Adirosi, E.; Baldini, L.; Roberto, N.; Gorgucci, E.] CNR, Ist Sci Atmosfera & Clima, Rome, Italy. [Gatlin, P.] NASA, Marshall Space Flight Ctr, Huntsville, AL USA. [Tokay, A.] Univ Maryland Baltimore Cty, Joint Ctr Earth Syst Technol, Baltimore, MD 21228 USA. [Tokay, A.] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. RP Adirosi, E (reprint author), CNR, Ist Sci Atmosfera & Clima, Rome, Italy. NR 4 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-9-0900-8628-6 PY 2015 PG 1 WC Engineering, Electrical & Electronic; Remote Sensing SC Engineering; Remote Sensing GA BF3OZ UT WOS:000380563800256 ER PT J AU Bilitza, D Galkin, IA Stolle, C Vesnin, A Reinisch, BW AF Bilitza, Dieter Galkin, Ivan A. Stolle, Claudia Vesnin, Artem Reinisch, Bodo W. GP IEEE TI SWARM Electron Density Measurements and Predictions by IRI and IRI-Real-Time SO 2015 1st URSI Atlantic Radio Science Conference (URSI AT-RASC) LA English DT Proceedings Paper CT 1st URSI Atlantic Radio Science Conference (URSI AT-RASC) CY MAY 16-24, 2015 CL Gran Canaria, SPAIN C1 [Bilitza, Dieter] George Mason Univ, Fairfax, VA 22030 USA. [Bilitza, Dieter] NASA Goddard Space Flight Ctr, Greenbelt, MD USA. [Galkin, Ivan A.; Vesnin, Artem; Reinisch, Bodo W.] Univ Massachusetts Lowell, Lowell, MA USA. [Stolle, Claudia] GFZ, Helmholtz Ctr Potsdam, Potsdam, Germany. [Reinisch, Bodo W.] Lowell Digisonde Int, Lowell, MA USA. RP Bilitza, D (reprint author), George Mason Univ, Fairfax, VA 22030 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-9-0900-8628-6 PY 2015 PG 1 WC Engineering, Electrical & Electronic; Remote Sensing SC Engineering; Remote Sensing GA BF3OZ UT WOS:000380563800303 ER PT J AU Gopalswamy, N Makela, P Xie, H Yashiro, S AF Gopalswamy, Nat Makela, Pertti Xie, Hong Yashiro, Seiji GP IEEE TI Low-frequency Solar Radio Bursts and their Space Weather Implications SO 2015 1st URSI Atlantic Radio Science Conference (URSI AT-RASC) LA English DT Proceedings Paper CT 1st URSI Atlantic Radio Science Conference (URSI AT-RASC) CY MAY 16-24, 2015 CL Gran Canaria, SPAIN C1 [Gopalswamy, Nat] NASA Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Makela, Pertti; Xie, Hong; Yashiro, Seiji] Catholic Univ, Washington, DC USA. RP Gopalswamy, N (reprint author), NASA Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-9-0900-8628-6 PY 2015 PG 1 WC Engineering, Electrical & Electronic; Remote Sensing SC Engineering; Remote Sensing GA BF3OZ UT WOS:000380563800343 ER PT J AU Hovey, G Baker, L Cortes, G DeBoer, D Fleming, M Imbriale, W Lacy, G Veidt, B Byrnes, P Fitzsimmons, J Knee, L Kesteven, M AF Hovey, G. Baker, L. Cortes, G. DeBoer, D. Fleming, M. Imbriale, W. Lacy, G. Veidt, B. Byrnes, P. Fitzsimmons, J. Knee, L. Kesteven, M. GP IEEE TI Dish Verification Antenna-1: A Next Generation Antenna for em-wave Radio Telescopes SO 2015 1st URSI Atlantic Radio Science Conference (URSI AT-RASC) LA English DT Proceedings Paper CT 1st URSI Atlantic Radio Science Conference (URSI AT-RASC) CY MAY 16-24, 2015 CL Gran Canaria, SPAIN C1 [Hovey, G.; Lacy, G.; Veidt, B.] Natl Res Council Herzberg, Penticton, BC, Canada. [Baker, L.; Cortes, G.] Cornell Univ, Ithaca, NY USA. [DeBoer, D.] Univ Calif Berkeley, Berkeley, CA 94720 USA. [Fleming, M.] Minex Engn, Antioch, CA USA. [Imbriale, W.] Jet Prop Lab, Pasadena, CA USA. [Byrnes, P.; Fitzsimmons, J.; Knee, L.] Natl Res Council Herzberg, Victoria, BC, Canada. [Kesteven, M.] CSIRO, Canberra, ACT, Australia. RP Hovey, G (reprint author), Natl Res Council Herzberg, Penticton, BC, Canada. NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-9-0900-8628-6 PY 2015 PG 1 WC Engineering, Electrical & Electronic; Remote Sensing SC Engineering; Remote Sensing GA BF3OZ UT WOS:000380563800378 ER PT J AU Shim, JS Kuznetsova, MM Rastaetter, L Bilitza, D Bingham, S Bust, G Calfas, R Codrescu, M Coster, AJ Crowley, G Emery, BA Foerster, M Foster, B Fuller-Rowell, TJ Goncharenko, L Huba, J Mannucci, A Namgaladze, AA Pi, XQ Prokhorov, BE Ridley, AJ Scherliess, L Schunk, RW Sojka, JJ Zhu, L AF Shim, Ja Soon Kuznetsova, Maria M. Rastaetter, Lutz Bilitza, Dieter Bingham, Suzy Bust, Gary Calfas, Roy Codrescu, Mihail Coster, Anthea J. Crowley, Geoff Emery, Barbara A. Foerster, Matthias Foster, Ben T. Fuller-Rowell, Timothy J. Goncharenko, Larisa Huba, Joe Mannucci, Anthony Namgaladze, Alexander A. Pi, Xiaoqing Prokhorov, Boris E. Ridley, Aaron J. Scherliess, Ludger Schunk, Robert W. Sojka, Jan J. Zhu, Lie GP IEEE TI Community-Wide Model Validation Study for Systematic Assessment of Ionosphere Models SO 2015 1st URSI Atlantic Radio Science Conference (URSI AT-RASC) LA English DT Proceedings Paper CT 1st URSI Atlantic Radio Science Conference (URSI AT-RASC) CY MAY 16-24, 2015 CL Gran Canaria, SPAIN C1 [Shim, Ja Soon] CUA NASA GSFC, Greenbelt, MD 20771 USA. [Kuznetsova, Maria M.; Rastaetter, Lutz] NASA GSFC, Greenbelt, MD USA. [Bilitza, Dieter] George Mason Univ, Sch Phys Astron & Computat Sci, Fairfax, VA 22030 USA. [Bingham, Suzy] Met Off, Exeter EX1 3PB, Devon, England. [Bust, Gary] JHU APL, Laurel, MD USA. [Calfas, Roy] Univ Texas Austin, Austin, TX 78712 USA. [Codrescu, Mihail; Fuller-Rowell, Timothy J.] NOAA SWPC, Boulder, CO USA. [Coster, Anthea J.; Goncharenko, Larisa] MIT, Haystack Observ, Westford, MA 01886 USA. [Crowley, Geoff] ASTRA LLC, Boulder, CO USA. [Emery, Barbara A.; Foster, Ben T.] NCAR HAO, Boulder, CO USA. [Foerster, Matthias; Prokhorov, Boris E.] Helmholtz Ctr Potsdam, GFZ German Res Ctr Geosci, Potsdam, Germany. [Huba, Joe] NRL, Div Plasma Phys, Washington, DC USA. [Mannucci, Anthony; Pi, Xiaoqing] CALTECH, JPL, Pasadena, CA 91125 USA. [Namgaladze, Alexander A.] Murmansk State Tech Univ, Murmansk, Russia. [Ridley, Aaron J.] Univ Michigan, Space Phys Res Lab, Ann Arbor, MI 48109 USA. [Scherliess, Ludger; Schunk, Robert W.; Sojka, Jan J.; Zhu, Lie] Utah State Univ, Logan, UT 84322 USA. RP Shim, JS (reprint author), CUA NASA GSFC, Greenbelt, MD 20771 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-9-0900-8628-6 PY 2015 PG 1 WC Engineering, Electrical & Electronic; Remote Sensing SC Engineering; Remote Sensing GA BF3OZ UT WOS:000380563800381 ER PT J AU Hihn, J Menzies, T AF Hihn, Jairus Menzies, Tim GP IEEE TI Data Mining Methods and Cost Estimation Models Why is it so hard to infuse new ideas? SO 2015 30th IEEE/ACM International Conference on Automated Software Engineering Workshop (ASEW) LA English DT Proceedings Paper CT 30th IEEE/ACM International Conference on Automated Software Engineering Workshops (ASEW) CY NOV 09-13, 2015 CL Lincoln, NE SP IEEE Comp Soc, Techn Council Software Engn, Assoc Comp Machinery SIGAI, Special Interest Group Software Engn, Univ Nebraska Lincoln, Off Res Econom Dev, ESQuaRed, NASA Ames Res Ctr, Microsoft Res, Zillow Group, hudl, Comp Sci engn, Univ Nebraska Lincoln, NC State Univ, Stevens Inst Technol DE software; cost estimation; effort estimation; data mining; technology infusion AB Infusing new technologies and methods is hard and can often be described as "banging ones head on a brick wall". The is especially true when trying to get project managers, systems, engineers and cost analysts to add a radically new tool to their tool box. In this paper we suggest that the underlying causes are rooted in the fact that the different players have fundamental differences in mental models, vocabulary and objectives. We based this work on lessons learned from ten years of working on the infusion of software costing models into NASA. The good news is that, lately, a crack has begun to appear in what was previously a brick wall. C1 [Hihn, Jairus] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. [Menzies, Tim] North Carolina State Univ, Dept Comp Sci, Raleigh, NC 27695 USA. RP Hihn, J (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. EM jhihn@jpl.nasa.gov; tim.menzies@gmail.com NR 10 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-9775-9 PY 2015 BP 5 EP 9 DI 10.1109/ASEW.2015.27 PG 5 WC Computer Science, Software Engineering; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF3OX UT WOS:000380563500002 ER PT J AU Mattmann, CA Oh, JH Palsulich, T McGibbney, LJ Gil, Y Ratnakar, V AF Mattmann, Chris A. Oh, Ji-Hyun Palsulich, Tyler McGibbney, Lewis John Gil, Yolanda Ratnakar, Varun GP IEEE TI DRAT: An Unobtrusive, Scalable Approach to Large Scale Software License Analysis SO 2015 30th IEEE/ACM International Conference on Automated Software Engineering Workshop (ASEW) LA English DT Proceedings Paper CT 30th IEEE/ACM International Conference on Automated Software Engineering Workshops (ASEW) CY NOV 09-13, 2015 CL Lincoln, NE SP IEEE Comp Soc, Techn Council Software Engn, Assoc Comp Machinery SIGAI, Special Interest Group Software Engn, Univ Nebraska Lincoln, Off Res Econom Dev, ESQuaRed, NASA Ames Res Ctr, Microsoft Res, Zillow Group, hudl, Comp Sci engn, Univ Nebraska Lincoln, NC State Univ, Stevens Inst Technol DE DRAT; Open source; Software license auditing *Palsulich performed this work while at NASA JPL; currently at Google AB The Apache Release Audit Tool (RAT) performs software open source license auditing and checking, however RAT fails to successfully audit today's large code bases. Being a natural language processing (NLP) tool and a crawler, RAT marches through a code base, but uses rudimentary black lists and white lists to navigate source code repositories, and often does a poor job of identifying source code versus binary files. In addition RAT produces no incremental output and thus on code bases that themselves are "Big Data", RAT could run for e.g., a month and still not provide any status report. We introduce Distributed "RAT" or the Distributed Release Audit Tool (DRAT). DRAT overcomes RAT's limitations by leveraging: (1) Apache Tika to automatically detect and classify files in source code repositories and determine what is a binary file; what is source code; what are notes that need skipping, etc. (2) Apache Solr to interactively perform analytics on a code repository and to extract metadata using Apache Tika; and finally (3) Apache OODT to run RAT on per-MIME type (e.g., C/C++, Java, Javascript, etc.) and per configurable K-file sized chunks in a MapReduce workflow. Each Mapper task is an instance of RAT running on a K-file sized per Multipurpose Internet Mail Extensions (MIME) type chunk (split using Tika) and each mapper produces and incremental and intermediate log file; and where the Reducer aggregates the individual log files. C1 [Mattmann, Chris A.; Oh, Ji-Hyun; Palsulich, Tyler; McGibbney, Lewis John] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. [Mattmann, Chris A.; Oh, Ji-Hyun; Gil, Yolanda] Univ So Calif, Dept Comp Sci, Los Angeles, CA 90089 USA. [Gil, Yolanda; Ratnakar, Varun] Univ So Calif, USC Informat Sci Inst, Marina Del Rey, CA USA. RP Mattmann, CA (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. EM mattmann@jpl.nasa.gov; jihyuno@usc.edu; gil@isi.edu; varunr@isi.edu NR 5 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-9775-9 PY 2015 BP 97 EP 101 DI 10.1109/ASEW.2015.14 PG 5 WC Computer Science, Software Engineering; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF3OX UT WOS:000380563500019 ER PT J AU Cheng, J Adams, RJ Young, JC Khayat, MA AF Cheng, Jin Adams, R. J. Young, J. C. Khayat, M. A. GP IEEE TI Stable Formulation of Scattering from Perfect Electrical Conductors with Matrix Binormalization SO 2015 31st International Review of Progress in Applied Computational Electromagnetics (ACES) Vol 31 LA English DT Proceedings Paper CT 31st International Review of Progress in Applied Computational Electromagnetics CY MAR 22-26, 2015 CL Williamsburg, VA SP FEKO, CST, ANDRO DE Electric field integral equations; frequency stability; method of moments; Nystrom ID FIELD INTEGRAL-EQUATION AB A stable formulation of scattering from perfect electrical conductors ( PECs) with matrix binormalization is presented. The new system is composed of the augmented electric field integral equation ( AEFIE) and a constraint on the normal component of the magnetic field with static charge extraction. C1 [Cheng, Jin; Adams, R. J.; Young, J. C.] Univ Kentucky, Elect & Comp Engn, Lexington, KY 40506 USA. [Khayat, M. A.] NASA, Johnson Space Ctr, Houston, TX 77058 USA. RP Cheng, J (reprint author), Univ Kentucky, Elect & Comp Engn, Lexington, KY 40506 USA. EM jcheng@uky.edu; rjadams@uky.edu; jyoung@engr.uky.edu; michael.a.khayat@nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-0-9960-0781-8 PY 2015 PG 2 WC Engineering, Electrical & Electronic SC Engineering GA BF3MD UT WOS:000380555900036 ER PT J AU Mackenzie, AI AF Mackenzie, Anne I. GP IEEE TI Comparison of Two AMC's on a High-Permittivity Substrate SO 2015 31st International Review of Progress in Applied Computational Electromagnetics (ACES) Vol 31 LA English DT Proceedings Paper CT 31st International Review of Progress in Applied Computational Electromagnetics CY MAR 22-26, 2015 CL Williamsburg, VA SP FEKO, CST, ANDRO DE Artificial magnetic conductor; band gap; electromagnetic simulation; metamaterial; mushroom; UC-EBG AB Two types of artificial magnetic conductors (AMC's), mushroom and uniplanar compact electromagnetic band gap (UC-EBG), were designed and simulated using FEKO and HFSS. Designs were determined for reflection with zero phase change at 8.425, 5.5, and 2.4 GHz. The resulting geometries and band gap characteristics are compared. C1 [Mackenzie, Anne I.] NASA, Electromagnet & Sensors Branch, Langley Res Ctr, Hampton, VA 23666 USA. RP Mackenzie, AI (reprint author), NASA, Electromagnet & Sensors Branch, Langley Res Ctr, Hampton, VA 23666 USA. EM anne.mackenzie-1@nasa.gov NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-0-9960-0781-8 PY 2015 PG 2 WC Engineering, Electrical & Electronic SC Engineering GA BF3MD UT WOS:000380555900077 ER PT J AU Sala, F Schoeny, C Divsalar, D Dolecek, L AF Sala, Frederic Schoeny, Clayton Divsalar, Dariush Dolecek, Lara BE Matthews, MB TI Asymmetric ECCs for Flash in High-Radiation Environments SO 2015 49TH ASILOMAR CONFERENCE ON SIGNALS, SYSTEMS AND COMPUTERS LA English DT Proceedings Paper CT 2015 49th Asilomar Conference on Signals, Systems and Computers CY NOV 08-11, 2015 CL Asilomar Hotel & Conference Grounds, Pacific Grove, CA SP IEEE Signal Proc Soc HO Asilomar Hotel & Conference Grounds DE Codes for Flash; Algebraic codes; Asymmetric errors; Radiation-induced errors ID ERROR-CORRECTING CODES; MEMORIES AB Research in coding for Flash devices typically deals with errors that occur during normal device operation. This work is instead concerned with codes that protect Flash devices that are experiencing errors caused by exposure to large radiation dosages. Such errors occur when, for example, Flash is used as onboard memory in satellites and space probes. In a previous paper, we examined the effects of errors on MLC Flash cells and introduced appropriate code constructions. In this work, we focus on the single level cell (SLC) case. We model the errors as being the result of a binary asymmetric channel (BASC). We show how to modify existing error-correcting codes in order to produce codes capable of correcting radiation-induced errors. Our approach focuses on finding and dealing with miscorrections, where an asymmetric decoder incorrectly deals with errors it is not designed to handle. C1 [Sala, Frederic; Schoeny, Clayton; Dolecek, Lara] Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90095 USA. [Divsalar, Dariush] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Sala, F (reprint author), Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90095 USA. EM fredsala@ucla.edu; cschoeny@ucla.edu; dariush.divsalar@jpl.nasa.gov; dolecek@ee.ucla.edu NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-8576-3 PY 2015 BP 844 EP 848 PG 5 WC Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BF2JA UT WOS:000380471900153 ER PT J AU Abid, MM Focardi, P Lee, DK Butman, SA Amaro, LR Imbriale, WA AF Abid, Mohamed M. Focardi, Paolo Lee, Dennis K. Butman, Stanley A. Amaro, Luis R. Imbriale, William A. GP IEEE TI SMAP Telecom and Science Antenna Multiple Interference SO 2015 9th European Conference on Antennas and Propagation (EuCAP) LA English DT Proceedings Paper CT 9th European Conference on Antennas and Propagation EuCAP CY MAY 13-17, 2015 CL Lisbon, PORTUGAL DE NASA SMAP Mission; reflector antenna; deployable mesh reflector; antenna measurements; multipath; telecom; S-band; X-band; low gain AB NASA's Soil Moisture Active Passive (SMAP) mission is a sun-synchronous low Earth orbit mission that will perform a global mapping of soil moisture and freeze/thaw state. The data collected will be useful in understanding the land/surface processes and the link between water, energy and carbon cycles. This will lead to better weather forecasting, and improve flood prediction and drought monitoring capability. SMAP uses a Radiometer and a Synthetic Aperture Radar (SAR) which share a high gain 6-meter diameter offset mesh reflector, fed by a dual polarization, dual band feed-horn. Two low gain antennas, one in S-band and one in X-band provide telecommunications. All these antennas and frequencies make SMAP an RF-rich environment that could corrupt telecom and/or contaminate science. This paper covers SMAP's telecom performance with interference due to multipath reflections from the 6-m reflector, verification challenges, and its mitigation. C1 [Abid, Mohamed M.; Focardi, Paolo; Lee, Dennis K.; Butman, Stanley A.; Amaro, Luis R.; Imbriale, William A.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Abid, MM (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-8-8907-0185-6 PY 2015 PG 4 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BF3ES UT WOS:000380533100774 ER PT J AU Chattopadhyay, G Reck, T Tang, A Jung-Kubiak, C Lee, C Siles, J Schlecht, E Kim, YM Chang, MCF Mehdi, I AF Chattopadhyay, Goutam Reck, Theodore Tang, Adrian Jung-Kubiak, Cecile Lee, Choonsup Siles, Jose Schlecht, Erich Kim, Yanghyo M. Chang, M-C F. Mehdi, Imran GP IEEE TI Compact Terahertz Instruments for Planetary Missions SO 2015 9th European Conference on Antennas and Propagation (EuCAP) LA English DT Proceedings Paper CT 9th European Conference on Antennas and Propagation EuCAP CY MAY 13-17, 2015 CL Lisbon, PORTUGAL DE Terahertz; Micromachining; DRIE; Antennas; planetary science ID LIMB SOUNDER MLS; SATELLITE AB Using newly developed silicon micromachining technology that enables low-mass and highly integrated receivers, we are developing a state-of-the-art terahertz radiometer/spectrometer instrument for planetary orbiter missions to Mars, Venus, Titan, and the Galilean moons. Our flexible receiver architecture provides a powerful instrument capability in a light-weight, low-power consuming compact package which offer unprecedented sensitivity performance, spectral coverage, and scalability to meet the scientific requirements of multiple missions. The instrument will allow a large number of chemical species, such as water, NO2, N2O, NH3, SO2, H2S, CH4, and HCN, among others, in the atmospheres of Mars, Venus, and Titan to be detected at concentrations below a part per billion. It will also be able to pinpoint their location in latitude, longitude, and in altitude. The maturation of this terahertz instrument will have an immediate impact on other areas such as multi-pixel focal plane heterodyne arrays for astrophysics and terahertz imagers and radars for a variety of national security applications. C1 [Chattopadhyay, Goutam; Reck, Theodore; Tang, Adrian; Jung-Kubiak, Cecile; Lee, Choonsup; Siles, Jose; Schlecht, Erich; Mehdi, Imran] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. [Tang, Adrian; Kim, Yanghyo M.; Chang, M-C F.] Univ Calif Los Angeles, Los Angeles, CA USA. RP Chattopadhyay, G (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. EM goutam@jpl.nasa.gov NR 14 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-8-8907-0185-6 PY 2015 PG 4 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BF3ES UT WOS:000380533100051 ER PT J AU Focardi, P Brown, PR Vacchione, JD Harrell, JA AF Focardi, Paolo Brown, Paula R. Vacchione, Joseph D. Harrell, Jefferson A. GP IEEE TI SMAP: Performance Verification and Testing of a Challenging Instrument Antenna SO 2015 9th European Conference on Antennas and Propagation (EuCAP) LA English DT Proceedings Paper CT 9th European Conference on Antennas and Propagation EuCAP CY MAY 13-17, 2015 CL Lisbon, PORTUGAL DE NASA SMAP Mission; reflector antenna; deployable mesh reflector; antenna measurements AB NASA's Soil Moisture Active and Passive (SMAP) Mission will soon provide global measurements of soil moisture and its freeze/thaw state. These data will be used to enhance our understanding of the processes that link water, energy and carbon cycles, and to extend the capabilities of weather and climate prediction models. Accurate predictions of the antenna radiation pattern are needed for instrument calibration but measurements of the flight reflector will not be performed. Therefore, requirement verification was accomplished through a combination of RF model predictions, scale model measurements and flight feed measurements. This paper provides an overview of this complex instrument antenna with particular emphasis on the challenges overcome during the development phases. A description of the RF model used to predict the SMAP antenna performance is provided along with an overview of the scale model measurement campaign. The excellent agreement between the RF model predictions and the scale model measurements allowed the use of the former as a means of verifying that the antenna met its challenging requirements. C1 [Focardi, Paolo; Brown, Paula R.; Vacchione, Joseph D.; Harrell, Jefferson A.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Focardi, P (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-8-8907-0185-6 PY 2015 PG 3 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BF3ES UT WOS:000380533100259 ER PT J AU Nessel, J Zemba, M Morse, J AF Nessel, James Zemba, Michael Morse, Jacquelynne GP IEEE TI Results from Three Years of Ka-band Propagation Characterization at Svalbard, Norway SO 2015 9th European Conference on Antennas and Propagation (EuCAP) LA English DT Proceedings Paper CT 9th European Conference on Antennas and Propagation EuCAP CY MAY 13-17, 2015 CL Lisbon, PORTUGAL DE radiometer; RF propagation measurements; Ka-band; polar climate AB Over the next several years, NASA plans to launch several earth science missions which are expected to achieve data throughputs of 5-40 terabits per day transmitted from low earth orbiting spacecraft to ground stations. The current S-band and X-band frequency allocations in use by NASA, however, are incapable of supporting the data rates required to meet this demand. As such, NASA is in the planning stages to upgrade its existing Near Earth Network (NEN) polar ground stations to support Ka-band (25.5-27 GHz) operations. Consequently, it becomes imperative that characterization of propagation effects at these NEN sites is conducted to determine expected system performance, particularly at low elevation angles (<10deg) where spacecraft signal acquisition typically occurs. Since May 2011, NASA Glenn Research Center has installed and operated a Ka-band radiometer at the NEN site located in Svalbard, Norway. The Ka-band radiometer monitors the water vapor line, as well as 4 frequencies around 26.5 GIz at a fixed 10 deg elevation angle. Three-year data collection results indicate good agreement with models and comparable performance to previously characterized northern latitude sites in the United States, i.e., Fairbanks, Alaska. The Svalbard data is used to derive availability results for an upcoming earth-observation mission, JPSS-1, and indicate a requirement of 4 dB of atmospheric attenuation margin necessary to close the link with 99% overall system availability for the expected LEO orbital cycle, as observed from the Svalbard location. C1 [Nessel, James; Zemba, Michael; Morse, Jacquelynne] NASA Glenn Res Ctr, Adv High Frequency Branch, Cleveland, OH 44135 USA. RP Nessel, J (reprint author), NASA Glenn Res Ctr, Adv High Frequency Branch, Cleveland, OH 44135 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-8-8907-0185-6 PY 2015 PG 5 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BF3ES UT WOS:000380533100715 ER PT J AU Nessel, J Zemba, M Morse, J Luini, L Riva, C AF Nessel, James Zemba, Michael Morse, Jacquelynne Luini, Lorenzo Riva, Carlo GP IEEE TI Preliminary Statistics from the NASA Alphasat Beacon Receiver in Milan, Italy SO 2015 9th European Conference on Antennas and Propagation (EuCAP) LA English DT Proceedings Paper CT 9th European Conference on Antennas and Propagation EuCAP CY MAY 13-17, 2015 CL Lisbon, PORTUGAL DE Alphasat; propagation; Q-band; measurement AB NASA Glenn Research Center (GRC) and the Politecnico di Milano (POLIMI) have initiated a joint propagation campaign within the framework of the Alphasat propagation experiment to characterize rain attenuation, scintillation, and gaseous absorption effects of the atmosphere in the 40 GHz band. NASA GRC has developed and installed a K/Q-band (20/40 GHz) beacon receiver at the POLIMI campus in Milan, Italy, which receives the 20/40 GHz signals broadcast from the Alphasat Aldo Paraboni TDP#5 beacon payload. The primary goal of these measurements is to develop a physical model to improve predictions of communications systems performance within the Q-band. Herein, we provide an overview of the design and data calibration procedure, and present 6 months of preliminary statistics of the NASA propagation terminal, which has been installed and operating in Milan since May 2014. The Q-band receiver has demonstrated a dynamic range of 40 dB at an 8-Hz sampling rate. A weather station with an optical disdrometer is also installed to characterize rain drop size distribution for correlation with physical based models. C1 [Nessel, James; Zemba, Michael; Morse, Jacquelynne] NASA Glenn Res Ctr, Cleveland, OH 44135 USA. [Luini, Lorenzo; Riva, Carlo] Politecn Milan, Dipartimento Elettron Informaz & Bioingn, Milan, Italy. RP Nessel, J (reprint author), NASA Glenn Res Ctr, Cleveland, OH 44135 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-8-8907-0185-6 PY 2015 PG 5 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BF3ES UT WOS:000380533100712 ER PT J AU Rahmat-Samii, Y Amaro, L Kovitz, JM AF Rahmat-Samii, Yahya Amaro, Luis Kovitz, Joshua M. GP IEEE TI Characterizing the Near Field Strength of ISS-RapidScat Reflector Antenna From Measurement Data Using Spectral Back Projection Method SO 2015 9th European Conference on Antennas and Propagation (EuCAP) LA English DT Proceedings Paper CT 9th European Conference on Antennas and Propagation EuCAP CY MAY 13-17, 2015 CL Lisbon, PORTUGAL DE antenna; back projection; FFT; near field; plane wave spectrum; measurement; reflector; space station AB A newly developed instrument, known as the Rapid Scatterometer (ISS-RapidScat), has been designed to replace QuickScat and SeaWinds in measuring ocean surface winds. The new design utilizes much of the engineering model hardware from SeaWinds. ISS RF safety requirements necessitated a blanker circuit that was designed to manage ISS-RapidScat interference on sensitive nearby objects such as spacecraft and humans. This required a detailed knowledge of the antenna near-field distribution and absolute strength, which can be challenging to obtain experimentally. This paper outlines a procedure to determine the near-field values with the knowledge of the measured far-field patterns and the radiated power. The accuracy of the method has been validated through many simulations. C1 [Rahmat-Samii, Yahya; Kovitz, Joshua M.] Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90024 USA. [Amaro, Luis] CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Rahmat-Samii, Y (reprint author), Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90024 USA. EM rahmat@ee.ucla.edu; luis.r.amaro@jpl.nasa.gov; jmkovitz@ucla.edu NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-8-8907-0185-6 PY 2015 PG 2 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BF3ES UT WOS:000380533100190 ER PT J AU Shemelya, CM Zemba, M Liang, M Espalin, D Kief, C Xin, H Wicker, RB MacDonald, EW AF Shemelya, C. M. Zemba, M. Liang, M. Espalin, D. Kief, C. Xin, H. Wicker, R. B. MacDonald, E. W. GP IEEE TI 3D PRINTING MULTI-FUNCTIONALITY: Embedded RF Antennas and Components SO 2015 9th European Conference on Antennas and Propagation (EuCAP) LA English DT Proceedings Paper CT 9th European Conference on Antennas and Propagation EuCAP CY MAY 13-17, 2015 CL Lisbon, PORTUGAL DE antenna; micro-strip 3D printing ID STRUCTURAL ELECTRONICS AB Significant research and press has recently focused on the fabrication freedom of Additive Manufacturing (AM) to create both conceptual models and final end-use products. This flexibility allows design modifications to be immediately reflected in 3D printed structures, creating new paradigms within the manufacturing process. 3D printed products will inevitably be fabricated locally, with unit-level customization, optimized to unique mission requirements. However, for the technology to be universally adopted, the processes must be enhanced to incorporate additional technologies; such as electronics, actuation, and electromagnetics. Recently, a novel 3D printing platform, Multi31 manufacturing, was funded by the presidential initiative for revitalizing manufacturing in the USA using 3D printing (America Makes - also known as the National Additive Manufacturing Innovation Intuitive). The Multi 3D system specifically targets 3D printed electronics in arbitrary form; and building upon the potential of this system, this paper describes RF antennas and components fabricated through the integration of material extrusion 3D printing with embedded wire, mesh, and RF elements. C1 [Shemelya, C. M.; Espalin, D.; Wicker, R. B.; MacDonald, E. W.] Univ Texas El Paso, WM Keck Ctr Innovat 3D, El Paso, TX 79968 USA. [Liang, M.; Xin, H.] Univ Arizona, Elect & Comp Engn, Tucson, AZ USA. [Zemba, M.] NASA Glenn Res Ctr, Cleveland, OH USA. Univ New Mexico, COSMIAC, Albuquerque, NM 87131 USA. RP Shemelya, CM (reprint author), Univ Texas El Paso, WM Keck Ctr Innovat 3D, El Paso, TX 79968 USA. NR 14 TC 0 Z9 0 U1 3 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-8-8907-0185-6 PY 2015 PG 5 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BF3ES UT WOS:000380533100669 ER PT J AU Ahmad, T Bebis, G Nicolescu, M Nefian, A Fong, T AF Ahmad, Touqeer Bebis, George Nicolescu, Monica Nefian, Ara Fong, Terry GP IEEE TI An Edge-Less Approach to Horizon Line Detection SO 2015 IEEE 14TH INTERNATIONAL CONFERENCE ON MACHINE LEARNING AND APPLICATIONS (ICMLA) LA English DT Proceedings Paper CT IEEE 14th International Conference on Machine Learning and Applications ICMLA CY DEC 09-11, 2015 CL Miami, FL SP IEEE, AML&A ID AIRCRAFT AB Horizon line is a promising visual cue which can be exploited for robot localization or visual geo-localization. Prominent approaches to horizon line detection rely on edge detection as a pre-processing step which is inherently a non-stable approach due to parameter choices and underlying assumptions. We present a novel horizon line detection approach which uses machine learning and Dynamic Programming (DP) to extract the horizon line from a classification map instead of an edge map. The key idea is assigning a classification score to each pixel, which can be interpreted as the likelihood of the pixel belonging to the horizon line, and representing the classification map as a multi-stage graph. Using DP, the horizon line can be extracted by finding the path that maximizes the sum of classification scores. In contrast to edge maps which are typically binary (edge vs no-edge) and contain gaps, classification maps are continuous and contain no gaps, yielding significantly better solutions. Using classification maps instead of edge maps allows for removing certain assumptions such as the horizon is close to the top of the image or that the horizon forms a straight line. The purpose of these assumptions is to bias the DP solution but they fail to produce good results when they are not valid. We demonstrate our approach on three different data sets and provide comparisons with a traditional approach based on edge maps. Although our training set is comprised of a very small number of images from the same location, our results illustrate that our method generalizes well to images acquired under different conditions and geographical locations. C1 [Ahmad, Touqeer; Bebis, George; Nicolescu, Monica] Univ Nevada, Dept Comp Sci & Engn, Reno, NV 89557 USA. [Nefian, Ara; Fong, Terry] NASA, Ames Res Ctr, Washington, DC 20546 USA. RP Ahmad, T (reprint author), Univ Nevada, Dept Comp Sci & Engn, Reno, NV 89557 USA. EM ahmad@cse.unr.edu; bebis@cse.unr.edu; monica@cse.unr.edu; ara.nefian@nasa.gov; terry.fong@nasa.gov NR 30 TC 0 Z9 0 U1 1 U2 1 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS BN 978-1-5090-0287-0 PY 2015 BP 1095 EP 1102 DI 10.1109/ICMLA.2015.67 PG 8 WC Computer Science, Cybernetics SC Computer Science GA BF2NR UT WOS:000380483600190 ER PT J AU Iturbe, X Keymeulen, D Yiu, P Berisford, D Hand, K Carlson, R Ozer, E AF Iturbe, Xabier Keymeulen, Didier Yiu, Patrick Berisford, Dan Hand, Kevin Carlson, Robert Ozer, Emre GP IEEE TI A Highly-Efficient, Adaptive and Fault-Tolerant SoC Implementation of a Fourier Transform Spectrometer Data Processing SO 2015 IEEE 23rd Annual International Symposium on Field-Programmable Custom Computing Machines (FCCM) LA English DT Proceedings Paper CT 2015 IEEE 23rd Annual International Symposium on Field-Programmable Custom Computing Machines (FCCM) CY MAY 03-05, 2015 CL Vancouver, CANADA SP Computer Society Techn Committe on Computer Architecture, IEEE, IEEE COMPUTER SOCIETY, XILINX, Microsoft, CMC, HUAWEI, LATTICE, DSP, picocomputing, ALTERA, VectorBlox, CYPRESS, synopsys, TOPIC, VP Academ, irmacs, SFU Faculty of Applied Sciences, Atomic Rules, ALGO-LOGIC AB We present here one of the first research efforts conducted at Jet Propulsion Laboratory (JPL) to implement on a single chip (Xilinx Zynq) all the functionality necessary to control a NASA instrument, namely a Fourier Transform Spectrometer (FTS) that is proposed for deployment on future missions to Jupiter's moon Europa. The system requires custom logic to process the data delivered by the instrument, and software, to perform floating-point operations and to drive the interface with the main spacecraft computer. Three features are central in our SoC FTS implementation: (1) Efficiency, as the system achieves a high data processing throughput at relatively low power consumption, (2) Adaptivity, as the system can be configured from Earth based on the data observed while exploring a priori unknown space environments and (3) Fault-Tolerance, as the system needs to operate in the harsh radiation Jupiter magnetosphere where Europa orbits. C1 [Iturbe, Xabier; Yiu, Patrick] CALTECH, Pasadena, CA 91125 USA. [Keymeulen, Didier; Berisford, Dan; Hand, Kevin; Carlson, Robert] CALTECH, NASA Jet Prop Lab, Pasadena, CA 91125 USA. [Iturbe, Xabier; Ozer, Emre] ARM R&D, Cambridge, England. RP Iturbe, X (reprint author), CALTECH, Pasadena, CA 91125 USA. EM xabier.iturbe@jpl.nasa.gov NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-9969-9 PY 2015 BP 231 EP 231 DI 10.1109/FCCM.2015.26 PG 1 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF3AZ UT WOS:000380517700053 ER PT J AU Boerner, WM Krieger, G Reigber, A Hajnsek, I Schmullius, CC Moreira, A Eineder, M Bamler, R Meyer, FJ Hensley, S vanZyl, JJ Neumann, M Shimada, M Ohki, M Sumantyo, JTS Hattori, K Ocampo-Torres, FJ Ponce, O Moreira, J Campos, J Lu, YL Dubois-Fernandez, P Pottier, E LeToan, T Surussavadee, C Koo, VC Lim, TS Triharjanto, RH Hasbi, W Mohan, S Singh, G AF Boerner, Wolfgang-Martin Krieger, Gerhard Reigber, Andreas Hajnsek, Irena Schmullius, Christiane C. Moreira, Alberto Eineder, Michael Bamler, Richard Meyer, Franz-Josef Hensley, Scott vanZyl, Jakob. J. Neumann, Maxim Shimada, Masanobu Ohki, Masato Sumantyo, Josaphat Tetuko Sri Hattori, Katsumi Ocampo-Torres, Francisco J. Ponce, Octavio Moreira, Joao Campos, Joao Lu Yi-Long Dubois-Fernandez, Pascale Pottier, Eric Thuy LeToan Surussavadee, Chinnawat Koo, Voon-Chet Lim, Tien-Sze Triharjanto, R. Heru Hasbi, Wahyudi Mohan, Shiv Singh, Gulab GP IEEE TI Development of new multi-band equatorially orbiting POLinSAR satellite sensors system configurations for varying latitudinal coverage within total tropical belt SO 2015 IEEE 5TH ASIA-PACIFIC CONFERENCE ON SYNTHETIC APERTURE RADAR (APSAR) LA English DT Proceedings Paper CT IEEE 5th Asia-Pacific Conference on Synthetic Aperture Radar (APSAR) CY SEP 01-04, 2015 CL Marina Bay Sands, SINGAPORE SP ST Electroni, NANYANG TECHNOLOGICAL UNIV, DSO, AIRBUS DEFENCE & SPACE, TEXAS INSTRUMENT, HARRIS, SIIS, ThalesAlenia, AIR FORCE OFF OF SCI RES USA, ASIAN OFF OF AEROSPAE R&D, US ARMY RDECOM, ARROW DE Polarization radar; Polarimetric Synthetic Aperture Radar (SAR); Environmental remote sensing; Geophysical monitoring; Tropical Equatorial Belt (TEB); Surveillance; Natural and manmade hazard detection; Disaster assessment and reduction; Equatorial orbiting satellite sensors AB The relevance of this challenging still unresolved development of multi-band equatorially orbiting fully polarimetric POLinSAR satellite configurations to the entire terrestrial globe will be highlighted. Special attention will be given to generation of global weather phenomena, supply of an ever more relevant stable food base, extraction of mineral and energy resources with its implicit local environmental deterioration, and of more successfully securing bio-diversity. All of these daunting natural hazards of top international priority should justify the immense financial resources required for pursuing this timely and urgently to be realized proposal. In retrospect, collaboration with additional international National Research Centers involved in advancing multi-band POLinSAR satellite sensors is sincerely desired and so is the financial support from our national, regional and international governmental sponsors - foremost the United Nations. The proposer (author) and dedicated collaborators consider APSAR-2015 to be the ideal forum for introducing this timely proposal, well suited for the Lead-Session of Space- & Air-borne SAR Systems and Missions. C1 [Boerner, Wolfgang-Martin] UIC ECE CSN Lab, Chicago, IL USA. [Krieger, Gerhard; Reigber, Andreas; Hajnsek, Irena; Schmullius, Christiane C.; Moreira, Alberto] DLR IHR, Oberpfaffenhofen, Germany. [Eineder, Michael; Bamler, Richard; Ponce, Octavio] DLR IFM, Oberpfaffenhofen, Germany. [Meyer, Franz-Josef] UAF GI, Earth & Planetary Remote Sensing Ctr, Fairbanks, AK USA. [Hensley, Scott; vanZyl, Jakob. J.; Neumann, Maxim] NASA JPL, Pasadena, CA USA. [Shimada, Masanobu; Ohki, Masato] JAXA EORC, Tsukuba, Ibaraki, Japan. [Sumantyo, Josaphat Tetuko Sri; Hattori, Katsumi] CEReS MRSL Chiba U, Inage Ku, Chiba, Japan. RP Boerner, WM (reprint author), UIC ECE CSN Lab, Chicago, IL USA. EM wmb1uic@yhoo.com; gerhard.krieger@dlr.de; michael.eineder@dlr.de; fmeyer@gi.alaska.edu; Scott.hensley@nasa.gov; shimada.masnobu@jaxa.jp; teukoss@faculty.chiba-u.jp; ocampos@cicese.mx; joao.moreira@bradar.com.br; eylu@ntu.edu.sg; pdubois@onera.fr; pop@alum.mit.edu; vckoo@mmu.edu.my; rtriharjanto@yahoo.com; shivmohan.isro@gmail.com RI Moreira, Alberto/C-1147-2013; Krieger, Gerhard/D-5164-2012 OI Moreira, Alberto/0000-0002-3436-9653; Krieger, Gerhard/0000-0002-4548-0285 NR 9 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-7297-8 PY 2015 BP 342 EP 345 PG 4 WC Engineering, Electrical & Electronic; Remote Sensing SC Engineering; Remote Sensing GA BF1UX UT WOS:000380439100083 ER PT J AU Hensley, S Smrekar, S Shaffer, S Paller, M Figueroa, H Freeman, A Hodges, R Walkemeyer, P AF Hensley, Scott Smrekar, Suzanne Shaffer, Scott Paller, Mimi Figueroa, Harry Freeman, Anthony Hodges, Richard Walkemeyer, Philip GP IEEE TI VISAR: A Next Generation Interferometric Radar for Venus Exploration SO 2015 IEEE 5TH ASIA-PACIFIC CONFERENCE ON SYNTHETIC APERTURE RADAR (APSAR) LA English DT Proceedings Paper CT IEEE 5th Asia-Pacific Conference on Synthetic Aperture Radar (APSAR) CY SEP 01-04, 2015 CL Marina Bay Sands, SINGAPORE SP ST Electroni, NANYANG TECHNOLOGICAL UNIV, DSO, AIRBUS DEFENCE & SPACE, TEXAS INSTRUMENT, HARRIS, SIIS, ThalesAlenia, AIR FORCE OFF OF SCI RES USA, ASIAN OFF OF AEROSPAE R&D, US ARMY RDECOM, ARROW AB Magellan, a NASA mission to Venus in the early 1990s, mapped nearly the entire surface of Venus with an S-band (12 cm) synthetic aperture radar and microwave radiometer and made radar altimeter measurements of the topography, [1]. These measurements revolutionized our understanding of the geomorphology, geology and geophysical processes that have shaped the evolution of the surface of Venus. However, the lack of finer resolution imagery and topography of the surface than that obtained by the Magellan mission has hampered the definitive answer to key questions concerning the processes and evolution of the surface of Venus. The Venus Emissivity, Radio Science, InSAR Topography And Spectroscopy (VERITAS) Mission is a proposed mission to Venus designed to obtain high resolution imagery and topography of the surface using an X-band radar configured as a single pass radar interferometer (called VISAR) coupled with a multispectral NIR emissivity mapping sensor. C1 [Hensley, Scott; Smrekar, Suzanne; Shaffer, Scott; Paller, Mimi; Figueroa, Harry; Freeman, Anthony; Hodges, Richard; Walkemeyer, Philip] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Hensley, S (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Scott.Hensley@jpl.nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-7297-8 PY 2015 BP 362 EP 366 PG 5 WC Engineering, Electrical & Electronic; Remote Sensing SC Engineering; Remote Sensing GA BF1UX UT WOS:000380439100085 ER PT J AU Hensley, S Moller, D Kwok, R Wu, XQ Oveisgharan, S Michel, T AF Hensley, Scott Moller, Delwyn Kwok, Ronald Wu, Xiaoqing Oveisgharan, Shadi Michel, Thierry GP IEEE TI Interferometric Penetration Into Dry Snow and Sea Ice at Ka-band SO 2015 IEEE 5TH ASIA-PACIFIC CONFERENCE ON SYNTHETIC APERTURE RADAR (APSAR) LA English DT Proceedings Paper CT IEEE 5th Asia-Pacific Conference on Synthetic Aperture Radar (APSAR) CY SEP 01-04, 2015 CL Marina Bay Sands, SINGAPORE SP ST Electroni, NANYANG TECHNOLOGICAL UNIV, DSO, AIRBUS DEFENCE & SPACE, TEXAS INSTRUMENT, HARRIS, SIIS, ThalesAlenia, AIR FORCE OFF OF SCI RES USA, ASIAN OFF OF AEROSPAE R&D, US ARMY RDECOM, ARROW AB Ice sheet topography in Greenland and Antartica and sea ice thickness are integral measurements to quantifying and understanding the impact of climate to the Earth's environment. Multiple sensors, lidars, radars and optical systems have been used to make such measurements. To allow maximal flexibility in making such measurements and to utilize the beneficial characteristics of each measurement type it is essential to understand exactly where within the ice volume each sensor type is making its measurement. This paper examines interferometric radar penetration at Ka-band made by the GLISTIN instrument in the dry snow regions of Greenland and over sea ice in the Beaufort Sea in Alaska. C1 [Hensley, Scott; Kwok, Ronald; Wu, Xiaoqing; Oveisgharan, Shadi; Michel, Thierry] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Moller, Delwyn] Remote Sensing Solut, Barnstable, MA 02630 USA. RP Hensley, S (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Scott.Hensley@jpl.nasa.gov; dkmoller@remotesensingsolutions.com NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-7297-8 PY 2015 BP 809 EP 814 PG 6 WC Engineering, Electrical & Electronic; Remote Sensing SC Engineering; Remote Sensing GA BF1UX UT WOS:000380439100187 ER PT J AU Lindvall, M Ganesan, D Ardal, R Wiegand, RE AF Lindvall, Mikael Ganesan, Dharmalingam Ardal, Ragnar Wiegand, Robert E. GP IEEE TI Metamorphic Model-based Testing Applied on NASA DAT -an experience report SO 2015 IEEE/ACM 37th IEEE International Conference on Software Engineering, Vol 2 LA English DT Proceedings Paper CT IEEE/ACM 2nd International Workshop on Software Architecture and Metrics (SAM) CY MAY 16-16, 2015 CL Florence, ITALY SP IEEE computer society, Technical Council on Software Engineering, Association for Computing Machinery, SPECIAL INTEREST GROUP IN SOFTWARE ENGINEERING, Advancing computing as a science & Profession AB Testing is necessary for all types of systems, but becomes difficult when the tester cannot easily determine whether the system delivers the correct result or not. NASA's Data Access Toolkit allows NASA analysts to query a large database of telemetry data. Since the user is unfamiliar with the data and several data transformations can occur, it is impossible to determine whether the system behaves correctly or not in full scale production situations. Small scale testing was already conducted manually by other teams and unit testing was conducted on individual functions. However, there was still a need for full scale acceptance testing on a broad scale. We describe how we addressed this testing problem by applying the idea of metamorphic testing [1]. Specifically, we base it on equivalence of queries and by using the system itself for testing. The approach is implemented using a model-based testing approach in combination with a test data generation and test case outcome analysis strategy. We also discuss some of the issues that were detected using this approach. C1 [Lindvall, Mikael; Ganesan, Dharmalingam; Ardal, Ragnar] Fraunhofer USA Ctr Expt Software Engn CESE, College Pk, MD 20740 USA. [Ardal, Ragnar] Reykjavik Univ, Sch Comp Sci, Reykjavik, Iceland. [Wiegand, Robert E.] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. RP Lindvall, M (reprint author), Fraunhofer USA Ctr Expt Software Engn CESE, College Pk, MD 20740 USA. NR 10 TC 6 Z9 6 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-1934-5 PY 2015 BP 129 EP 138 DI 10.1109/ICSE.2015.348 PG 10 WC Computer Science, Software Engineering; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF3SC UT WOS:000380572400015 ER PT J AU Denney, E Pai, G Habli, I AF Denney, Ewen Pai, Ganesh Habli, Ibrahim GP IEEE TI Dynamic Safety Cases for Through-life Safety Assurance SO 2015 IEEE/ACM 37th IEEE International Conference on Software Engineering, Vol 2 LA English DT Proceedings Paper CT IEEE/ACM 2nd International Workshop on Software Architecture and Metrics (SAM) CY MAY 16-16, 2015 CL Florence, ITALY SP IEEE computer society, Technical Council on Software Engineering, Association for Computing Machinery, SPECIAL INTEREST GROUP IN SOFTWARE ENGINEERING, Advancing computing as a science & Profession DE Dynamic safety case; Safety assurance; Lifecycle processes; Safety management AB We describe dynamic safety cases, a novel operationalization of the concept of through-life safety assurance, whose goal is to enable proactive safety management. Using an example from the aviation systems domain, we motivate our approach, its underlying principles, and a lifecycle. We then identify the key elements required to move towards a formalization of the associated framework. C1 [Denney, Ewen; Pai, Ganesh] NASA, Ames Res Ctr, SGT, Moffett Field, CA 94035 USA. [Habli, Ibrahim] Univ York, Dept Comp Sci, York YO10 5DD, N Yorkshire, England. RP Denney, E (reprint author), NASA, Ames Res Ctr, SGT, Moffett Field, CA 94035 USA. EM ewen.denney@nasa.gov; ganesh.pai@nasa.gov; ibrahim.habli@york.ac.uk NR 17 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-1934-5 PY 2015 BP 587 EP 590 DI 10.1109/ICSE.2015.199 PG 4 WC Computer Science, Software Engineering; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF3SC UT WOS:000380572400077 ER PT J AU Grechanik, M Alonso, J Nikora, AP AF Grechanik, Mark Alonso, Javier Nikora, Allen P. GP IEEE TI 1st International Workshop on Complex faUlts and Failures in LargE Software Systems (COUFLESS 2015) SO 2015 IEEE/ACM 37th IEEE International Conference on Software Engineering, Vol 2 LA English DT Proceedings Paper CT IEEE/ACM 2nd International Workshop on Software Architecture and Metrics (SAM) CY MAY 16-16, 2015 CL Florence, ITALY SP IEEE computer society, Technical Council on Software Engineering, Association for Computing Machinery, SPECIAL INTEREST GROUP IN SOFTWARE ENGINEERING, Advancing computing as a science & Profession DE Workshop; Mandelbug; failure; debugging AB COUFLESS is a one-day workshop that starts with keynote speaker, Prof. Kishor S. Trivedi from Duke University, North Carolina, USA whose talk's title is titled: "Why Does Software Fail and What Should be Done About It?" A total of 15 papers were submitted to COUFLESS with 53 authors from nine countries and each paper received at least three reviews by the 26 members of the program committee from 11 countries, making it a truly International Workshop. After a long discussion, 11 papers were accepted with the acceptance rate of 73%. Accepted papers address the issues of localizing and debugging complex faults in large-scale software applications. C1 [Grechanik, Mark] Univ Illinois, Chicago, IL 60612 USA. [Alonso, Javier] Univ Leon, Res Inst Appl Sci Cybersecur, E-24071 Leon, Spain. [Alonso, Javier] Duke Univ Corp, Durham, NC USA. [Nikora, Allen P.] Jet Prop Lab, Los Angeles, CA USA. RP Grechanik, M (reprint author), Univ Illinois, Chicago, IL 60612 USA. EM drmark@uic.edu; javier.alonso@unileon.es; allen.p.nikora@jpl.nasa.go NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-1934-5 PY 2015 BP 971 EP 972 DI 10.1109/ICSE.2015.310 PG 2 WC Computer Science, Software Engineering; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF3SC UT WOS:000380572400190 ER PT J AU Stang, J Chen, GB Haynes, M Moghaddam, M AF Stang, John Chen, Guanbo Haynes, Mark Moghaddam, Mahta GP IEEE TI Advances in Real-Time Non-Contact Monitoring of Medical Thermal Treatment Through Multistatic Array Microwave Imaging SO 2015 IEEE CONFERENCE ON ANTENNA MEASUREMENTS & APPLICATIONS (CAMA) LA English DT Proceedings Paper CT IEEE Conference on Antenna Measurements (CAMA) CY NOV 30-DEC 02, 2015 CL Electrical Engineering/Electronics, Computer, Telecommunications and Infor, Chiang Mai, THAILAND SP IEEE Antennas and Propagation Society, Electrical Engineering/Electronics, Computer, Telecommunications and Information Technology (ECTI) Association, IEEE Thailand Section, IEEE MTT/AP/ED Thailand chapter HO Electrical Engineering/Electronics, Computer, Telecommunications and Infor AB In this paper, we present some recent advances in real-time non-contact monitoring of thermal treatment through multistatic array imaging. The work presented was primarily motivated by the need to improve the flexibility and computational efficiency of the forward modeling of microwave imaging systems in general and of our real-time microwave thermal monitoring system in particular. Specifically, we have developed a conformal finite-difference time domain (CFDTD) solver that addresses several limitations inherent to our previously reported forward modeling methods. In particular, this CFDTD solver has enabled the implementation of a fully integrated numerical vector Green's function that addresses the task of linking the object's scattered field to the measured scattered voltage in a more general and flexible way than the waveport vector Green's function method used in our earlier work. Both the CFDTD solver and the integrated numerical Green's function are validated for a prototype microwave imaging cavity through comparison with CST Microwave Studio. These validated methods are currently being used in an ongoing experimental characterization of microwave imaging for both dielectric reconstruction and real-time thermal monitoring. C1 [Stang, John; Chen, Guanbo; Moghaddam, Mahta] Univ Southern Calif, Dept Elect Engn Electrophys, Los Angeles, CA 90089 USA. [Haynes, Mark] Jet Prop Lab, Pasadena, CA 91109 USA. RP Stang, J (reprint author), Univ Southern Calif, Dept Elect Engn Electrophys, Los Angeles, CA 90089 USA. NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-9149-8 PY 2015 PG 4 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BF1UK UT WOS:000380437900005 ER PT J AU Kim, D Hwang, BW Han, JW Seol, ML Oh, Y Choi, YK AF Kim, Daewon Hwang, Byeong-Woon Han, Jin-Woo Seol, Myeong-Lok Oh, Yura Choi, Yang-Kyu GP IEEE TI Output Enhancement of Triboelectric Energy Harvester by Micro-Porous Triboelectric Layer SO 2015 IEEE INTERNATIONAL ELECTRON DEVICES MEETING (IEDM) LA English DT Proceedings Paper CT IEEE International Electron Devices Meeting (IEDM) CY DEC 07-09, 2015 CL Washington, DC ID GENERATOR; NANOGENERATOR AB A micro-porous polymer film is utilized as a triboelectric layer of triboelectric energy harvester. The relationship between porosity of the triboelectric layer and output characteristics is analyzed for the first time. There are two key parameters found to influence the output performance of the triboelectric energy harvester: the surface charge density and effective capacitance of the triboelectric layer. Experiment, modeling, and simulation based on electrodynamics are performed to investigate how the two parameters affect the output performance. C1 [Kim, Daewon; Hwang, Byeong-Woon; Seol, Myeong-Lok; Oh, Yura; Choi, Yang-Kyu] Korea Adv Inst Sci & Technol, Sch Elect Engn, Daejeon 305701, South Korea. [Han, Jin-Woo] NASA Ames, Moffett Field, CA 94035 USA. RP Choi, YK (reprint author), Korea Adv Inst Sci & Technol, Sch Elect Engn, Daejeon 305701, South Korea. EM ykchoi@ee.kaist.ac.kr NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-9894-7 PY 2015 PG 4 WC Engineering, Electrical & Electronic SC Engineering GA BF2JG UT WOS:000380472500124 ER PT J AU Jow, TR MacDougall, FW Ennis, JB Yang, XH Schneider, MA Scozzie, CJ White, JD MacDonald, JR Schalnat, MC Cooper, RA Yen, SPS AF Jow, T. R. MacDougall, F. W. Ennis, J. B. Yang, X. H. Schneider, M. A. Scozzie, C. J. White, J. D. MacDonald, J. R. Schalnat, M. C. Cooper, R. A. Yen, S. P. S. GP IEEE TI PULSED POWER CAPACITOR DEVELOPMENT AND OUTLOOK SO 2015 IEEE PULSED POWER CONFERENCE (PPC) LA English DT Proceedings Paper CT 2015 IEEE Pulsed Power Conference (PPC) CY MAY 31-JUN 04, 2015 CL Austin, TX AB Pulsed power capacitors are one of the key components the pulsed power systems for applications in mobile platforms including vehicles, ships and airplanes. The advances of capacitor technology have evolved slowly but steadily in the past 25 years. The energy density of large format millisecond discharge capacitors in >50 kJ sizes has been increased from 0.7 J/cc in the early 1990s to >2.4 J/cc in the 2010s with lifetimes over 10,000 shots. The energy density of microsecond discharge capacitors has been increased from 0.7 J/cc with a DC life less than 100 hours in early 1990s to 1.3 J/cc with a DC life of 2000 hours. The self-healing electrode has been the key to achieving higher energy density capacitors. The fault tolerance provided by these electrodes enables reliable operation near intrinsic breakdown strengths. In addition, the availability of higher quality and thinner biaxially oriented polypropylene (BOPP) film starting 2000s has contributed significantly by increasing the intrinsic breakdown strength of the films themselves. Coupled with design improvements, capacitors based on BOPP film have had significant, order-of-magnitude scale improvements in peak energy densities and peak power densities. The unfortunate consequence of this development is that these technologies have reached a point of diminishing returns, leading to significant efforts to develop new films to replace BOPP. We take this opportunity to review the advances and reflect what works so far to think about the future path. C1 [Jow, T. R.; Scozzie, C. J.] US Army Res Lab, Adelphi, MD 20783 USA. [Ennis, J. B.] NWL Capacitors, Beach, FL 33404 USA. [Yang, X. H.] CSI Technol, Vista, CA 92081 USA. [Schneider, M. A.; MacDonald, J. R.; Schalnat, M. C.; Cooper, R. A.] Gen Atom, San Diego, CA 92127 USA. [White, J. D.] US Army TARDEC, Warren, MI 48397 USA. [Yen, S. P. S.] Jet Prop Lab, Pasadena, CA 91109 USA. RP Jow, TR (reprint author), US Army Res Lab, Adelphi, MD 20783 USA. EM t.r.jow.civ@mail.mil NR 23 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-8403-9 PY 2015 PG 7 WC Engineering, Electrical & Electronic SC Engineering GA BF1SW UT WOS:000380434000185 ER PT J AU Bock, A Pembroke, A Mays, ML Rastaetter, L Ynnerman, A Ropinski, T AF Bock, Alexander Pembroke, Asher Mays, M. Leila Rastaetter, Lutz Ynnerman, Anders Ropinski, Timo BE Ahrens, J Qu, H Roerdink, J TI Visual Verification of Space Weather Ensemble Simulations SO 2015 IEEE Scientific Visualization Conference (SciVis) LA English DT Proceedings Paper CT 2015 IEEE Scientific Visualization Conference CY OCT 25-30, 2015 CL Chicago, IL SP IEEE, IEEE Comp Soc, IEEE Visualizat & Graph Tech Comm DE Visual Verification; Space Weather; Coronal Mass Ejections; Ensemble ID UNCERTAINTY; FIELD; MODEL; TOOL AB We propose a system to analyze and contextualize simulations of coronal mass ejections. As current simulation techniques require manual input, uncertainty is introduced into the simulation pipeline leading to inaccurate predictions that can be mitigated through ensemble simulations. We provide the space weather analyst with a multi-view system providing visualizations to: 1. compare ensemble members against ground truth measurements, 2. inspect time-dependent information derived from optical flow analysis of satellite images, and 3. combine satellite images with a volumetric rendering of the simulations. This three-tier workflow provides experts with tools to discover correlations between errors in predictions and simulation parameters, thus increasing knowledge about the evolution and propagation of coronal mass ejections that pose a danger to Earth and interplanetary travel. C1 [Bock, Alexander; Ynnerman, Anders] Linkoping Univ, S-58183 Linkoping, Sweden. [Pembroke, Asher; Mays, M. Leila; Rastaetter, Lutz] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Ropinski, Timo] Univ Ulm, D-89069 Ulm, Germany. RP Bock, A (reprint author), Linkoping Univ, S-58183 Linkoping, Sweden. EM alexander.bock@liu.se; asher.d.pembroke@nasa.gov; m.leila.mays@nasa.gov; lutz.rastaetter@nasa.gov; anders.ynnerman@liu.se; timo.ropinski@uni-ulm.de NR 25 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-9785-8 PY 2015 BP 17 EP 24 PG 8 WC Computer Science, Software Engineering; Imaging Science & Photographic Technology SC Computer Science; Imaging Science & Photographic Technology GA BF3PE UT WOS:000380564400003 ER PT J AU Weiss, S Brockers, R Albrektsen, S Matthies, L AF Weiss, Stephan Brockers, Roland Albrektsen, Sigurd Matthies, Larry GP IEEE TI Inertial Optical Flow for Throw-And-Go Micro Air Vehicles SO 2015 IEEE Winter Conference on Applications of Computer Vision (WACV) LA English DT Proceedings Paper CT IEEE Winter Conference on Applications of Computer Vision (WACV 2015) CY JAN 06-09, 2015 CL Waikoloa, HI SP IEEE, IEEE Comp Soc, IEEE Biometrics Council, Amazon AB In this paper, we describe a novel method using only optical flow from a single camera and inertial information to quickly initialize, deploy, and autonomously stabilize an inherently unstable aerial vehicle. Our approach requires a minimal number of tracked features in only two consecutive frames and inertial readings eliminating the need of long feature tracks or local maps and rendering it inherently fail-safe. We show theoretically, in simulation, and in real experiments that we can reliably estimate and control the vehicle velocity, full attitude, and metric distance to the scene while self-calibrating inertial intrinsics and sensor extrinsics. In fact, the fast initialization, self-calibration, and inherent fail-safe property leads to the first visual-inertial throw-and-go capable system. C1 [Weiss, Stephan; Brockers, Roland; Albrektsen, Sigurd; Matthies, Larry] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Weiss, S (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. EM stephan.weiss@ieee.org; brockers@jpl.nasa.gov; sigurd.albrektsen@itk.ntnu.no; lhm@jpl.nasa.gov NR 18 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-6683-7 PY 2015 BP 262 EP 269 DI 10.1109/WACV.2015.42 PG 8 WC Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF3EN UT WOS:000380532600035 ER PT J AU Xia, L Gori, I Aggarwal, JK Ryoo, MS AF Xia, Lu Gori, Ilaria Aggarwal, J. K. Ryoo, M. S. GP IEEE TI Robot-Centric Activity Recognition from First-Person RGB-D Videos SO 2015 IEEE Winter Conference on Applications of Computer Vision (WACV) LA English DT Proceedings Paper CT IEEE Winter Conference on Applications of Computer Vision (WACV 2015) CY JAN 06-09, 2015 CL Waikoloa, HI SP IEEE, IEEE Comp Soc, IEEE Biometrics Council, Amazon AB We present a framework and algorithm to analyze first-person RGBD videos captured from the robot while physically interacting with humans. Specifically, we explore reactions and interactions of persons facing a mobile robot from a robot centric view. This new perspective offers social awareness to the robots, enabling interesting applications. As far as we know, there is no public 3D dataset for this problem. Therefore, we record two multi-modal first-person RGBD datasets that reflect the setting we are analyzing. We use a humanoid and a non-humanoid robot equipped with a Kinect. Notably, the videos contain a high percentage of ego-motion due to the robot self-exploration as well as its reactions to the persons' interactions. We show that separating the descriptors extracted from ego-motion and independent motion areas, and using them both, allows us to achieve superior recognition results. Experiments show that our algorithm recognizes the activities effectively and outperforms other state-of-the-art methods on related tasks. C1 [Xia, Lu; Gori, Ilaria; Aggarwal, J. K.] Univ Texas Austin, Dept ECE, Austin, TX 78712 USA. [Gori, Ilaria] Ist Italiano Tecnol, iCub Facil, Genoa, Italy. [Ryoo, M. S.] CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Xia, L (reprint author), Univ Texas Austin, Dept ECE, Austin, TX 78712 USA. EM xialu@utexas.edu; ilaria.gori@iit.it; aggarwaljk@mail.utexas.edu; mryoo@jpl.nasa.gov NR 27 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-6683-7 PY 2015 BP 357 EP 364 DI 10.1109/WACV.2015.54 PG 8 WC Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF3EN UT WOS:000380532600047 ER PT J AU Cheng, Y Matthies, LH AF Cheng, Yang Matthies, Larry H. GP IEEE TI Stereovision Bias Removal by Autocorrelation SO 2015 IEEE Winter Conference on Applications of Computer Vision (WACV) LA English DT Proceedings Paper CT IEEE Winter Conference on Applications of Computer Vision (WACV 2015) CY JAN 06-09, 2015 CL Waikoloa, HI SP IEEE, IEEE Comp Soc, IEEE Biometrics Council, Amazon AB Subpixel interpolation of stereo disparity is essential to achieve adequate range resolution for many applications, especially in autonomous navigation. Subpixel interpolation is plagued by systematic biases caused by pixel-locking, foreshortening, and scaling phenomena. Prior work on this problem has produced partial solutions or solutions that are undesirably slow for real-time applications. We describe a new algorithm - Stereovision Bias Removal by Autocorrelation (SBRA) - to correct these biases. SBRA addresses all three of these causes of bias, achieving 0.02 pixel RMS disparity error in synthetic stereo image data and a significant error reduction on real stereo images for which no ground truth is available. SBRA is simple and fast, increasing the runtime of a sum square difference (SSD) stereo matching algorithm by about 10%. C1 [Cheng, Yang; Matthies, Larry H.] Jet Prop Lab, Pasadena, CA USA. RP Cheng, Y (reprint author), Jet Prop Lab, Pasadena, CA USA. EM ycheng@jpl.nasa.gov; lhm@jpl.nasa.gov NR 21 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-6683-7 PY 2015 BP 1153 EP 1160 DI 10.1109/WACV.2015.158 PG 8 WC Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF3EN UT WOS:000380532600151 ER PT S AU El Ghazaly, MOA Dehnel, M Defrance, P AF El Ghazaly, Mohamed O. A. Dehnel, Morgan Defrance, Pierre BE Doyle, BL Glass, GA McDaniel, FD Wang, Y Parriott, CR TI Development of a High Resolution Analyzing Magnet System for Heavy Molecular Ions SO 23rd International Conference on the Application of Accelerators in Research and Industry - CAARI 2014 SE Physics Procedia LA English DT Proceedings Paper CT 23rd International Conference on the Application of Accelerators in Research and Industry (CAARI) CY MAY 25-30, 2014 CL San Antonio, TX DE Ion-beam injector; magnetic fields; electrostatic storage rings; atomic and molecular physics ID ELECTROSTATIC STORAGE-RING; PHYSICS; KACST AB At the King Abdulaziz City for Science and Technology (KACST, Saudi Arabia), a versatile ion-beam injector was constructed to provide the electrostatic storage ring with the required high-quality ion beams. In order to remove the ambiguity over the ion mass due to the exclusive application of electric fields in the set-up, the injector is being equipped with a high resolution mass analyzing magnet. A high resolution Analyzing Magnet System has been designed to provide a singly-charged ion beam of kinetic energy up to 50 keV, mass up to 1500 Amu, and with the mass resolution fixed to Delta m/m = 1:1500. The system includes specific entrance and exit slits, designed to sustain the required mass resolution. Furthermore, specific focusing and shaping optics have been added upstream and downstream the system, in order to monitor and adapt the shape of the ion beam at the entrance and exit of the system, respectively. The present paper gives an overview on the design of this mass analyzing magnet system together with the upstream/downstream adapting optics. (C) 2015 The Authors. Published by Elsevier B.V. C1 [El Ghazaly, Mohamed O. A.] CALTECH, Jet Prop Lab, Astrophys & Space Sci Sect, Pasadena, CA 91109 USA. [El Ghazaly, Mohamed O. A.] King Abdulaziz City Sci & Technol, Riyadh 11442, Saudi Arabia. [El Ghazaly, Mohamed O. A.; Defrance, Pierre] Catholic Univ Louvain, Inst Condensed Matter & Nanosci, B-1348 Louvain La Neuve, Belgium. [Dehnel, Morgan] Dehnel Particle Accelerator Components & Engn Inc, Nelson, BC, Canada. RP El Ghazaly, MOA (reprint author), CALTECH, Jet Prop Lab, Astrophys & Space Sci Sect, Pasadena, CA 91109 USA. EM Mohamed.El.Ghazaly@jpl.nasa.gov NR 4 TC 1 Z9 1 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 1875-3892 J9 PHYSCS PROC PY 2015 VL 66 BP 10 EP 15 DI 10.1016/j.phpro.2015.05.003 PG 6 WC Physics, Applied; Physics, Atomic, Molecular & Chemical; Physics, Nuclear SC Physics GA BF3UY UT WOS:000380585500002 ER PT S AU Larsen, CE Irvine, T AF Larsen, Curtis E. Irvine, Tom BE Papuga, J Ruzicka, M TI A review of spectral methods for variable amplitude fatigue prediction and new results SO 3RD INTERNATIONAL CONFERENCE ON MATERIAL AND COMPONENT PERFORMANCE UNDER VARIABLE AMPLITUDE LOADING, VAL 2015 SE Procedia Engineering LA English DT Proceedings Paper CT 3rd International Conference on Material and Component Performance under Variable Amplitude Loading, VAL CY MAR 23-26, 2015 CL Prague, CZECH REPUBLIC DE damage accumulation; rainflow analysis; random processes; stationary Gaussian; spectral methods; stochastic fatigue AB A review of the available methods for estimating fatigue damage from variable amplitude loading is presented. The dependence of fatigue damage accumulation on power spectral density (psd) is investigated for stationary Gaussian random processes. Improvements to the Rayleigh approximation are examined by comparison to rainflow analysis of time histories simulated from psd functions representative of simple theoretical and real world applications. Spectral methods investigated include those by Wirsching and Light, Ortiz and Chen, the Dirlik formula, and the Single-Moment method, among other recent methods. Guidelines and limitations are given for using spectral methods to increase confidence in the damage estimate. Published by Elsevier Ltd. C1 [Larsen, Curtis E.] NASA, Engn & Safety Ctr NESC, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. [Irvine, Tom] Dynam Concepts Inc, NESC Loads & Dynam Tech Discipline Team, Huntsville, AL 35806 USA. RP Larsen, CE (reprint author), NASA, Engn & Safety Ctr NESC, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. EM curtis.e.larsen@nasa.gov NR 16 TC 5 Z9 5 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 1877-7058 J9 PROCEDIA ENGINEER PY 2015 VL 101 BP 243 EP 250 DI 10.1016/j.proeng.2015.02.034 PG 8 WC Engineering, Multidisciplinary; Engineering, Mechanical SC Engineering GA BF2RF UT WOS:000380492500030 ER PT S AU Kumar, U Milesi, C Nemani, RR Basu, S AF Kumar, Uttam Milesi, Cristina Nemani, Ramakrishna R. Basu, Saikat BE Zhang, J Lu, Z Zeng, Y TI MULTI-SENSOR MULTI-RESOLUTION IMAGE FUSION FOR IMPROVED VEGETATION AND URBAN AREA CLASSIFICATION SO IWIDF 2015 SE International Archives of the Photogrammetry Remote Sensing and Spatial Information Sciences LA English DT Proceedings Paper CT International Workshop on Image and Data Fusion (IWIDF) CY JUL 21-23, 2015 CL Kona, HI DE multi-sensor; multi-resolution; linear mixture model; data fusion; classification ID LANDSAT ETM PLUS; RANDOM FORESTS; MODELS AB In this paper, we perform multi-sensor multi-resolution data fusion of Landsat-5 TM bands (at 30 m spatial resolution) and multispectral bands of World View-2 (WV-2 at 2 m spatial resolution) through linear spectral unmixing model. The advantages of fusing Landsat and WV-2 data are two fold: first, spatial resolution of the Landsat bands increases to WV-2 resolution. Second, integration of data from two sensors allows two additional SWIR bands from Landsat data to the fused product which have advantages such as improved atmospheric transparency and material identification, for example, urban features, construction materials, moisture contents of soil and vegetation, etc. In 150 separate experiments, WV-2 data were clustered in to 5, 10, 15, 20 and 25 spectral classes and data fusion were performed with 3x3, 5x5, 7x7, 9x9 and 11x11 kernel sizes for each Landsat band. The optimal fused bands were selected based on Pearson product-moment correlation coefficient, RMSE (root mean square error) and ERGAS index and were subsequently used for vegetation, urban area and dark objects (deep water, shadows) classification using Random Forest classifier for a test site near Golden Gate Bridge, San Francisco, California, USA. Accuracy assessment of the classified images through error matrix before and after fusion showed that the overall accuracy and Kappa for fused data classification (93.74%, 0.91) was much higher than Landsat data classification (72.71%, 0.70) and WV-2 data classification (74.99%, 0.71). This approach increased the spatial resolution of Landsat data to WV-2 spatial resolution while retaining the original Landsat spectral bands with significant improvement in classification. C1 [Kumar, Uttam] NASA, Ames Res Ctr, ORAU, Moffett Field, CA 94035 USA. [Milesi, Cristina; Nemani, Ramakrishna R.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Basu, Saikat] Louisiana State Univ, Dept Comp Sci, Baton Rouge, LA 70803 USA. RP Kumar, U (reprint author), NASA, Ames Res Ctr, ORAU, Moffett Field, CA 94035 USA. EM uttam.kumar@nasa.gov; cristina.milesi@nasa.gov; rama.nemani@nasa.gov; sbasu8@lsu.edu NR 31 TC 0 Z9 0 U1 1 U2 1 PU COPERNICUS GESELLSCHAFT MBH PI GOTTINGEN PA BAHNHOFSALLE 1E, GOTTINGEN, 37081, GERMANY SN 2194-9034 J9 INT ARCH PHOTOGRAMM PY 2015 VL 47 IS W4 BP 51 EP 58 DI 10.5194/isprsarchives-XL-7-W4-51-2015 PG 8 WC Geography, Physical; Remote Sensing; Imaging Science & Photographic Technology SC Physical Geography; Remote Sensing; Imaging Science & Photographic Technology GA BF3UT UT WOS:000380584900010 ER PT S AU Kumar, U Milesi, C Nemani, RR Raja, SK Ganguly, S Wang, WL AF Kumar, Uttam Milesi, Cristina Nemani, Ramakrishna R. Raja, S. Kumar Ganguly, Sangram Wang, Weile BE Zhang, J Lu, Z Zeng, Y TI SPARSE UNMIXING VIA VARIABLE SPLITTING AND AUGMENTED LAGRANGIAN FOR VEGETATION AND URBAN AREA CLASSIFICATION USING LANDSAT DATA SO IWIDF 2015 SE International Archives of the Photogrammetry Remote Sensing and Spatial Information Sciences LA English DT Proceedings Paper CT International Workshop on Image and Data Fusion (IWIDF) CY JUL 21-23, 2015 CL Kona, HI DE sparse regression; spectral unmixing; Landsat; abundance estimation; spectral libraries; endmember ID ALGORITHM; MODELS AB In this paper, we explore the possibility of sparse regression, a new direction in unmixing, for vegetation and urban area classification. SUnSAL (Sparse unmixing via variable splitting and augmented Lagrangian) in both unconstrained and constrained forms (with the abundance non-negativity and abundance sum-to-one constraints) were used with a set of global endmembers (substrate, vegetation and dark objects) to unmix a set of computer simulated noise-free and noisy data (with Gaussian noise of different signal-to-noise ratio) in order to judge the robustness of the algorithm. The error in the fractional estimate was examined for varying noise power (variance): 2, 4, 8, 16, 32, 64, 128 and 256. In the second set of experiments, a spectrally diverse collection of 11 scenes of Level 1 terrain corrected, cloud free Landsat-5 TM data representing an agricultural setup in Fresno, California, USA were used. The corresponding ground data for validation were collected on the same days of satellite overpass. Finally in the third set of experiments, a clear sky Landsat-5 TM data for an area near the Golden Gate Bridge, San Francisco (an urbanized landscape), California, USA were used to assess the algorithm. The fractional estimates of the 30 m Landsat-5 TM data were compared with the fractional estimates of a high-resolution World View-2 data (2 m spatial resolution) obtained using a fully constrained least squares algorithm. The results were evaluated using descriptive statistics, correlation coefficient, RMSE, probability of success and bivariate distribution function, which showed that constrained model was better than unconstrained form. C1 [Kumar, Uttam] NASA, Ames Res Ctr, ORAU, Moffett Field, CA 94035 USA. [Milesi, Cristina; Nemani, Ramakrishna R.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Raja, S. Kumar] Airbus Engn Ctr India, Bangalore 560048, Karnataka, India. [Ganguly, Sangram] NASA, Ames Res Ctr, BAERI, Moffett Field, CA 94035 USA. [Wang, Weile] NASA, Ames Res Ctr, CSUMB, Moffett Field, CA 94035 USA. RP Kumar, U (reprint author), NASA, Ames Res Ctr, ORAU, Moffett Field, CA 94035 USA. EM uttam.kumar@nasa.gov; cristina.milesi@nasa.gov; rama.nemani@nasa.gov; sk.kumar.raja@gmail.com; sangram.ganguly@nasa.gov; weile.wang@nasa.gov NR 19 TC 0 Z9 0 U1 0 U2 0 PU COPERNICUS GESELLSCHAFT MBH PI GOTTINGEN PA BAHNHOFSALLE 1E, GOTTINGEN, 37081, GERMANY SN 2194-9034 J9 INT ARCH PHOTOGRAMM PY 2015 VL 47 IS W4 BP 59 EP 65 DI 10.5194/isprsarchives-XL-7-W4-59-2015 PG 7 WC Geography, Physical; Remote Sensing; Imaging Science & Photographic Technology SC Physical Geography; Remote Sensing; Imaging Science & Photographic Technology GA BF3UT UT WOS:000380584900011 ER PT J AU Wallace, A Yamakov, VI Hochhalter, JD Leser, WP Warner, JE Newman, JA Pun, GPP Mishin, Y AF Wallace, A. Yamakov, V. I. Hochhalter, J. D. Leser, W. P. Warner, J. E. Newman, J. A. Pun, G. P. Purja Mishin, Y. BE Poole, W Christensen, S Kalidindi, S Luo, A Madison, J Raabe, D Sun, X TI COMPUTATIONAL MODELING AND EXPERIMENTAL CHARACTERIZATION OF MARTENSITIC TRANSFORMATIONS IN NiCoAl FOR SELF-SENSING MATERIALS SO Proceedings of the 3rd World Congress on Integrated Computational Materials Engineering (ICME) LA English DT Proceedings Paper CT Proceedings of the 3rd World Congress on Integrated Computational Materials Engineering CY MAY 31-JUN 04, 2015 CL Cheyenne Mountain Resort, Colorado Springs, CO SP TMS Minerals, Metals & Mat Soc HO Cheyenne Mountain Resort DE shape memory alloys; computational materials; molecular dynamics AB Fundamental changes to aero-vehicle management require the utilization of automated health monitoring of vehicle structural components. A novel method is the use of self-sensing materials, which contain embedded sensory particles (SP). SPs are micron-sized pieces of shape-memory alloy that undergo transformation when the local strain reaches a prescribed threshold. The transformation is a result of a spontaneous rearrangement of the atoms in the crystal lattice under intensified stress near damaged locations, generating acoustic waves of a specific spectrum that can be detected by a suitably placed sensor. The sensitivity of the method depends on the strength of the emitted signal and its propagation through the material. To study the transition behavior of the sensory particle inside a metal matrix under load, a simulation approach based on a coupled atomistic-continuum model is used. The simulation results indicate a strong dependence of the particle's pseudoelastic response on its crystallographic orientation with respect to the loading direction and suggest possible ways of optimizing particle sensitivity. The technology of embedded sensory particles will serve as the key element in an autonomous structural health monitoring system that will constantly monitor for damage initiation in service, which will enable quick detection of unforeseen damage initiation and progression in real-time and during on-ground inspections. C1 [Wallace, A.; Yamakov, V. I.; Hochhalter, J. D.; Leser, W. P.; Warner, J. E.; Newman, J. A.] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Yamakov, V. I.] Natl Inst Aerosp, Hampton, VA 23666 USA. [Pun, G. P. Purja; Mishin, Y.] George Mason Univ, Fairfax, VA 22030 USA. RP Wallace, A (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. NR 6 TC 0 Z9 0 U1 1 U2 1 PU JOHN WILEY & SONS INC PI HOBOKEN PA 111 RIVER ST, HOBOKEN, NJ 07030 USA BN 978-1-119-13950-8 PY 2015 BP 229 EP 236 PG 8 WC Materials Science, Multidisciplinary SC Materials Science GA BF3GA UT WOS:000380538900021 ER PT B AU Sarikurt, S Sevik, C Kinaci, A Haskins, JB Cagin, T AF Sarikurt, Sevil Sevik, Cem Kinaci, Alper Haskins, Justin B. Cagin, Tahir BE Karaman, I Arroyave, R Masad, E TI Tailoring Thermal Conductivity of Ge/Si Core-Shell Nanowires SO Proceedings of the TMS Middle East - Mediterranean Materials Congress on Energy and Infrastructure Systems (MEMA 2015) LA English DT Proceedings Paper CT Proceedings of the TMS Middle East Mediterranean Materials Congress on Energy and Infrastructure Systems (MEMA 2015) CY JAN 11-14, 2015 CL Doha, QATAR DE Ge/Si core-shell nanowires; thermal conductivity; thermoelectrics ID NANOSCALE ELECTRONIC DEVICES; SILICON NANOWIRES; TRANSPORT-COEFFICIENTS; MOLECULAR-DYNAMICS; CARBON NANOTUBES; HETEROSTRUCTURES AB Low-dimensional nanostructured materials show large variation in their thermal transport properties. Here, we investigate the influence of core-shell architecture on nanowire ( NW) thermal conductivity using molecular dynamics with Tersoff potentials Si-Ge, to design structures with desired thermal conductivity for thermoelectric device applications. To explore the parameter space, we have calculated thermal conductivity values of Ge/Si core-shell NWs having different lengths, cross-section sizes and Ge concentrations at several temperatures. We have found that ( 1) increasing the cross-sectional area of pure Si NW causes an increase in thermal conductivity ( 2) increasing the Ge core size in the Ge/Si structure results in a decrease in the thermal conductivity values at 300. ( 3) there is no significant variation in the thermal conductivity of Si NW for temperature values larger than 300. ( 4) the predicted thermal conductivity around 10 W m(-1)K(-1) is still larger than the value convenient for thermoelectric applications. C1 [Sarikurt, Sevil] Dokuz Eylul Univ, Dept Phys, Fac Sci, TR-35390 Izmir, Turkey. [Sevik, Cem] Anadolu Univ, Dept Mech Engn, Fac Engn, TR-26555 Eskisehir, Turkey. [Kinaci, Alper] Argonne Natl Lab, Argonne, IL 60439 USA. [Haskins, Justin B.; Cagin, Tahir] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Sarikurt, Sevil; Kinaci, Alper; Haskins, Justin B.; Cagin, Tahir] Texas A&M Univ, Dept Mat Sci & Engn, College Stn, TX 77843 USA. RP Sarikurt, S (reprint author), Dokuz Eylul Univ, Dept Phys, Fac Sci, TR-35390 Izmir, Turkey. NR 28 TC 0 Z9 0 U1 1 U2 1 PU WILEY-BLACKWELL PI MALDEN PA COMMERCE PLACE, 350 MAIN STREET, MALDEN 02148, MA USA BN 978-1-119-09042-7; 978-1-119-06527-2 PY 2015 BP 433 EP 440 DI 10.1002/9781119090427.ch46 PG 8 WC Energy & Fuels; Engineering, Mechanical; Materials Science, Multidisciplinary SC Energy & Fuels; Engineering; Materials Science GA BF3QM UT WOS:000380568300046 ER PT S AU Ferri, E Bagliani, D Biasotti, M Ceruti, G Corsini, D Faverzani, M Gatti, F Giachero, A Gotti, C Kilbourne, C Kling, A Maino, M Manfrinetti, P Nucciotti, A Pessina, G Pizzigoni, G Gomes, MR Sisti, M AF Ferri, E. Bagliani, D. Biasotti, M. Ceruti, G. Corsini, D. Faverzani, M. Gatti, F. Giachero, A. Gotti, C. Kilbourne, C. Kling, A. Maino, M. Manfrinetti, P. Nucciotti, A. Pessina, G. Pizzigoni, G. Ribeiro Gomes, M. Sisti, M. BE Haxton, W Avignone, F TI The status of the MARE experiment with Re-187 and Ho-163 isotopes SO 13TH INTERNATIONAL CONFERENCE ON TOPICS IN ASTROPARTICLE AND UNDERGROUND PHYSICS, TAUP 2013 SE Physics Procedia LA English DT Proceedings Paper CT 13th International Conference on Topics in Astroparticle and Underground Physics (TAUP) CY SEP 08-13, 2013 CL Monterey Peninsula, CA SP Lawrence Berkeley Natl Lab DE neutrino mass; single beta decay; electron capture decay; microcalorimeter ID NEUTRINO MASS EXPERIMENT; DETECTOR; MICROCALORIMETERS; SPECTRUM; SEARCH; MILAN AB Neutrino oscillation experiments have proved that neutrinos are massive particles but the assessment of their absolute mass scale is still an outstanding challenge in today particle physics and cosmology. The laboratory experiments dedicated to effective electron-neutrino mass determination are the ones based on the study of single beta decay or electron capture (EC) decay. Exploiting only on energy-momentum conservation, this kinematic measurement is the only one which permits to estimate neutrino masses without theoretical assumptions on neutrino nature and it is truly model-independent. To date the most competitive isotopes for a calorimetric measurement of the neutrino mass are Re-187 and Ho-163. While the first decays beta, the latter decays via electron capture, and both have a Q-value around 2.5 keV. The measurement of Ho-163 EC is an appealing alternative to the Re-187 beta decay measurement because few nuclei are needed and it is a self-calibrating measurement. In this context the MARE project, based on rhenium thermal detectors has been born. We report here the status of MARE in Milan with Rhenium and the activity concerning the production of radioactive Ho-163 isotope in the framework of MARE. (C) 2015 The Authors. Published by Elsevier B.V. C1 [Ferri, E.; Ceruti, G.; Faverzani, M.; Giachero, A.; Gotti, C.; Maino, M.; Nucciotti, A.; Pessina, G.; Sisti, M.] Univ Milano Bicocca, Milan, Italy. [Ferri, E.; Ceruti, G.; Faverzani, M.; Giachero, A.; Gotti, C.; Maino, M.; Nucciotti, A.; Pessina, G.; Sisti, M.] Ist Nazl Fis Nucl, Sez Milan Bicocca, Milan, Italy. [Bagliani, D.; Biasotti, M.; Corsini, D.; Gatti, F.; Manfrinetti, P.; Pizzigoni, G.] Univ Genoa, Genoa, Italy. [Bagliani, D.; Biasotti, M.; Corsini, D.; Gatti, F.; Manfrinetti, P.; Pizzigoni, G.] Ist Nazl Fis Nucl, Sez Genoa, Genoa, Italy. [Kilbourne, C.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Kling, A.] Univ Lisbon, Ctr Nucl Phys, P-1699 Lisbon, Portugal. [Kling, A.] IST ID, Lisbon, Portugal. [Ribeiro Gomes, M.] Univ Lisbon, Ctr Nucl Phys, Lisbon, Portugal. RP Ferri, E (reprint author), Univ Milano Bicocca, Milan, Italy. EM elena.ferri@mib.infn.it RI Nucciotti, Angelo/I-8888-2012; Giachero, Andrea/I-1081-2013; Kling, Andreas/C-1115-2012; Biasotti, Michele/C-7890-2017 OI Nucciotti, Angelo/0000-0002-8458-1556; Gotti, Claudio/0000-0003-2501-9608; Giachero, Andrea/0000-0003-0493-695X; Kling, Andreas/0000-0002-5597-502X; Biasotti, Michele/0000-0002-7241-8479 NR 19 TC 0 Z9 0 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 1875-3892 J9 PHYSCS PROC PY 2015 VL 61 BP 227 EP 231 DI 10.1016/j.phpro.2014.12.037 PG 5 WC Physics, Applied SC Physics GA BF1JQ UT WOS:000380402900033 ER PT S AU Livas, JC AF Livas, Jeffrey C. BE Haxton, W Avignone, F TI Status of Space-based Gravitational-wave Observatories (SGOs) SO 13TH INTERNATIONAL CONFERENCE ON TOPICS IN ASTROPARTICLE AND UNDERGROUND PHYSICS, TAUP 2013 SE Physics Procedia LA English DT Proceedings Paper CT 13th International Conference on Topics in Astroparticle and Underground Physics (TAUP) CY SEP 08-13, 2013 CL Monterey Peninsula, CA SP Lawrence Berkeley Natl Lab AB The direct observation of gravitational waves in the 0.1 mHz to 1 Hz band is possible only from space. This band is expected to be rich with astrophysical sources that will yield a wealth of information measured with an accuracy and precision that can be obtained no other way. The Laser Interferometric Space Antenna (LISA) mission concept remains the reference design for this type of mission, but budget and programmatic constraints have forced reformulation of the original concept. This paper will briefly summarize recent activity in the US and Europe toward realizing a gravitational wave mission in space. Published by Elsevier B. V. C1 [Livas, Jeffrey C.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Livas, JC (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM jeffrey.livas@nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 1875-3892 J9 PHYSCS PROC PY 2015 VL 61 BP 648 EP 653 DI 10.1016/j.phpro.2014.12.065 PG 6 WC Physics, Applied SC Physics GA BF1JQ UT WOS:000380402900091 ER PT J AU Iturbe, X Keymeulen, D Ozer, E Yiu, P Berisford, D Hand, K Carlson, R AF Iturbe, Xabier Keymeulen, Didier Ozer, Emre Yiu, Patrick Berisford, Daniel Hand, Kevin Carlson, Robert BE Buchner, T Zhao, D Bhatia, K Sridhar, R TI Designing a SoC to Control the Next-Generation Space Exploration Flight Science Instruments SO 2015 28TH IEEE INTERNATIONAL SYSTEM-ON-CHIP CONFERENCE (SOCC) LA English DT Proceedings Paper CT IEEE International System on Chip Conference (SOCC) CY SEP 08-11, 2015 CL Beijing, PEOPLES R CHINA SP IEEE Circuits & Systems Soc DE System-m-Chip; Fauft-Tolerance; RHBD; Avionics; High-Performance; Signal Processing AB SoC technology permits to integrate all the computational power required by next-generation space exploration flight science instruments on a single chip. This paper describes the Xilinx Zynq-based Advanced Processor for space EXploration SoC (APEX-SoC) that has been developed at the Jet Propulsion Laboratory (JPL) in collaboration with ARM. The paper discusses the APEX-SoC architecture and demonstrates its main capabilities when used to control JPL's Compositional InfraRed Imaging Spectrometer (CIRIS). As the CIRIS instrument is intended to explore harsh space environments, the paper also deals with the Radiation Hardened By Design (RHBD) features that have been implemented in the APEX-SoC. C1 [Iturbe, Xabier; Yiu, Patrick] CALTECH, Pasadena, CA 91125 USA. [Iturbe, Xabier; Keymeulen, Didier; Berisford, Daniel; Hand, Kevin; Carlson, Robert] CALTECH, NASA, Jet Prop Lab, Pasadena, CA 91125 USA. [Iturbe, Xabier; Ozer, Emre] ARM R&D, Cambridge, England. RP Iturbe, X (reprint author), CALTECH, Pasadena, CA 91125 USA. EM xabier.iturbe@jpl.nasa.gov NR 24 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-9094-1 PY 2015 BP 13 EP 18 PG 6 WC Engineering, Electrical & Electronic SC Engineering GA BF1IR UT WOS:000380400500003 ER PT J AU Hamran, SE Berger, T Brovoll, S Damsgard, L Helleren, O Oyan, MJ Amundsen, HE Carter, L Ghent, R Kohler, J Mellon, M Paige, D Plettemeier, D Eide, J AF Hamran, Svein-Erik Berger, Tor Brovoll, Sverre Damsgard, Leif Helleren, Oystein Oyan, Mats Jorgen Amundsen, Hans Erik Carter, Lynn Ghent, Rebecca Kohler, Jack Mellon, Michael Paige, David Plettemeier, Dirk Eide, Jo GP IEEE TI RIMFAX: a GPR for the Mars 2020 Rover Mission SO 2015 8TH INTERNATIONAL WORKSHOP ON ADVANCED GROUND PENETRATING RADAR (IWAGPR) LA English DT Proceedings Paper CT 8th International Workshop on Advanced Ground Penetrating Radar (IWAGPR) CY JUL 07-10, 2015 CL Firenze, ITALY SP IEEE DE GPR; Gated-FMCW; Radar Imaging; Mars; Mars 2020 AB The RIMFAX radar is a Gated-FMCW Ground Penetrating Radar to be on aboard the NASA Mars 2020 rover mission. The radar is operating from 150 - 1200 MHz and is using an Ultra Wideband Bow-Tie Slot antenna at 60 cm above the ground surface. Depending on ground conditions the radar has the ability to penetrate to more than 10 meters depth. First results from glacier measurements are promising. C1 [Hamran, Svein-Erik; Berger, Tor; Brovoll, Sverre; Damsgard, Leif; Helleren, Oystein; Oyan, Mats Jorgen] FFI, N-2027 Kjeller, Norway. [Amundsen, Hans Erik] Vestfonna Geophys, Nordland, Norway. [Carter, Lynn] NASA, GSFC, Greenbelt, MD USA. [Ghent, Rebecca] Univ Toronto, Toronto, ON M5S 1A1, Canada. [Kohler, Jack] Norwegian Polar Res Inst, Tromso, Norway. [Mellon, Michael] Johns Hopkins Univ, APL, Baltimore, MD 21218 USA. [Paige, David] Univ Calif Los Angeles, Los Angeles, CA 90024 USA. [Plettemeier, Dirk] Tech Univ Dresden, Dresden, Germany. [Eide, Jo] Comrod, Tau, Norway. RP Hamran, SE (reprint author), FFI, N-2027 Kjeller, Norway. EM svein-erik.hamran@ffi.no NR 12 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-6495-6 PY 2015 PG 4 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BF1KD UT WOS:000380404100080 ER PT J AU Holt, J Cady, N Yang-Scharlotta, J AF Holt, Joshua Cady, Nathaniel Yang-Scharlotta, Jean GP IEEE TI Radiation Testing of Tantalum Oxide-based Resistive Memory SO 2015 IEEE INTERNATIONAL INTEGRATED RELIABILITY WORKSHOP (IIRW) LA English DT Proceedings Paper CT IEEE International Integrated Reliability Workshop Final Report CY OCT 11-15, 2015 CL S Lake Tahoe, CA SP IEEE Electron Devices Soc, IEEE Reliability Soc DE resistive memory; RRAM; radiation; tantalum oxide; memory ID TAOX AB Resistive memory (RRAM) is an emerging memory technology, expected to have inherent resistance to radiation damage. We present an initial study characterizing the effects of several types of radiation on a set of tantalum oxide-based RRAM devices. Gamma radiation (64.7 Mrad(Si)) was found to have no significant impact on switching properties. Likewise, ionic radiation (H, N, Ar+) up to 10(15) ions/cm(2) did not have any significant effect. This resistance to radiation, combined with high endurance and data retention, make RRAM an excellent candidate for use in harsh environments. C1 [Holt, Joshua; Cady, Nathaniel] SUNY Polytech Inst, Coll Nanoscale Sci, Albany, NY 12203 USA. [Holt, Joshua; Cady, Nathaniel] SUNY Polytech Inst, Coll Engn, Albany, NY USA. [Yang-Scharlotta, Jean] NASA, Jet Prop Lab, Pasadena, CA USA. RP Holt, J (reprint author), SUNY Polytech Inst, Coll Nanoscale Sci, Albany, NY 12203 USA. EM jholt@sunypoly.edu NR 7 TC 0 Z9 0 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-7396-8 PY 2015 BP 155 EP 158 PG 4 WC Engineering, Electrical & Electronic SC Engineering GA BF1QM UT WOS:000380428100035 ER PT B AU Swanger, AM Notardonato, WU Jumper, KM AF Swanger, Adam M. Notardonato, William U. Jumper, Kevin M. BE Zhao, MX TI ASME SECTION VIII RECERTIFICATION OF A 33,000 GALLON VACUUM-JACKETED LH2 STORAGE VESSEL FOR DENSIFIED HYDROGEN TESTING AT NASA KENNEDY SPACE CENTER SO ASME PRESSURE VESSELS AND PIPING CONFERENCE - 2015, VOL 3 LA English DT Proceedings Paper CT ASME Pressure Vessels and Piping Conference, PVP-2015 CY JUL 19-23, 2015 CL Boston, MA SP ASME, Pressure Vessels & Pip Div AB The Ground Operations Demonstration Unit for Liquid Hydrogen (GODU-LH2) has been developed at NASA Kennedy Space Center in Florida. GODU-LH2 has three main objectives: zero-loss storage and transfer, liquefaction, and densification of liquid hydrogen. A cryogenic refrigerator has been integrated into an existing, previously certified, 33,000 gallon vacuum jacketed storage vessel built by Minnesota Valley Engineering in 1991 for the Titan program. The dewar has an inner diameter of 9.5' and a length of 71.5'; original design temperature and pressure ranges are -423 degrees F to 100 degrees F and 0 to 95 psig respectively. During densification operations the liquid temperature will be decreased below the normal boiling point by the refrigerator, and consequently the pressure inside the inner vessel will be sub-atmospheric. These new operational conditions rendered the original certification invalid, so an effort was undertaken to recertify the tank to the new pressure and temperature requirements (-12.7 to 95 psig and -433 degrees F to 100 degrees F respectively) per ASME Boiler and Pressure Vessel Code, Section VIII, Division 1. This paper will discuss the unique design, analysis and implementation issues encountered during the vessel recertification process. C1 [Swanger, Adam M.; Notardonato, William U.] NASA, Cryogen Test Lab, Kennedy Space Ctr, Kennedy Space Ctr, FL 32899 USA. [Jumper, Kevin M.] Sierra Lobo ESC, Cryogen Test Lab, Kennedy Space Ctr, Kennedy Space Ctr, FL USA. RP Swanger, AM (reprint author), NASA, Cryogen Test Lab, Kennedy Space Ctr, Kennedy Space Ctr, FL 32899 USA. EM adam.m.swanger@nasa.gov; bill.notardonato@nasa.gov; kevin.m.jumper@nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-5696-3 PY 2015 AR V003T03A055 PG 9 WC Engineering, Mechanical SC Engineering GA BF1EK UT WOS:000380382800055 ER PT S AU Burgoyne, HA Newman, JA Jackson, WC Daraio, C AF Burgoyne, Hayden A. Newman, John A. Jackson, Wade C. Daraio, Chiara BE Schonberg, WP TI Guided Impact Mitigation in 2D and 3D Granular Crystals SO PROCEEDINGS OF THE 2015 HYPERVELOCITY IMPACT SYMPOSIUM (HVIS 2015) SE Procedia Engineering LA English DT Proceedings Paper CT Proceedings of the 2015 Hypervelocity Impact Symposium (HVIS) CY APR 26-30, 2015 CL Boulder, CO DE granular; impact protection; wave speed; dispersion; dissipation; metamaterials ID WAVE PROPAGATION; PLANE-WAVE; MEDIA AB We simulate the dynamics of impacts on 1D, 2D and 3D arrays of metallic spheres in order to design novel granular protection systems. The dynamics of these highly organized systems of spheres, commonly called granular crystals, are governed by the contact law that describes how each particle interacts with the others. We use our recently developed force-displacement model of the dynamic compression of elastic-plastic spheres as the building block to investigate the response of systems comprised of metallic spheres to an impact. We first provide preliminary experimental results using a drop tower as validation of our numerical approach for 2D and 3D systems. We then use simulations of large periodic granular crystals in order to determine which particle properties govern the velocity of stress waves in these materials. We show that the properties of 1D systems can be scaled to predict the behavior of more complex 2D and 3D granular crystals. Because we can choose the material properties of each of the constituent particles and design how the particles are geometrically packed, we can leverage the heterogeneity of the system to create materials with unique properties such as anisotropic local stiffnesses and wave propagation velocities. We show that these materials allow us to design the dispersion and dissipation properties within the material in order to influence the propagation of a stress wave. Using these materials, we can therefore design protection systems or armor that directs damage away from sensitive parts or localizes damage to an unimportant area after impact from a projectile or a blast. (C) 2015 Published by Elsevier Ltd. C1 [Burgoyne, Hayden A.; Daraio, Chiara] CALTECH, Pasadena, CA 91125 USA. [Newman, John A.; Jackson, Wade C.] NASA, Langley Res Ctr, Hampton, VA 23666 USA. [Daraio, Chiara] ETH, Tannenstr 3, CH-8092 Zurich, Switzerland. RP Daraio, C (reprint author), ETH, Tannenstr 3, CH-8092 Zurich, Switzerland. EM daraio@ethz.ch RI Daraio, Chiara/N-2170-2015 OI Daraio, Chiara/0000-0001-5296-4440 NR 19 TC 2 Z9 2 U1 2 U2 3 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 1877-7058 J9 PROCEDIA ENGINEER PY 2015 VL 103 BP 52 EP 59 DI 10.1016/j.proeng.2015.04.008 PG 8 WC Engineering, Multidisciplinary SC Engineering GA BF3FJ UT WOS:000380535200007 ER PT S AU Christiansen, EL Lear, DM AF Christiansen, Eric L. Lear, Dana M. BE Schonberg, WP TI Toughened Thermal Blanket for Micrometeoroid and Orbital Debris Protection SO PROCEEDINGS OF THE 2015 HYPERVELOCITY IMPACT SYMPOSIUM (HVIS 2015) SE Procedia Engineering LA English DT Proceedings Paper CT Proceedings of the 2015 Hypervelocity Impact Symposium (HVIS) CY APR 26-30, 2015 CL Boulder, CO DE orbital debris; micrometeoroids; MMOD; thermal blanket AB Toughened thermal blankets have been developed that greatly improve protection from hypervelocity micrometeoroid and orbital debris (MMOD) impacts. Three types of materials were added to the thermal blanket to enhance its MMOD performance: (1) disrupter layers, near the outside of the blanket to improve breakup of the projectile, (2) standoff layers, in the middle of the blanket to provide an area or gap that the broken-up projectile can expand, and (3) stopper layers, near the back of the blanket where the projectile debris is captured and stopped. Hypervelocity impact tests were performed on candidate toughened thermal blanket configurations at the NASA White Sands Test Facility and at the University of Dayton Research Institute. From these tests the best disrupter materials were found to be beta-cloth and fiberglass fabric. Polyimide open-cell foams provide a light-weight means to increase the blanket thickness and improve MMOD protection. The best stopper material is Spectra(TM) 1000-952 or Kevlar(TM) KM2-705. These blankets can be outfitted if so desired with a reliable means to determine the location, depth and extent of MMOD impact damage by incorporating an impact sensitive piezoelectric film. (C) 2015 Published by Elsevier Ltd. C1 [Christiansen, Eric L.; Lear, Dana M.] NASA, Johnson Space Ctr, Houston, TX 77058 USA. RP Christiansen, EL (reprint author), NASA, Johnson Space Ctr, Houston, TX 77058 USA. EM Eric.L.Christiansen@nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 1877-7058 J9 PROCEDIA ENGINEER PY 2015 VL 103 BP 73 EP 80 DI 10.1016/j.proeng.2015.04.011 PG 8 WC Engineering, Multidisciplinary SC Engineering GA BF3FJ UT WOS:000380535200010 ER PT S AU Cwalina, CD Dombrowski, RD McCutcheon, CJ Christiansen, EL Wagner, NJ AF Cwalina, Colin D. Dombrowski, Richard D. McCutcheon, Charles J. Christiansen, Eric L. Wagner, Norman J. BE Schonberg, WP TI MMOD Puncture Resistance of EVA Suits with Shear Thickening Fluid (STF) - Armor (TM) Absorber Layers SO PROCEEDINGS OF THE 2015 HYPERVELOCITY IMPACT SYMPOSIUM (HVIS 2015) SE Procedia Engineering LA English DT Proceedings Paper CT Proceedings of the 2015 Hypervelocity Impact Symposium (HVIS) CY APR 26-30, 2015 CL Boulder, CO DE Shear thickening fluids; micrometeoroids and orbital debris; extra-vehicular activity suit; hypodermic needle ID SPHERE COLLOIDAL DISPERSIONS; PENETRATION; FABRICS; IMPACT; MODEL AB Absorber layers comprised of shear thickening fluid (STF) intercalated Kevlar(R) (STF-Armor(TM)) are integrated within the standard extravehicular activity (EVA) suit and tested for efficacy against both needle puncture and hypervelocity impact (HVI) tests characteristic of micrometeoroids and orbital debris (MMOD). An improvement in puncture resistance against hypodermic needle threats is achieved by substituting STF-Armor(TM) in place of neoprene-coated nylon as the absorber layer in the standard EVA suit. The prototype lay-ups containing STF-Armor(TM) have the benefit of being 17% thinner and 13% lighter than the standard EVA suit and the ballistic limit is identified in HVI testing. The results here demonstrate that EVA suit lay-ups containing STF-Armor(TM) as absorber layers offer meaningful resistance to MMOD threats. (C) 2015 Published by Elsevier Ltd. C1 [Cwalina, Colin D.; Dombrowski, Richard D.; McCutcheon, Charles J.; Wagner, Norman J.] Univ Delaware, Dept Chem & Biomol Engn, Newark, DE 19716 USA. [Christiansen, Eric L.] NASA, Johnson Space Ctr, Houston, TX 77058 USA. RP Wagner, NJ (reprint author), Univ Delaware, Dept Chem & Biomol Engn, Newark, DE 19716 USA. EM wagnernj@udel.edu RI Wagner, Norman/B-6558-2012 OI Wagner, Norman/0000-0001-9565-619X NR 21 TC 3 Z9 3 U1 1 U2 7 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 1877-7058 J9 PROCEDIA ENGINEER PY 2015 VL 103 BP 97 EP 104 DI 10.1016/j.proeng.2015.04.014 PG 8 WC Engineering, Multidisciplinary SC Engineering GA BF3FJ UT WOS:000380535200013 ER PT S AU Henderson, M Blume, W AF Henderson, Monte Blume, William BE Schonberg, WP TI Deep Impact - A Review of the World's Pioneering Hypervelocity Impact Mission SO PROCEEDINGS OF THE 2015 HYPERVELOCITY IMPACT SYMPOSIUM (HVIS 2015) SE Procedia Engineering LA English DT Proceedings Paper CT Proceedings of the 2015 Hypervelocity Impact Symposium (HVIS) CY APR 26-30, 2015 CL Boulder, CO DE autonomous navigation; comet impact; spacecraft design; NASA AB On July 4th, 2005, in celebration of our nation's birthday, NASA's Deep Impact Impactor spacecraft collided with comet Tempel1 at 10km/sec - marking the first hypervelocity impact of a celestial body by a human-made spacecraft. With closing speeds of 23,000 mph, the Impactor's active guidance system steered it to impact on a sunlit portion of the comet's surface. As it closed in on Tempel 1, the Impactor's camera relayed close-up images of the comet's surface to the Flyby spacecraft for downlink to Earth. Meanwhile, the Flyby spacecraft used its two instruments to image the impact and then continued to photograph the comet as it followed its orbital path around the Sun. The primary science data was returned to Earth in near real-time, and all data was returned to Earth within 24 hours of the encounter. For the NASA Discovery-class Deep Impact mission, a two-part Deep Impact spacecraft was constructed: the Impactor spacecraft and the impact characterization (flyby) spacecraft, and an associated suite of surveillance instruments. These instruments included one high resolution visible imager, two identical medium-resolution visible imagers (one on the flyby and one on the Impactor) and one infrared spectrometer. The two-part spacecraft launched together in January 12, 2005 and separated on July 3rd, 24 hours before reaching its Tempel 1 target. The Impactor separated from the flyby spacecraft and autonomously positioned itself directly in front of the encroaching Tempel 1 comet for a spectacular hypervelocity impact. This paper highlights portions of the article Deep Impact: Excavating Comet Tempel 1 written by the Deep Impact science team and published in Science as well as on-line by Science Express, 09/08/05. (C) 2015 Published by Elsevier Ltd. C1 [Henderson, Monte] Ball Aerosp & Technol Corp, 1600 Commerce St,M-S WMR 1, Boulder, CO 80301 USA. [Blume, William] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Henderson, M (reprint author), Ball Aerosp & Technol Corp, 1600 Commerce St,M-S WMR 1, Boulder, CO 80301 USA. NR 4 TC 0 Z9 0 U1 0 U2 1 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 1877-7058 J9 PROCEDIA ENGINEER PY 2015 VL 103 BP 165 EP 172 DI 10.1016/j.proeng.2015.04.023 PG 8 WC Engineering, Multidisciplinary SC Engineering GA BF3FJ UT WOS:000380535200022 ER PT S AU Hyde, J Christiansen, E Lear, D AF Hyde, J. Christiansen, E. Lear, D. BE Schonberg, WP TI Shuttle MMOD Impact Database SO PROCEEDINGS OF THE 2015 HYPERVELOCITY IMPACT SYMPOSIUM (HVIS 2015) SE Procedia Engineering LA English DT Proceedings Paper CT Proceedings of the 2015 Hypervelocity Impact Symposium (HVIS) CY APR 26-30, 2015 CL Boulder, CO DE hypervelocity impact database; orbital debris; micrometeoroids; Space Shuttle AB The Shuttle Hypervelocity Impact Database documents damage features on each Orbiter from micrometeoroids (MM) and orbital debris (OD). Data is divided into tables for crew module windows, payload bay door radiators and thermal protection systems along with other miscellaneous regions. The database contains nearly 3000 records, with each providing impact feature dimensions, location on the vehicle and relevant mission information. Additional detail on the type and size of particle that produced the damage site is provided when sampling data and definitive spectroscopic analysis results are available. Relationships assumed when converting from observed feature sizes in different shuttle materials to particle sizes will be presented. (C) 2015 Published by Elsevier Ltd. C1 [Hyde, J.] Jacobs, Johnson Space Ctr, Houston, TX 77058 USA. [Christiansen, E.; Lear, D.] NASA, Johnson Space Ctr, Houston, TX 77058 USA. RP Hyde, J (reprint author), Jacobs, Johnson Space Ctr, Houston, TX 77058 USA. EM james.l.hyde@nasa.gov NR 4 TC 1 Z9 1 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 1877-7058 J9 PROCEDIA ENGINEER PY 2015 VL 103 BP 246 EP 253 DI 10.1016/j.proeng.2015.04.044 PG 8 WC Engineering, Multidisciplinary SC Engineering GA BF3FJ UT WOS:000380535200032 ER PT S AU Miller, JE Bjorkman, MD Christiansen, EL Ryan, SJ AF Miller, J. E. Bjorkman, M. D. Christiansen, E. L. Ryan, S. J. BE Schonberg, WP TI Analytic Ballistic Performance Model of Whipple Shields SO PROCEEDINGS OF THE 2015 HYPERVELOCITY IMPACT SYMPOSIUM (HVIS 2015) SE Procedia Engineering LA English DT Proceedings Paper CT Proceedings of the 2015 Hypervelocity Impact Symposium (HVIS) CY APR 26-30, 2015 CL Boulder, CO DE Whipple shield; MMOD; ballistic equation AB The dual-wall, Whipple shield is the shield of choice for lightweight, long-duration flight. The shield uses an initial sacrificial wall to initiate fragmentation and melt an impacting threat that expands over a void before hitting a subsequent shield wall of a critical component. The key parameters to this type of shield are the rear wall and its mass which stops the debris, as well as the minimum shock wave strength generated by the threat particle impact of the sacrificial wall and the amount of room that is available for expansion. Ensuring the shock wave strength is sufficiently high to achieve large scale fragmentation/melt of the threat particle enables the expansion of the threat and reduces the momentum flux of the debris on the rear wall. Three key factors in the shock wave strength achieved are the thickness of the sacrificial wall relative to the characteristic dimension of the impacting particle, the density and material cohesion contrast of the sacrificial wall relative to the threat particle and the impact speed. The mass of the rear wall and the sacrificial wall are desirable to minimize for launch costs making it important to have an understanding of the effects of density contrast and impact speed. An analytic model is developed here, to describe the influence of these three key factors. In addition this paper develops a description of a fourth key parameter related to fragmentation and its role in establishing the onset of projectile expansion. (C) 2015 The Authors. Published by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license. C1 [Miller, J. E.] Univ Texas El Paso, 500 W Univ Ave, El Paso, TX 79968 USA. [Miller, J. E.; Bjorkman, M. D.; Christiansen, E. L.] NASA Johnson Space Ctr, Houston, TX 77058 USA. [Ryan, S. J.] Def Sci & Technol Org, Fishermans Bend, Vic 3207, Australia. RP Miller, JE (reprint author), Univ Texas El Paso, 500 W Univ Ave, El Paso, TX 79968 USA. EM joshua.e.miller@nasa.gov NR 10 TC 1 Z9 1 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 1877-7058 J9 PROCEDIA ENGINEER PY 2015 VL 103 BP 389 EP 397 DI 10.1016/j.proeng.2015.04.037 PG 9 WC Engineering, Multidisciplinary SC Engineering GA BF3FJ UT WOS:000380535200050 ER PT S AU Miller, JE Christiansen, EL Davis, BA Deighton, KD AF Miller, J. E. Christiansen, E. L. Davis, B. A. Deighton, K. D. BE Schonberg, WP TI Ballistic performance model of crater formation in monolithic, porous thermal protection systems SO PROCEEDINGS OF THE 2015 HYPERVELOCITY IMPACT SYMPOSIUM (HVIS 2015) SE Procedia Engineering LA English DT Proceedings Paper CT Proceedings of the 2015 Hypervelocity Impact Symposium (HVIS) CY APR 26-30, 2015 CL Boulder, CO DE thermal protection system; ballistic performance; Avcoat AB Monolithic, porous, thermal protection systems were used heavily on the Apollo command module, and they are currently being used on the next generation of US manned spacecraft, Orion. These systems insulate reentry critical components of a spacecraft against the intense thermal environments of atmospheric reentry. Additionally, these materials may be highly exposed to space environment hazards like solid particle impacts. This paper discusses impact studies up to 10 km/s on nominally 0.56 g/cm(3) Avcoat ablator with phenolic flexible hexcore. An impact model that describes projectile dispersion in a monolithic material is described that provides excellent agreement with observations over a broad range of impact velocities, obliquities and projectile materials. (C) 2015 The Authors. Published by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license. C1 [Miller, J. E.] Univ Texas El Paso, 500 W Univ Ave, El Paso, TX 79968 USA. [Miller, J. E.; Christiansen, E. L.; Davis, B. A.] NASA Johnson Space Ctr, Houston, TX 77058 USA. [Deighton, K. D.] Lockheed Martin, Houston, TX 77058 USA. RP Miller, JE (reprint author), Univ Texas El Paso, 500 W Univ Ave, El Paso, TX 79968 USA. EM joshua.e.miller@nasa.gov NR 6 TC 0 Z9 0 U1 2 U2 2 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 1877-7058 J9 PROCEDIA ENGINEER PY 2015 VL 103 BP 398 EP 404 DI 10.1016/j.proeng.2015.04.038 PG 7 WC Engineering, Multidisciplinary SC Engineering GA BF3FJ UT WOS:000380535200051 ER PT S AU Miller, JE Christiansen, EL Davis, BA Lear, DM Liou, JC AF Miller, J. E. Christiansen, E. L. Davis, B. A. Lear, D. M. Liou, J. -C. BE Schonberg, WP TI Multi-Shock Shield Performance At 14 MJ for Catalogued Debris SO PROCEEDINGS OF THE 2015 HYPERVELOCITY IMPACT SYMPOSIUM (HVIS 2015) SE Procedia Engineering LA English DT Proceedings Paper CT Proceedings of the 2015 Hypervelocity Impact Symposium (HVIS) CY APR 26-30, 2015 CL Boulder, CO DE multi-shock shield; catalogued debris; fabric shield ID COMPRESSIBILITY AB As the orbital debris population continues to grow significant tangible threats to robotic and crewed spacecraft have risen greatly over the last decade. These threats are currently mitigated operationally; however, an understanding of engineered solutions is useful to consider with respect to the risks and costs of operational mitigation. To this end a multi-shock shield has been designed and tested to demonstrate what it takes to stop an object that fits the energy profile of catalogued debris. A 14.25 MJ hypervelocity impact test has been performed on an enhanced, multi-shock shield at orbital speeds at the Arnold Engineering Development Complex (AEDC). The projectile was a hollow aluminum and nylon cylinder with characteristic dimensions typical of catalogued debris. The AEDC test of the shield occurred without any issues, and the shield successfully stopped the 598 g projectile at a mass penalty of 10.35 g/cm(2). (C) 2015 The Authors. Published by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license. C1 [Miller, J. E.] Univ Texas El Paso, 500 W Univ Ave, El Paso, TX 79968 USA. [Miller, J. E.; Christiansen, E. L.; Davis, B. A.; Lear, D. M.; Liou, J. -C.] NASA Johnson Space Ctr, Houston, TX 77058 USA. RP Miller, JE (reprint author), Univ Texas El Paso, 500 W Univ Ave, El Paso, TX 79968 USA. EM joshua.e.miller@nasa.gov NR 19 TC 0 Z9 0 U1 1 U2 1 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 1877-7058 J9 PROCEDIA ENGINEER PY 2015 VL 103 BP 405 EP 412 DI 10.1016/j.proeng.2015.04.039 PG 8 WC Engineering, Multidisciplinary SC Engineering GA BF3FJ UT WOS:000380535200052 ER PT S AU Miller, JE Bohl, WE Christiansen, EL Davis, BA Deighton, KD AF Miller, J. E. Bohl, W. E. Christiansen, E. L. Davis, B. A. Deighton, K. D. BE Schonberg, WP TI HVI Ballistic Limit Characterization of Fused Silica Thermal Panes SO PROCEEDINGS OF THE 2015 HYPERVELOCITY IMPACT SYMPOSIUM (HVIS 2015) SE Procedia Engineering LA English DT Proceedings Paper CT Proceedings of the 2015 Hypervelocity Impact Symposium (HVIS) CY APR 26-30, 2015 CL Boulder, CO DE multi-shock shield; catalogued debris; fabric shield ID IMPACT AB Fused silica window systems are used heavily on crewed reentry vehicles, and they are currently being used on the next generation of US crewed spacecraft, Orion. These systems improve crew situational awareness and comfort, as well as, insulating the reentry critical components of a spacecraft against the intense thermal environments of atmospheric reentry. Additionally, these materials are highly exposed to space environment hazards like solid particle impacts. This paper discusses impact studies up to 10 km/s on a fused silica window system proposed for the Orion spacecraft. A ballistic limit equation that describes the threshold of perforation of a fused silica pane over a broad range of impact velocities, obliquities and projectile materials is discussed here. (C) 2015 The Authors. Published by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license. C1 [Miller, J. E.] Univ Texas El Paso, 500 W Univ Ave, El Paso, TX 79968 USA. [Miller, J. E.; Christiansen, E. L.; Davis, B. A.] NASA Johnson Space Ctr, Houston, TX 77058 USA. [Bohl, W. E.] Lockheed Martin Space Syst Co, Denver, CO 80125 USA. [Deighton, K. D.] Lockheed Martin, Houston, TX 77058 USA. RP Miller, JE (reprint author), Univ Texas El Paso, 500 W Univ Ave, El Paso, TX 79968 USA. EM joshua.e.miller@nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 1877-7058 J9 PROCEDIA ENGINEER PY 2015 VL 103 BP 413 EP 420 DI 10.1016/j.proeng.2015.04.040 PG 8 WC Engineering, Multidisciplinary SC Engineering GA BF3FJ UT WOS:000380535200053 ER PT S AU Schonberg, WP Ratliff, JM AF Schonberg, William P. Ratliff, J. Martin BE Schonberg, WP TI A First-Principles-Based Model for Crack Formation in a Pressurized Tank Following an MMOD Impact SO PROCEEDINGS OF THE 2015 HYPERVELOCITY IMPACT SYMPOSIUM (HVIS 2015) SE Procedia Engineering LA English DT Proceedings Paper CT Proceedings of the 2015 Hypervelocity Impact Symposium (HVIS) CY APR 26-30, 2015 CL Boulder, CO DE Pressure vessel; MMOD; fracture; hypervelocity impact; analytical model AB Most robotic spacecraft have at least one pressurized vessel on board, usually a liquid propellant tank. One of the design considerations of such spacecraft is the anticipation and mitigation of the possible damage that might occur from on-orbit impacts by micro-meteoroids or orbital debris (MMOD). While considerable effort has been expended in the study of the response of non-pressurized spacecraft components to MMOD impacts, relatively few studies have been conducted on the pressurized elements of such spacecraft. In particular, since it was first proposed nearly 45 years ago, NASA's current evaluation methodology for determining impact-induced failure of pressurized tanks has undergone little scrutiny. This paper presents a first-principles based model that has been developed to predict whether or not cracking might start or a through-crack might be created under an impact crater in a thin plate. This model was used to examine the effect of penetration depth on crack formation and whether or not the crack might grow through the tank wall thickness. The predictions of the model are compared to experimental data with encouraging results. The paper also develops some suggestions for future work in this area, including the extension of the first-principles model to include 3-D crack initiation modelling. (C) 2015 The Authors. Published by Elsevier Ltd. C1 [Schonberg, William P.] Missouri Univ Sci & Technol, Rolla, MO 65409 USA. [Ratliff, J. Martin] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Schonberg, WP (reprint author), Missouri Univ Sci & Technol, Rolla, MO 65409 USA. EM wschon@mst.edu NR 21 TC 0 Z9 0 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 1877-7058 J9 PROCEDIA ENGINEER PY 2015 VL 103 BP 546 EP 552 DI 10.1016/j.proeng.2015.04.071 PG 7 WC Engineering, Multidisciplinary SC Engineering GA BF3FJ UT WOS:000380535200070 ER PT J AU Dhombres, S Michez, A Boch, J Beauvivre, S Vaille, JR Touboul, AD Adell, PC Bezerra, F Lorfevre, E Kraehenbuehl, D Saigne, F AF Dhombres, S. Michez, A. Boch, J. Beauvivre, S. Vaille, J-R. Touboul, A. D. Adell, P. C. Bezerra, F. Lorfevre, E. Kraehenbuehl, D. Saigne, F. GP IEEE TI Dose Effects on CMOS Active Pixel Sensors SO 2015 15TH EUROPEAN CONFERENCE ON RADIATION AND ITS EFFECTS ON COMPONENTS AND SYSTEMS (RADECS) LA English DT Proceedings Paper CT 2015 15th European Conference on Radiation and Its Effects on Components and Systems (RADECS) CY SEP 14-18, 2015 CL Moscow, RUSSIA SP IEEE, United Rock Space Corp, Inst Space Device Engn, Joint Inst Nucl Res, China Aerosp Components Eng Ctr, Specialized Elect Systems, Res Inst Sci Instruments, Sci Prod Ctr GRANAT, Sci Prod Ctr EITest, Vostok Co, Aerosp Sci Res Test Mfg Ass, RNII Electronstandart, Conseil Europeen Rech Nucl, EHO DE CMOS image sensor; thermal annealing; isochronal annealing; extending lifetime; ionizing radiation; total ionizing dose (TID) AB A thermal annealing approach is applied on irradiated CMOS active pixel sensors to investigate total dose effects and improve device lifetime. Results are discussed and help identified the sensor's sensitive areas. C1 [Dhombres, S.; Michez, A.; Boch, J.; Vaille, J-R.; Touboul, A. D.; Saigne, F.] Univ Montpellier, IES, CNRS, UMR UM2, 5214 Pl E Bataillon, F-34095 Montpellier 5, France. [Dhombres, S.; Beauvivre, S.; Kraehenbuehl, D.] Systheia, F-34000 Montpellier, France. [Adell, P. C.] Jet Prop Lab, Pasadena, CA USA. [Bezerra, F.; Lorfevre, E.] Ctr Natl Etud Spatiales, F-31401 Toulouse, France. RP Dhombres, S (reprint author), Univ Montpellier, IES, CNRS, UMR UM2, 5214 Pl E Bataillon, F-34095 Montpellier 5, France. EM dhombres@ies.univ-montp2.fr NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-5090-0232-0 PY 2015 PG 3 WC Engineering, Electrical & Electronic; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BF1KE UT WOS:000380404200029 ER PT J AU Prokopenko, GV Mukhanov, OA Romanofsky, RR AF Prokopenko, Georgy V. Mukhanov, Oleg A. Romanofsky, Robert R. GP IEEE TI SQIF Antenna Measurement in Near Field SO 2015 15TH INTERNATIONAL SUPERCONDUCTIVE ELECTRONICS CONFERENCE (ISEC) LA English DT Proceedings Paper CT 15th International Superconductive Electronics Conference (ISEC) CY JUL 06-09, 2015-2019 CL Nagoya, JORDAN SP ISEC, JAPAN SOC PROMOTIONAL SCI, MURATA SCI FDN, NAGOYA UNIV, IEEE COUNCIL SUPERCONDUCTIVITY, TAIYO DENSHI KK DE SQUID; wideband; electrically small; high sensitivity; superconducting quantum arrays ID FILTERS AB We have been developing superconducting microwave (8-15 GHz bandwidth) magnetic field receiving antennas based on a two-dimensional (2D) Superconducting Quantum Interference Filter (SQIF) composed of bi-SQUID arrays. The 2D arrays are designed and fabricated using standard HYPRES niobium 4.5 kA/cm(2) process. The designed non-uniformity in inductances of bi-SQUID cells produces a pronounced zero-field antipeak in the flux-voltage response curve. We select the active antenna operation point by applying an appropriate dc flux bias current to set it in the middle of the antipeak linear slope. We measured comparative responses of the antenna with the SQIF dc bias at ON and OFF states when irradiated by a microwave signal from four different conventional planar ring and patch antennas placed in the near field. C1 [Prokopenko, Georgy V.; Mukhanov, Oleg A.] Hypres Inc, 175 Clearbrook Rd, Elmsford, NY 10523 USA. [Romanofsky, Robert R.] NASA, Glenn Res Ctr, Cleveland, OH USA. RP Prokopenko, GV (reprint author), Hypres Inc, 175 Clearbrook Rd, Elmsford, NY 10523 USA. EM georgy@hypres.com; mukhanov@hypres.com; robert.r.romanofsky@hasa.gov NR 15 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-8348-6 PY 2015 PG 3 WC Engineering, Electrical & Electronic; Materials Science, Multidisciplinary SC Engineering; Materials Science GA BF1FO UT WOS:000380391200056 ER PT J AU Volkmann, MH Swenson, LJ Spear, P Whittaker, JD Altomare, F Berkley, AJ Bunyk, P Harris, R Hilton, JP Hoskinson, EH Johnson, MW Ladizinsky, E Lanting, TM Oh, T Perminov, I Tolkacheva, E Wilkinson, W Yao, J Bumble, B Day, PK Eom, BH Kleinsasser, A AF Volkmann, Mark H. Swenson, Loren J. Spear, Peter Whittaker, Jed D. Altomare, Fabio Berkley, Andrew J. Bunyk, Paul Harris, Richard Hilton, Jeremy P. Hoskinson, Emile H. Johnson, Mark W. Ladizinsky, Eric Lanting, Trevor M. Oh, Travis Perminov, Ilya Tolkacheva, Elena Wilkinson, Warren Yao, Jason Bumble, Bruce Day, Peter K. Eom, Byeong Ho Kleinsasser, Alan GP IEEE TI Low-dissipation multiplexed flux-sensitive readout in superconducting circuits SO 2015 15TH INTERNATIONAL SUPERCONDUCTIVE ELECTRONICS CONFERENCE (ISEC) LA English DT Proceedings Paper CT 15th International Superconductive Electronics Conference (ISEC) CY JUL 06-09, 2015-2019 CL Nagoya, JORDAN SP ISEC, JAPAN SOC PROMOTIONAL SCI, MURATA SCI FDN, NAGOYA UNIV, IEEE COUNCIL SUPERCONDUCTIVITY, TAIYO DENSHI KK DE low-dissipation; readout; resonator AB D-Wave's quantum processors require a high-fidelity readout architecture for fast and accurate operation. The need for cold operation precludes readout methods with significant dissipation. The readout architecture must be scalable and compatible with an inherently dense qubit circuit layout. Superconducting microresonators have been successfully utilized as detection elements for a wide variety of applications, enabling superior multiplexing factors. In existing designs, resonators undergo a non-uniform shift in frequency and sensitivity with fabrication imperfections, ultimately limiting effective bandwidth utilization. We overcome this drawback by implementing independent control of both frequency and sensitivity. We describe the design of the detector and report experimental results demonstrating its resilience to fabrication tolerances. C1 [Volkmann, Mark H.; Swenson, Loren J.; Spear, Peter; Whittaker, Jed D.; Altomare, Fabio; Berkley, Andrew J.; Bunyk, Paul; Harris, Richard; Hilton, Jeremy P.; Hoskinson, Emile H.; Johnson, Mark W.; Ladizinsky, Eric; Lanting, Trevor M.; Oh, Travis; Perminov, Ilya; Tolkacheva, Elena; Wilkinson, Warren; Yao, Jason] D Wave Syst Inc, Proc Dev Grp, 3033 Beta Ave, Burnaby, BC, Canada. [Bumble, Bruce; Day, Peter K.; Eom, Byeong Ho; Kleinsasser, Alan] Jet Prop Labs, Microdevices Lab, Pasadena, CA USA. RP Volkmann, MH (reprint author), D Wave Syst Inc, Proc Dev Grp, 3033 Beta Ave, Burnaby, BC, Canada. EM mvolkmann@dwavesys.com NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-8348-6 PY 2015 AR QI-O04 PG 3 WC Engineering, Electrical & Electronic; Materials Science, Multidisciplinary SC Engineering; Materials Science GA BF1FO UT WOS:000380391200041 ER PT J AU Sorce, M Pointeau, G Petit, M Mealier, AL Gibert, G Dominey, PF AF Sorce, Marwin Pointeau, Gregoire Petit, Maxime Mealier, Anne-Laure Gibert, Guillaume Dominey, Peter Ford GP IEEE TI Proof of Concept for a User-Centered System for Sharing Cooperative Plan Knowledge Over Extended Periods and Crew Changes in Space-Flight Operations SO 2015 24TH IEEE INTERNATIONAL SYMPOSIUM ON ROBOT AND HUMAN INTERACTIVE COMMUNICATION (RO-MAN) LA English DT Proceedings Paper CT 24th IEEE International Symposium on Robot and Human Interactive Communication (RO-MAN) CY AUG 31-SEP 04, 2015 CL Kobe, JAPAN SP IEEE, Robot Soc Japan, Korea Robot Soc, IEEE Robot & Automat Soc DE human-robot interaction; shared-plan; behavior learning; robotic teaching; space-flight operations ID LANGUAGE; ROBOT; IMITATION; TASKS AB With the Robonaut-2 humanoid robot now permanently flying on the ISS, the potential role for robots participating in cooperative activity in space is becoming a reality. Recent research has demonstrated that cooperation in the joint achievement of shared goals is a promising framework for human interaction with robots, with application in space. Perhaps more importantly, with the turn-over of crew members, robots could play an important role in maintaining and transferring expertise between outgoing and incoming crews. In this context, the current research builds on our experience in systems for cooperative human-robot interaction, introducing novel interface and interaction modalities that exploit the long-term experience of the robot. We implement a system where the human agent can teach the Nao humanoid new actions by physical demonstration, visual imitation, and spoken command. These actions can then be composed into joint action plans that coordinate the cooperation between agent and human. We also implement algorithms for an Autobiographical Memory (ABM) that provides access to of all of the robots interaction experience. These functions are assembled in a novel interaction paradigm for the capture, maintenance and transfer of knowledge in a five-tiered structure. The five tiers allow the robot to 1) learn simple behaviors, 2) learn shared plans composed from the learned behaviors, 3) execute the learned shared plans efficiently, 4) teach shared plans to new humans, and 5) answer questions from the human to better understand the origin of the shared plan. Our results demonstrate the feasibility of this system and indicate that such humanoid robot systems will provide a potential mechanism for the accumulation and transfer of knowledge, between humans who are not co-present. Applications to space flight operations as a target scenario are discussed. C1 [Sorce, Marwin; Pointeau, Gregoire; Petit, Maxime; Mealier, Anne-Laure; Gibert, Guillaume; Dominey, Peter Ford] INSERM, Human & Robot Interact Syst Grp, U846, 18 Ave Doyen, F-69675 Bron, France. [Dominey, Peter Ford] NASA, Jet Prop Lab, Mission Operat Syst Engn Sect, Sect 317, Pasadena, CA USA. [Dominey, Peter Ford] Imperial Coll, Personal Robot Lab, London, England. RP Sorce, M (reprint author), INSERM, Human & Robot Interact Syst Grp, U846, 18 Ave Doyen, F-69675 Bron, France. EM marwin.sorce@inserm.fr; Gregoire.pointeau@inserm.fr; maxime.petit@inserm.fr; anne-laure.mealier@inserm.fr; guillaume.gibert@inserm.fr; peter.dominey@inserm.fr NR 27 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-6704-2 PY 2015 BP 776 EP 783 PG 8 WC Computer Science, Cybernetics; Robotics SC Computer Science; Robotics GA BF1GF UT WOS:000380393600129 ER PT J AU Pavlis, EC Ciufolini, I Paolozzi, A Paris, C Sindoni, G AF Pavlis, E. C. Ciufolini, I. Paolozzi, A. Paris, C. Sindoni, G. GP IEEE TI Quality assessment of LARES satellite ranging data LARES contribution for improving the terrestrial reference frame SO 2015 2ND IEEE INTERNATIONAL WORKSHOP ON METROLOGY FOR AEROSPACE (METROAEROSPACE) LA English DT Proceedings Paper CT 2nd IEEE International Workshop on Metrology for Aerospace CY JUN 03-05, 2015 CL BENEVENTO, ITALY SP Ieee, Ieee Instrumentat & Measurement soc, AESS, Univ Studi Sannio DE LARES; laser ranging; general relativity; frame-dragging; CCR ID SYSTEM AB LARES is an Italian Space Agency mission designed to test General Relativity in the weak field of Earth. In particular, the satellite will be able to measure frame-dragging with an accuracy of about 1%. The difficulty of the measurement is mainly due to the perturbations acting on the satellite and the relatively tiny size of the effect, amounting to about 118 milliarcseconds/year. LARES will also provide data to geodesists and it will contribute to GNSS by improving the origin definition of the International Terrestrial Reference Frame. The mission was designed and the satellite subsystems built and tested in less than four years. The short time to launch and the very limited budget of the LARES mission, raised doubts whether LARES could be, as expected by design, one of the best satellite laser ranging targets. The best way to confirm the success of the mission is to look at the range residuals from the primary stations of the International Laser Ranging Service (ILRS). In the paper it will be shown that from the majority of these stations LARES behaves as the best target. C1 [Pavlis, E. C.] Univ Maryland Baltimore Cty, Goddard Earth Sci & Technol Ctr, Baltimore, MD 21228 USA. [Ciufolini, I.] Univ Salento, Lecce & Ctr Fermi, Dipartimento Ingn Innovaz, Rome, Italy. [Paolozzi, A.; Paris, C.; Sindoni, G.] Sapienza Univ Rome, Scuola Ingn Aerosp, Rome, Italy. [Paolozzi, A.; Paris, C.; Sindoni, G.] Sapienza Univ Rome, DIAEE, Rome, Italy. [Paolozzi, A.; Paris, C.] Ctr Fermi, Rome, Italy. RP Pavlis, EC (reprint author), Univ Maryland Baltimore Cty, Goddard Earth Sci & Technol Ctr, Baltimore, MD 21228 USA. EM epavlis@umbc.edu; ignazio.ciufolini@unisalento.it; antonio.paolozzi@uniroma1.it; claudio.paris@uniroma1.it; giampiero.sindoni@uniroma1.it NR 18 TC 3 Z9 3 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-7569-3 PY 2015 BP 1 EP 5 PG 5 WC Engineering, Aerospace SC Engineering GA BF1KM UT WOS:000380405000001 ER PT J AU Sindoni, G Pavlis, EC Paolozzi, A Paris, C Ciufolini, I AF Sindoni, G. Pavlis, E. C. Paolozzi, A. Paris, C. Ciufolini, I. GP IEEE TI Orbital predictions for the LARES satellite mission The International Space Time Analysis Research Center (ISTARC) SO 2015 2ND IEEE INTERNATIONAL WORKSHOP ON METROLOGY FOR AEROSPACE (METROAEROSPACE) LA English DT Proceedings Paper CT 2nd IEEE International Workshop on Metrology for Aerospace CY JUN 03-05, 2015 CL BENEVENTO, ITALY SP Ieee, Ieee Instrumentat & Measurement soc, AESS, Univ Studi Sannio DE LARES; General Relativity; Frame-Dragging; Lense-Thirring effect; SLR; Orbital Determination; ILRS ID GENERAL-RELATIVITY AB LARES is an Italian Space Agency satellite specifically designed, built and launched to test general relativity. It is a passive satellite covered with Cube Corner Reflectors that reflect laser pulses from tracking stations, thus allowing accurate measurement of the distance. That in turn enables accurate orbit reconstruction that is a key ingredient to allow the measurement of the tiny Lense-Thirring effect predicted by general relativity. The International Space Time Analysis Research Center provides the International Laser Ranging Service-ILRS, the orbital predictions for LARES for pointing of the tracking telescopes toward the target. The paper describes the technical aspects of generating the orbital predictions. C1 [Sindoni, G.; Paolozzi, A.; Paris, C.] Sapienza Univ Rome, DIAEE, Rome, Italy. [Sindoni, G.; Paolozzi, A.; Paris, C.] Sapienza Univ Rome, Scuola Ingn Aerosp, Rome, Italy. [Pavlis, E. C.] Univ Maryland Baltimore Cty, Goddard Earth Sci & Technol Ctr, Baltimore, MD 21228 USA. [Paolozzi, A.; Paris, C.; Ciufolini, I.] Ctr Fermi, Rome, Italy. [Ciufolini, I.] Univ Salento, Dipartimento Ingn Innovaz, Lecce, Italy. RP Sindoni, G (reprint author), Sapienza Univ Rome, DIAEE, Rome, Italy. EM giampiero.sindoni@uniroma1.it; epavlis@umbc.edu; antonio.paolozzi@uniroma1.it; claudio.paris@uniroma1.it; ignazio.ciufolini@unisalento.it NR 23 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-7569-3 PY 2015 BP 66 EP 70 PG 5 WC Engineering, Aerospace SC Engineering GA BF1KM UT WOS:000380405000013 ER PT J AU Graydon, PJ AF Graydon, Patrick John GP IEEE TI Formal Assurance Arguments: A Solution In Search of a Problem? SO 2015 45TH ANNUAL IEEE/IFIP INTERNATIONAL CONFERENCE ON DEPENDABLE SYSTEMS AND NETWORKS LA English DT Proceedings Paper CT 45th Annual IEEE/IFIP International Conference on Dependable Systems and Networks CY JUN 22-25, 2015 CL Univ Estadual Campinas, Rio de Janeiro, BRAZIL SP IEEE Comp Soc Int Fed Inform Proc (IFIP), Brazilian Comp Soc (SBC), Coordenacao Aperfeicoamento Pessoal Nivel Superior (CAPES), Ministerio Educacao Brazil, Conselho Nacl Desenvolvimento Cientifico Tecnologico (CNPq), Fundacao Carlos Chagas Filho Amparo Pesquisa Estado Rio de Janeiro (FAPERJ) HO Univ Estadual Campinas DE safety case; security case; assurance argument; formal argumentation AB An assurance case comprises evidence and argument showing how that evidence supports assurance claims (e.g., about safety or security). It is unsurprising that some computer scientists have proposed formalising assurance arguments: most associate formality with rigour. But while engineers can sometimes prove that source code refines a formal specification, it is not clear that formalisation will improve assurance arguments or that this benefit is worth its cost. For example, formalisation might reduce the benefits of argumentation by limiting the audience to people who can read formal logic. In this paper, we present (1) a systematic survey of the literature surrounding formal assurance arguments, (2) an analysis of errors that formalism can help to eliminate, (3) a discussion of existing evidence, and (4) suggestions for experimental work to definitively answer the question. C1 [Graydon, Patrick John] Malardalen Univ, Vasteras, Sweden. [Graydon, Patrick John] NASA, Langley Res Ctr, Washington, DC 20546 USA. RP Graydon, PJ (reprint author), Malardalen Univ, Vasteras, Sweden. EM patrick.j.graydon@nasa.gov NR 45 TC 1 Z9 1 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-8629-3 PY 2015 BP 517 EP 528 DI 10.1109/DSN.2015.28 PG 12 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF1PN UT WOS:000380425700046 ER PT J AU McGibbney, LJ Whitehall, KD Mattmann, CA Carter, PM AF McGibbney, Lewis J. Whitehall, Kim D. Mattmann, Chris A. Carter, Phillip M. GP IEEE TI Enabling Linguistic Analysis of Scientific Metadata through Internationalizing NASA JPL's PODAAC SO 2015 IEEE 16TH INTERNATIONAL CONFERENCE ON INFORMATION REUSE AND INTEGRATION LA English DT Proceedings Paper CT IEEE 16th International Conference on Information Reuse and Integration CY AUG 13-15, 2015 CL San Francisco, CA SP SIRI, IEEE Comp Soc, FIU Comp & Informat Sci, Nanjing Univ Posts & Telecommun, Almanden Inst IBM DE Web-Services; Scientific Data; Scientific Language; Machine Translation; Training; Apache Tika AB This paper describes the iPReS(1) project, which provides a web service-based framework for i18n-type (internationalized) access to scientific data products and product metadata contained within the NASA Jet Propulsion Laboratory Physical Oceanography Distributed Active Archive Center, otherwise known as PO.DAAC. PO.DAAC is an element of the EOSDIS2, which freely provides science data to the global community of users. The mission of the PO.DAAC is to preserve the quality of NASA's oceanic and climate data and make these universally accessible. iPReS directly shadows this mission objective. C1 [McGibbney, Lewis J.; Whitehall, Kim D.; Mattmann, Chris A.] NASA Jet Prop Lab, Comp Sci Data Intens Applicat Grp 398M, Pasadena, CA 91109 USA. [Carter, Phillip M.] Oregon State Univ, Sch Elect Engn & Comp Sci, Corvallis, OR 97331 USA. RP McGibbney, LJ (reprint author), NASA Jet Prop Lab, Comp Sci Data Intens Applicat Grp 398M, Pasadena, CA 91109 USA. EM Lewis.j.mcgibbney@jpl.nasa.gov; carterp@onid.oregonstate.edu NR 7 TC 0 Z9 0 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-6656-4 PY 2015 BP 207 EP 210 DI 10.1109/IRI.2015.41 PG 4 WC Computer Science, Artificial Intelligence SC Computer Science GA BF2EB UT WOS:000380459500028 ER PT J AU Verma, R Mattmann, CA AF Verma, Rishi Mattmann, Chris A. GP IEEE TI Extending Spark Analytics through Tika-based Information Extraction and Retrieval SO 2015 IEEE 16TH INTERNATIONAL CONFERENCE ON INFORMATION REUSE AND INTEGRATION LA English DT Proceedings Paper CT IEEE 16th International Conference on Information Reuse and Integration CY AUG 13-15, 2015 CL San Francisco, CA SP SIRI, IEEE Comp Soc, FIU Comp & Informat Sci, Nanjing Univ Posts & Telecommun, Almanden Inst IBM DE Spark; Tika; Hadoop; cluster computing; distributed computing AB In this paper, we focus on techniques to merge the parallelized data processing (i.e. map-reduce) capabilities of Apache Spark with the extensive file-type parsing support of Apache Tika. These two frameworks each have unique appeal for data scientists. Where Spark makes highly efficient the parallelized processing of very large, often text-based data sets, Tika makes consistent the information extraction of over 1,200 text and binary file types on a sequential file basis. The technical integration of these two frameworks is the subject of our investigation, and is relevant for data scientists pursuing two types of use cases: (1) analysis of numerous (1000x) un-partitioned small to medium sized Tika parse-able files, and (2) analysis of very large partition-able Tika parse-able files. Given Tika's niche specialization of file extraction and Spark's specialization of parallelized computing, there is a need to explore the benefits of integration. Thus, we investigate best practices so as to empower data scientists with tools to gain insight into a greater portion of data formats commonly in use. C1 [Verma, Rishi; Mattmann, Chris A.] Univ Southern Calif, Dept Comp Sci, Los Angeles, CA 90089 USA. [Verma, Rishi; Mattmann, Chris A.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Verma, R (reprint author), Univ Southern Calif, Dept Comp Sci, Los Angeles, CA 90089 USA. EM rverma@usc.edu; mattmann@usc.edu NR 7 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-6656-4 PY 2015 BP 215 EP 218 DI 10.1109/IRI.2015.43 PG 4 WC Computer Science, Artificial Intelligence SC Computer Science GA BF2EB UT WOS:000380459500030 ER PT J AU Kumar, U Milesi, C Ganguly, S Raja, SK Nemani, RR AF Kumar, Uttam Milesi, Cristina Ganguly, Sangram Raja, S. Kumar Nemani, Ramakrishna R. GP IEEE TI Simplex Projection for Land Cover Information Mining from Landsat-5 TM Data SO 2015 IEEE 16TH INTERNATIONAL CONFERENCE ON INFORMATION REUSE AND INTEGRATION LA English DT Proceedings Paper CT IEEE 16th International Conference on Information Reuse and Integration CY AUG 13-15, 2015 CL San Francisco, CA SP SIRI, IEEE Comp Soc, FIU Comp & Informat Sci, Nanjing Univ Posts & Telecommun, Almanden Inst IBM DE land cover; information mining; linear spectral unmixing; mixed pixels; simplex projection ID IMAGE CLASSIFICATION; MIXTURE-MODELS; ALGORITHM AB In this paper we explore the efficacy of simplex projection for land cover (LC) information mining. LC is the observed biophysical cover on the surface of the Earth and describes how much of a region is covered by forests, wetlands, impervious surfaces, etc. LC information can be extracted by processing remotely sensed data acquired through sensors mounted either on space borne satellites or aircrafts. Since these data are a mixture of more than two LC class types, unmixing algorithms based on linear mixture model such as simplex projection, aims to resolve the different components of mixed pixels in the data. This method is based on the equivalence of the fully constrained least squares problem of projecting a point onto a simplex. The algorithm does not perform optimization and is analytical, thus reducing the computational complexity. The algorithm is tested on computer-simulated data of various signal to noise ratio and Landsat-5 TM data of an agricultural landscape and an urban scenario. The results are validated using descriptive statistics, correlation coefficient, root mean square error, probability of success and bivariate distribution function. C1 [Kumar, Uttam] NASA Ames Res Ctr, Oak Ridge Associated Univ, Moffett Field, CA 94035 USA. [Milesi, Cristina; Nemani, Ramakrishna R.] NASA Ames Res Ctr, Moffett Field, CA 94035 USA. [Ganguly, Sangram] BAERI NASA Ames Res Ctr, Moffett Field, CA 94035 USA. [Raja, S. Kumar] Airbus Engn Ctr India, EADS Innovat Works, Bangalore 560048, Karnataka, India. RP Kumar, U (reprint author), NASA Ames Res Ctr, Oak Ridge Associated Univ, Moffett Field, CA 94035 USA. EM uttam.kumar@nasa.gov; cristina.milesi@nasa.gov; sangram.ganguly@nasa.gov; sk.kumar.raja@gmail.com; rama.nemani@nasa.gov NR 29 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-6656-4 PY 2015 BP 244 EP 251 DI 10.1109/IRI.2015.48 PG 8 WC Computer Science, Artificial Intelligence SC Computer Science GA BF2EB UT WOS:000380459500035 ER PT J AU Kumar, U Milesi, C Raja, SK Ganguly, S Nemani, RR AF Kumar, Uttam Milesi, Cristina Raja, S. Kumar Ganguly, Sangram Nemani, Ramakrishna R. GP IEEE TI Unconstrained Linear Spectral Mixture Models for Spatial Information Extraction: A Comparative Study SO 2015 IEEE 16TH INTERNATIONAL CONFERENCE ON INFORMATION REUSE AND INTEGRATION LA English DT Proceedings Paper CT IEEE 16th International Conference on Information Reuse and Integration CY AUG 13-15, 2015 CL San Francisco, CA SP SIRI, IEEE Comp Soc, FIU Comp & Informat Sci, Nanjing Univ Posts & Telecommun, Almanden Inst IBM DE mixed pixels; unconstrained mixture models; information extraction; linear spectral unmixing; algorithms ID ALGORITHM AB Linear spectral unmixing remains an important subject of research in image processing community. It deals with disintegrating a pixel spectrum into its constituent spectra through a mixture model assuming that observed data are linear mixtures of two or more objects, representing a mixed pixel. The linear mixture model allows a number of target materials (classes) to be present, each contributing a fraction of its unique, fixed spectrum corresponding to the area occupied by that material in a pixel. The linear model is inverted to produce estimates of those fractional abundances. The optimal solution of the mixture model can be an unconstrained solution, partially constrained solution or a fully constrained solution when the abundance non-negativity and abundance sum-to-one constraints are imposed. Although constrained algorithms are appropriate for target quantification and for estimating abundance fractions, unconstrained models are more suitable for applications seeking target detection, identification and discrimination. In this paper we perform a comparative study of five unconstrained mixture models - unconstrained least squares, orthogonal subspace projection, singular value decomposition, sparse unmixing via variable splitting and augmented Lagrangian (SUnSAL) and SUnSAL Total Variation (SUnSAL TV). The algorithms are tested on computer-simulated data of various signal to noise ratio and Landsat-5 TM data of an agricultural landscape and an urban scenario. The results were validated using descriptive statistics, correlation coefficient, RMSE, probability of success, and bivariate distribution function. C1 [Kumar, Uttam] NASA, Ames Res Ctr, Oak Ridge Associated Univ, Moffett Field, CA 94035 USA. [Milesi, Cristina; Nemani, Ramakrishna R.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Raja, S. Kumar] Airbus Engn Ctr India, EADS Innovat Works, Bangalore 560048, Karnataka, India. [Ganguly, Sangram] NASA, Ames Res Ctr, BAERI, Moffett Field, CA 94035 USA. RP Kumar, U (reprint author), NASA, Ames Res Ctr, Oak Ridge Associated Univ, Moffett Field, CA 94035 USA. EM uttam.kumar@nasa.gov; cristina.milesi@nasa.gov; sk.kumar.raja@gmail.com; sangram.ganguly@nasa.gov; rama.nemani@nasa.gov NR 37 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-6656-4 PY 2015 BP 574 EP 581 DI 10.1109/IRI.2015.91 PG 8 WC Computer Science, Artificial Intelligence SC Computer Science GA BF2EB UT WOS:000380459500080 ER PT S AU Beohar, N Bakliwal, P Roy, S Mandal, D Adell, P Vermeire, B Bakkaloglu, B Ozev, S AF Beohar, Navankur Bakliwal, Priyanka Roy, Sidhanto Mandal, Debashis Adell, Philippe Vermeire, Bert Bakkaloglu, Bertan Ozev, Sule GP IEEE TI Disturbance-free BIST for Loop Characterization of DC-DC Buck Converters SO 2015 IEEE 33RD VLSI TEST SYMPOSIUM (VTS) SE IEEE VLSI Test Symposium LA English DT Proceedings Paper CT 2015 IEEE 33rd VLSI TEST SYMPOSIUM (VTS) CY APR 27-29, 2015 CL Napa, CA SP IEEE Comp Soc, TTTC Test Technol Tech Council ID CROSS-CORRELATION METHODS; POWER CONVERTERS; IDENTIFICATION AB Complex electronic systems include multiple power domains and drastically varying dynamic power consumption patterns, requiring the use of multiple power conversion and regulation units. High frequency switching converters have been gaining prominence in the DC-DC converter market due to their high efficiency. Unfortunately, they are also subject to higher process variations jeopardizing stable operation of the power supply. This paper presents a technique to track changes in the dynamic loop characteristics of the DC-DC converters without disturbing the normal mode of operation using a white noise based excitation and correlation. White noise excitation is generated via pseudo random disturbance at reference and PWM input of the converter with the test signal energy being spread over a wide bandwidth, below the converter noise and ripple floor. Test signal analysis is achieved by correlating the pseudo random input sequence with the output response and thereby accumulating the desired behavior over time and pulling it above the noise floor of the measurement set-up. An off-the-shelf power converter, LM27402 is used as the DUT for the experimental verification. Experimental results show that the proposed technique can estimate converter's natural frequency and Q-factor within +/- 2.5% and +/- 0.7% error margin respectively, over changes in load inductance and capacitance. C1 [Beohar, Navankur; Bakliwal, Priyanka; Roy, Sidhanto; Mandal, Debashis; Bakkaloglu, Bertan; Ozev, Sule] Arizona State Univ, Sch Elect Comp & Energy Engn, Tempe, AZ 85281 USA. [Adell, Philippe] NASA, Jet Prop Lab, Pasadena, CA USA. [Vermeire, Bert] Space Micro Inc, San Diego, CA USA. RP Beohar, N (reprint author), Arizona State Univ, Sch Elect Comp & Energy Engn, Tempe, AZ 85281 USA. NR 15 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1093-0167 BN 978-1-4799-7597-6 J9 IEEE VLSI TEST SYMP PY 2015 PG 6 WC Computer Science, Hardware & Architecture; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF1UG UT WOS:000380437500006 ER PT S AU Francis, R Estlin, T Gaines, D Bornstein, B Schaffer, S Verma, V Anderson, R Burl, M Chu, S Castano, R Thompson, D Blaney, D de Flores, L Doran, G Nelson, T Wiens, R AF Francis, Raymond Estlin, Tara Gaines, Daniel Bornstein, Benjamin Schaffer, Steven Verma, Vandi Anderson, Robert Burl, Michael Chu, Selina Castano, Rebecca Thompson, David Blaney, Diana de Flores, Lauren Doran, Gary Nelson, Tony Wiens, Roger GP IEEE TI AEGIS Autonomous Targeting for the Curiosity Rover's ChemCam Instrument SO 2015 IEEE APPLIED IMAGERY PATTERN RECOGNITION WORKSHOP (AIPR) SE IEEE Applied Imagery Pattern Recognition Workshop LA English DT Proceedings Paper CT IEEE Applied Imagery Pattern Recognition Workshop (AIPR) CY OCT 13-15, 2015 CL Washington, DC DE autonomous science; mars; planetary exploration; image interpretation; natural scene interpretation AB AEGIS (Autonomous Exploration for Gathering Increased Science) is a software suite that will imminently be operational aboard NASA's Curiosity Mars rover, allowing the rover to autonomously detect and prioritize targets in its surroundings, and acquire geochemical spectra using its ChemCam instrument. ChemCam, a Laser-Induced Breakdown Spectrometer (LIBS), is normally used to study targets selected by scientists using images taken by the rover on a previous sol and relayed by Mars orbiters to Earth. During certain mission phases, ground-based target selection entails significant delays and the use of limited communication bandwidth to send the images. AEGIS will allow the science team to define the properties of preferred targets, and obtain geochemical data more quickly, at lower data penalty, without the extra ground-in-the-loop step. The system uses advanced image analysis techniques to find targets in images taken by the rover's stereo navigation cameras (NavCam), and can rank, filter, and select targets based on properties selected by the science team. AEGIS can also be used to analyze images from ChemCam's Remote Micro Imager (RMI) context camera, allowing it to autonomously target very fine-scale features - such as veins in a rock outcrop - which are too small to detect with the range and resolution of NavCam. AEGIS allows science activities to be conducted in a greater range of mission conditions, and saves precious time and command cycles during the rover's surface mission. The system is currently undergoing initial tests and checkouts aboard the rover, and is expected to be operational by late 2015. Other current activities are focused on science team training and the development of target profiles for the environments in which AEGIS is expected to be used on Mars. C1 [Francis, Raymond; Estlin, Tara; Gaines, Daniel; Bornstein, Benjamin; Schaffer, Steven; Verma, Vandi; Anderson, Robert; Burl, Michael; Chu, Selina; Castano, Rebecca; Thompson, David; Blaney, Diana; de Flores, Lauren; Doran, Gary] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. [Nelson, Tony; Wiens, Roger] Los Alamos Natl Lab, Los Alamos, NM USA. RP Francis, R (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. EM raymond.francis@jpl.nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1550-5219 BN 978-1-4673-9558-8 J9 IEEE APP IMG PAT PY 2015 PG 5 WC Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic; Imaging Science & Photographic Technology SC Computer Science; Engineering; Imaging Science & Photographic Technology GA BF1YA UT WOS:000380444400023 ER PT S AU Assad, C Wolf, MT Karras, J Reid, J Stoica, A AF Assad, Christopher Wolf, Michael T. Karras, Jaakko Reid, Jason Stoica, Adrian GP IEEE TI JPL BioSleeve for Gesture-Based Control Technology Development and Field Trials SO 2015 IEEE INTERNATIONAL CONFERENCE ON TECHNOLOGIES FOR PRACTICAL ROBOT APPLICATIONS (TEPRA) SE IEEE International Conference on Technologies for Practical Robot Applications LA English DT Proceedings Paper CT IEEE International Conference on Technologies for Practical Robot Applications (TePRA) CY MAY 11-12, 2013 CL Wobrun, MA DE gesture recognition; Human-Robot Interaction; surface EMG; IROC Challenge ID RECOGNITION AB The JPL BioSleeve is a wearable gesture-based human interface for natural robot control. Activity of the user's hand and arm is monitored via surface electromyography sensors and an inertial measurement unit that are embedded in a forearm sleeve. Gesture recognition software then decodes the sensor signals, classifies gesture type, and maps the result to output commands to be sent to a robot. The BioSleeve interface can accurately and reliably decode as many as sixteen discrete hand and finger gestures and estimate the continuous orientation of the forearm. Here we report development of a new wireless BioSleeve prototype that enables portable field use. Gesture-based commands were developed to control a QinetiQ Dragon Runner tracked robot, including a 4 degree-of-freedom manipulator and a stereo camera pair. Gestures can be sent in several modes: for supervisory point-to-goal driving commands, virtual joystick for teleoperation of driving and manipulator, and pan-tilt of the camera. Hand gestures and arm positions are mapped to various commands recognized by the robot's onboard control software, and are meant to integrate with the robot's perception of its environment and its ability to complete tasks with various levels of autonomy. The portable BioSleeve interface was demonstrated through control of the Dragon Runner during participation in field trials at the 2014 Intuitive Robotic Operator Control Challenge. The successful completion of Challenge events demonstrated the versatility of the system to provide multiple commands in different modes of control to a robot operating under difficult real-world environmental conditions. C1 [Assad, Christopher; Wolf, Michael T.; Karras, Jaakko; Reid, Jason; Stoica, Adrian] CALTECH, Mobil & Robot Syst Sect, Jet Prop Lab, Pasadena, CA 91125 USA. RP Assad, C (reprint author), CALTECH, Mobil & Robot Syst Sect, Jet Prop Lab, Pasadena, CA 91125 USA. EM chris.assad@jpl.nasa.gov NR 9 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2325-0526 BN 978-1-4799-8757-3 J9 IEEE INT CONF TECH PY 2015 PG 6 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic; Robotics SC Automation & Control Systems; Computer Science; Engineering; Robotics GA BF1IX UT WOS:000380401000013 ER PT J AU Zhang, J Wang, W Wei, X Lee, C Lee, S Pan, L Lee, TJ AF Zhang, Jia Wang, Wei Wei, Xing Lee, Chris Lee, Seungwon Pan, Lei Lee, Tsengdar J. BA Zhu, H BF Zhu, H BE Miller, JS TI Climate Analytics Workflow Recommendation as a Service - Provenance-driven Automatic Workflow Mashup SO 2015 IEEE INTERNATIONAL CONFERENCE ON WEB SERVICES (ICWS) LA English DT Proceedings Paper CT Web Services ICWS IEEE International Conference CY JUN 27-JUL 02, 2015 CL New York, NY SP IEEE COMP SOC, SERV SOC, SERV COMP, BIG DATA, HP, IBM, ERICSSON, SAP, IBM RES, HUAWEI, OBJECT MANAGEMENT GRP, IEEE CLOUD COMP, BUSINESS PROCESS INTEGRAT & MANAGEMENT, PROFESS, INT J WEB SERV RES, COMP NOW, IEEE T SERV COMP, IEEE, CLOUD COMP DE Service recommendation; automatic workflow generation AB Existing scientific workflow tools, created by computer scientists, require that domain scientists meticulously design their multi-step experiments before analyzing data. However, this is oftentimes contradictory to a domain scientist's routine of conducting research and exploration. This paper presents a novel way to resolve this dispute, in the context of service-oriented science. After scrutinizing how Earth scientists conduct data analytics research in their daily work, a provenance model is developed to record their activities. Reverse-engineering the provenance, a technology is developed to automatically generate workflows for scientists to review and revise, supported by a Petri nets-based workflow verification instrument. In addition, dataset is proposed to be treated as first-class citizen to drive the knowledge sharing and recommendation. A data-centric repository infrastructure is established to catch richer provenance to further facilitate collaboration in the science community. In this way, we aim to revolutionize computer-supported Earth science. C1 [Zhang, Jia; Wang, Wei; Wei, Xing; Lee, Chris] Carnegie Mellon Univ Silicon Valley, Moffett Field, CA 94035 USA. [Lee, Seungwon; Pan, Lei] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. [Lee, Tsengdar J.] NASA Headquarters, Sci Miss Directorate, Washington, DC USA. RP Zhang, J (reprint author), Carnegie Mellon Univ Silicon Valley, Moffett Field, CA 94035 USA. EM jia.zhang@sv.cmu.edu; seungwon.lee@jpl.nasa.gov; lei.pan@jpl.nasa.gov; tsengdar.j.lee@nasa.gov NR 24 TC 1 Z9 1 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-7272-5 PY 2015 BP 89 EP 97 DI 10.1109/ICWS.2015.22 PG 9 WC Engineering, Electrical & Electronic SC Engineering GA BF2OU UT WOS:000380486400012 ER PT J AU Hensley, S Van Zyl, J Lavalle, M Neumann, M Michel, T Muellerschoen, R Pinto, N Simard, M Moghaddam, M AF Hensley, Scott Van Zyl, Jakob Lavalle, Marco Neumann, Maxim Michel, Thierry Muellerschoen, Ron Pinto, Naiara Simard, Marc Moghaddam, Mahta GP IEEE TI L-Band and P-Band Studies of Vegetation at JPL SO 2015 IEEE RADAR CONFERENCE LA English DT Proceedings Paper CT IEEE Radar Conference CY OCT 27-30, 2015 CL Johannesburg, SOUTH AFRICA SP Inst Elect & Elect Engineers, Geosci & Remote Sensing Soc AB Longer wavelength radar signals are known to penetrate deeper into foliage. L-Band and P-band radars have been used extensively by the remote sensing community for vegetation studies. Radar interferometry, in particular polarimetric radar interferometry has been shown to be able to estimate vegetation structure parameters, for example vegetation height, to meter level accuracy with suitable imaging geometries. Several proposed mission including the ESA BIOMASS and NASA NISAR are planned to operate at these higher frequencies and to estimate various biophysical vegetation parameters. This paper will present some results of polarimetric-interferometric studies of temporal and tropical forests using airborne L-band and P-band radar data collected by the UAVSAR and AIRMOSS radars and comparing them to in situ measurements. These will be used to inform the ability to extract vegetation information for these spaceborne missions. C1 [Hensley, Scott; Van Zyl, Jakob; Lavalle, Marco; Neumann, Maxim; Michel, Thierry; Muellerschoen, Ron; Pinto, Naiara; Simard, Marc] CALTECH, Jet Prop Lab, Radar Sci & Engn Sect, Pasadena, CA 91109 USA. [Moghaddam, Mahta] Univ Southern Calif, Dept Elect Enigineering, Los Angeles, CA 90089 USA. RP Hensley, S (reprint author), CALTECH, Jet Prop Lab, Radar Sci & Engn Sect, Pasadena, CA 91109 USA. NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-9655-4 PY 2015 BP 516 EP 520 PG 5 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BF1WN UT WOS:000380440700093 ER PT S AU Iturbe, X Keymeulen, D Yiu, P Berisford, D Hand, K Carlson, R Ozer, E AF Iturbe, Xabier Keymeulen, Didier Yiu, Patrick Berisford, Dan Hand, Kevin Carlson, Robert Ozer, Emre GP IEEE TI Towards a Generic and Adaptive System-on-Chip Controller for Space Exploration Instrumentation SO 2015 NASA/ESA CONFERENCE ON ADAPTIVE HARDWARE AND SYSTEMS (AHS) SE NASA/ESA Conference on Adaptive Hardware and Systems LA English DT Proceedings Paper CT 2015 NASA ESA Conference on Adaptive Hardware and Systems AHS CY JUN 15-18, 2015 CL Montreal, CANADA SP ADEVO, Athens Consulting, JPL, NASA, Fraunhofer IIS, eesa, Sic da, CAS, RESMIQ, IEEE, Polytech Montreal DE System-on-Chip; ARM; FPGA; Data Processing AB This paper introduces one of the first efforts conducted at NASA's Jet Propulsion Laboratory (JPL) to develop a generic System-on-Chip (SoC) platform to control science instruments that are proposed for future NASA missions. The SoC platform is named APEX-SoC, where APEX stands for Advanced Processor for space Exploration, and is based on a hybrid Xilinx Zynq that combines an FPGA and an ARM Cortex-A9 dual-core processor on a single chip. The Zynq implements a generic and customizable on-chip infrastructure that can be reused with a variety of instruments, and it has been coupled with a set of off-chip components that are necessary to deal with the different instruments. We have taken JPL's Compositional InfraRed Imaging Spectrometer (CIRIS), which is proposed for NASA icy moons missions, as a use-case scenario to demonstrate that the entire data processing, control and interface of an instrument can be implemented on a single device using the on-chip infrastructure described in this paper. We show that the performance results achieved in this preliminary version of the instrumentation controller are sufficient to fulfil the science requirements demanded to the CIRIS instrument in future NASA missions, such as Europa. C1 [Iturbe, Xabier; Yiu, Patrick] CALTECH, Pasadena, CA 91125 USA. [Iturbe, Xabier; Keymeulen, Didier; Berisford, Dan; Hand, Kevin; Carlson, Robert] CALTECH, Jet Prop Lab, NASA, Pasadena, CA USA. [Iturbe, Xabier; Ozer, Emre] ARM R&D, Cambridge, England. RP Iturbe, X (reprint author), CALTECH, Pasadena, CA 91125 USA. EM xabier.iturbe@jpl.nasa.gov NR 28 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1939-7003 BN 978-1-4673-7501-6 J9 NASA ESA CONF PY 2015 PG 8 WC Computer Science, Hardware & Architecture; Computer Science, Information Systems SC Computer Science GA BF2PD UT WOS:000380487200003 ER PT S AU Petrick, D Gill, N Hassouneh, M Stone, R Winternitz, L Thomas, L Davis, M Sparacino, P Flatley, T AF Petrick, David Gill, Nat Hassouneh, Munther Stone, Robert Winternitz, Luke Thomas, Luke Davis, Milton Sparacino, Pietro Flatley, Thomas GP IEEE TI Adapting the SpaceCube v2.0 Data Processing System for Mission-Unique Application Requirements SO 2015 NASA/ESA CONFERENCE ON ADAPTIVE HARDWARE AND SYSTEMS (AHS) SE NASA/ESA Conference on Adaptive Hardware and Systems LA English DT Proceedings Paper CT 2015 NASA ESA Conference on Adaptive Hardware and Systems AHS CY JUN 15-18, 2015 CL Montreal, CANADA SP ADEVO, Athens Consulting, JPL, NASA, Fraunhofer IIS, eesa, Sic da, CAS, RESMIQ, IEEE, Polytech Montreal AB The paceCube (TM) v2.0 system is a high performance, reconfigurable, hybrid data processing system that can be used in a multitude of applications including those that require a radiation hardened and reliable solution. This paper provides an overview of the design architecture, flexibility, and the advantages of the modular SpaceCube v2.0 high performance data processing system for space applications. The current state of the proven SpaceCube technology is based on nine years of engineering and operations. Five systems have been successfully operated in space starting in 2008 with four more to be delivered for launch vehicle integration in 2015. The SpaceCube v2.0 system is also baselined as the avionics solution for five additional flight projects and is always a top consideration as the core avionics for new instruments or spacecraft control. This paper will highlight how this multipurpose system is currently being used to solve design challenges of three independent applications. The SpaceCube hardware adapts to new system requirements by allowing for application-unique interface cards that are utilized by reconfiguring the underlying programmable elements on the core processor card. We will show how this system is being used to improve on a heritage NASA GPS technology, enable a cutting-edge LiDAR instrument, and serve as a typical command and data handling (C&DH) computer for a space robotics technology demonstration. C1 [Petrick, David; Gill, Nat; Hassouneh, Munther; Stone, Robert; Winternitz, Luke; Thomas, Luke; Davis, Milton; Sparacino, Pietro; Flatley, Thomas] NASA, Goddard Space Flight, Greenbelt, MD 20771 USA. RP Petrick, D (reprint author), NASA, Goddard Space Flight, Greenbelt, MD 20771 USA. EM david.j.petrick@nasa.gov NR 14 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1939-7003 BN 978-1-4673-7501-6 J9 NASA ESA CONF PY 2015 PG 8 WC Computer Science, Hardware & Architecture; Computer Science, Information Systems SC Computer Science GA BF2PD UT WOS:000380487200005 ER PT B AU Hah, C AF Hah, Chunill GP ASME TI EFFECTS OF UNSTEADY FLOW INTERACTIONS ON THE PERFORMANCE OF A HIGHLY-LOADED TRANSONIC COMPRESSOR STAGE SO ASME TURBO EXPO: TURBINE TECHNICAL CONFERENCE AND EXPOSITION, 2015, VOL 2A LA English DT Proceedings Paper CT ASME Turbo Expo: Turbine Technical Conference and Exposition CY JUN 15-19, 2015 CL Montreal, CANADA SP Int Gas Turbine Inst ID WAKES AB The primary focus of this paper is to investigate the loss sources in an advanced GE transonic compressor design with high reaction and high stage loading. This advanced compressor has been investigated both experimentally and analytically in the past. The measured compressor efficiency is significantly lower than the efficiency calculated with various existing tools based on RANS and URANS. The general understanding is that some important flow physics in this modern compressor design are not represented in the current tools. To pinpoint the source of the efficiency miss, an advanced test with detailed flow traverse was performed for the front one and a half stage at the NASA Glenn Research Center. In the present paper, a Large Eddy Simulation (LES) is employed to determine whether a higher-fidelity simulation can pick up any additional flow physics that can explain past efficiency miss with RANS and URANS. The results from the. Large Eddy Simulation were compared with the NASA test results and the GE interpretation of the test data. LES calculates lower total pressure and higher total temperature on the pressure side of the stator, resulting in large loss generation on the pressure side of the stator. On the other hand, existing tools based on the RANS and URANS do not calculate this high total temperature and low total pressure on the pressure side of the stator. The calculated loss through the stator from LES seems to match the measured data and the GE data interpretation. Detailed examination of the unsteady flow field from LES indicates that the accumulation of high loss near the pressure side of the stator is due to the interaction of the rotor wake with the stator blade. The strong rotor wake interacts quite differently with the pressure side of the stator than with the suction side of the stator blade. The concave curvature on the pressure side of the stator blade increases the mixing of the rotor wake with the pressure side boundary layer significantly. On the other hand, the convex curvature on the suction side of the stator blade decreases the mixing and the suction side blade boundary layer remains thin. The jet velocity in the rotor wake in the stator frame seems to magnify the curvature effect in addition to inviscid redistribution of wake fluid toward the pressure side of the blade. C1 [Hah, Chunill] NASA Glenn Res Ctr, MS 5-10, Cleveland, OH 44135 USA. RP Hah, C (reprint author), NASA Glenn Res Ctr, MS 5-10, Cleveland, OH 44135 USA. NR 18 TC 0 Z9 0 U1 1 U2 1 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-5663-5 PY 2015 AR V02AT37A037 PG 12 WC Engineering, Mechanical SC Engineering GA BF1AC UT WOS:000380084400037 ER PT B AU Prahst, PS Kulkarni, S Sohn, KH AF Prahst, Patricia S. Kulkarni, Sameer Sohn, Ki H. GP ASME TI EXPERIMENTAL RESULTS OF THE FIRST TWO STAGES OF AN ADVANCED TRANSONIC CORE COMPRESSOR UNDER ISOLATED AND MULTI-STAGE CONDITIONS SO ASME TURBO EXPO: TURBINE TECHNICAL CONFERENCE AND EXPOSITION, 2015, VOL 2A LA English DT Proceedings Paper CT ASME Turbo Expo: Turbine Technical Conference and Exposition CY JUN 15-19, 2015 CL Montreal, CANADA SP Int Gas Turbine Inst AB NASA's Environmentally Responsible Aviation (ERA) Program calls for investigation of the technology barriers associated with improved fuel efficiency for large gas turbine engines. Under ERA, the highly loaded core compressor technology program attempts to realize the fuel burn reduction goal by increasing overall pressure ratio of the compressor to increase thermal efficiency of the engine. Study engines with overall pressure ratio of 60 to 70 are now being investigated. This means that the high pressure compressor would have to almost double in pressure ratio while keeping a high level of efficiency. NASA and GE teamed to address this challenge by testing the first two stages of an advanced GE compressor designed to meet the requirements of a very high pressure ratio core compressor. Previous test experience of a compressor which included these front two stages indicated a performance deficit relative to design intent. Therefore, the current rig was designed to run in 1-stage and 2-stage configurations in two separate tests to assess whether the bow shock of the second rotor interacting with the upstream stage contributed to the unpredicted performance deficit, or if the culprit was due to interaction of rotor 1 and stator 1. Thus, the goal was to fully understand the stage 1 performance under isolated and multistage conditions, and additionally to provide a detailed aerodynamic data set for CFD validation. Full use was made of steady and unsteady measurement methods to understand fluid dynamics loss source mechanisms due to rotor shock interaction and endwall losses. This paper will present the description of the compressor test article and its measured performance and operability, for both the single stage and two stage configurations. We focus the paper on measurements at 97% corrected speed with design intent vane setting angles. C1 [Prahst, Patricia S.] Zin Technologies Inc, Cleveland, OH 44130 USA. [Kulkarni, Sameer] NASA Glenn Res Ctr, Cleveland, OH USA. [Sohn, Ki H.] GE Co, Cincinnati, OH USA. RP Prahst, PS (reprint author), Zin Technologies Inc, Cleveland, OH 44130 USA. NR 12 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-5663-5 PY 2015 AR V02AT37A023 PG 10 WC Engineering, Mechanical SC Engineering GA BF1AC UT WOS:000380084400023 ER PT B AU Shyam, V Ameri, A Poinsatte, P Thurman, D Wroblewski, A Snyder, C AF Shyam, Vikram Ameri, Ali Poinsatte, Philip Thurman, Douglas Wroblewski, Adam Snyder, Christopher GP ASME TI APPLICATION OF PINNIPED VIBRISSAE TO AEROPROPULSION SO ASME TURBO EXPO: TURBINE TECHNICAL CONFERENCE AND EXPOSITION, 2015, VOL 2A LA English DT Proceedings Paper CT ASME Turbo Expo: Turbine Technical Conference and Exposition CY JUN 15-19, 2015 CL Montreal, CANADA SP Int Gas Turbine Inst ID LEADING-EDGE PROTUBERANCES; PERFORMANCE; SURFACES AB Vibrissae (whiskers) of Phoca Vitulina (Harbor Seal) and Mirounga Angustirostris (Elephant Seal) possess undulations along their length. Harbor Seal Vibrissae have been shown to reduce vortex induced vibrations and reduce drag compared to appropriately scaled cylinders and ellipses. Samples of Harbor Seal vibrissae, Elephant Seal vibrissae and California Sea Lion vibrissae were collected from the Marine Mammal Center in California. CT scanning, microscopy and 3D scanning techniques were utilized to characterize the whiskers. Leading edge parameters from the whiskers were used to create a 3D profile based on a modern power turbine blade. The NASA SW-2 cascade wind tunnel facility was used to perform hotwire surveys and pitot surveys in the wake of the 'Seal Blades' to provide validation of Computational Fluid Dynamics simulations. Computational Fluid Dynamics simulations were used to study the effect of incidence angles from -37 to +10 degrees on the aerodynamic performance of the Seal blade. The tests and simulations were conducted at a Reynolds number of 100,000 based on inlet conditions and blade axial chord. The Seal blades showed consistent performance improvements over the baseline configuration. It was determined that a fuel burn reduction of approximately 5% could be achieved for a fixed wing aircraft. C1 [Shyam, Vikram; Poinsatte, Philip; Wroblewski, Adam; Snyder, Christopher] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. [Ameri, Ali] Ohio State Univ, Columbus, OH 43210 USA. [Thurman, Douglas] US Army, Res Lab, Cleveland, OH USA. RP Shyam, V (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 29 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-5663-5 PY 2015 AR V02AT38A023 PG 10 WC Engineering, Mechanical SC Engineering GA BF1AC UT WOS:000380084400066 ER PT B AU Garai, A Diosady, L Murman, S Madavan, N AF Garai, Anirban Diosady, Laslo Murman, Scott Madavan, Nateri GP ASME TI DNS OF FLOW IN A LOW-PRESSURE TURBINE CASCADE USING A DISCONTINUOUS-GALERKIN SPECTRAL-ELEMENT METHOD SO ASME TURBO EXPO: TURBINE TECHNICAL CONFERENCE AND EXPOSITION, 2015, VOL 2B LA English DT Proceedings Paper CT ASME Turbo Expo: Turbine Technical Conference and Exposition CY JUN 15-19, 2015 CL Montreal, CANADA SP Int Gas Turbine Inst ID LARGE-EDDY SIMULATION; DIRECT NUMERICAL-SIMULATION; INCOMING WAKES; TURBULENT-FLOW; NAVIER-STOKES; BLADE; FORMULATION; EQUATIONS; PASSAGE AB A new computational capability under development for accurate and efficient high-fidelity direct numerical simulation (DNS) and large-eddy simulation (LES) of turbomachinery is described. This capability is based on an entropy-stable Discontinuous-Galerkin spectral-element approach that extends to arbitrarily high orders of spatial and temporal accuracy, and is implemented in a computationally efficient manner on a modern high performance computer architecture. A validation study using this method to perform DNS of flow in a low-pressure turbine airfoil cascade is presented. The results indicate that the method captures the main features of the flow. C1 [Garai, Anirban] Oak Ridge Associated Univ, NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Diosady, Laslo] Sci & Technol Corp, NASA, Ames Res Ctr, Moffett Field, CA USA. [Murman, Scott; Madavan, Nateri] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Garai, A (reprint author), Oak Ridge Associated Univ, NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 34 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-5664-2 PY 2015 AR V02BT39A023 PG 10 WC Engineering, Mechanical SC Engineering GA BF1AE UT WOS:000380084700023 ER PT J AU Das, K Bhaduri, K Matthews, BL Oza, NC AF Das, Kamalika Bhaduri, Kanishka Matthews, Bryan L. Oza, Nikunj C. BE Ho, H Ooi, BC Zaki, MJ Hu, XH Haas, L Kumar, V Rachuri, S Yu, SP Hsiao, MHI Li, J Luo, F Pyne, S Ogan, K TI Large scale support vector regression for aviation safety SO PROCEEDINGS 2015 IEEE INTERNATIONAL CONFERENCE ON BIG DATA LA English DT Proceedings Paper CT IEEE International Conference on Big Data CY OCT 29-NOV 01, 2015 CL Santa Clara, CA SP IEEE, IEEE Comp Soc, Natl Sci Fdn, CCF, HUAWEI, Springer, ELSEVIER, CISCO, Intel DE distributed optimization; support vector regression; aviation ID MACHINES AB Regression problems on massive data sets are ubiquitous in many application domains including the Internet, earth and space sciences, and aviation. Support vector regression (SVR) is a popular technique for modeling the input-output relations of a set of variables under the added constraint of maximizing the margin, thereby leading to a very generalizable and regularized model. However, for a dataset with m training points, it is challenging to build SVR models due to the O(m(3)) cost involved in building them. In this paper we propose ParitoSVR - a parallel iterated optimizer for Support Vector Regression in the primal that can be deployed over a network of machines, where each machine iteratively solves a small (sub-)problem based only on the data observed locally and these solutions are then combined to form the solution to the global problem. Our proposed method is based on the Alternating Direction Method of Multipliers (ADMM) optimization technique. Unlike many other existing techniques, ParitoSVR is provably convergent to the results obtained from the centralized algorithm, where the optimization has access to the entire data set. The experimental results show that the algorithm is scalable both with respect to accuracy and time to convergence. We use ParitoSVR to identify flights having anomalous fuel consumption from a large fleet-wide commercial aviation database containing thousands of flights. Along with the algorithmic contributions, this paper also describes the process of deployment of the ADMM-based SVR method on a multicore architecture, namely, the NASA Pleiades supercomputing infrastructure. We have been successful in running ParitoSVR on millions of training data points and hundreds of compute nodes. C1 [Das, Kamalika] NASA Ames Res Ctr, UARC, Moffett Field, CA 94035 USA. [Bhaduri, Kanishka] Intuit Inc, Mountain View, CA 94043 USA. [Matthews, Bryan L.] NASA Ames Res Ctr, SGT Inc, Moffett Field, CA 94035 USA. [Oza, Nikunj C.] NASA Ames Res Ctr, Moffett Field, CA 94035 USA. RP Das, K (reprint author), NASA Ames Res Ctr, UARC, Moffett Field, CA 94035 USA. EM Kamalika.Das@nasa.gov; kanishka.bh@gmail.com; Bryan.L.Matthews@nasa.gov; Nikunj.C.Oza@nasa.gov NR 15 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-9925-5 PY 2015 BP 999 EP 1006 PG 8 WC Computer Science, Information Systems; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF1KI UT WOS:000380404600120 ER PT J AU Gyurjyan, V Bartle, A Lukashin, C Mancilla, S Oyarzun, R Vakhnin, A AF Gyurjyan, V. Bartle, A. Lukashin, C. Mancilla, S. Oyarzun, R. Vakhnin, A. BE Ho, H Ooi, BC Zaki, MJ Hu, XH Haas, L Kumar, V Rachuri, S Yu, SP Hsiao, MHI Li, J Luo, F Pyne, S Ogan, K TI Component Based Dataflow Processing Framework SO PROCEEDINGS 2015 IEEE INTERNATIONAL CONFERENCE ON BIG DATA LA English DT Proceedings Paper CT IEEE International Conference on Big Data CY OCT 29-NOV 01, 2015 CL Santa Clara, CA SP IEEE, IEEE Comp Soc, Natl Sci Fdn, CCF, HUAWEI, Springer, ELSEVIER, CISCO, Intel DE service oriented; publish-subscribe; data-driven; data-flow; earth science; data fusion AB In this paper we present SOA based CLAs12 event Reconstruction and Analyses (CLARA) framework used to develop Earth Science multi-sensor data fusion, processing, and analytics applications (NAIADS: NASA JLAB collaboration). CLARA design focus is on two main traits: a) real-time data stream processing, and b) service oriented architecture (SOA) in a flow based programming (FBP) paradigm. Data driven and data centric architecture of CLARA presents an environment for developing agile, elastic, multilingual data processing applications. The CLARA framework presents solutions, capable of processing large volumes of data interactively and substantially faster than batch systems. C1 [Gyurjyan, V.] TJNAF, Newport News, VA 23606 USA. [Lukashin, C.] NASA, Langley Res Ctr, Hampton, VA 23665 USA. [Bartle, A.] Mechdyne Co, Virginia Beach, VA USA. [Mancilla, S.; Oyarzun, R.] Univ Tecn Federico Santa Maria, Valparaiso, Chile. [Vakhnin, A.] Sci Syst & Applicat Inc, Hampton, VA USA. RP Gyurjyan, V (reprint author), TJNAF, Newport News, VA 23606 USA. NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-9925-5 PY 2015 BP 1938 EP 1942 PG 5 WC Computer Science, Information Systems; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF1KI UT WOS:000380404600239 ER PT J AU Lukashin, C Bartle, A Callaway, E Gyurjyan, V Mancilla, S Oyarzun, R Vakhnin, A AF Lukashin, C. Bartle, A. Callaway, E. Gyurjyan, V. Mancilla, S. Oyarzun, R. Vakhnin, A. BE Ho, H Ooi, BC Zaki, MJ Hu, XH Haas, L Kumar, V Rachuri, S Yu, SP Hsiao, MHI Li, J Luo, F Pyne, S Ogan, K TI Earth Science Data Fusion with Event Building Approach SO PROCEEDINGS 2015 IEEE INTERNATIONAL CONFERENCE ON BIG DATA LA English DT Proceedings Paper CT IEEE International Conference on Big Data CY OCT 29-NOV 01, 2015 CL Santa Clara, CA SP IEEE, IEEE Comp Soc, Natl Sci Fdn, CCF, HUAWEI, Springer, ELSEVIER, CISCO, Intel DE earth science; data fusion; framework; event builder AB Objectives of the NASA Information And Data System (NAIADS) project are to develop a prototype of a conceptually new middleware framework to modernize and significantly improve efficiency of the Earth Science data fusion, big data processing and analytics. The key components of the NAIADS include: Service Oriented Architecture (SOA) multi-lingual framework, multi-sensor coincident data Predictor, fast into-memory data Staging, multi-sensor data-Event Builder, complete data-Event streaming (a workflow with minimized IO), on-line data processing control and analytics services. The NAIADS project is leveraging CLARA framework, developed in Jefferson Lab, and integrated with the ZeroMQ messaging library. The science services are prototyped and incorporated into the system. Merging the SCIAMACHY Level-1 observations and MODIS/Terra Level-2 (Clouds and Aerosols) data products, and ECMWF re-analysis will be used for NAIADS demonstration and performance tests in compute Cloud and Cluster environments. C1 [Lukashin, C.] NASA, Langley Res Ctr, Hampton, VA 23665 USA. [Bartle, A.; Callaway, E.] Mechdyne Corp, Virginia Beach, VA USA. [Gyurjyan, V.] Thomas Jefferson Natl Accelerator Facil, Newport News, VA USA. [Mancilla, S.; Oyarzun, R.] Univ Tecn Federico Santa Maria, Valparaiso, Chile. [Vakhnin, A.] Sci Syst & Applicat Inc, Hampton, VA USA. RP Lukashin, C (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. NR 7 TC 0 Z9 0 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-9925-5 PY 2015 BP 1943 EP 1947 PG 5 WC Computer Science, Information Systems; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF1KI UT WOS:000380404600240 ER PT J AU Lee, S Pan, L Zhai, CX Tang, BY Kubar, T Zhang, J Wang, W AF Lee, Seungwon Pan, Lei Zhai, Chengxing Tang, Benyang Kubar, Terry Zhang, Jia Wang, Wei BE Ho, H Ooi, BC Zaki, MJ Hu, XH Haas, L Kumar, V Rachuri, S Yu, SP Hsiao, MHI Li, J Luo, F Pyne, S Ogan, K TI Climate Model Diagnostic Analyzer SO PROCEEDINGS 2015 IEEE INTERNATIONAL CONFERENCE ON BIG DATA LA English DT Proceedings Paper CT IEEE International Conference on Big Data CY OCT 29-NOV 01, 2015 CL Santa Clara, CA SP IEEE, IEEE Comp Soc, Natl Sci Fdn, CCF, HUAWEI, Springer, ELSEVIER, CISCO, Intel DE climate data; analytics; model evaluation; online collaborative environment; web services; cloud computing AB The comprehensive and innovative evaluation of climate models with newly available global observations is critically needed for the improvement of climate model current-state representation and future-state predictability. A climate model diagnostic evaluation process requires physics-based multi-variable analyses that typically involve large-volume and heterogeneous datasets, making them both computation-and data-intensive. With an exploratory nature of climate data analyses and an explosive growth of datasets and service tools, scientists are struggling to keep track of their datasets, tools, and execution/study history, let alone sharing them with others. In response, we have developed a cloud-enabled, provenance-supported, web-service system called Climate Model Diagnostic Analyzer (CMDA). CMDA enables the physics-based, multi-variable model performance evaluations and diagnoses through the comprehensive and synergistic use of multiple observational data, reanalysis data, and model outputs. At the same time, CMDA provides a crowdsourcing space where scientists can organize their work efficiently and share their work with others. CMDA is empowered by many current state-of-the-art software packages in web service, provenance, and semantic search. C1 [Lee, Seungwon; Pan, Lei; Zhai, Chengxing; Tang, Benyang; Kubar, Terry] CALTECH, Jet Prop Lab, Pasadena, CA USA. [Zhang, Jia; Wang, Wei] Carnegie Mellon Univ, Dept Software Engn, Silicon Valley, CA USA. RP Lee, S (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA USA. EM Seungwon.Lee@jpl.nasa.gov; Jia.Zhang@sv.cmu.edu NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-9925-5 PY 2015 BP 1948 EP 1952 PG 5 WC Computer Science, Information Systems; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF1KI UT WOS:000380404600241 ER PT J AU Zhou, SJ Yang, X Li, XW Matsui, T Liu, S Sun, XH Tao, WK AF Zhou, Shujia Yang, Xi Li, Xiaowen Matsui, Toshihisa Liu, Si Sun, Xian-He Tao, Weikuo BE Ho, H Ooi, BC Zaki, MJ Hu, XH Haas, L Kumar, V Rachuri, S Yu, SP Hsiao, MHI Li, J Luo, F Pyne, S Ogan, K TI A Hadoop-Based Visualization and Diagnosis Framework for Earth Science Data SO PROCEEDINGS 2015 IEEE INTERNATIONAL CONFERENCE ON BIG DATA LA English DT Proceedings Paper CT IEEE International Conference on Big Data CY OCT 29-NOV 01, 2015 CL Santa Clara, CA SP IEEE, IEEE Comp Soc, Natl Sci Fdn, CCF, HUAWEI, Springer, ELSEVIER, CISCO, Intel DE Hadoop; MapReduce; Visualization; NetCDF; Cloud Resolve Model ID PRECIPITATION AB With rapidly growing computing power, ultra high-resolution Earth science simulations with a long period of time are feasible. However, it is still very challenging to distribute and analyze a huge amount of simulation results, which could be over 100TB. One key reason is that typical Earth science data are represented in NetCDF, which is not supported by the popular and powerful Hadoop Distribute File System (HDFS) and consequently cannot be analyzed with tools based on HDFS. In this paper, we propose a Hadoop-based visualization and diagnosis framework for visualizing and analyzing Earth science data. It has a data model to transform data from the format of NetCDF to CSV (Comma Separated Value) that is supported by HDFS. With this model, data can be processed with the operations such as maximize, sum, and subset through HIVE and Cloudera Impala and, therefore, typical diagnoses can be performed. In addition, the framework has a technique to visualize and diagnose HDFS-resident data with the popular visualization and diagnosis tool, IDL. To speed up this process, a concurrent reader is developed to obtain HDFS-resident data. Moreover, a dynamic reader to transfer data from a parallel file system (PFS) to HDFS is developed to efficiently visualize and diagnose PFS-resident data. The cloud resolve mode simulations are used for testing and evaluating this framework. C1 [Zhou, Shujia] Northrop Grumman Informat Technol, Mclean, VA 22102 USA. [Yang, Xi; Liu, Si; Sun, Xian-He] IIT, Chicago, IL 60616 USA. [Li, Xiaowen] Morgan State Univ, Baltimore, MD 21251 USA. [Matsui, Toshihisa] Univ Maryland, College Pk, MD 20742 USA. [Li, Xiaowen; Matsui, Toshihisa; Tao, Weikuo] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Zhou, SJ (reprint author), Northrop Grumman Informat Technol, Mclean, VA 22102 USA. EM shujia.zhou@ngc.com; xyang34@hawk.iit.edu; xiaowen.li@nasa.gov; Toshihisa.Matsui-1@nasa.gov; sliu89@hawk.iit.edu; sun@iit.edu; wei-kuo.tao-1@nasa.gov NR 15 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-9925-5 PY 2015 BP 1972 EP 1977 PG 6 WC Computer Science, Information Systems; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF1KI UT WOS:000380404600245 ER PT J AU Palamuttam, R Mogrovejo, RM Mattmann, C Wilson, B Whitehall, K Verma, R McGibbney, L Ramirez, P AF Palamuttam, Rahul Mogrovejo, Renato Marroquin Mattmann, Chris Wilson, Brian Whitehall, Kim Verma, Rishi McGibbney, Lewis Ramirez, Paul BE Ho, H Ooi, BC Zaki, MJ Hu, XH Haas, L Kumar, V Rachuri, S Yu, SP Hsiao, MHI Li, J Luo, F Pyne, S Ogan, K TI SciSpark: Applying In-memory Distributed Computing to Weather Event Detection and Tracking SO PROCEEDINGS 2015 IEEE INTERNATIONAL CONFERENCE ON BIG DATA LA English DT Proceedings Paper CT IEEE International Conference on Big Data CY OCT 29-NOV 01, 2015 CL Santa Clara, CA SP IEEE, IEEE Comp Soc, Natl Sci Fdn, CCF, HUAWEI, Springer, ELSEVIER, CISCO, Intel DE Apache Spark; in-memory distributed computing; large scientific datasets; mesoscale convective complexes AB In this paper we present SciSpark, a Big Data framework that extends Apache (TM) Spark for scaling scientific computations. The paper details the initial architecture and design of SciSpark. We demonstrate how SciSpark achieves parallel ingesting and partitioning of earth science satellite and model datasets. We also illustrate the usability and extensibility of SciSpark by implementing aspects of the Grab 'em Tag 'em Graph 'em (GTG) algorithm using SciSpark and its Map Reduce capabilities. GTG is a topical automated method for identifying and tracking Mesoscale Convective Complexes in satellite infrared datasets. C1 [Palamuttam, Rahul; Mogrovejo, Renato Marroquin; Mattmann, Chris; Wilson, Brian; Whitehall, Kim; Verma, Rishi; McGibbney, Lewis; Ramirez, Paul] CALTECH, NASA, Jet Prop Lab, Pasadena, CA 91125 USA. [Mattmann, Chris] Univ So Calif, Dept Comp Sci, Los Angeles, CA 90089 USA. [Palamuttam, Rahul] Univ Calif San Diego, La Jolla, CA USA. [Mogrovejo, Renato Marroquin] ETH Univ, Zurich, Switzerland. RP Palamuttam, R (reprint author), CALTECH, NASA, Jet Prop Lab, Pasadena, CA 91125 USA. EM rahulpalamut@gmail.com NR 16 TC 2 Z9 2 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-9925-5 PY 2015 BP 2020 EP 2026 PG 7 WC Computer Science, Information Systems; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF1KI UT WOS:000380404600251 ER PT J AU Lee, H Cinquini, L Crichton, D Braverman, A AF Lee, Huikyo Cinquini, Luca Crichton, Daniel Braverman, Amy BE Ho, H Ooi, BC Zaki, MJ Hu, XH Haas, L Kumar, V Rachuri, S Yu, SP Hsiao, MHI Li, J Luo, F Pyne, S Ogan, K TI Optimization of system architecture for Big Data analysis in climate science SO PROCEEDINGS 2015 IEEE INTERNATIONAL CONFERENCE ON BIG DATA LA English DT Proceedings Paper CT IEEE International Conference on Big Data CY OCT 29-NOV 01, 2015 CL Santa Clara, CA SP IEEE, IEEE Comp Soc, Natl Sci Fdn, CCF, HUAWEI, Springer, ELSEVIER, CISCO, Intel ID ACCESS AB In this paper, we describe an emergent tool called DAWN (short for "Distributed Analytics, Workflows and Numeric") which is a model for simulating, analyzing and optimizing system architectures for executing arbitrary data processing pipelines. As an example, we will apply DAWN to the investigation of a real-life Big Data use case in climate science: the evaluation of simulated rainfall characteristics using high-resolution observational data. We will show how DAWN can help in determining the optimal architecture, and science algorithms, to execute this case study analyzing distributed datasets, as a tradeoff between the overall time cost and the uncertainty of calculated metrics for model evaluation. We will also show how DAWN can guide architectural decisions for future research, specifically impacting how data should be generated and analyzed to cope with future projected data volumes. C1 [Lee, Huikyo; Cinquini, Luca; Crichton, Daniel; Braverman, Amy] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Lee, H (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. EM huikyo.lee@jpl.nasa.gov NR 4 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-9925-5 PY 2015 BP 2169 EP 2172 PG 4 WC Computer Science, Information Systems; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF1KI UT WOS:000380404600270 ER PT J AU Huffer, B Cotnoir, M Gleason, J AF Huffer, Beth Cotnoir, Marc Gleason, Jonathan BE Ho, H Ooi, BC Zaki, MJ Hu, XH Haas, L Kumar, V Rachuri, S Yu, SP Hsiao, MHI Li, J Luo, F Pyne, S Ogan, K TI Ontology-drive data access at the NASA Earth Exchange SO PROCEEDINGS 2015 IEEE INTERNATIONAL CONFERENCE ON BIG DATA LA English DT Proceedings Paper CT IEEE International Conference on Big Data CY OCT 29-NOV 01, 2015 CL Santa Clara, CA SP IEEE, IEEE Comp Soc, Natl Sci Fdn, CCF, HUAWEI, Springer, ELSEVIER, CISCO, Intel DE Ontology; semantics; NASA Earth Exchange; data access; data discovery; faceted search AB The Ontology-driven Interactive Search Environment for Earth Science (ODISEES) and the Ontology-based Meta-data Portal for Unified Semantics (OlyMPUS), currently being developed under a ROSES AIST award, offer long-term solutions that will allow enhanced discovery and delivery of Earth Science data in the exascale-computing era. The ODISEES and OlyMPUS systems rely on an Earth science ontology and metadata repository that provide an ontological framework for describing NASA data holdings with enough detail and fidelity to enable researchers to quickly find and evaluate individual data variables. The Earth Science ontology is a highly precise and robust model of the Earth Science domain, expressed in a formal, logic-based language, that provides a conceptual framework for describing in detail the phenomena (i.e., radiation, aerosols, hydrology, carbon cycles, temperature, cloud properties, etc.) that are the subject of satellite observations and climate modeling, and the measurements of these phenomena that are the subject of NASA data products. To meet the challenges of using NASA big data to address global environmental issues, the Earth science research community needs a rich collaborative environment bringing together data access, computing capability and collaboration tools. The NASA Earth Exchange (NEX) project provides this environment. The NEX is a collaborative platform to increase the capability of researchers to analyze large datasets by staging TB to PB-scale datasets and providing analysis tools to operate on those data, saving time and costs of data transfer. The NEX roadmap calls for incorporating enhanced search capability into NEX to assist scientists in identifying applicable datasets. The ODISEES system is being integrated into the NEX to provide this capability and the ODISEES ontology will be extended to include key NEX datasets such as Landsat. C1 [Huffer, Beth] Lingua Logica LLC, Denver, CO 80207 USA. [Cotnoir, Marc] Comp Sci Corp, Moffett Field, CA USA. [Gleason, Jonathan] NASA, Langley Res Ctr, Sci Directorate, Hampton, VA USA. RP Huffer, B (reprint author), Lingua Logica LLC, Denver, CO 80207 USA. EM beth@lingualogica.net; marc.cotnoir@gmail.com; jonathan.l.gleason@nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-9925-5 PY 2015 BP 2177 EP 2181 PG 5 WC Computer Science, Information Systems; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF1KI UT WOS:000380404600272 ER PT J AU Williams, DN Lautenschlager, M Balaji, V Cinquini, L DeLuca, C Denvil, S Duffy, D Evans, B Ferraro, R Juckes, M Trenham, C AF Williams, Dean N. Lautenschlager, Michael Balaji, Venkatramani Cinquini, Luca DeLuca, Cecilia Denvil, Sebastien Duffy, Daniel Evans, Ben Ferraro, Robert Juckes, Martin Trenham, Claire BE Ho, H Ooi, BC Zaki, MJ Hu, XH Haas, L Kumar, V Rachuri, S Yu, SP Hsiao, MHI Li, J Luo, F Pyne, S Ogan, K TI Strategic Roadmap for the Earth System Grid Federation SO PROCEEDINGS 2015 IEEE INTERNATIONAL CONFERENCE ON BIG DATA LA English DT Proceedings Paper CT IEEE International Conference on Big Data CY OCT 29-NOV 01, 2015 CL Santa Clara, CA SP IEEE, IEEE Comp Soc, Natl Sci Fdn, CCF, HUAWEI, Springer, ELSEVIER, CISCO, Intel AB This article describes the Earth System Grid Federation (ESGF) mission and an international integration strategy for data, database and computational architecture, and stable infrastructure highlighted by the authors (the ESGF Executive Committee). These highlights are key developments needed over the next five to seven years in response to large-scale national and international climate community projects that depend on ESGF for success. Quality assurance and baseline performance from laptop to high performance computing characterizes available and potential data streams and strategies. These are required for interactive data collections to remedy gaps in handling enormous international federated climate data archives. Appropriate cyber security ensures protection of data according to projects but still allows access and portability to different ESGF and individual groups and users. A timeline and plan for forecasting interoperable tools takes ESGF from a federated database archive to a robust virtual laboratory and concludes the article. C1 [Williams, Dean N.] Lawrence Livermore Natl Lab, Livermore, CA 94550 USA. [Lautenschlager, Michael] German Climate Comp Ctr, DKRZ, Hamburg, Germany. [Balaji, Venkatramani] Princeton Univ, Princeton, NJ USA. [Cinquini, Luca; Ferraro, Robert] NASA, Jet Prop Lab, Pasadena, CA USA. [DeLuca, Cecilia] NOAA, Earth Syst Res Lab, Boulder, CO USA. [Denvil, Sebastien] IPSL, Paris, France. [Duffy, Daniel] NASA, Goddard Space Flight Ctr Address, Greenbelt, MD USA. [Evans, Ben; Trenham, Claire] Australian Natl Univ, Natl Computat Infrastruct, Canberra, ACT, Australia. [Juckes, Martin] British Atmosphere Data Ctr, Chilton, Oxon, England. RP Williams, DN (reprint author), Lawrence Livermore Natl Lab, Livermore, CA 94550 USA. EM williams13@llnl.gov; lautenschlager@dkrz.de; balaji@princeton.edu; luca.cinquini@jpl.nasa.gov; cecilia.deluca@noaa.gov; sebastien.denvil@ipsl.jussieu.fr; daniel.q.duffy@nasa.gov; ben.evans@anu.edu.au; robert.ferraro@jpl.nasa.gov; Martin.juckes@stfc.ac.uk; Claire.trenham@anu.edu.au NR 9 TC 0 Z9 0 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-9925-5 PY 2015 BP 2182 EP 2190 PG 9 WC Computer Science, Information Systems; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF1KI UT WOS:000380404600273 ER PT J AU Djorgovski, SG Mahabal, AA Chaudhry, B Crichton, DJ AF Djorgovski, S. G. Mahabal, A. A. Chaudhry, B. Crichton, D. J. BE Ho, H Ooi, BC Zaki, MJ Hu, XH Haas, L Kumar, V Rachuri, S Yu, SP Hsiao, MHI Li, J Luo, F Pyne, S Ogan, K TI From Stars to Patients: Lessons from Space Science and Astrophysics for Health Care Informatics SO PROCEEDINGS 2015 IEEE INTERNATIONAL CONFERENCE ON BIG DATA LA English DT Proceedings Paper CT IEEE International Conference on Big Data CY OCT 29-NOV 01, 2015 CL Santa Clara, CA SP IEEE, IEEE Comp Soc, Natl Sci Fdn, CCF, HUAWEI, Springer, ELSEVIER, CISCO, Intel DE data science; Virtual Observatory; space science; health care informatics ID BIG DATA AB Big Data are revolutionizing nearly every aspect of the modern society. One area where this can have a profound positive societal impact is the field of Health Care Informatics (HCI), which faces many challenges. The key idea behind this study is: can we use some of the experience and technical and methodological solutions from the fields that have successfully adapted to the Big Data era, namely astronomy and space science, to help accelerate the progress of HCI? We illustrate this with examples from the Virtual Observatory framework, and the NCI EDRN project. An effective sharing and reuse of tools, methods, and experiences from different fields can save a lot of effort, time, and expense. HCI can thus benefit from the proven solutions to big data challenges from other domains. C1 [Djorgovski, S. G.; Mahabal, A. A.] CALTECH, Pasadena, CA 91125 USA. [Chaudhry, B.] TupleHealth, Washington, DC 20008 USA. [Crichton, D. J.] Jet Prop Lab, Pasadena, CA 91109 USA. RP Djorgovski, SG (reprint author), CALTECH, Pasadena, CA 91125 USA. EM george@astro.caltech.edu; aam@astro.caltech.edu; basitchaudhry@tuplehealth.com; daniel.j.crichton@jpl.nasa.gov NR 15 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-9925-5 PY 2015 BP 2957 EP 2959 PG 3 WC Computer Science, Information Systems; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BF1KI UT WOS:000380404600403 ER PT B AU Cheng, B Price, S Gong, XB Lydon, J Cooper, K Chou, K AF Cheng, Bo Price, Steven Gong, Xibing Lydon, James Cooper, Kenneth Chou, Kevin GP ASME TI Speed Function Effects in Electron Beam Additive Manufacturing SO PROCEEDINGS OF THE ASME INTERNATIONAL MECHANICAL ENGINEERING CONGRESS AND EXPOSITION, 2014, VOL 2A LA English DT Proceedings Paper CT ASME International Mechanical Engineering Congress and Exposition (IMECE) CY NOV 14-20, 2014 CL Montreal, CANADA SP ASME DE Electron beam additive manufacturing (EBAM); Speed function; Finite element analysis; melt pool size ID FINITE-ELEMENT-ANALYSIS; LASER; MICROSTRUCTURE; DEPOSITION; TI-6AL-4V; POWDER; STEEL; SIZE AB In this paper, the process parameter effects on the thermal characteristics in powder-bed electron beam additive manufacturing (EBAM) using Ti-6Al-4V powder were investigated. The machine-specific setting, called "speed function" (SF) index that controls the beam speed and the beam current during a build, was utilized to evaluate the beam scanning speed effects. EBAM parts were fabricated using different levels of SF index (20 to 65) and build surface morphology and part microstructures were examined. A near infrared (NIR) thermal imager was used for temperatures measurements during the EBAM process. In addition, a thermal model previously developed was employed for temperature predictions and comparison with the experimental results. The major results are summarized as follows. The SF index noticeably affects the thermal characteristics in EBAM, e.g., a melt pool length of 1.72 mm vs. 1.26 mm for SF20 and SF65, respectively, at the 24.43 mm build height. This is because the higher the speed function index, the higher the beam speed, which reduces the energy density input and results in a lower process temperature. For the surface conditions and part microstructures, in general, a higher SF index tends to produce parts of rougher surfaces with more residual porosity features and large beta grain columnar widths. C1 [Cheng, Bo; Price, Steven; Gong, Xibing; Chou, Kevin] Univ Alabama, Dept Mech Engn, Tuscaloosa, AL 35487 USA. [Lydon, James; Cooper, Kenneth] Marshall Space Flight Ctr, Addit Mfg Lab, Huntsville, AL 35812 USA. RP Cheng, B (reprint author), Univ Alabama, Dept Mech Engn, Tuscaloosa, AL 35487 USA. NR 28 TC 0 Z9 0 U1 1 U2 1 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-4643-8 PY 2015 AR V02AT02A003 PG 9 WC Engineering, Manufacturing; Engineering, Mechanical SC Engineering GA BF0UD UT WOS:000379448900003 ER PT B AU Gong, XB Lydon, J Cooper, K Chou, K AF Gong, Xibing Lydon, James Cooper, Kenneth Chou, Kevin GP ASME TI MICROSTRUCTURAL ANALYSIS AND NANOINDENTATION CHARACTERIZATION OF TI-6AL-4V PARTS FROM ELECTRON BEAM ADDITIVE MANUFACTURING SO PROCEEDINGS OF THE ASME INTERNATIONAL MECHANICAL ENGINEERING CONGRESS AND EXPOSITION, 2014, VOL 2A LA English DT Proceedings Paper CT ASME International Mechanical Engineering Congress and Exposition (IMECE) CY NOV 14-20, 2014 CL Montreal, CANADA SP ASME DE Electron beam additive manufacturing (EBAM); Microstructure; Nanoindentation; Ti-6Al-4V alloy ID MECHANICAL-PROPERTIES; MELTED TI-6AL-4V; TEXTURE; ALLOY; LASER AB In this study, the microstructure analysis and nanoindentation characterization from electron beam additive manufacturing (EBAM) were experimentally investigated. Specimens with different build heights of an EBAM built part were tested for microstructure observations by optical microscopy and scanning electron microscopy. The correspondent Young's modulus and hardness were measured by nanoindentation. Columnar prior 13 structure is found along the build direction from the X-plane, while the Z-plane is characterized by equiaxed grains and fine Widmanstatten (alpha+beta) structure. The microstructure varies along the build height: the top layers present finer columnar prior beta grains and inside Widmanstatten (alpha+beta) structure, while the bottom layers show bigger percentage of alpha' martensitic phase owing to the very high cooling rate. Nanoindentation tests identify the highest Young's modulus of 127.9 GPa and hardness of 6.5 GPa from the top layers of Z-plane. The Young's modulus and hardness of the middle layers are lower because of the repeated heating. The Z-plane shows higher mechanical properties compared to that of the X-plane. The enhancement of modulus and hardness of the Ti-6Al-4V alloy could be attributed to the strengthening phase of a' and fine microstructure. C1 [Gong, Xibing; Chou, Kevin] Univ Alabama, Dept Mech Engn, Tuscaloosa, AL 35487 USA. [Lydon, James; Cooper, Kenneth] Marshall Space Flight Ctr, Addit Mfg Lab, Huntsville, AL 35812 USA. RP Gong, XB (reprint author), Univ Alabama, Dept Mech Engn, Tuscaloosa, AL 35487 USA. NR 34 TC 0 Z9 0 U1 3 U2 3 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-4643-8 PY 2015 AR V02AT02A004 PG 8 WC Engineering, Manufacturing; Engineering, Mechanical SC Engineering GA BF0UD UT WOS:000379448900004 ER PT B AU Price, S Lydon, J Cooper, K Chou, K AF Price, Steven Lydon, James Cooper, Ken Chou, Kevin GP ASME TI Temperature Measurements in Powder-Bed Electron Beam Additive Manufacturing SO PROCEEDINGS OF THE ASME INTERNATIONAL MECHANICAL ENGINEERING CONGRESS AND EXPOSITION, 2014, VOL 2A LA English DT Proceedings Paper CT ASME International Mechanical Engineering Congress and Exposition (IMECE) CY NOV 14-20, 2014 CL Montreal, CANADA SP ASME DE Electron beam additive manufacturing; Near Infrared; Temperature measurement AB Thermal characteristics such as process temperatures and melt pool sizes offer important information in metal additive manufacturing (AM) technologies such as powder-bed electron beam additive manufacturing (EBAM). In this study, a near infrared (NIR) thermal imager was employed to acquire build surface process temperatures during EBAM fabrications using Ti-6Al-4V powder. Challenges in NIR temperature measurements for EBAM were tackled including compensating temperatures due to the transmission loss and estimating the emissivity of Ti-6Al-4V in its molten state. At a beam speed of about 728 mm/s, a beam current of about 7.2 mA and a diameter of 0.55 mm, the maximum process temperature is on the order of around 2700 degrees C, and the melt pools have dimensions of about 2.72 mm and 0.72 mm in length and width, respectively. C1 [Price, Steven; Chou, Kevin] Univ Alabama, Dept Mech Engn, Tuscaloosa, AL 35487 USA. [Lydon, James; Cooper, Ken] Marshall Space Flight Ctr, Addit Mfg Lab, Huntsville, AL 35812 USA. RP Price, S (reprint author), Univ Alabama, Dept Mech Engn, Tuscaloosa, AL 35487 USA. NR 9 TC 0 Z9 0 U1 3 U2 3 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-4643-8 PY 2015 AR V02AT02A002 PG 8 WC Engineering, Manufacturing; Engineering, Mechanical SC Engineering GA BF0UD UT WOS:000379448900002 ER PT B AU Van Zante, DE AF Van Zante, Dale E. GP ASME TI PROGRESS IN OPEN ROTOR RESEARCH: A US PERSPECTIVE SO ASME TURBO EXPO: TURBINE TECHNICAL CONFERENCE AND EXPOSITION, 2015, VOL 1 LA English DT Proceedings Paper CT ASME Turbo Expo: Turbine Technical Conference and Exposition CY JUN 15-19, 2015 CL Montreal, CANADA SP Int Gas Turbine Inst AB In response to the 1970s oil crisis, NASA created the Advanced Turboprop Project (ATP) to mature technologies for high-speed propellers to enable large reductions in fuel burn relative to turbofan engines of that era. Both single rotation and contra-rotation concepts were designed and tested in ground based facilities as well as flight. Some novel concepts/configurations were proposed as part of the effort. The high-speed propeller concepts did provide fuel burn savings, albeit with some acoustics and structural challenges to overcome. When fuel prices fell, the business case for radical new engine configurations collapsed and the research emphasis returned to high bypass ducted configurations. With rising oil prices and increased environmental concerns there is renewed interest in high-speed propeller based engine architectures. Contemporary analysis tools for aerodynamics and aeroacoustics have enabled a new era of blade designs that have both high efficiency and lower noise characteristics. A recent series of tests in the U.S. have characterized the aerodynamic performance and noise from these modern contra-rotating propeller designs. Additionally the installation and noise shielding aspects for conventional airframes and blended wing bodies have been studied. Historical estimates of 'propfan' performance have relied on legacy propeller performance and acoustics data. Current system studies make use of the modern propeller data and higher fidelity installation effects data to estimate the performance of a contemporary aircraft system. Contemporary designs have demonstrated high net efficiency, similar to 86%, at 0.78 Mach, and low noise, >15 EPNdB cumulative margin to Chapter 4 when analyzed on a NASA derived aircraft/mission. This paper presents the current state of high-speed propeller/open rotor research within the U.S. from an overall viewpoint of the various efforts ongoing. The remaining technical challenges to a production engine include propulsion airframe integration, acoustic sensitivity to aircraft weight and certification issues. C1 [Van Zante, Dale E.] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Van Zante, DE (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 28 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-5662-8 PY 2015 AR V001T01A003 PG 14 WC Engineering, Mechanical SC Engineering GA BF1AB UT WOS:000380084300003 ER PT B AU Steinthorsson, E Mansour, A Hollon, B Teter, M Chang, C AF Steinthorsson, Erlendur Mansour, Adel Hollon, Brian Teter, Michael Chang, Clarence GP ASME TI ADVANCED MULTI-CUP FUEL INJECTOR TECHNOLOGY FOR ENVIRONMENTALLY RESPONSIBLE AVIATION GAS TURBINE ENGINES SO ASME TURBO EXPO: TURBINE TECHNICAL CONFERENCE AND EXPOSITION, 2015, VOL 4A LA English DT Proceedings Paper CT ASME Turbo Expo: Turbine Technical Conference and Exposition CY JUN 15-19, 2015 CL Montreal, CANADA SP Int Gas Turbine Inst AB Participating in NASA's Environmentally Responsible Aviation (ERA) Project, Parker Hannifin built and tested multipoint Lean Direct Injection (LDI) fuel injectors designed for NASA's N+2 55:1 Overall Pressure-Ratio (OPR) gas turbine engine cycles. The injectors are based on Parker's earlier three-zone injector (3ZI) which was conceived to enable practical implementation of multipoint LDI schemes in conventional aviation gas turbine engines. The new injectors offer significant aerodynamic design flexibility, excellent thermal performance, and scalability to various engine sizes. The injectors built for this project contain 15 injection points and incorporate staging to enable operation at low power conditions. Ignition and flame stability were demonstrated at ambient conditions with ignition air pressure. drop as low as 0.3% and fuel-to-air ratio (FAR) as low as 0.011. Lean Blowout (LBO) occurred at FAR as low as 0.005 with air at 460 K and atmospheric pressure. A high pressure combustion testing campaign was conducted in the CE-5 test facility at NASA Glenn Research Center at pressures up to 250 psi and combustor exit temperatures up to 2,033 K (3,200 F). The tests demonstrated estimated LTO cycle emissions that are about 30% of CAEP/6 for a reference 60,000 lbf thrust, 54.8-OPR engine. This paper presents some details of the injector design along with results from ignition, LBO and emissions testing. C1 [Steinthorsson, Erlendur; Mansour, Adel; Teter, Michael] Parker Hannifin Corp, Mentor, OH 44060 USA. [Hollon, Brian] Parker Hannifin Corp, Moncks Corner, SC USA. [Chang, Clarence] NASA, Glenn Res Ctr, Cleveland, OH USA. RP Steinthorsson, E (reprint author), Parker Hannifin Corp, Mentor, OH 44060 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-5668-0 PY 2015 AR V04AT04A054 PG 12 WC Engineering, Mechanical SC Engineering GA BF1AM UT WOS:000380176700054 ER PT B AU Thurman, D Poinsatte, P Ameri, A Culley, D Raghu, S Shyam, V AF Thurman, Douglas Poinsatte, Philip Ameri, Ali Culley, Dennis Raghu, Surya Shyam, Vikram GP ASME TI INVESTIGATION OF SPIRAL AND SWEEPING HOLES SO ASME TURBO EXPO: TURBINE TECHNICAL CONFERENCE AND EXPOSITION, 2015, VOL 5B LA English DT Proceedings Paper CT ASME Turbo Expo: Turbine Technical Conference and Exposition CY JUN 15-19, 2015 CL Montreal, CANADA SP Int Gas Turbine Inst AB Surface infrared thermography, hotwire anemometry, and thermocouple surveys were performed on two new film cooling hole geometries: spiral/rifled holes and fluidic sweeping holes. The spiral holes attempt to induce large-scale vorticity to the film cooling jet as it exits the hole to prevent the formation of the kidney shaped vortices commonly associated with film cooling jets. The fluidic sweeping hole uses a passive in-hole geometry to induce jet sweeping at frequencies that scale with blowing ratios. The spiral hole performance is compared to that of round holes with and without compound angles. The fluidic hole is of the diffusion class of holes and is therefore compared to a 777 hole and Square holes. A patent-pending spiral hole design showed the highest potential of the non-diffusion type hole configurations. Velocity contours and flow temperature were acquired at discreet cross-sections of the downstream flow field. The passive fluidic sweeping hole shows the most uniform cooling distribution but suffers from low span-averaged effectiveness levels due to enhanced mixing. The data was taken at a Reynolds number of 11,000 based on hole diameter and freestream velocity. Infrared thermography was taken for blowing ratios of 1.0, 1.5, 2.0, and 2.5 at a density ratio of 1.05. The flow inside the fluidic sweeping hole was studied using 3D unsteady RANS. C1 [Thurman, Douglas] US Army Res Lab, Cleveland, OH 44135 USA. [Poinsatte, Philip; Culley, Dennis; Shyam, Vikram] NASA Glenn Res Ctr, Cleveland, OH USA. [Ameri, Ali] Ohio State Univ, Columbus, OH 43210 USA. [Raghu, Surya] Adv Fluid LLC, Columbia, MD USA. RP Thurman, D (reprint author), US Army Res Lab, Cleveland, OH 44135 USA. NR 15 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-5672-7 PY 2015 AR V05BT12A044 PG 14 WC Engineering, Mechanical SC Engineering GA BF1AJ UT WOS:000380175100044 ER PT J AU Sainath, K Teixeira, FL Hensley, S AF Sainath, Kamalesh Teixeira, Fernando L. Hensley, Scott GP IEEE TI Interferometric SAR Coherence Arising from the Vertically-Polarized Electromagnetic Interrogation of Layered, Penetrable Dielectric Media SO 2015 12TH EUROPEAN RADAR CONFERENCE (EURAD) SE European Radar Conference EuRAD LA English DT Proceedings Paper CT 12th European Radar Conference (EuRAD) CY SEP 09-11, 2015 CL Paris, FRANCE SP IEEE Antennas & Propagat Soc, IEEE Aerosp & Elect Syst Soc DE Radar interferometry; radar remote sensing ID SYNTHETIC APERTURE RADARS; DECORRELATION AB We model coherence trends in vv-polarized Interferometric Synthetic Aperture Radar (InSAR) images arising specifically from the penetration of electromagnetic (EM) waves into geophysical media. Departing from previous InSAR coherence models, we simultaneously incorporate the interacting effects (on coherence) of (i) "multi-bounce" (wave guidance) within an arbitrary number of dielectric layers, (ii) azimuthal deviation in antenna pointing, (iii) local topography, and (iv) subsurface interface and volume scatter mechanisms. Including multibounce phenomena, in particular, allows better understanding of chief mechanisms behind backscatter enhancement, and the resultant strong corruption of InSAR observables, arising from interrogation of strongly guiding geophysical medium layers. Moreover, modeling the subsurface guidance behavior's influence from terrain topography expands upon many previous InSAR models that assumed simpler terrain and sensor geometries. As the two key results of this paper then, we quantitatively elucidate (i) how guidance behavior in dielectric slabs can engender unbounded, diverging interferometric phase bias, as well as (ii) how terrain sloping can render sub-sections of InSAR coherence images, generated by otherwise terrain-robust sensor geometries, susceptible to guidance-related phase bias and correlation degradation. C1 [Sainath, Kamalesh; Teixeira, Fernando L.] Ohio State Univ, ElectroSci Lab, Columbus, OH 43212 USA. [Hensley, Scott] CALTECH, NASA Jet Prop Lab, Pasadena, CA 91109 USA. RP Sainath, K (reprint author), Ohio State Univ, ElectroSci Lab, Columbus, OH 43212 USA. EM sainath.1@osu.edu; teixeira.5@osu.edu; shensley@jpl.nasa.gov NR 13 TC 2 Z9 2 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-2-8748-7041-5 J9 EUROP RADAR CONF PY 2015 BP 5 EP 8 PG 4 WC Engineering, Electrical & Electronic; Physics, Applied; Telecommunications SC Engineering; Physics; Telecommunications GA BF0OE UT WOS:000379172900002 ER PT S AU Zhang, MM Choi, J Daniilidis, K Wolf, MT Kanan, C AF Zhang, Mabel M. Choi, Jean Daniilidis, Kostas Wolf, Michael T. Kanan, Christopher GP IEEE TI VAIS: A Dataset for Recognizing Maritime Imagery in the Visible and Infrared Spectrums SO 2015 IEEE CONFERENCE ON COMPUTER VISION AND PATTERN RECOGNITION WORKSHOPS (CVPRW) SE IEEE Computer Society Conference on Computer Vision and Pattern Recognition Workshops LA English DT Proceedings Paper CT IEEE Conference on Computer Vision and Pattern Recognition (CVPR) CY JUN 07-12, 2015 CL Boston, MA SP IEEE ID FACE RECOGNITION; FUSION AB The development of fully autonomous seafaring vessels has enormous implications to the world's global supply chain and militaries. To obey international marine traffic regulations, these vessels must be equipped with machine vision systems that can classify other ships nearby during the day and night. In this paper, we address this problem by introducing VAIS, the world's first publicly available dataset of paired visible and infrared ship imagery. This dataset contains more than 1,000 paired RGB and infrared images among six ship categories - merchant, sailing, passenger, medium, tug, and small - which are salient for control and following maritime traffic regulations. We provide baseline results on this dataset using two off-the-shelf algorithms: gnostic fields and deep convolutional neural networks. Using these classifiers, we are able to achieve 87.4% mean per-class recognition accuracy during the day and 61.0% at night. C1 [Zhang, Mabel M.; Daniilidis, Kostas] Univ Penn, Philadelphia, PA 19104 USA. [Choi, Jean] Gwangju Inst Sci & Technol, Gwangju, South Korea. [Wolf, Michael T.; Kanan, Christopher] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Zhang, MM (reprint author), Univ Penn, Philadelphia, PA 19104 USA. EM zmen@seas.upenn.edu; pereus@gist.ac.kr; kostas@cis.upenn.edu; wolf@jpl.nasa.gov; kanan@jpl.nasa.gov NR 25 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2160-7508 BN 978-1-4673-6759-2 J9 IEEE COMPUT SOC CONF PY 2015 PG 7 WC Computer Science, Artificial Intelligence SC Computer Science GA BF0IK UT WOS:000378887900026 ER PT J AU Milinecsky, G Yatskiv, Y Degtyaryov, O Syniavskyi, I Ivanov, Y Bovchaliuk, A Mishchenko, M Danylevsky, V Sosonkin, M Bovchaliuk, V AF Milinecsky, G. Yatskiv, Ya Degtyaryov, O. Syniavskyi, I. Ivanov, Yu Bovchaliuk, A. Mishchenko, M. Danylevsky, V. Sosonkin, M. Bovchaliuk, V. TI Remote sensing of aerosol in the terrestrial atmosphere from space: new missions SO ADVANCES IN ASTRONOMY AND SPACE PHYSICS LA English DT Article DE atmosphere; aerosol; cloud; climate; polarimeter ID OPTICAL DEPTH; AERONET; NETWORK; RETRIEVAL; INSTRUMENT AB The distribution and properties of atmospheric aerosols on a global scale are not well known in terms of determination of their effects on climate. This mostly is due to extreme variability of aerosol concentrations, properties, sources, and types. Aerosol climate impact is comparable to the effect of greenhouse gases, but its influence is more difficult to measure, especially with respect to aerosol microphysical properties and the evaluation of anthropogenic aerosol effect. There are many satellite missions studying aerosol distribution in the terrestrial atmosphere, such as MISR/Terra, OMI/Aura, AVHHR, MODIS/Terra and Aqua, CALIOP/CALIPSO. To improve the quality of data and climate models, and to reduce aerosol climate forcing uncertainties, several new missions are planned. The gap in orbital instruments for studying aerosol microphysics has arisen after the Glory mission failed during launch in 2011. In this review paper, we describe several planned aerosol space missions, including the Ukrainian project Aerosol-UA that obtains data using a multi-channel scanning polarimeter and wide-angle polarimetric camera. The project is designed for remote sensing of the aerosol microphysics and cloud properties on a global scale. C1 [Milinecsky, G.; Yatskiv, Ya; Syniavskyi, I.; Ivanov, Yu; Bovchaliuk, A.; Sosonkin, M.] NAS Ukraine, Main Astron Observ, 27 Akad Zabolotnoho Str, UA-03680 Kiev, Ukraine. [Milinecsky, G.; Danylevsky, V.; Bovchaliuk, V.] Taras Shevchenko Natl Univ Kyiv, UA-01601 Kiev, Ukraine. [Degtyaryov, O.] State Space Agcy Ukraine, Yangel Yuzhnoye State Design Off, UA-49008 Dnepropetrovsk, Ukraine. [Bovchaliuk, A.; Bovchaliuk, V.] Univ Lille 1, CNRS, Opt Atmospher Lab, F-59655 Villeneuve Dascq, France. [Mishchenko, M.] NASA, Goddard Inst Space Studies, 2880 Broadway, New York, NY 10025 USA. RP Milinecsky, G (reprint author), NAS Ukraine, Main Astron Observ, 27 Akad Zabolotnoho Str, UA-03680 Kiev, Ukraine. EM genmilinevsky@gmail.com RI Danylevsky, Vassyl/F-5383-2017 OI Danylevsky, Vassyl/0000-0001-8311-0907 NR 39 TC 1 Z9 1 U1 2 U2 2 PU TARAS SHEVCHENKO NATL UNIV KYIV PI KYIV PA TARAS SHEVCHENKO NATL UNIV KYIV, KYIV, 00000, UKRAINE SN 2227-1481 J9 ADV ASTRON SPACE PHY JI Adv. Astron. Space Phys. PY 2015 VL 5 IS 1 BP 11 EP 16 PG 6 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA DP8CG UT WOS:000378724900002 ER PT J AU Lind, FD Lonsdale, CJ Faulkner, AJ Mattmann, C Razavi-Ghods, N Acedo, ED Alexander, P Marchese, J McWhirter, R Eckert, C Vierinen, J Schaefer, R Rideout, W Cappallo, R Pankratius, V Oberoi, D Khudikyan, S Yoyce, M Goodale, C Boustani, M Cinquini, L Verma, R Starch, M AF Lind, F. D. Lonsdale, Colin J. Faulkner, Andrew J. Mattmann, Chris Razavi-Ghods, Nima Acedo, Eloy de Lera Alexander, Paul Marchese, Jim McWhirter, Russ Eckert, Chris Vierinen, Juha Schaefer, Robert Rideout, William Cappallo, Roger Pankratius, Victor Oberoi, Divya Khudikyan, Shakeh Yoyce, Michael Goodale, Cameron Boustani, Maziya Cinquini, Luca Verma, Rishi Starch, Michael GP IEEE TI Radio Array of Portable Interferometric Detectors (RAPID): Development of a deployable multiple application radio array SO PROCEEDINGS OF THE 2015 INTERNATIONAL CONFERENCE ON ELECTROMAGNETICS IN ADVANCED APPLICATIONS (ICEAA) LA English DT Proceedings Paper CT 17th International Conference on Electromagnetics in Advanced Applications (ICEAA) / 5th IEEE-APS Topical Conference on Antennas and Propagation in Wireless Communications (IEEE-APWC) CY SEP 07-11, 2015 CL Torino, ITALY SP Politecnico Torino, IEIIT CNR, Int Union Radio Sci, IEEE Antennas & Propagat Soc, IEEE Italy Sect, IEEE N Italy AP ED MTT Chapter, Ist Superiore Mario Boella, Tecnologie Informazione Telecomunicazione, Torino Wireless Fdn, IEEE Antenna & Propagat Soc AB The Radio Array of Portable Interferometric Detectors (RAPID) is an advanced radio designed for multi-role applications. The system implements a spatially diverse sparse array technology and can be deployed and reconfigured easily. Data are captured at the raw voltage level using the system in the field and processed post-experiment. Signal processing for the system is software defined and uses a scalable Cloud computing architecture. The system builds upon the Square Kilometer Array Low Frequency Aperture antenna (SKALA) in combination with custom hardware for data acquisition on a per antenna basis. The instrument uses physically disconnected elements, a high performance direct digitization receiver, hot swap solid state storage, solar and battery power, and wireless control for interconnection. Schedule based operation can also be used in radio quiet locations or to enable minimally attended operation. RAPID is intended for application as both an Astronomical radio telescope and a Geospace imaging radar system. The high degree of mobility afforded by the system enables a wide variety of interferometric configurations and allows deployment of the instrument at locations which are optimal for specific scientific goals. C1 [Lind, F. D.; Lonsdale, Colin J.; Marchese, Jim; McWhirter, Russ; Eckert, Chris; Vierinen, Juha; Schaefer, Robert; Rideout, William; Cappallo, Roger; Pankratius, Victor; Oberoi, Divya] MIT, Haystack Observ, Route 40, Westford, MA 01886 USA. [Faulkner, Andrew J.; Razavi-Ghods, Nima; Acedo, Eloy de Lera; Alexander, Paul] Univ Cambridge, Cavendish Lab, Cambridge CB3 0HE, England. [Mattmann, Chris; Khudikyan, Shakeh; Yoyce, Michael; Goodale, Cameron; Boustani, Maziya; Cinquini, Luca; Verma, Rishi; Starch, Michael] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Lind, FD (reprint author), MIT, Haystack Observ, Route 40, Westford, MA 01886 USA. EM flind@haystack.mit.edu NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4799-7806-9 PY 2015 BP 1337 EP 1340 PG 4 WC Engineering, Electrical & Electronic SC Engineering GA BF0AR UT WOS:000378428800256 ER PT S AU Karunaratne, AS Azam-Ali, SN Walker, S Ruane, A AF Karunaratne, A. S. Azam-Ali, S. N. Walker, S. Ruane, A. BE Jaenicke, H Ashmore, SE Dulloo, ME Guarino, L Taylor, M TI Modelling the productivity of underutilised crops for climate resilience SO XXIX INTERNATIONAL HORTICULTURAL CONGRESS ON HORTICULTURE: SUSTAINING LIVES, LIVELIHOODS AND LANDSCAPES (IHC2014): IV INTERNATIONAL SYMPOSIUM ON PLANT GENETIC RESOURCES SE Acta Horticulturae LA English DT Proceedings Paper CT 29th International Horticultural Congress on Horticulture - Sustaining Lives, Livelihoods and Landscapes (IHC) / 4th International Symposium on Plant Genetic Resources CY AUG 17-22, 2014 CL Brisbane, AUSTRALIA SP Int Soc Hort Sci DE crop model; sensitivity; yield; landraces ID BAMBARA GROUNDNUT AB Current agriculture depends on a few 'major' species grown as monocultures that are supported by global research and development systems underpinning the current productivity with quantitative evidences. Whereas many hundreds of 'underutilised' crops have no such support systems but knowledge about them is fragmentary and based on the qualitative local evidences of the growers themselves rather than multi-locational research. Farmers in developing parts of the world have traditionally used indigenous knowledge to cope with climate hazards based upon observations and interpretation of natural phenomena. Crop choices, crop mixes and seasonal cropping calendars are largely based on farmer-level local forecasts. Since climate change is characterized mainly by uncertainty, it is vital to assess the crops and system resilience by means of underutilised crops. These neglected crops have the potential to meet real world challenges by means of sustaining humanity, diversifying the agricultural systems and especially responding to climate change with climate-resilient characters. The main analysis engine of the present study involves crop-climate modelling that introduces specific underutilised crops into recognised crop models (APSIM, DSSAT, AquaCrop) and links available climate databases within a geospatial information system framework. The preliminary use-cases on bambara groundnut (an African legume) evaluated the yield, total biomass and water productivity under the following scenarios: (i) Baseline, (ii) 5 Global Climate Models (CCSM4, GFDLESM2M, HadGEM2-ES, MIROC5, MPI-ESM-MR) with high emission scenario for mid-century, and (iii) for 99 climate sensitivities (C3MP). Productivity simulations for contrasting African locations demonstrated that interrogation methods can be devised for genetically distinct materials from matched climatic conditions to predict optimal selections of parental germplasm suited to different geographical locations for climate resilience. C1 [Karunaratne, A. S.; Azam-Ali, S. N.; Walker, S.] Univ Nottingham, Crops Future Res Ctr, Malaysia Campus, Jalan Broga, Semenyih, Malaysia. [Karunaratne, A. S.] Sabaragamuwa Univ Sri Lanka, Belihuloya, Sri Lanka. [Ruane, A.] NASA, Goddard Inst Space Studies, New York, NY 10025 USA. RP Karunaratne, AS (reprint author), Univ Nottingham, Crops Future Res Ctr, Malaysia Campus, Jalan Broga, Semenyih, Malaysia. EM asha.karunaratne@cffresearch.org NR 5 TC 0 Z9 0 U1 1 U2 1 PU INT SOC HORTICULTURAL SCIENCE PI LEUVEN 1 PA PO BOX 500, 3001 LEUVEN 1, BELGIUM SN 0567-7572 BN 978-94-62610-87-3 J9 ACTA HORTIC PY 2015 VL 1101 BP 113 EP 117 DI 10.17660/ActaHortic.2015.1101.17 PG 5 WC Plant Sciences; Horticulture SC Plant Sciences; Agriculture GA BF0FH UT WOS:000378649000017 ER PT S AU Amrbar, M Irom, F Guertin, SM Allen, G AF Amrbar, Mehran Irom, Farokh Guertin, Steven M. Allen, Greg GP IEEE TI Heavy Ion Single Event Effects Measurements of Xilinx Zynq-7000 FPGA SO 2015 IEEE RADIATION EFFECTS DATA WORKSHOP (REDW) SE IEEE Radiation Effects Data Workshop LA English DT Proceedings Paper CT IEEE Radiation Effects Data Workshop (REDW) CY JUL 13-17, 2015 CL Boston, MA SP IEEE, IEEE Nucl & Plasma Sci Soc AB Heavy ion single-event effect (SEE) measurements on Xilinx Zynq-7000 are reported. Heavy ion susceptibility to Single-Event latchup (SEL), single event upsets (SEUs) of BRAM, configuration bits of FPGA and on chip memory (OCM) of the processor were investigated. C1 [Amrbar, Mehran; Irom, Farokh; Guertin, Steven M.; Allen, Greg] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Amrbar, M (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM mehran.amrbar@jpl.nasa.gov; farokh.irom@jpl.nasa.gov; steven.m.guertin@jpl.nasa.gov; gregory.r.allen@jpl.nasa.gov NR 10 TC 0 Z9 0 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2154-0519 BN 978-1-4673-7641-9 J9 IEEE RADIAT EFFECTS PY 2015 BP 1 EP 4 PG 4 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic; Physics, Fluids & Plasmas; Physics, Nuclear SC Computer Science; Engineering; Physics GA BE9LZ UT WOS:000377773700001 ER PT S AU O'Bryan, MV LaBel, KA Chen, DK Campola, MJ Casey, MC Lauenstein, JM Pellish, JA Ladbury, RL Berg, MD AF O'Bryan, Martha V. LaBel, Kenneth A. Chen, Dakai Campola, Michael J. Casey, Megan C. Lauenstein, Jean Marie Pellish, Jonathan A. Ladbury, Raymond L. Berg, Melanie D. GP IEEE TI Compendium of Current Single Event Effects for Candidate Spacecraft Electronics for NASA SO 2015 IEEE RADIATION EFFECTS DATA WORKSHOP (REDW) SE IEEE Radiation Effects Data Workshop LA English DT Proceedings Paper CT IEEE Radiation Effects Data Workshop (REDW) CY JUL 13-17, 2015 CL Boston, MA SP IEEE, IEEE Nucl & Plasma Sci Soc DE Single event effects; spacecraft electronics; digital; linear bipolar; hybrid devices ID PULSED-LASER AB We present the results of single event effects (SEE) testing and analysis investigating the effects of radiation on electronics. This paper is a summary of test results. C1 [O'Bryan, Martha V.; Berg, Melanie D.] ASRC Fed Space & Def Inc AS&D Inc, 7515 Mission Dr,Suite 200, Seabrook, MD 20706 USA. [LaBel, Kenneth A.; Chen, Dakai; Campola, Michael J.; Casey, Megan C.; Lauenstein, Jean Marie; Pellish, Jonathan A.; Ladbury, Raymond L.] NASA, GSFC, Code 561-4, Greenbelt, MD 20771 USA. RP O'Bryan, MV (reprint author), ASRC Fed Space & Def Inc AS&D Inc, 7515 Mission Dr,Suite 200, Seabrook, MD 20706 USA. EM martha.v.obryan@nasa.gov; kenneth.a.label@nasa.gov; Dakai.Chen-1@nasa.gov; michael.j.campola@nasa.gov; megan.c.casey@nasa.gov; jean.m.lauenstein@nasa.gov; jonathan.a.pellish@nasa.gov; raymond.l.ladbury@nasa.gov; Melanie.D.Berg@nasa.gov NR 25 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2154-0519 BN 978-1-4673-7641-9 J9 IEEE RADIAT EFFECTS PY 2015 BP 45 EP 53 PG 9 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic; Physics, Fluids & Plasmas; Physics, Nuclear SC Computer Science; Engineering; Physics GA BE9LZ UT WOS:000377773700010 ER PT S AU Allen, GR Scheick, LZ Irom, F Guertin, SM Adell, PC Amrbar, M Vartanian, S O'Connor, M AF Allen, Gregory R. Scheick, Leif Z. Irom, Farokh Guertin, Steven M. Adell, Philippe C. Amrbar, Mehran Vartanian, Sergeh O'Connor, Michael GP IEEE TI 2015 Compendium of Recent Test Results of Single Event Effects Conducted by the Jet Propulsion Laboratory's Radiation Effects Group SO 2015 IEEE RADIATION EFFECTS DATA WORKSHOP (REDW) SE IEEE Radiation Effects Data Workshop LA English DT Proceedings Paper CT IEEE Radiation Effects Data Workshop (REDW) CY JUL 13-17, 2015 CL Boston, MA SP IEEE, IEEE Nucl & Plasma Sci Soc DE Single Event Effects; compendium; analog switches; ADC; DAC; oscillators; SDRAM; FPGA; drivers; microprocessors; voltage comparator; and voltage regulator AB This paper reports heavy ion, proton, and laser induced single event effects (SEE) results for a variety of microelectronic devices targeted for possible use in JPL spacecraft. The compendium covers devices tested within the timeframe of August 2012 through February 2015. It is an update to the SEE compendia JPL has historically published. C1 [Allen, Gregory R.; Scheick, Leif Z.; Irom, Farokh; Guertin, Steven M.; Adell, Philippe C.; Amrbar, Mehran; Vartanian, Sergeh; O'Connor, Michael] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Allen, GR (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM grallen@jpl.nasa.gov; leif.z.scheick@jpl.nasa.gov; firom@jpl.nasa.gov; steven.m.guertin@jpl.nasa.gov; philippe.c.adell@jpl.nasa.gov; mehran.amrbar@jpl.nasa.gov; sergeh.vartanian@jpl.nasa.gov; michael.d.oconnor@jpl.nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2154-0519 BN 978-1-4673-7641-9 J9 IEEE RADIAT EFFECTS PY 2015 BP 54 EP 75 PG 22 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic; Physics, Fluids & Plasmas; Physics, Nuclear SC Computer Science; Engineering; Physics GA BE9LZ UT WOS:000377773700011 ER PT S AU Guertin, SM Amrbar, M Vartanian, S AF Guertin, Steven M. Amrbar, Mehran Vartanian, Sergeh GP IEEE TI Radiation Test Results for Common CubeSat Microcontrollers and Microprocessors SO 2015 IEEE RADIATION EFFECTS DATA WORKSHOP (REDW) SE IEEE Radiation Effects Data Workshop LA English DT Proceedings Paper CT IEEE Radiation Effects Data Workshop (REDW) CY JUL 13-17, 2015 CL Boston, MA SP IEEE, IEEE Nucl & Plasma Sci Soc AB SEL, SEU, and TID results are presented for microcontrollers and microprocessors of interest for small satellite systems such as the TI MSP430F1611, MSP430F1612 and MSP430FR5739, Microchip PIC24F256GA110 and dsPIC33FJ256GP710, Atmel AT91SAM9G20, and Intel Atom E620T, and the Qualcomm Snapdragon APQ8064. C1 [Guertin, Steven M.; Amrbar, Mehran; Vartanian, Sergeh] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Guertin, SM (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM steven.m.guertin@jpl.nasa.gov; mehran.amrbar@jpl.nasa.gov; sergeh.vartanian@jpl.nasa.gov NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2154-0519 BN 978-1-4673-7641-9 J9 IEEE RADIAT EFFECTS PY 2015 BP 152 EP 160 PG 9 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic; Physics, Fluids & Plasmas; Physics, Nuclear SC Computer Science; Engineering; Physics GA BE9LZ UT WOS:000377773700025 ER PT S AU Irom, F Amrbar, M AF Irom, Farokh Amrbar, Mehran GP IEEE TI Heavy Ion Single Event Effects Measurements Of 512Mb ISSI SDRAM SO 2015 IEEE RADIATION EFFECTS DATA WORKSHOP (REDW) SE IEEE Radiation Effects Data Workshop LA English DT Proceedings Paper CT IEEE Radiation Effects Data Workshop (REDW) CY JUL 13-17, 2015 CL Boston, MA SP IEEE, IEEE Nucl & Plasma Sci Soc AB Heavy ion single-event measurements on 512Mb ISSI synchronous dynamic random-access memory (SDRAM) are reported. Heavy ion susceptibility to single event latchup (SEL), single bit upsets (SBUs), double bit upsets (DBUs), multiple bit upset (MBUs) and single effect functional interrupts (SEFIs) were investigated. C1 [Irom, Farokh; Amrbar, Mehran] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Irom, F (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM farokh.irom@jpl.nasa.gov; mehran.amrbar@jpl.nasa.gov NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2154-0519 BN 978-1-4673-7641-9 J9 IEEE RADIAT EFFECTS PY 2015 BP 172 EP 177 PG 6 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic; Physics, Fluids & Plasmas; Physics, Nuclear SC Computer Science; Engineering; Physics GA BE9LZ UT WOS:000377773700028 ER PT S AU Irom, F Allen, GR Rax, BG AF Irom, Farokh Allen, Gregory R. Rax, Bernard G. GP IEEE TI Proton Displacement Damage Measurements in Commercial Optocouplers SO 2015 IEEE RADIATION EFFECTS DATA WORKSHOP (REDW) SE IEEE Radiation Effects Data Workshop LA English DT Proceedings Paper CT IEEE Radiation Effects Data Workshop (REDW) CY JUL 13-17, 2015 CL Boston, MA SP IEEE, IEEE Nucl & Plasma Sci Soc ID DIODES AB Proton Displacement Damage (DD) measurements on Isolink OLH249, Isocom IS49, Isocom CSM141A, Isocom CSM1800 and Avago HCPL-5700 are reported. The OLH249 has the worst degradation, 3% of the initial CTR remains when it is used with I-F = 10 mA at 3 x 10(12) 1-MeV n/cm(2) fluence in Silicon. The remaining CTR percentage for IS49, CMS141A, CSM1800 and HCPL-5700 are 28%, 62%, 32%, and 81% at 3 x 10(12) 1-MeV n/cm(2) fluence in Silicon, respectively. C1 [Irom, Farokh; Allen, Gregory R.; Rax, Bernard G.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Irom, F (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Farokh.irom@jpl.nasa.gov; Gregory.r.allen@jpl.nasa.gov; Bernard.g.rax@jpl.nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2154-0519 BN 978-1-4673-7641-9 J9 IEEE RADIAT EFFECTS PY 2015 BP 178 EP 182 PG 5 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic; Physics, Fluids & Plasmas; Physics, Nuclear SC Computer Science; Engineering; Physics GA BE9LZ UT WOS:000377773700029 ER PT S AU Irom, F Agarwal, SG AF Irom, Farokh Agarwal, Shri G. GP IEEE TI Compendium of Single-Event Latchup and Total Ionizing Dose Test Results of Commercial Digital to Analog Converters SO 2015 IEEE RADIATION EFFECTS DATA WORKSHOP (REDW) SE IEEE Radiation Effects Data Workshop LA English DT Proceedings Paper CT IEEE Radiation Effects Data Workshop (REDW) CY JUL 13-17, 2015 CL Boston, MA SP IEEE, IEEE Nucl & Plasma Sci Soc AB This paper reports single-event latchup and total ionizing dose results for a variety of digital to analog converters targeted for possible use in NASA spacecraft. It covers devices tested over the last 15 years. C1 [Irom, Farokh; Agarwal, Shri G.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Irom, F (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM farokh.irom@jpl.nasa.gov; shri.g.agarwal@jpl.nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2154-0519 BN 978-1-4673-7641-9 J9 IEEE RADIAT EFFECTS PY 2015 BP 183 EP 190 PG 8 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic; Physics, Fluids & Plasmas; Physics, Nuclear SC Computer Science; Engineering; Physics GA BE9LZ UT WOS:000377773700030 ER PT S AU Szabo, CM Duncan, A LaBel, KA Kay, M Bruner, P Krzesniak, M Dong, L AF Szabo, Carl M., Jr. Duncan, Adam LaBel, Kenneth A. Kay, Matt Bruner, Pat Krzesniak, Mike Dong, Lei GP IEEE TI Preliminary Radiation Testing of a State-of-the-Art Commercial 14nm CMOS Processor/System-on-a-Chip SO 2015 IEEE RADIATION EFFECTS DATA WORKSHOP (REDW) SE IEEE Radiation Effects Data Workshop LA English DT Proceedings Paper CT IEEE Radiation Effects Data Workshop (REDW) CY JUL 13-17, 2015 CL Boston, MA SP IEEE, IEEE Nucl & Plasma Sci Soc DE radiation; total ionizing dose; 14nm; SoC; processor; proton-induced effects; commercial motherboard; software stress testing; test method AB Hardness assurance test results of Intel state-ofthe-art 14nm "Broadwell" U-series processor / System-on-a Chip (SoC) for total ionizing dose (TID) are presented, along with exploratory results from trials at a medical proton facility. Test method builds upon previous efforts [1] by utilizing commercial laptop motherboards and software stress applications as opposed to more traditional automated test equipment (ATE). C1 [Szabo, Carl M., Jr.] AS&D Inc ASRC Fed Space & Def, 7515 Mission Dr,Suite 200, Seabrook, MD 20706 USA. [Szabo, Carl M., Jr.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Duncan, Adam; Kay, Matt; Bruner, Pat; Krzesniak, Mike] NSWC Crane, Crane, IN 47522 USA. [LaBel, Kenneth A.] NASA, GSFC, Greenbelt, MD 20771 USA. [Dong, Lei] Scripps Proton Therapy Ctr, San Diego, CA 92121 USA. RP Szabo, CM (reprint author), AS&D Inc ASRC Fed Space & Def, 7515 Mission Dr,Suite 200, Seabrook, MD 20706 USA. EM carl.m.szabo@nasa.gov; adam.duncan@navy.mil; kenneth.a.label@nasa.gov; matthew.kay@navy.mil; patrick.bruner@navy.mil; michael.krzesniak@navy.mil; dong.lei@scrippshealth.org NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2154-0519 BN 978-1-4673-7641-9 J9 IEEE RADIAT EFFECTS PY 2015 BP 203 EP 210 PG 8 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic; Physics, Fluids & Plasmas; Physics, Nuclear SC Computer Science; Engineering; Physics GA BE9LZ UT WOS:000377773700034 ER PT S AU Lee, DS Allen, GR Swift, G Cannon, M Wirthlin, M George, JS Koga, R Huey, K AF Lee, David S. Allen, Gregory R. Swift, Gary Cannon, Matthew Wirthlin, Michael George, Jeffrey S. Koga, Rokutaro Huey, Kangsen GP IEEE TI Single-Event Characterization of the 20 nm Xilinx Kintex UltraScale Field-Programmable Gate Array under Heavy Ion Irradiation SO 2015 IEEE RADIATION EFFECTS DATA WORKSHOP (REDW) SE IEEE Radiation Effects Data Workshop LA English DT Proceedings Paper CT IEEE Radiation Effects Data Workshop (REDW) CY JUL 13-17, 2015 CL Boston, MA SP IEEE, IEEE Nucl & Plasma Sci Soc AB This study examines the single-event response of the Xilinx 20 nm Kintex UltraScale Field-Programmable Gate Array irradiated with heavy ions. Results for single-event latchup and single- event upset on configuration SRAM cells and Block RAM memories are provided. C1 [Lee, David S.] Sandia Natl Labs, Albuquerque, NM 87123 USA. [Allen, Gregory R.] NASA, Jet Prop Lab, Pasadena, CA 91109 USA. [Swift, Gary] Swift Engn & Radiat Serv LLC, San Jose, CA 95124 USA. [Cannon, Matthew; Wirthlin, Michael] Brigham Young Univ, Dept Elect & Comp Engn, Ctr High Performance Reconfigurable Comp, Provo, UT 84602 USA. [George, Jeffrey S.; Koga, Rokutaro] Aerosp Corp, El Segundo, CA 90245 USA. [Huey, Kangsen] Xilinx Inc, San Jose, CA 95124 USA. RP Lee, DS (reprint author), Sandia Natl Labs, Albuquerque, NM 87123 USA. EM dslee@sandia.gov; gregory.r.allen@jpl.nasa.gov; gary.m.swift@ieee.org; matthew.cannon@byu.edu; wirthlin@byu.edu; jeffrey.s.george@aero.org; rokutaro.koga@aero.org; kangsen.huey@xilinx.com NR 12 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2154-0519 BN 978-1-4673-7641-9 J9 IEEE RADIAT EFFECTS PY 2015 BP 222 EP 227 PG 6 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic; Physics, Fluids & Plasmas; Physics, Nuclear SC Computer Science; Engineering; Physics GA BE9LZ UT WOS:000377773700037 ER PT S AU Caluwaerts, K Steil, JJ AF Caluwaerts, Ken Steil, Jochen J. GP IEEE TI Independent Joint Learning in Practice: Local Error Estimates to Improve Inverse Dynamics Control SO 2015 IEEE-RAS 15TH INTERNATIONAL CONFERENCE ON HUMANOID ROBOTS (HUMANOIDS) SE IEEE-RAS International Conference on Humanoid Robots LA English DT Proceedings Paper CT 15th IEEE-RAS International Conference on Humanoid Robots (Humanoids) CY NOV 03-05, 2015 CL Seoul, SOUTH KOREA SP IEEE Robot & Automat Soc, IEEE ID MODELS AB Independent Joint Learning (IJL) was recently introduced as a learning-based approach to account for inverse dynamics (ID) model errors. The fundamental idea is to combine an ID model with learned torque error estimators that only rely on joint-local information. This approach improves task-to-task generalization and reduces learning times as each torque error estimators depends only on the state of a single joint instead of the global configuration. Herein, we adapt the IJL method to a real robotic platform, namely the COMAN compliant humanoid robot. We test the algorithm under different loading conditions in open and closed loop control (PD, forward non-linear control, and ID control). In our implementation, IJL becomes a flexible component that fits in between the output of an existing computed-torque controller and low-level motor drivers. Our results show that IJL reduces torque estimation errors in the open loop case and improves tracking performance in the closed loop case. Under varying loading conditions, IJL's performance is on par with and in some cases exceeds the adapted model (i.e. a modified ID model with updated inertial parameters). Finally, the compartmented design and limited number of assumptions of the algorithm allow it to be easily integrated into existing platforms. C1 [Caluwaerts, Ken] NASA, ORAU, Ames Intelligent Robot Grp, Moffett Field, CA 94035 USA. [Caluwaerts, Ken] Univ Bielefeld, CITEC Ctr Excellence Cognit Interact Technol, D-33615 Bielefeld, Germany. [Steil, Jochen J.] Univ Bielefeld, Res Inst Cognit & Robot CoR Lab, D-33615 Bielefeld, Germany. [Steil, Jochen J.] Univ Bielefeld, Fac Technol, D-33615 Bielefeld, Germany. RP Caluwaerts, K (reprint author), NASA, ORAU, Ames Intelligent Robot Grp, Moffett Field, CA 94035 USA. EM ken.caluwaerts@nasa.gov; jsteil@cor-lab.uni-bielefeld.de NR 22 TC 1 Z9 1 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2164-0572 BN 978-1-4799-6885-5 J9 IEEE-RAS INT C HUMAN PY 2015 BP 643 EP 650 PG 8 WC Robotics SC Robotics GA BE9OE UT WOS:000377954900097 ER PT B AU Alvin, MA Anderson, I Heidloff, A White, E Bhatt, R Grady, J McMordie, B AF Alvin, M. A. Anderson, I. Heidloff, A. White, E. Bhatt, R. Grady, J. McMordie, B. GP ASME TI Development of Advanced Material Systems for Future Gas Turbine Applications SO PROCEEDINGS OF THE ASME TURBO EXPO: TURBINE TECHNICAL CONFERENCE AND EXPOSITION, 2015, VOL 6 LA English DT Proceedings Paper CT ASME Turbo Expo: Turbine Technical Conference and Exposition CY JUN 15-19, 2015 CL Montreal, CANADA SP Int Gas Turbine Inst ID SIC MATRIX COMPOSITES AB Advanced coating systems in conjunction with novel internal airfoil cooling configurations continue to be a critical research focus to provide enhanced oxidation protection and cooling of commercial metal alloys as future land-based gas turbines are being designed for inlet gas temperature operations of > 1300-1400 degrees C. With the application of densified oxide dispersion strengthened (ODS) coatings on cast near surface embedded micro-channel (NSEMC) airfoil surfaces, improvements of >50-70% in heat removal capabilities are projected over that of conventional, smooth channeled, internally -cooled, airfoil configurations. For turbine inlet and airfoil surface design temperatures exceeding 1400-1600 degrees C, oxide-coated, silicon carbide-based ceramic matric composites (CMCs) have been developed. In this paper we will review our recent advancements that have been made with respect to ODS coating development and the oxidation stability of CMCs during bench-scale laboratory testing. C1 [Alvin, M. A.] US DOE, Natl Energy Technol Lab, Pittsburgh, PA 15236 USA. [Anderson, I.; Heidloff, A.; White, E.] Iowa State Univ, Ames Lab, Ames, IA 50011 USA. [Bhatt, R.; Grady, J.] NASA Glenn Res Ctr, Cleveland, OH 44135 USA. [McMordie, B.] Coatings Ind, Souderton, PA 18964 USA. RP Alvin, MA (reprint author), US DOE, Natl Energy Technol Lab, Pittsburgh, PA 15236 USA. EM maryanne.alvin@netl.doe.gov; andersoi@ameslab.gov; aheidloff@gmail.com; ewhite@iastate.edu; ramakrishna.t.bhatt@nasa.gov; joseph.e.grady@nasa.gov; bmcmordie@cficoatings.com NR 21 TC 0 Z9 0 U1 1 U2 1 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-5675-8 PY 2015 AR V006T21A010 PG 8 WC Engineering, Mechanical; Materials Science, Multidisciplinary SC Engineering; Materials Science GA BE9JB UT WOS:000377639400049 ER PT B AU Kiser, JD Bansal, NP Szelagowski, J Sokhey, J Heffernan, T Clegg, J Pierluissi, A Riedel, J Wyen, T Atmur, S Ursic, J AF Kiser, J. Douglas Bansal, Narottam P. Szelagowski, James Sokhey, Jagdish (Jack) Heffernan, Tab Clegg, Joseph Pierluissi, Anthony Riedel, Jim Wyen, Travis Atmur, Steven Ursic, Joseph GP ASME TI OXIDE/OXIDE CERAMIC MATRIX COMPOSITE (CMC) EXHAUST MIXER DEVELOPMENT IN THE NASA ENVIRONMENTALLY RESPONSIBLE AVIATION (ERA) PROJECT SO PROCEEDINGS OF THE ASME TURBO EXPO: TURBINE TECHNICAL CONFERENCE AND EXPOSITION, 2015, VOL 6 LA English DT Proceedings Paper CT ASME Turbo Expo: Turbine Technical Conference and Exposition CY JUN 15-19, 2015 CL Montreal, CANADA SP Int Gas Turbine Inst AB LibertyWorks (R), a subsidiary of Rolls-Royce Corporation, first studied CMC (ceramic matrix composite) exhaust mixers for potential weight benefits in 2008. Oxide CMC potentially offered weight reduction, higher temperature capability, and the ability to fabricate complex -shapes for increased mixing and noise suppression. In 2010, NASA was pursuing the reduction of NOx emissions, fuel burn, and noise from turbine engines in Phase I of the Environmentally Responsible Aviation (ERA) Project (within the Integrated Systems Research Program). ERA subtasks, including those focused on CMC components, were being formulated with the goal of maturing technology from Proof of Concept Validation (Technology Readiness Level 3 (TRL 3)) to System/Subsystem or Prototype Demonstration in a Relevant Environment (TRL 6). In April 2010, the NASA Glenn Research Center (GRC) and Rolls-Royce (RR) jointly initiated a CMC Exhaust System Validation Program within the ERA Project, teaming on CMC exhaust mixers for subsonic jet engines. The initial objective was to fabricate and characterize the performance of a 0.25 scale low bypass exhaust system that was based on a RR advanced design, with a 16-lobe oxide/oxide CMC mixer and tail cone (center body). Support Services, LLC (Allendale, MI) and COI Ceramics, Inc. (COIC) supported the design of a mixer assembly that consisted of the following oxide/oxide CMC components mounted on separate metallic attachment flanges: a) a lobed mixer and outer fan shrouds, and b) a tail cone. TRL 4 (Component/Subscale Component Validation in a Laboratory Environment) was achieved in a cost-effective manner through subscale rig validation of the aerodynamic and acoustic performance via testing at ASE FluiDyne (Plymouth, MN) and at NASA GRC, respectively. This encouraged the NASA/RR/COIC team to move to the next phase of component development; full scale CMC mixer design for a RR AE3007 engine. COIC fabricated the full scale CMC mixer, which was vibration tested at GRC under conditions simulating the structural and dynamic environment of a mixer. Air Force Research Laboratory (AFRL, Wright-Patterson Air Force Base (WPAFB)) provided test support by assisting with instrumentation and performing 3D laser vibrometry to identify the mixer mode shapes and modal frequencies over the engine operating range. Successful vibration testing demonstrated COIC's new process for fabricating full scale CMC mixers and the durability of the Oxide CMC component at both room and elevated temperatures. A TRI approximate to-5 (Component Validation in a Relevant Environment) was attained and the CMC mixer was cleared for ground testing on a Rolls-Royce AE3007 engine for performance evaluation to achieve TRL 6. C1 [Kiser, J. Douglas; Bansal, Narottam P.; Szelagowski, James] NASA, Glenn Res Ctr, Cleveland, OH USA. [Sokhey, Jagdish (Jack); Heffernan, Tab; Clegg, Joseph; Pierluissi, Anthony] LibertyWorks Rolls Royce Corp, Rolls Royce North Amer Technol Inc, Indianapolis, IN USA. [Riedel, Jim] COI Ceram Inc, San Diego, CA USA. [Wyen, Travis] AFRL RQVV, Wright Patterson AFB, OH USA. [Atmur, Steven] COI Ceram Inc, Rocket Ctr, WV USA. [Ursic, Joseph] ZIN Technol Inc, Brookpark, OH USA. RP Kiser, JD (reprint author), NASA, Glenn Res Ctr, Cleveland, OH USA. NR 16 TC 0 Z9 0 U1 1 U2 4 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-5675-8 PY 2015 AR V006T02A002 PG 15 WC Engineering, Mechanical; Materials Science, Multidisciplinary SC Engineering; Materials Science GA BE9JB UT WOS:000377639400002 ER PT B AU Simon, DL AF Simon, Donald L. GP ASME TI SENSOR SELECTION FOR AIRCRAFT ENGINE PERFORMANCE ESTIMATION AND GAS PATH FAULT DIAGNOSTICS SO PROCEEDINGS OF THE ASME TURBO EXPO: TURBINE TECHNICAL CONFERENCE AND EXPOSITION, 2015, VOL 6 LA English DT Proceedings Paper CT ASME Turbo Expo: Turbine Technical Conference and Exposition CY JUN 15-19, 2015 CL Montreal, CANADA SP Int Gas Turbine Inst AB This paper presents analytical techniques for aiding system designers in making aircraft engine health management sensor selection decisions. The presented techniques, which are based on linear estimation and probability theory, are tailored for gas turbine engine performance estimation and gas path fault diagnostics applications. They enable quantification of the performance estimation and diagnostic accuracy offered by different candidate sensor suites. For performance estimation, sensor selection metrics are presented for two types of estimators including a Kalman filter and a maximum a posteriori estimator. For each type of performance estimator, sensor selection is based on minimizing the theoretical sum of squared estimation errors in health parameters representing performance deterioration in the major rotating modules of the engine. For gas path fault diagnostics, the sensor selection metric is set up to maximize correct classification rate for a diagnostic strategy that performs fault classification by identifying the fault type that most closely matches the observed measurement signature in a weighted least squares sense. Results from the application of the sensor selection metrics to a linear engine model are presented and discussed. Given a baseline sensor suite and a candidate list of optional sensors, an exhaustive search is performed to determine the optimal sensor suites for performance estimation and fault diagnostics. For any given sensor suite, Monte Carlo simulation results are found to exhibit good agreement with theoretical predictions of estimation and diagnostic accuracies. C1 [Simon, Donald L.] NASA, Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. RP Simon, DL (reprint author), NASA, Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. NR 13 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-5675-8 PY 2015 AR V006T05A027 PG 12 WC Engineering, Mechanical; Materials Science, Multidisciplinary SC Engineering; Materials Science GA BE9JB UT WOS:000377639400032 ER PT S AU Horton, R Milner-Bolotin, M AF Horton, Renee Milner-Bolotin, Marina BE Cunningham, BA ORiordan, C Ghose, S TI Workshop II: Physics Education SO WOMEN IN PHYSICS: 5TH IUPAP INTERNATIONAL CONFERENCE ON WOMEN IN PHYSICS SE AIP Conference Proceedings LA English DT Proceedings Paper CT 5th IUPAP International Conference on Women in Physics CY AUG 05-08, 2014 CL Wilfrid Laurier Univ, Waterloo, CANADA SP IUPAP Working Grp Women Phys, Canadian Assoc Physicists, Laurier Ctr Women Sci HO Wilfrid Laurier Univ AB Participants in the Physics Education Workshop at the 5th IUPAP International Conference on Women in Physics heard about, among other topics, a study exploring why students have difficulty with concepts related to magnetism (and whether explicitly evoking gender affects the results), work in Europe to develop materials to help teachers implement inquiry-based science education, and the use of peer instruction and online collaboration to help teacher-candidates develop questioning skills. C1 [Horton, Renee] NASA, Michoud Assembly Facil, New Orleans, LA USA. [Milner-Bolotin, Marina] Univ British Columbia, Vancouver, BC V5Z 1M9, Canada. RP Horton, R (reprint author), NASA, Michoud Assembly Facil, New Orleans, LA USA. NR 0 TC 0 Z9 0 U1 1 U2 1 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 978-0-7354-1344-3 J9 AIP CONF PROC PY 2015 VL 1697 AR 050002 DI 10.1063/1.4937644 PG 2 WC Physics, Multidisciplinary SC Physics GA BE9ID UT WOS:000377585500010 ER PT S AU Siles, JV Jung-Kubiak, C Reck, T Lee, C Lin, R Chattopadhyay, G Mehdi, I AF Siles, Jose V. Jung-Kubiak, Cecile Reck, Theodore Lee, Choonsup Lin, Robert Chattopadhyay, Goutam Mehdi, Imran GP IEEE TI A Dual-Output 550 GHz Frequency Tripler featuring Ultra-Compact Silicon Micromachining Packaging and Enhanced Power-Handling Capabilities SO 2015 45TH EUROPEAN MICROWAVE CONFERENCE (EUMC) SE European Microwave Conference LA English DT Proceedings Paper CT 45th European Microwave Conference (EuMC) CY SEP 06-11, 2015 CL Paris, FRANCE SP Keysight Technol, COBHAM, Copper Mountain Technol, CST, Infineon, MiCIAN, Natl Instruments, ROHDE & SCHWARZ, THALES, ThalesAlenia, United Monolith Semiconductors, European Microwave Assoc, Horizon House, IEEE, IEEE MTT Soc, IEEE Antennas & Propagat Soc DE Schottky diodes; frequency multipliers; sumbillimeter-wave technology; terahertz technology; Silicon micromachining; power-combining AB We report on an ultra-compact 550 GHz Schottky diode based frequency tripler based on an on-chip power combined structure that allows to integrate and combine four multiplying structures onto a single chip to increase up to a factor of four the power handling capabilities of traditional frequency multipliers. The chip is mounted onto a Silicon micromachined stack to increase compactness. The design features to very well balance independent outputs that can be used to feed multi-pixel receivers with no additional power dividing. The tripler is designed to operate in the 520-600 GHz band, showing a measured peak power of 1.6-1.8 mW per output when pumped with 200 mW. This corresponds to an efficiency of around 4% in the device once the output power is corrected for the text fixture losses and other unexpected losses. C1 [Siles, Jose V.; Jung-Kubiak, Cecile; Reck, Theodore; Lee, Choonsup; Lin, Robert; Chattopadhyay, Goutam; Mehdi, Imran] CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Siles, JV (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA USA. EM Jose.V.Siles@jpl.nasa.gov NR 9 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2325-0305 BN 978-2-8748-7039-2 J9 EUR MICROW CONF PY 2015 BP 845 EP 848 PG 4 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BE9BI UT WOS:000377204600208 ER PT S AU Ehsan, N Piepmeier, J Solly, M Macmurphy, S Lucey, J Wollack, E AF Ehsan, Negar Piepmeier, Jeffrey Solly, Michael Macmurphy, Shawn Lucey, Jared Wollack, Edward GP IEEE TI A Robust Waveguide Millimeter-Wave Noise Source SO 2015 45TH EUROPEAN MICROWAVE CONFERENCE (EUMC) SE European Microwave Conference LA English DT Proceedings Paper CT 45th European Microwave Conference (EuMC) CY SEP 06-11, 2015 CL Paris, FRANCE SP Keysight Technol, COBHAM, Copper Mountain Technol, CST, Infineon, MiCIAN, Natl Instruments, ROHDE & SCHWARZ, THALES, ThalesAlenia, United Monolith Semiconductors, European Microwave Assoc, Horizon House, IEEE, IEEE MTT Soc, IEEE Antennas & Propagat Soc AB This paper presents the design, fabrication, and characterization of a millimeter-wave noise source for the 160-210 GHz frequency range. The noise source has been implemented in an E-split-block waveguide package and the internal circuitry was developed on a quartz substrate. The measured excess noise ratio at 200 GHz is 9.6 dB. C1 [Ehsan, Negar; Piepmeier, Jeffrey; Solly, Michael; Lucey, Jared; Wollack, Edward] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Macmurphy, Shawn] AS & D Inc, Greenbelt, MD 20771 USA. RP Ehsan, N (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM negar.ehsan@nasa.gov RI Wollack, Edward/D-4467-2012 OI Wollack, Edward/0000-0002-7567-4451 NR 12 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2325-0305 BN 978-2-8748-7039-2 J9 EUR MICROW CONF PY 2015 BP 853 EP 856 PG 4 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BE9BI UT WOS:000377204600209 ER PT S AU U-yen, K Wollack, EJ AF U-yen, Kongpop Wollack, Edward J. GP IEEE TI Waveguide Photonic Choke Joint with Wide Out-of-band Rejection SO 2015 45TH EUROPEAN MICROWAVE CONFERENCE (EUMC) SE European Microwave Conference LA English DT Proceedings Paper CT 45th European Microwave Conference (EuMC) CY SEP 06-11, 2015 CL Paris, FRANCE SP Keysight Technol, COBHAM, Copper Mountain Technol, CST, Infineon, MiCIAN, Natl Instruments, ROHDE & SCHWARZ, THALES, ThalesAlenia, United Monolith Semiconductors, European Microwave Assoc, Horizon House, IEEE, IEEE MTT Soc, IEEE Antennas & Propagat Soc DE frequency selective surfaces; microwave filters; microwave devices; waveguide junctions; surface waves AB A photonic choke joint structure with a wide- stop-band is proposed for use as a waveguide flange interface. The structure consists of arrays of square metal pillars arranged in a periodic pattern to suppress the dominant-mode wave propagation in parallel-plate waveguide over a wide frequency bandwidth. The measurement results at microwave frequencies confirm the structure can provide broadband suppression, more than 56 dB over 6.25 times its operating frequency. Applications at millimeter wavelength are discussed. C1 [U-yen, Kongpop; Wollack, Edward J.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP U-yen, K (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM Kongpop.u-yen-1@nasa.gov RI Wollack, Edward/D-4467-2012 OI Wollack, Edward/0000-0002-7567-4451 NR 11 TC 1 Z9 1 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2325-0305 BN 978-2-8748-7039-2 J9 EUR MICROW CONF PY 2015 BP 1116 EP 1119 PG 4 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BE9BI UT WOS:000377204600273 ER PT B AU Seaman, CH Brower, DV Le, SQ Tang, HH AF Seaman, Calvin H. Brower, David V. Le, Suy Q. Tang, Henry H. GP ASME TI DEVELOPMENT AND TESTING OF A POST-INSTALLABLE DEEPWATER MONITORING SYSTEM USING FIBER-OPTIC SENSORS SO PROCEEDINGS OF THE ASME 34TH INTERNATIONAL CONFERENCE ON OCEAN, OFFSHORE AND ARCTIC ENGINEERING, 2015, VOL 5B LA English DT Proceedings Paper CT 34th ASME International Conference on Ocean, Offshore and Arctic Engineering (OMAE2015) CY MAY 31-JUN 05, 2015 CL St John's, CANADA SP Amer Soc Mech Engn, Ocean Offshore & Arct Engn Div AB This paper addresses the design and development of a fiber-optic monitoring system that can be deployed on existing deep water risers and flow lines; and provides a summary of test article fabrication and the subsequent laboratory testing performed at the National Aeronautics and Space Administration-Johnson Space Center (NASA-JSC). A major challenge of a post-installed instrumentation system is to ensure adequate coupling between the instruments and the riser or flow line of interest. This work investigates the sensor coupling for pipelines that are suspended in a water column (from topside platform to seabed) using a fiber-optic sensor clamp and subsea bonding adhesive. The study involved the design, fabrication, and test of several prototype clamps that contained fiber-optic sensors. A mold was produced by NASA using 3-D printing methods that allowed the casting of polyurethane clamp test articles to accommodate 4-inch and 8-inch diameter pipes. The prototype clamps were installed with a subsea adhesive in a "wet" environment and then tested in the NASA Structures Test Laboratory (STL). The tension, compression, and bending test data showed that the prototype sensor clamps achieved good structural coupling, and could provide high quality strain measurement for active monitoring. C1 [Seaman, Calvin H.; Le, Suy Q.] NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. [Brower, David V.] Astro Technol Inc, Houston, TX USA. [Tang, Henry H.] Aerodyne Ind LLC, Houston, TX USA. RP Seaman, CH (reprint author), NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-5652-9 PY 2015 AR V05BT04A048 PG 8 WC Engineering, Ocean; Engineering, Mechanical SC Engineering GA BE9GD UT WOS:000377420400048 ER PT B AU Hossain, MA Hossain, S AF Hossain, Mohammad A. Hossain, Sarzina GP ASME TI Numeric investigation of an Axi-symmetric Turbulent Jet SO PROCEEDINGS OF THE ASME INTERNATIONAL MECHANICAL ENGINEERING CONGRESS AND EXPOSITION, 2014, VOL 7 LA English DT Proceedings Paper CT ASME International Mechanical Engineering Congress and Exposition (IMECE2014) CY NOV 14-20, 2014 CL Montreal, CANADA SP ASME AB This work is focused on a numerical investigation of a turbulent axi-symmetric round jet in order to incorporate the knowledge of turbulence. Flow field analysis of a turbulent jet is one of the major research areas in recent years as turbulent jet dictates the interaction between fluid and other physical phenomena. Heat transfer, natural convection, frame propagation all depend on the behavior of turbulent jet. The mass and momentum transfer phenomena governs the flow field of the jet. A two dimensional pressure based Navier-stock solver is used to resolve the flow parameter of a turbulent round jet. Around One hundred twenty five thousand quadratic mesh elements are used for the simulation. A Mesh independency test has been done before resolving results. Characteristic flow parameters such as mean axial velocity, mean radial velocity distribution, turbulent kinetic energy, turbulent intensity, the turbulent dissipation rate are determined and presented. Similarity solution for mean axial velocity distribution and mean radial velocity distribution at different axial location are calculated and compared with experimental data. The result shows good agreement with experimental data. C1 [Hossain, Mohammad A.; Hossain, Sarzina] Univ Texas El Paso, Dept Mech Engn, NASA, Ctr Space Explorat & Technol Res, El Paso, TX 79968 USA. RP Hossain, MA (reprint author), Univ Texas El Paso, Dept Mech Engn, NASA, Ctr Space Explorat & Technol Res, El Paso, TX 79968 USA. NR 7 TC 0 Z9 0 U1 1 U2 1 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-4954-5 PY 2015 AR V007T09A102 PG 6 WC Engineering, Mechanical SC Engineering GA BE9HJ UT WOS:000377555200102 ER PT B AU Hossain, MA Hossain, S Soiket, MIH AF Hossain, Mohammad A. Hossain, Sarzina Soiket, Mohammad Ikthair Hossain GP ASME TI Numerical Investigation of Vortex Shedding in A Square Cylinder Using RANS and LES Model SO PROCEEDINGS OF THE ASME INTERNATIONAL MECHANICAL ENGINEERING CONGRESS AND EXPOSITION, 2014, VOL 7 LA English DT Proceedings Paper CT ASME International Mechanical Engineering Congress and Exposition (IMECE2014) CY NOV 14-20, 2014 CL Montreal, CANADA SP ASME ID TURBULENT; SIMULATION AB This work deals with the numerical investigation of vortex shedding in a square cylinder. The simulation has been done for 2D turbulent flow. Reynolds number (Re) is considered 22000. In order to resolve the flow field, both Reynolds Average Navier-stokes (RANS) model and Large Eddy Simulation (LES) technique were used. Standard k-epsilon model is considered among different RANS model in order to resolve the mean velocity field and the LES is used to capture the flow separation in the flow field. Both average velocity and velocity fluctuation are determined and compared. Different turbulence properties such as turbulent kinetic energy, turbulent intensity, eddy viscosity and vorticity magnitude are determined and presented for different downstream location to describe the complex flow property in turbulent regime. First the mesh independence test is done by different mesh size. ANSYS Fluent is used for the simulation. A pressured based solver is used with SIMPLE solution scheme, in order to find different flow variables. The results are compared with available published data. There are significant agreements with the experimental data. C1 [Hossain, Mohammad A.; Hossain, Sarzina] Univ Texas El Paso, NASA, Ctr Space Explorat & Technol Res, Dept Mech Engn, El Paso, TX 79968 USA. [Soiket, Mohammad Ikthair Hossain] McGill Univ, Dept Min & Mat Engn, Montreal, PQ, Canada. RP Hossain, MA (reprint author), Univ Texas El Paso, NASA, Ctr Space Explorat & Technol Res, Dept Mech Engn, El Paso, TX 79968 USA. NR 14 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-4954-5 PY 2015 PG 8 WC Engineering, Mechanical SC Engineering GA BE9HJ UT WOS:000377555200078 ER PT S AU Chattopadhyay, G Reck, T Schlecht, E Deal, W Mehdi, I AF Chattopadhyay, Goutam Reck, Theodore Schlecht, Erich Deal, William Mehdi, Imran GP IEEE TI Cryogenic Amplifier Based Sideband Separating Receivers SO 2015 40TH INTERNATIONAL CONFERENCE ON INFRARED, MILLIMETER AND TERAHERTZ WAVES (IRMMW-THZ) SE International Conference on Infrared Millimeter and Terahertz Waves LA English DT Proceedings Paper CT 40th International Conference on Infrared, Millimeter, and Terahertz Waves (IRMMW-THz) CY AUG 23-28, 2015 CL Chinese Univ Hong Kong, Hong Kong, PEOPLES R CHINA SP IEEE, IEEE Microwave Theory & Tech Soc, Virginal Diodes Inc, TeraView, Microtech Instruments Inc, Hong Kong Univ Sci & Technol, Dept Elect & Comp Engn, Croucher Fdn, Capital Normal Univ, K C Wong Educ Fdn, Meetings & Exhibit Hong Kong, Army Res Off, NSF HO Chinese Univ Hong Kong AB We have developed HEMT-based sideband-separating receivers operating in the 180 to 270 GHz and 620 to 660 GHz bands. These receivers utilize 30nm InP HEMT MMICs for the front-end low-noise amplifiers and balanced mixers cryogenically cooled to 20K. This paper presents the room and cryogenic temperature characterization of the receiver front-end system. C1 [Chattopadhyay, Goutam; Reck, Theodore; Schlecht, Erich; Mehdi, Imran] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Deal, William] Northrop Grumman Aerosp Syst, Redondo Beach, CA 90277 USA. RP Chattopadhyay, G (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2162-2027 BN 978-1-4799-8272-1 J9 INT CONF INFRA MILLI PY 2015 PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BE8OY UT WOS:000376674000017 ER PT S AU Fung, A Samoska, L Kangaslahti, P Sadowy, G Brown, A O'Connor, S Gritters, D AF Fung, Andy Samoska, Lorene Kangaslahti, Pekka Sadowy, Greg Brown, Andrew O'Connor, Shane Gritters, Darin GP IEEE TI W-Band Gallium Nitride MMIC Amplifiers for Cloud Doppler Radar Arrays SO 2015 40TH INTERNATIONAL CONFERENCE ON INFRARED, MILLIMETER AND TERAHERTZ WAVES (IRMMW-THZ) SE International Conference on Infrared Millimeter and Terahertz Waves LA English DT Proceedings Paper CT 40th International Conference on Infrared, Millimeter, and Terahertz Waves (IRMMW-THz) CY AUG 23-28, 2015 CL Chinese Univ Hong Kong, Hong Kong, PEOPLES R CHINA SP IEEE, IEEE Microwave Theory & Tech Soc, Virginal Diodes Inc, TeraView, Microtech Instruments Inc, Hong Kong Univ Sci & Technol, Dept Elect & Comp Engn, Croucher Fdn, Capital Normal Univ, K C Wong Educ Fdn, Meetings & Exhibit Hong Kong, Army Res Off, NSF HO Chinese Univ Hong Kong AB We present an effort in developing W-band (75-110 GHz) gallium nitride (GaN) monolithic microwave integrated circuit (MMIC) amplifiers for radar arrays. Due to GaN's high electric field breakdown capability and good 2D electron gas mobility in heterostructure field effect transistors, GaN power amplifiers provide best performance for high output power, high efficiency and small MMIC form factor amplifiers at W-band frequencies. GaN low noise amplifiers can also provide large receiver input dynamic range, reduce receiver noise figure and can be more tolerant of input power leakage from the transmitter without the need of protective limiter circuitry. All these characteristics are crucial for high frequency arrays where design require small circuit spacings, high efficiency to reduce power consumption and heating, and the minimization of circuit components for manufacturability and reliability. We will discuss results of power, driver and low noise amplifiers that we have designed, fabricated and characterized for radar array applications. C1 [Fung, Andy; Samoska, Lorene; Kangaslahti, Pekka; Sadowy, Greg] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Brown, Andrew; O'Connor, Shane; Gritters, Darin] Raytheon Co, Rancho Cucamonga, CA 91730 USA. RP Fung, A (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 5 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2162-2027 BN 978-1-4799-8272-1 J9 INT CONF INFRA MILLI PY 2015 PG 1 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BE8OY UT WOS:000376674000331 ER PT S AU Karasik, BS Cunnane, DP Sergeev, AV AF Karasik, Boris S. Cunnane, Daniel P. Sergeev, Andrei V. GP IEEE TI High-T-C THz HEB Mixers: Progress and Prospects SO 2015 40TH INTERNATIONAL CONFERENCE ON INFRARED, MILLIMETER AND TERAHERTZ WAVES (IRMMW-THZ) SE International Conference on Infrared Millimeter and Terahertz Waves LA English DT Proceedings Paper CT 40th International Conference on Infrared, Millimeter, and Terahertz Waves (IRMMW-THz) CY AUG 23-28, 2015 CL Chinese Univ Hong Kong, Hong Kong, PEOPLES R CHINA SP IEEE, IEEE Microwave Theory & Tech Soc, Virginal Diodes Inc, TeraView, Microtech Instruments Inc, Hong Kong Univ Sci & Technol, Dept Elect & Comp Engn, Croucher Fdn, Capital Normal Univ, K C Wong Educ Fdn, Meetings & Exhibit Hong Kong, Army Res Off, NSF HO Chinese Univ Hong Kong ID SUPERCONDUCTING PHOTODETECTORS AB We analyze the pathways for achieving the THz hotelectron bolometer (HEB) mixers using high-TC superconductors. Requirements to the material in order to obtain large (up to 10 GHz) intermediate frequency bandwidth as well as recent results on MgB2 HEB mixer devices are discussed. Based on a thermal model of the energy relaxation in a thin film, we explain the difference between the mixing behaviors in previously studied HEB materials. We also introduce the concept of the HEB mixer based on the low electron density MBE-grown quasi-2DEG LaCuO/LaSrCuO superconductors with tunable critical temperature. C1 [Karasik, Boris S.; Cunnane, Daniel P.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Sergeev, Andrei V.] SUNY Buffalo, Buffalo, NY 14260 USA. RP Karasik, BS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2162-2027 BN 978-1-4799-8272-1 J9 INT CONF INFRA MILLI PY 2015 PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BE8OY UT WOS:000376674000019 ER PT S AU Lesser, D Walker, CK Smith, IS Goldsmith, PF Cortes, G Dougherty, S Swift, B Kloosterman, J Honniball, C Young, A Peters, W Kulesa, C Perry, W Noll, J Bernasconi, P Groppi, C Mani, H Duffy, B AF Lesser, David Walker, Christopher K. Smith, I. Steve Goldsmith, Paul F. Cortes, German Dougherty, Stefan Swift, Brandon Kloosterman, Jenna Honniball, Casey Young, Abram Peters, William Kulesa, Craig Perry, William Noll, James Bernasconi, Pietro Groppi, Christopher Mani, Hamdi Duffy, Brian GP IEEE TI 10 Meter Sub-Orbital Large Balloon Reflector (LBR) SO 2015 40TH INTERNATIONAL CONFERENCE ON INFRARED, MILLIMETER AND TERAHERTZ WAVES (IRMMW-THZ) SE International Conference on Infrared Millimeter and Terahertz Waves LA English DT Proceedings Paper CT 40th International Conference on Infrared, Millimeter, and Terahertz Waves (IRMMW-THz) CY AUG 23-28, 2015 CL Chinese Univ Hong Kong, Hong Kong, PEOPLES R CHINA SP IEEE, IEEE Microwave Theory & Tech Soc, Virginal Diodes Inc, TeraView, Microtech Instruments Inc, Hong Kong Univ Sci & Technol, Dept Elect & Comp Engn, Croucher Fdn, Capital Normal Univ, K C Wong Educ Fdn, Meetings & Exhibit Hong Kong, Army Res Off, NSF HO Chinese Univ Hong Kong AB Now in Phase II of the NASA Innovative Advanced Concepts (NIAC) Program, our team is advancing key technologies required to realize a suborbital, 10 meter class telescope suitable for operation from radio to THz frequencies. The telescope consists of an inflatable, half-aluminized spherical reflector deployed within a much larger carrier balloon - either zero pressure or super pressure. C1 [Lesser, David; Walker, Christopher K.; Dougherty, Stefan; Swift, Brandon; Honniball, Casey; Young, Abram; Peters, William; Kulesa, Craig; Duffy, Brian] Univ Arizona, Dept Astron, Tucson, AZ USA. [Smith, I. Steve; Perry, William; Noll, James] Southwest Res Inst, North Space Sci & Engn Div, San Antonio, TX USA. [Goldsmith, Paul F.; Kloosterman, Jenna] CALTECH, Jet Prop Lab, Pasadena, CA USA. [Bernasconi, Pietro] Johns Hopkins Appl Phys Lab, Laurel, MD USA. [Groppi, Christopher; Mani, Hamdi] Arizona State Univ, Sch Earth & Space Explorat, Tempe, AZ USA. [Cortes, German] Cornell Univ, Dept Astron, Ithaca, NY 14853 USA. RP Lesser, D (reprint author), Univ Arizona, Dept Astron, Tucson, AZ USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2162-2027 BN 978-1-4799-8272-1 J9 INT CONF INFRA MILLI PY 2015 PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BE8OY UT WOS:000376674000155 ER PT S AU Mariani, G Kenyon, M AF Mariani, Giacomo Kenyon, Matthew GP IEEE TI Room-Temperature Remote Sensing: Far-Infrared Imaging based on Thermopile Technology SO 2015 40TH INTERNATIONAL CONFERENCE ON INFRARED, MILLIMETER AND TERAHERTZ WAVES (IRMMW-THZ) SE International Conference on Infrared Millimeter and Terahertz Waves LA English DT Proceedings Paper CT 40th International Conference on Infrared, Millimeter, and Terahertz Waves (IRMMW-THz) CY AUG 23-28, 2015 CL Chinese Univ Hong Kong, Hong Kong, PEOPLES R CHINA SP IEEE, IEEE Microwave Theory & Tech Soc, Virginal Diodes Inc, TeraView, Microtech Instruments Inc, Hong Kong Univ Sci & Technol, Dept Elect & Comp Engn, Croucher Fdn, Capital Normal Univ, K C Wong Educ Fdn, Meetings & Exhibit Hong Kong, Army Res Off, NSF HO Chinese Univ Hong Kong AB This work presents recent advances on room-temperature far-infrared thermopile detectors. The focal plane arrays micromachined at JPL are integrated with dedicated radiation-hardened read-out circuit chips to provide remote sensing under high radiation conditions environments. C1 [Mariani, Giacomo; Kenyon, Matthew] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Mariani, G (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2162-2027 BN 978-1-4799-8272-1 J9 INT CONF INFRA MILLI PY 2015 PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BE8OY UT WOS:000376674000312 ER PT S AU Mehdi, I Siles, J Lee, C Lin, R AF Mehdi, Imran Siles, Jose Lee, Choonsup Lin, Robert GP IEEE TI Compact Submillimeter-wave Multi-Pixel Local Oscillator Sources SO 2015 40TH INTERNATIONAL CONFERENCE ON INFRARED, MILLIMETER AND TERAHERTZ WAVES (IRMMW-THZ) SE International Conference on Infrared Millimeter and Terahertz Waves LA English DT Proceedings Paper CT 40th International Conference on Infrared, Millimeter, and Terahertz Waves (IRMMW-THz) CY AUG 23-28, 2015 CL Chinese Univ Hong Kong, Hong Kong, PEOPLES R CHINA SP IEEE, IEEE Microwave Theory & Tech Soc, Virginal Diodes Inc, TeraView, Microtech Instruments Inc, Hong Kong Univ Sci & Technol, Dept Elect & Comp Engn, Croucher Fdn, Capital Normal Univ, K C Wong Educ Fdn, Meetings & Exhibit Hong Kong, Army Res Off, NSF HO Chinese Univ Hong Kong C1 [Mehdi, Imran; Siles, Jose; Lee, Choonsup; Lin, Robert] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Mehdi, I (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2162-2027 BN 978-1-4799-8272-1 J9 INT CONF INFRA MILLI PY 2015 PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BE8OY UT WOS:000376674000175 ER PT S AU Pepper, BJ Bradford, CM Reck, T Echternach, PM AF Pepper, B. J. Bradford, C. M. Reck, T. Echternach, P. M. GP IEEE TI Evidence of 1.5 THz Single-Photon Detection in Quantum Capacitance Detectors via Telegraph Rate Distribution Asymmetry SO 2015 40TH INTERNATIONAL CONFERENCE ON INFRARED, MILLIMETER AND TERAHERTZ WAVES (IRMMW-THZ) SE International Conference on Infrared Millimeter and Terahertz Waves LA English DT Proceedings Paper CT 40th International Conference on Infrared, Millimeter, and Terahertz Waves (IRMMW-THz) CY AUG 23-28, 2015 CL Chinese Univ Hong Kong, Hong Kong, PEOPLES R CHINA SP IEEE, IEEE Microwave Theory & Tech Soc, Virginal Diodes Inc, TeraView, Microtech Instruments Inc, Hong Kong Univ Sci & Technol, Dept Elect & Comp Engn, Croucher Fdn, Capital Normal Univ, K C Wong Educ Fdn, Meetings & Exhibit Hong Kong, Army Res Off, NSF HO Chinese Univ Hong Kong AB Quantum Capacitance Detectors (QCDs) are shot noise limited terahertz detectors. Radiation breaks Cooper pairs, causing quasiparticle poisoning of a charge qubit, read out by a microwave resonator. We find asymmetry in the distribution of telegraph transition rates, interpreted as resulting from discrete single-photon events. C1 [Pepper, B. J.; Bradford, C. M.; Reck, T.; Echternach, P. M.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Pepper, BJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Brian.J.Pepper@jpl.nasa.gov NR 8 TC 0 Z9 0 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2162-2027 BN 978-1-4799-8272-1 J9 INT CONF INFRA MILLI PY 2015 PG 3 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BE8OY UT WOS:000376674000436 ER PT S AU Schlecht, E Siles, J Treuttel, J Lin, R Yee, JH Wu, D Thomas, B Mehdi, I AF Schlecht, Erich Siles, Jose Treuttel, Jeanne Lin, Robert Yee, Jeng-Hwa Wu, Dong Thomas, Bertrand Mehdi, Imran GP IEEE TI Terahertz Limb Sounder to Measure Winds and Temperature above 100 km SO 2015 40TH INTERNATIONAL CONFERENCE ON INFRARED, MILLIMETER AND TERAHERTZ WAVES (IRMMW-THZ) SE International Conference on Infrared Millimeter and Terahertz Waves LA English DT Proceedings Paper CT 40th International Conference on Infrared, Millimeter, and Terahertz Waves (IRMMW-THz) CY AUG 23-28, 2015 CL Chinese Univ Hong Kong, Hong Kong, PEOPLES R CHINA SP IEEE, IEEE Microwave Theory & Tech Soc, Virginal Diodes Inc, TeraView, Microtech Instruments Inc, Hong Kong Univ Sci & Technol, Dept Elect & Comp Engn, Croucher Fdn, Capital Normal Univ, K C Wong Educ Fdn, Meetings & Exhibit Hong Kong, Army Res Off, NSF HO Chinese Univ Hong Kong AB We describe a new instrument, the Terahertz Limb Sounder (TLS) designed to measure upper atmospheric winds and temperature in the altitude regime between 100 and 150 km. It is based on Doppler measurements of the line of neutral atomic oxygen, OI, at 2.06 THz. This measurement takes advantage of a Schottky diode based all solid state receiver. C1 [Schlecht, Erich; Siles, Jose; Treuttel, Jeanne; Lin, Robert; Mehdi, Imran] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Yee, Jeng-Hwa] Johns Hopkins Univ Appl Phys Lab, Laurel, MD 20723 USA. [Wu, Dong] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Thomas, Bertrand] Radiometer Phys GmbH, D-53340 Meckenheim, Germany. RP Schlecht, E (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2162-2027 BN 978-1-4799-8272-1 J9 INT CONF INFRA MILLI PY 2015 PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BE8OY UT WOS:000376674000156 ER PT S AU Siegel, PH Tang, A Virbila, G Kim, Y Chang, MCF Pikov, V AF Siegel, Peter H. Tang, Adrian Virbila, Gabriel Kim, Yanghyo Chang, M. C. Frank Pikov, Victor GP IEEE TI Compact Non-Invasive Millimeter-Wave Glucose Sensor SO 2015 40TH INTERNATIONAL CONFERENCE ON INFRARED, MILLIMETER AND TERAHERTZ WAVES (IRMMW-THZ) SE International Conference on Infrared Millimeter and Terahertz Waves LA English DT Proceedings Paper CT 40th International Conference on Infrared, Millimeter, and Terahertz Waves (IRMMW-THz) CY AUG 23-28, 2015 CL Chinese Univ Hong Kong, Hong Kong, PEOPLES R CHINA SP IEEE, IEEE Microwave Theory & Tech Soc, Virginal Diodes Inc, TeraView, Microtech Instruments Inc, Hong Kong Univ Sci & Technol, Dept Elect & Comp Engn, Croucher Fdn, Capital Normal Univ, K C Wong Educ Fdn, Meetings & Exhibit Hong Kong, Army Res Off, NSF HO Chinese Univ Hong Kong AB The authors describe a compact non-invasive CMOS-circuit-based glucose monitor using millimeter-wave transmission for use on animal and human subjects. Using an earlier device, in vivo measurements were performed through the ear in anesthetized animals and correlated with blood glucose concentration from test strips. In addition, millimeter wave absorption through glucose-containing solutions was measured in specialized liquid transmission cells and is shown to correlate with the animal and separate in vitro data. Design and performance information on the CMOS transceiver are given. C1 [Siegel, Peter H.] CALTECH, Pasadena, CA 91125 USA. [Siegel, Peter H.] THz Global, Pasadena, CA USA. [Tang, Adrian; Virbila, Gabriel; Kim, Yanghyo; Chang, M. C. Frank] Univ Calif Los Angeles, Los Angeles, CA USA. [Tang, Adrian] NASA, Jet Prop Lab, Los Angeles, CA USA. [Chang, M. C. Frank] Natl Chiao Tung Univ, Hsinchu, Taiwan. [Pikov, Victor] GlaxoSmithKline, Stevenage, Herts, England. RP Siegel, PH (reprint author), CALTECH, Pasadena, CA 91125 USA. NR 6 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2162-2027 BN 978-1-4799-8272-1 J9 INT CONF INFRA MILLI PY 2015 PG 3 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BE8OY UT WOS:000376674000021 ER PT S AU Siles, JV Schlecht, E Lin, R Lee, C Mehdi, I AF Siles, Jose V. Schlecht, Erich Lin, Robert Lee, Choonsup Mehdi, Imran GP IEEE TI High-Efficiency Planar Schottky Diode Based Submillimeter-Wave Frequency Multipliers Optimized for High-Power Operation SO 2015 40TH INTERNATIONAL CONFERENCE ON INFRARED, MILLIMETER AND TERAHERTZ WAVES (IRMMW-THZ) SE International Conference on Infrared Millimeter and Terahertz Waves LA English DT Proceedings Paper CT 40th International Conference on Infrared, Millimeter, and Terahertz Waves (IRMMW-THz) CY AUG 23-28, 2015 CL Chinese Univ Hong Kong, Hong Kong, PEOPLES R CHINA SP IEEE, IEEE Microwave Theory & Tech Soc, Virginal Diodes Inc, TeraView, Microtech Instruments Inc, Hong Kong Univ Sci & Technol, Dept Elect & Comp Engn, Croucher Fdn, Capital Normal Univ, K C Wong Educ Fdn, Meetings & Exhibit Hong Kong, Army Res Off, NSF HO Chinese Univ Hong Kong AB We report on a new series of millimeter and submillimeter-wave frequency multipliers specifically optimized for very high-power operation in order to meet the requirements of next generation terahertz instruments for Astrophysics, Planetary science, Earth science and radar imaging applications. New frequency multiplier chips have been designed and fabricated in the 100 GHz to 1 THz range focusing on higher power operation. Initial tests have shown efficiencies of around 30% for a single-chip 105-120 GHz tripler, and 25% for a singlechip 170-200 GHz doubler, when pumped with 500 mW. These results correspond to a factor of 2-3 improvement with regards to previous designs at these frequencies. Similar improvements are expected for the new designs at higher frequencies. C1 [Siles, Jose V.; Schlecht, Erich; Lin, Robert; Lee, Choonsup; Mehdi, Imran] CALTECH, Jet Prop Lab, Pasadena, CA 91101 USA. RP Siles, JV (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91101 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2162-2027 BN 978-1-4799-8272-1 J9 INT CONF INFRA MILLI PY 2015 PG 1 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BE8OY UT WOS:000376674000285 ER PT S AU Zeng, LZ Tong, CYE Wollack, EJ Chuss, DT AF Zeng, Lingzhen Tong, Cheuk-yu Edward Wollack, Edward J. Chuss, David T. GP IEEE TI A wideband profiled corrugated horn for multichroic applications SO 2015 40TH INTERNATIONAL CONFERENCE ON INFRARED, MILLIMETER AND TERAHERTZ WAVES (IRMMW-THZ) SE International Conference on Infrared Millimeter and Terahertz Waves LA English DT Proceedings Paper CT 40th International Conference on Infrared, Millimeter, and Terahertz Waves (IRMMW-THz) CY AUG 23-28, 2015 CL Chinese Univ Hong Kong, Hong Kong, PEOPLES R CHINA SP IEEE, IEEE Microwave Theory & Tech Soc, Virginal Diodes Inc, TeraView, Microtech Instruments Inc, Hong Kong Univ Sci & Technol, Dept Elect & Comp Engn, Croucher Fdn, Capital Normal Univ, K C Wong Educ Fdn, Meetings & Exhibit Hong Kong, Army Res Off, NSF HO Chinese Univ Hong Kong ID CROSS-POLARIZATION AB A wideband profiled corrugated feedhorn was developed for multichroic applications. This feedhorn features a return loss of better than -25 dB and cross polarization peaks below -30 dB, over a fractional bandwidth of > 50%. Its performance is close to that of the ring-loaded corrugated feedhorn; however, the design presented is much easier to fabricate at millimeter wavelengths. C1 [Zeng, Lingzhen; Tong, Cheuk-yu Edward] Harvard Smithsonian Ctr Astrophys, 60 Garden St, Cambridge, MA 02138 USA. [Wollack, Edward J.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Chuss, David T.] Villanova Univ, Villanova, PA 19085 USA. RP Zeng, LZ (reprint author), Harvard Smithsonian Ctr Astrophys, 60 Garden St, Cambridge, MA 02138 USA. RI Wollack, Edward/D-4467-2012 OI Wollack, Edward/0000-0002-7567-4451 NR 8 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2162-2027 BN 978-1-4799-8272-1 J9 INT CONF INFRA MILLI PY 2015 PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BE8OY UT WOS:000376674000444 ER PT S AU Petry, F Elmore, P AF Petry, Frederick Elmore, Paul BE Tamir, DE Rishe, ND Kandel, A TI Geospatial Uncertainty Representation: Fuzzy and Rough Set Approaches SO FIFTY YEARS OF FUZZY LOGIC AND ITS APPLICATIONS SE Studies in Fuzziness and Soft Computing LA English DT Article; Book Chapter DE Geographic information systems; Spatial database; Fuzzy sets; Rough sets; Triangulated irregular networks; Indiscernibility relation; Spatial relations; Upper and lower approximations ID SPATIAL QUERIES; BIG DATA; INTEGRATION; INFORMATION; CHALLENGES AB Uncertainty in geospatial data is often considered in the context of geographical information systems which enable a variety of operations and manipulation of spatial data. Here we consider how both fuzzy set and rough set theory has been used to represent geospatial data with uncertainty. Terrain modeling and triangulated irregular networks techniques utilizing fuzzy sets are presented. Rough set theory is overviewed and its application to spatial data is described. Issues of uncertainty in the representation of spatial relationships such as topological and directional relationships are discussed. C1 [Petry, Frederick] Marine Geosci Div, Geospatial Sci & Technol Branch, Bldg 1005, Raleigh, NC USA. [Elmore, Paul] Naval Res Lab, Stennis Space Ctr, Stennis Space Ctr, MS 39529 USA. RP Petry, F (reprint author), Marine Geosci Div, Geospatial Sci & Technol Branch, Bldg 1005, Raleigh, NC USA. EM fred.petry@nrlssc.navy.mil NR 50 TC 1 Z9 1 U1 2 U2 2 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY SN 1434-9922 BN 978-3-319-19683-1; 978-3-319-19682-4 J9 STUD FUZZ SOFT COMP PY 2015 VL 326 BP 483 EP 497 DI 10.1007/978-3-319-19683-1_24 D2 10.1007/978-3-319-19683-1 PG 15 WC Computer Science, Artificial Intelligence; Robotics SC Computer Science; Robotics GA BE6OR UT WOS:000374483600025 ER PT J AU Gross, JN Watson, RM Sivaneri, V Bar-Sever, YE Bertiger, WI Haines, B AF Gross, Jason N. Watson, Ryan M. Sivaneri, Victor Bar-Sever, Yoaz E. Bertiger, William I. Haines, Bruce GP Inst Navigat TI Integration of Inertial Navigation into Real-Time GIPSY-x (RTGx) SO PROCEEDINGS OF THE 28TH INTERNATIONAL TECHNICAL MEETING OF THE SATELLITE DIVISION OF THE INSTITUTE OF NAVIGATION (ION GNSS+ 2015) LA English DT Proceedings Paper CT 28th International Technical Meeting of The Satellite-Division-of-the-Institute-of-Navigation (ION GNSS+) CY SEP 14-18, 2015 CL Tampa, FL SP Inst Navigat, Satellite Div ID GPS; GLONASS AB This paper details the integration of an Inertial Navigation System (INS) processing capability within JPL's RTGx geodetic data analysis and navigation software, and provides a performance analysis with experimental flight data in order to validate the implementation. The RTGx software, when used in conjunction with JPL's Global Differential GPS System (GDGPS), can be configured for real-t ime kinematic Precise Point Positioning (K-PPP) for centimeter-level positioning accuracy. Since 2006, RTGx's predecessor, RTG, has provided operational real-time K-PPP for NASA's Uninhabited Aerial Vehicle Synthetic Aperture Radar (UAVSAR) repeat pass interferometry mission on campaigns all over the world. While RTG's GPS-only data processing is meeting mission requirements during nominal science operations, its performance naturally degrades during certain flight scenarios, such as abrupt changes in the aircraft attitude or high banking turns, which induce signal loss-of-lock, carrier-phase breaks and/or cycle slips. During these periods, the well-known downsides of K-PPP, including the position solution's sensitivity to phase breaks and slow convergence after loss-of-lock become apparent, and may impact the instruments critical data take periods. Therefore, tightly-coupled INS has been integrated into RTGx to offer additional robustness. This paper discusses the adopted INS formulation and uses the flight data made available to the community by the National Geodetic Survey's Kinematic Challenge (Damiani et al., 2013) to offer an experimental performance evaluation. The integration of INS in RTGx is shown to provide solution improvements both in terms of accuracy and precision with respect to a post-processed ambiguity-fixed reference solution. Furthermore, the integration of INS into the RTGx software will enable RTGx to support new application domains. C1 [Gross, Jason N.] W Virginia Univ, Morgantown, WV 26506 USA. [Watson, Ryan M.] W Virginia Univ, Dept Mech & Aerosp MAE Engn, Morgantown, WV 26506 USA. [Watson, Ryan M.; Sivaneri, Victor] W Virginia Univ, UAV Flight Testing Team, Morgantown, WV 26506 USA. [Sivaneri, Victor] W Virginia Univ, MAE Dept, Morgantown, WV 26506 USA. [Bar-Sever, Yoaz E.] Jet Prop Lab, Global Differential GPS Syst GDGPS, Pasadena, CA USA. [Bertiger, William I.] Jet Prop Lab, Pasadena, CA USA. [Haines, Bruce] Jet Prop Lab, Near Earth Tracking Applicat Grp, Pasadena, CA USA. RP Gross, JN (reprint author), W Virginia Univ, Morgantown, WV 26506 USA. NR 20 TC 1 Z9 1 U1 0 U2 0 PU INST NAVIGATION PI WASHINGTON PA 815 15TH ST NW, STE 832, WASHINGTON, DC 20005 USA PY 2015 BP 2560 EP 2569 PG 10 WC Remote Sensing; Telecommunications SC Remote Sensing; Telecommunications GA BE7FT UT WOS:000375211602055 ER PT J AU Yang, YM Komjathy, A Langley, RB Meng, X Verkhoglyadova, O Mannucci, AJ AF Yang, Y-M. Komjathy, A. Langley, R. B. Meng, X. Verkhoglyadova, Olga Mannucci, A. J. GP Inst Navigat TI Towards the Implementation of a GNSS-Based Tsunami Early Warning System Using Ionospheric Measurements SO PROCEEDINGS OF THE 28TH INTERNATIONAL TECHNICAL MEETING OF THE SATELLITE DIVISION OF THE INSTITUTE OF NAVIGATION (ION GNSS+ 2015) LA English DT Proceedings Paper CT 28th International Technical Meeting of The Satellite-Division-of-the-Institute-of-Navigation (ION GNSS+) CY SEP 14-18, 2015 CL Tampa, FL SP Inst Navigat, Satellite Div ID ELECTRON-CONTENT; EARTHQUAKE; WAVES AB Natural hazards and solid Earth events, such as earthquakes, tsunamis and volcanic eruptions are actual sources that may trigger acoustic and gravity waves resulting in traveling ionospheric disturbances (TIDs) in the upper atmosphere. Trans-ionospheric radio wave measurements sense the total electron content (TEC) along the signal propagation path. In this research, we introduce a novel GPS-based detection and estimation technique for remote sensing of atmospheric wave-induced TIDs including space weather phenomena induced by major natural hazard events, using TEC time series collected from worldwide ground-based dual-frequency GNSS (including GPS) receiver networks. We demonstrate the ability of using ground-and space-based dual-frequency GPS measurements to detect and monitor tsunami wave propagation from the 2011 Tohoku-Oki earthquake and tsunami. Major wave trains with different propagation speeds and wavelengths were identified through analysis of the GPS remote sensing observations. Dominant physical characteristics of atmospheric wave-induced TIDs are found to be associated with specific tsunami propagations and oceanic Rayleigh waves. In this research, we focus on the analysis of tsunami-induced TIDs observed from the U.S. west coast. We compared GPS-based observations, corresponding model simulations and tsunami wave propagation. Results are shown to lead to a better understanding of the tsunami-induced ionosphere responses. Based on current distribution of Plate Boundary Observatory GPS stations, the results indicate that tsunami-induced TIDs may be detected about 60 minutes prior to tsunamis arriving at the U.S. west coast. It is expected that this GNSS-based technology will become an integral part of future early-warning systems. C1 [Yang, Y-M.; Komjathy, A.; Meng, X.; Verkhoglyadova, Olga; Mannucci, A. J.] CALTECH, NASA, Jet Prop Lab, Pasadena, CA 91109 USA. [Komjathy, A.] Univ New Brunswick, POB 4400, Fredericton, NB E3B 5A3, Canada. [Langley, R. B.] Univ New Brunswick, Dept Geodesy & Geomat Engn, POB 4400, Fredericton, NB E3B 5A3, Canada. RP Yang, YM (reprint author), CALTECH, NASA, Jet Prop Lab, Pasadena, CA 91109 USA. NR 17 TC 0 Z9 0 U1 0 U2 0 PU INST NAVIGATION PI WASHINGTON PA 815 15TH ST NW, STE 832, WASHINGTON, DC 20005 USA PY 2015 BP 3480 EP 3484 PG 5 WC Remote Sensing; Telecommunications SC Remote Sensing; Telecommunications GA BE7FT UT WOS:000375211603054 ER PT S AU Emami, E Bebis, G Nefian, A Fong, T AF Emami, Ebrahim Bebis, George Nefian, Ara Fong, Terry BE Bebis, G Boyle, R Parvin, B Koracin, D Pavlidis, I Feris, R McGraw, T Elendt, M Kopper, R Ragan, E Ye, Z Weber, G TI Automatic Crater Detection Using Convex Grouping and Convolutional Neural Networks SO ADVANCES IN VISUAL COMPUTING, PT II (ISVC 2015) SE Lecture Notes in Computer Science LA English DT Proceedings Paper CT 11th International Symposium on Visual Computing (ISVC) CY DEC 14-16, 2015 CL Las Vegas, NV SP UNR, Desert Res Inst, LBNL, NASA Ames, BAE Syst, Intel, Ford, Hewlett Packard, Mitsubishi Elec Res Labs, Toyota, Gen Elect, Berkeley Lab ID FACE DETECTION; SHAPE AB Craters are some the most important landmarks on the surface of many planets which can be used for autonomous safe landing and spacecraft and rover navigation. Manual detection of craters is laborious and impractical, and many approaches have been proposed in the field to automate this task. However, none of these methods have yet become a standard tool for crater detection due to the challenging nature of this problem. In this paper, we propose a new crater detection algorithm (CDA) which employs a multi-scale candidate region detection step based on convexity cues and candidate region verification based on machine learning. Using an extensive dataset, our method has achieved a 92 % detection rate with an 85 % precision rate. C1 [Emami, Ebrahim; Bebis, George] Univ Nevada, Dept Comp Sci & Engn, Reno, NV 89557 USA. [Nefian, Ara; Fong, Terry] NASA, Intelligent Robot Grp IRG, Ames Res Ctr, Mountain View, CA USA. RP Bebis, G (reprint author), Univ Nevada, Dept Comp Sci & Engn, Reno, NV 89557 USA. EM ebrahim@nevada.unr.edu; bebis@cse.unr.edu; ara.nefian@nasa.gov; terry.fong@nasa.gov NR 20 TC 0 Z9 0 U1 1 U2 1 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 0302-9743 BN 978-3-319-27863-6; 978-3-319-27862-9 J9 LECT NOTES COMPUT SC PY 2015 VL 9475 BP 213 EP 224 DI 10.1007/978-3-319-27863-6_20 PG 12 WC Computer Science, Artificial Intelligence; Computer Science, Interdisciplinary Applications; Computer Science, Theory & Methods; Imaging Science & Photographic Technology SC Computer Science; Imaging Science & Photographic Technology GA BE8FF UT WOS:000376401000020 ER PT J AU Goldberg, RK Carney, KS Dubois, P Hoffarth, C Rajan, S Blankenhorn, G AF Goldberg, R. K. Carney, K. S. Dubois, P. Hoffarth, C. Rajan, S. Blankenhorn, G. BE Xiao, X Loos, A Liu, D TI Incorporation of Plasticity and Damage into an Orthotropic Three-Dimensional Model with Tabulated Input Suitable for Use in Composite Impact Problems SO PROCEEDINGS OF THE AMERICAN SOCIETY FOR COMPOSITES: THIRTIETH TECHNICAL CONFERENCE LA English DT Proceedings Paper CT 30th Technical Conference of the American-Society-for-Composites CY SEP 28-30, 2015 CL East Lansing, MI SP Amer Soc Composites ID ANISOTROPIC DAMAGE; FIBER-COMPOSITES AB The need for accurate material models to simulate the deformation, damage and failure of polymer matrix composites under impact conditions is becoming critical as these materials are gaining increased usage in the aerospace and automotive industries. While there are several composite material models currently available within commercial transient dynamic finite element codes, several features have been identified as being lacking in the currently available material models that could increase the predictive capability of the impact simulations. A specific desired feature includes the incorporation of both plasticity and damage within the material model. Another desired feature includes using experimentally based tabulated stress-strain input to define the evolution of plasticity and damage as opposed to specifying discrete input parameters (such as modulus and strength) and employing analytical functions to track the response of the material. To begin to address these needs, a combined plasticity and damage model suitable for use with both solid and shell elements is being developed for implementation within the commercial code LS-DYNA. The plasticity model is based on extending the Tsai-Wu composite failure model into a strain-hardening based orthotropic plasticity model with a non-associative flow rule. The evolution of the yield surface is determined based on tabulated stress-strain curves in the various normal and shear directions and is tracked using the effective plastic strain. The effective plastic strain is computed by using the non-associative flow rule in combination with appropriate numerical methods. To compute the evolution of damage, a strain equivalent semi-coupled formulation is used, in which a load in one direction results in a stiffness reduction in multiple coordinate directions. A specific laminated composite is examined to demonstrate the process of characterizing and analyzing the response of a composite using the developed model. C1 [Goldberg, R. K.; Carney, K. S.] NASA Glenn, 21000 Brookpark Rd, Cleveland, OH 44135 USA. [Dubois, P.] George Mason Univ, Fairfax, VA 22030 USA. [Hoffarth, C.; Rajan, S.] Arizona State Univ, Tempe, AZ 85287 USA. [Blankenhorn, G.] Livermore Software Technol Corp, Livermore, CA 94551 USA. RP Goldberg, RK (reprint author), NASA Glenn, 21000 Brookpark Rd, Cleveland, OH 44135 USA. NR 16 TC 0 Z9 0 U1 1 U2 1 PU DESTECH PUBLICATIONS, INC PI LANCASTER PA 439 DUKE STREET, LANCASTER, PA 17602-4967 USA BN 978-1-60595-225-3 PY 2015 BP 203 EP 219 PG 17 WC Engineering, Mechanical; Materials Science, Composites SC Engineering; Materials Science GA BE7MI UT WOS:000375565100018 ER PT J AU Mcelroy, M AF Mcelroy, M. BE Xiao, X Loos, A Liu, D TI An Enriched Shell Element for Delamination Simulation in Composite Laminates SO PROCEEDINGS OF THE AMERICAN SOCIETY FOR COMPOSITES: THIRTIETH TECHNICAL CONFERENCE LA English DT Proceedings Paper CT 30th Technical Conference of the American-Society-for-Composites CY SEP 28-30, 2015 CL East Lansing, MI SP Amer Soc Composites ID FRACTURE AB A formulation is presented for an enriched shell finite element capable of delamination simulation in composite laminates. The element uses an adaptive splitting approach for damage characterization that allows for straightforward low-fidelity model creation and a numerically efficient solution. The Floating Node Method is used in conjunction with the Virtual Crack Closure Technique to predict delamination growth and represent it discretely at an arbitrary ply interface. The enriched element is verified for Mode I delamination simulation using numerical benchmark data. After determining important mesh configuration guidelines for the vicinity of the delamination front in the model, a good correlation was found between the enriched shell element model results and the benchmark data set. C1 [Mcelroy, M.] NASA, Langley Res Ctr, 2 W Reid St,Mail Stop 188E, Hampton, VA 23681 USA. RP Mcelroy, M (reprint author), NASA, Langley Res Ctr, 2 W Reid St,Mail Stop 188E, Hampton, VA 23681 USA. NR 24 TC 0 Z9 0 U1 0 U2 0 PU DESTECH PUBLICATIONS, INC PI LANCASTER PA 439 DUKE STREET, LANCASTER, PA 17602-4967 USA BN 978-1-60595-225-3 PY 2015 BP 313 EP 329 PG 17 WC Engineering, Mechanical; Materials Science, Composites SC Engineering; Materials Science GA BE7MI UT WOS:000375565100026 ER PT J AU Cater, C Xiao, X Goldberg, RK Kolhman, LW AF Cater, C. Xiao, X. Goldberg, R. K. Kolhman, L. W. BE Xiao, X Loos, A Liu, D TI Experimental and Numerical Analysis of Triaxially Braided Composites Utilizing a Modified Subcell Modeling Approach SO PROCEEDINGS OF THE AMERICAN SOCIETY FOR COMPOSITES: THIRTIETH TECHNICAL CONFERENCE LA English DT Proceedings Paper CT 30th Technical Conference of the American-Society-for-Composites CY SEP 28-30, 2015 CL East Lansing, MI SP Amer Soc Composites AB A combined experimental and analytical approach was performed for characterizing and modeling triaxially braided composites with a modified subcell modeling strategy. Tensile coupon tests were conducted on a [0 degrees/60 degrees/-60 degrees] braided composite at angles of 0 degrees, 30 degrees, 45 degrees, 60 degrees and 90 degrees relative to the axial tow of the braid. It was found that measured coupon strength varied significantly with the angle of the applied load and each coupon direction exhibited unique final failures. The subcell modeling approach implemented into the finite element software LS-DYNA was used to simulate the various tensile coupon test angles. The modeling approach was successful in predicting both the coupon strength and reported failure mode for the 0 degrees, 30 degrees and 60 degrees loading directions. The model over-predicted the strength in the 90 degrees direction; however, the experimental results show a strong influence of free edge effects on damage initiation and failure. In the absence of these local free edge effects, the subcell modeling approach showed promise as a viable and computationally efficient analysis tool for triaxially braided composite structures. Future work will focus on validation of the approach for predicting the impact response of the braided composite against flat panel impact tests. C1 [Cater, C.; Xiao, X.] Michigan State Univ, Composite Vehicle Res Ctr, Lansing, MI 48910 USA. [Goldberg, R. K.; Kolhman, L. W.] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Cater, C (reprint author), Michigan State Univ, Composite Vehicle Res Ctr, Lansing, MI 48910 USA. NR 16 TC 0 Z9 0 U1 0 U2 0 PU DESTECH PUBLICATIONS, INC PI LANCASTER PA 439 DUKE STREET, LANCASTER, PA 17602-4967 USA BN 978-1-60595-225-3 PY 2015 BP 330 EP 349 PG 20 WC Engineering, Mechanical; Materials Science, Composites SC Engineering; Materials Science GA BE7MI UT WOS:000375565100027 ER PT J AU Jackson, KE Fasanella, EL Littell, JD AF Jackson, K. E. Fasanella, E. L. Littell, J. D. BE Xiao, X Loos, A Liu, D TI Impact Testing and Simulation of a Sinusoid Foam Sandwich Energy Absorber SO PROCEEDINGS OF THE AMERICAN SOCIETY FOR COMPOSITES: THIRTIETH TECHNICAL CONFERENCE LA English DT Proceedings Paper CT 30th Technical Conference of the American-Society-for-Composites CY SEP 28-30, 2015 CL East Lansing, MI SP Amer Soc Composites ID COMPOSITE-MATERIALS; ABSORPTION AB A sinusoidal-shaped foam sandwich energy absorber was developed and evaluated at NASA Langley Research Center through multi-level testing and simulation performed under the Transport Rotorcraft Airframe Crash Testbed (TRACT) research project. The energy absorber, designated the "sinusoid," consisted of hybrid carbon-Kevlar (R) plain weave fabric face sheets, two layers for each face sheet oriented at +/- 45 degrees with respect to the vertical or crush direction, and a closed-cell ELFOAM (R) P200 polyisocyanurate (2.0-lb/ft(3)) foam core. The design goal for the energy absorber was to achieve an average floor-level acceleration of between 25- and 40-g during the full-scale crash test of a retrofitted CH-46E helicopter airframe, designated TRACT 2. Variations in the design were assessed through quasi-static and dynamic crush testing of component specimens. Once the design was finalized, a 5-ft-long subfloor beam was fabricated and retrofitted into a barrel section of a CH-46E helicopter. A vertical drop test of the barrel section was conducted onto concrete to evaluate the performance of the energy absorber prior to retrofit into TRACT 2. Finite element models were developed of all test articles and simulations were performed using LS-DYNA (R), a commercial nonlinear explicit transient dynamic finite element code. Test-analysis results are presented for the sinusoid foam sandwich energy absorber as comparisons of load-displacement and acceleration-time-history responses, as well as predicted and experimental structural deformations and progressive damage for each evaluation level (component testing through barrel section drop testing). C1 [Jackson, K. E.; Littell, J. D.] NASA, Langley Res Ctr, 14 W Bush Rd, Hampton, VA 23681 USA. [Fasanella, E. L.] Natl Inst Aerosp, Hampton, VA 23681 USA. RP Jackson, KE (reprint author), NASA, Langley Res Ctr, 14 W Bush Rd, Hampton, VA 23681 USA. NR 20 TC 0 Z9 0 U1 0 U2 0 PU DESTECH PUBLICATIONS, INC PI LANCASTER PA 439 DUKE STREET, LANCASTER, PA 17602-4967 USA BN 978-1-60595-225-3 PY 2015 BP 407 EP 425 PG 19 WC Engineering, Mechanical; Materials Science, Composites SC Engineering; Materials Science GA BE7MI UT WOS:000375565100032 ER PT J AU Cramer, KE Leckey, CAC Howell, PA Johnston, PH Burke, ER Zalameda, JN Winfree, WP Seebo, JP AF Cramer, K. E. Leckey, C. A. C. Howell, P. A. Johnston, P. H. Burke, E. R. Zalameda, J. N. Winfree, W. P. Seebo, J. P. BE Xiao, X Loos, A Liu, D TI Quantitative NDE of Composite Structures at NASA SO PROCEEDINGS OF THE AMERICAN SOCIETY FOR COMPOSITES: THIRTIETH TECHNICAL CONFERENCE LA English DT Proceedings Paper CT 30th Technical Conference of the American-Society-for-Composites CY SEP 28-30, 2015 CL East Lansing, MI SP Amer Soc Composites ID DAMAGE; THERMOGRAPHY; CORROSION AB The use of composite materials continues to increase in the aerospace community due to the potential benefits of reduced weight, increased strength, and manufacturability. Ongoing work at NASA involves the use of the large-scale composite structures for spacecraft (payload shrouds, cryotanks, crew modules, etc). NASA is also working to enable the use and certification of composites in aircraft structures through the Advanced Composites Project (ACP). The rapid, in situ characterization of a wide range of the composite materials and structures has become a critical concern for the industry. In many applications it is necessary to monitor changes in these materials over a long time. The quantitative characterization of composite defects such as fiber waviness, reduced bond strength, delamination damage, and microcracking are of particular interest. The research approaches of NASA's Nondestructive Evaluation Sciences Branch include investigation of conventional, guided wave, and phase sensitive ultrasonic methods, infrared thermography and x-ray computed tomography techniques. The use of simulation tools for optimizing and developing these methods is also an active area of research. This paper will focus on current research activities related to large area NDE for rapidly characterizing aerospace composites. C1 [Cramer, K. E.; Leckey, C. A. C.; Howell, P. A.; Johnston, P. H.; Burke, E. R.; Zalameda, J. N.; Winfree, W. P.] NASA, Nondestruct Evaluat Sci Branch, Langley Res Ctr, Hampton, VA 23681 USA. [Seebo, J. P.] NASA, Analyt Mech Associates, Langley Res Ctr, Hampton, VA 23681 USA. RP Cramer, KE (reprint author), NASA, Nondestruct Evaluat Sci Branch, Langley Res Ctr, Hampton, VA 23681 USA. NR 23 TC 0 Z9 0 U1 1 U2 1 PU DESTECH PUBLICATIONS, INC PI LANCASTER PA 439 DUKE STREET, LANCASTER, PA 17602-4967 USA BN 978-1-60595-225-3 PY 2015 BP 979 EP 988 PG 10 WC Engineering, Mechanical; Materials Science, Composites SC Engineering; Materials Science GA BE7MI UT WOS:000375565100073 ER PT J AU Aitharaju, V Aashat, S Kia, H Atyanarayana, A Bogert, P AF Aitharaju, V. Aashat, S. Kia, H. Atyanarayana, A. Bogert, P. BE Xiao, X Loos, A Liu, D TI Axial Crush and Bending Collapse Analysis of Non-Crimped Fabric Composite Structures SO PROCEEDINGS OF THE AMERICAN SOCIETY FOR COMPOSITES: THIRTIETH TECHNICAL CONFERENCE LA English DT Proceedings Paper CT 30th Technical Conference of the American-Society-for-Composites CY SEP 28-30, 2015 CL East Lansing, MI SP Amer Soc Composites ID ENERGY-ABSORPTION; FIBER COMPOSITES; COHESIVE ZONE; CRACK-GROWTH; DELAMINATION; SIMULATION; DAMAGE; TUBES; MODEL; ELEMENT AB In this paper, the investigation of the energy absorption capability of non-crimped carbon fiber composite tubes in axial compression and bending will be documented. The tubular beams were comprised of an eight layer (0/-45/45/90/90/45/-45/0) unidirectional carbon fiber architecture manufactured using a compression molding process. The experiments for axial compression and bending were conducted using drop tower and Instron three-point bend fixtures, respectively. The COmplete STress Reduction (COSTR) damage model, developed for predicting intra-layer failures, was extended to predict the response under axial crush and bending collapse through a user written subroutine developed in the framework of the LS-DYNA computer program. Inter-layer cohesion and failure were modeled using a computationally efficient cohesive zone model governed by a bi-linear traction-separation law with a quadratic mixed mode delamination criterion and damage formulation. The comparison of numerical and experimental results for the crush and bending tests are also presented and show good correlation. C1 [Aitharaju, V.; Aashat, S.; Kia, H.] Gen Motors Global Res & Dev, 30500 Mound Rd, Warren, MI 48090 USA. [Atyanarayana, A.; Bogert, P.] NASA Langley Res Ctr, Hampton, VA 23681 USA. RP Aitharaju, V (reprint author), Gen Motors Global Res & Dev, 30500 Mound Rd, Warren, MI 48090 USA. NR 40 TC 0 Z9 0 U1 0 U2 0 PU DESTECH PUBLICATIONS, INC PI LANCASTER PA 439 DUKE STREET, LANCASTER, PA 17602-4967 USA BN 978-1-60595-225-3 PY 2015 BP 1132 EP 1151 PG 20 WC Engineering, Mechanical; Materials Science, Composites SC Engineering; Materials Science GA BE7MI UT WOS:000375565100086 ER PT J AU Hadden, CM Klimek-McDonald, DR Pineda, EJ King, JA Reichanadter, AM Miskioglu, I Gowtham, S Odegard, GM AF Hadden, C. M. Klimek-McDonald, D. R. Pineda, E. J. King, J. A. Reichanadter, A. M. Miskioglu, I. Gowtham, S. Odegard, G. M. BE Xiao, X Loos, A Liu, D TI Mechanical Properties of Graphene Nanoplatelet/Carbon Fiber/Epoxy Hybrid Composites: Multiscale Modeling and Experiments SO PROCEEDINGS OF THE AMERICAN SOCIETY FOR COMPOSITES: THIRTIETH TECHNICAL CONFERENCE LA English DT Proceedings Paper CT 30th Technical Conference of the American-Society-for-Composites CY SEP 28-30, 2015 CL East Lansing, MI SP Amer Soc Composites ID NEAR-INFRARED SPECTROSCOPY; MOLECULAR-DYNAMICS SIMULATIONS; STRESS-STRAIN BEHAVIOR; EPOXY-RESIN; NANOTUBE COMPOSITES; POLYMER COMPOSITES; SHEAR-STRENGTH; NANOCOMPOSITES; NETWORKS; DENSITY AB Because of the relatively high specific mechanical properties of carbon fiber/epoxy composite materials, they are often used as structural components in aerospace applications. Graphene nanoplatelets (GNPs) can be added to the epoxy matrix to improve the overall mechanical properties of the composite. The resulting GNP/carbon fiber/epoxy hybrid composites have been studied using multiscale modeling to determine the influence of GNP volume fraction, epoxy crosslink density, and GNP dispersion on the mechanical performance. The hierarchical multiscale modeling approach developed herein includes Molecular Dynamics (MD) and micromechanical modeling, and it is validated with experimental testing of the same hybrid composite material system. The results indicate that the multiscale modeling approach is accurate and provides physical insight into the composite mechanical behavior. Also, the results quantify the substantial impact of GNP volume fraction and dispersion on the transverse mechanical properties of the hybrid composite, while the effect on the axial properties is shown to be insignificant. C1 [Hadden, C. M.; Klimek-McDonald, D. R.; Reichanadter, A. M.; Miskioglu, I.; Gowtham, S.; Odegard, G. M.] Michigan Technol Univ, 1400 Townsend Dr, Houghton, MI 49931 USA. [Pineda, E. J.] NASA Glenn Res Ctr, Cleveland, OH 44135 USA. RP Hadden, CM (reprint author), Michigan Technol Univ, 1400 Townsend Dr, Houghton, MI 49931 USA. NR 42 TC 0 Z9 0 U1 2 U2 5 PU DESTECH PUBLICATIONS, INC PI LANCASTER PA 439 DUKE STREET, LANCASTER, PA 17602-4967 USA BN 978-1-60595-225-3 PY 2015 BP 1226 EP 1241 PG 16 WC Engineering, Mechanical; Materials Science, Composites SC Engineering; Materials Science GA BE7MI UT WOS:000375565100093 ER PT J AU Radue, MS Jensen, BD Gowtham, S Odegard, GM Klimek, DR King, JA AF Radue, M. S. Jensen, B. D. Gowtham, S. Odegard, G. M. Klimek, D. R. King, J. A. BE Xiao, X Loos, A Liu, D TI Applying Reactive Molecular Dynamics to Predict and Compare the Mechanical Response of Di-, Tri-, and Tetra-functional Resin Epoxies SO PROCEEDINGS OF THE AMERICAN SOCIETY FOR COMPOSITES: THIRTIETH TECHNICAL CONFERENCE LA English DT Proceedings Paper CT 30th Technical Conference of the American-Society-for-Composites CY SEP 28-30, 2015 CL East Lansing, MI SP Amer Soc Composites ID CROSS-LINKED EPOXY; POLYMER NETWORKS; THERMOMECHANICAL PROPERTIES; FORCE-FIELD; STRAIN; DEFORMATION; SIMULATIONS; BEHAVIOR; DENSITY; REAXFF AB The influence of monomer functionality on the mechanical properties of epoxies is studied using Molecular Dynamics (MD) with the Reax Force Field (ReaxFF). From straining simulations, the Young's modulus, yield point, and Poisson's ratio are calculated and analyzed. The results demonstrate an increase in stiffness and yield strength with increasing resin functionality. Experimental comparisons show reasonable agreement, and therefore, this technique is confirmed to be a useful tool for understanding the structure-property relationships of epoxies. C1 [Radue, M. S.; Gowtham, S.; Odegard, G. M.; Klimek, D. R.; King, J. A.] Michigan Technol Univ, 1400 Townsend Dr, Houghton, MI 49931 USA. [Jensen, B. D.] NASA Langley Res Ctr, Hampton, VA 23681 USA. RP Radue, MS (reprint author), Michigan Technol Univ, 1400 Townsend Dr, Houghton, MI 49931 USA. NR 24 TC 0 Z9 0 U1 1 U2 1 PU DESTECH PUBLICATIONS, INC PI LANCASTER PA 439 DUKE STREET, LANCASTER, PA 17602-4967 USA BN 978-1-60595-225-3 PY 2015 BP 1252 EP 1262 PG 11 WC Engineering, Mechanical; Materials Science, Composites SC Engineering; Materials Science GA BE7MI UT WOS:000375565100095 ER PT J AU Kim, JW Sauti, G Cano, RJ Wincheski, RA Ratcliffe, JG Czabaj, M Siochi, EJ AF Kim, J. -W. Sauti, G. Cano, R. J. Wincheski, R. A. Ratcliffe, J. G. Czabaj, M. Siochi, E. J. BE Xiao, X Loos, A Liu, D TI Structural CNT Composites Part II: Assessment of CNT Yarns as Reinforcement for Composite Overwrapped Pressure Vessels SO PROCEEDINGS OF THE AMERICAN SOCIETY FOR COMPOSITES: THIRTIETH TECHNICAL CONFERENCE LA English DT Proceedings Paper CT 30th Technical Conference of the American-Society-for-Composites CY SEP 28-30, 2015 CL East Lansing, MI SP Amer Soc Composites ID NANOTUBE SHEET NANOCOMPOSITES AB Carbon nanotubes (CNTs) are one-dimensional nanomaterials with outstanding electrical and thermal conductivities and mechanical properties. This combination of properties offers routes to enable lightweight structural aerospace components. Recent advances in the manufacturing of CNTs have made bulk forms such as yarns, tapes and sheets available in commercial quantities to permit the evaluation of these materials for aerospace use, where the superior tensile properties of CNT composites can be exploited in tension dominated applications such as composite overwrapped pressure vessels (COPVs). To investigate their utility in this application, aluminum rings were overwrapped with thermoset/CNT yarn composite and their mechanical properties measured. CNT composite overwrap characteristics such as processing method, CNT/resin ratio, and applied tension during CNT yarn winding were varied to determine their effects on the mechanical performance of the CNT composite overwrapped Al rings (CCOARs). Mechanical properties of the CCOARs were measured under static and cyclic loads at room, elevated, and cryogenic temperatures to evaluate their mechanical performance relative to bare Al rings. At room temperature, the breaking load of CCOARs with a 10.8% additional weight due to the CNT yarn/thermoset overwrap increased by over 200% compared to the bare Al ring. The quality of the wound CNT composites was also investigated using x-ray computed tomography. C1 [Kim, J. -W.; Sauti, G.] Natl Inst Aerosp, 100 Explorat Way, Hampton, VA 23666 USA. [Cano, R. J.; Siochi, E. J.] NASA Langley Res Ctr, Adv Mat & Proc Branch, Hampton, VA 23681 USA. [Wincheski, R. A.] NASA Langley Res Ctr, Nondestruct Evaluat Sci Branch, Hampton, VA 23681 USA. [Ratcliffe, J. G.; Czabaj, M.] NASA Langley Res Ctr, Durabil Damage Tolerance & Reliabil Branch, Hampton, VA 23681 USA. RP Kim, JW (reprint author), Natl Inst Aerosp, 100 Explorat Way, Hampton, VA 23666 USA. RI Kim, Jae-Woo/A-8314-2008 NR 8 TC 0 Z9 0 U1 0 U2 0 PU DESTECH PUBLICATIONS, INC PI LANCASTER PA 439 DUKE STREET, LANCASTER, PA 17602-4967 USA BN 978-1-60595-225-3 PY 2015 BP 1539 EP 1548 PG 10 WC Engineering, Mechanical; Materials Science, Composites SC Engineering; Materials Science GA BE7MI UT WOS:000375565100117 ER PT J AU Ricks, TM Lacy, TE Pineda, EJ Bednarcyk, BA Arnold, SM AF Ricks, T. M. Lacy, T. E., Jr. Pineda, E. J. Bednarcyk, B. A. Arnold, S. M. BE Xiao, X Loos, A Liu, D TI Computationally Efficient Solution of the High-Fidelity Generalized Method of Cells Micromechanics Relations SO PROCEEDINGS OF THE AMERICAN SOCIETY FOR COMPOSITES: THIRTIETH TECHNICAL CONFERENCE LA English DT Proceedings Paper CT 30th Technical Conference of the American-Society-for-Composites CY SEP 28-30, 2015 CL East Lansing, MI SP Amer Soc Composites ID PROPER ORTHOGONAL DECOMPOSITION; MODEL-REDUCTION; HOMOGENIZATION; DYNAMICS AB The High-Fidelity Generalized Method of Cells (HFGMC) is a powerful technique for simulating composite materials and is based on Aboudi's method of cells micromechanics theories. Unlike the original generalized method of cells, the HFGMC uses a higher order approximation for the subcell displacement field. Although this allows for a more accurate determination of the subcell stress/strain fields, the solution to the simultaneous set of equations can become computationally burdensome. In order to overcome expensive computational costs associated with solving large systems of equations, order-reduction techniques have been developed to approximate the solution with an acceptable error. These techniques are widely used in the computational fluid dynamics community and are increasingly being implemented for solving solid mechanics problems involving the finite element method. In this study, the HFGMC global system of equations for doubly-periodic RUCs was reduced in size through the use of Proper Orthogonal Decomposition (POD) with Galerkin projection. Order-reduced models were then implemented within an ABAQUS UMAT and used to perform multiscale analyses. A number of cases were presented that show the computational feasibility of using order-reduction techniques to solve the HFGMC set of simultaneous equations. By simulating composite materials in a more computationally efficient manner, a pathway forward is presented for performing multiscale analyses of composite structures consistent with the Airframe Digital Twin concept. C1 [Ricks, T. M.] Mississippi State Univ, Dept Aerosp Engn, POB A, Mississippi State, MS 39762 USA. [Lacy, T. E., Jr.] Mississippi State Univ, Dept Aerosp Engn, Mississippi State, MS 39762 USA. [Bednarcyk, B. A.] NASA Glenn Res Ctr, Mech & Life Predict Branch, Cleveland, OH 44135 USA. [Pineda, E. J.] NASA Glenn Res Ctr, Mech & Life Predict Branch, Cleveland, OH 44135 USA. [Arnold, S. M.] NASA Glenn Res Ctr, Mat & Struct Div, Multiscale Multiphys Modeling, Cleveland, OH 44135 USA. RP Ricks, TM (reprint author), Mississippi State Univ, Dept Aerosp Engn, POB A, Mississippi State, MS 39762 USA. NR 16 TC 0 Z9 0 U1 0 U2 1 PU DESTECH PUBLICATIONS, INC PI LANCASTER PA 439 DUKE STREET, LANCASTER, PA 17602-4967 USA BN 978-1-60595-225-3 PY 2015 BP 1561 EP 1572 PG 12 WC Engineering, Mechanical; Materials Science, Composites SC Engineering; Materials Science GA BE7MI UT WOS:000375565100119 ER PT J AU Pineda, EJ Myers, DE Bednarcyk, BA Krivanek, TM AF Pineda, E. J. Myers, D. E. Bednarcyk, B. A. Krivanek, T. M. BE Xiao, X Loos, A Liu, D TI A Numerical Study on the Effect of Facesheet-Core Disbonds on the Buckling Load of Curved Honeycomb Sandwich Panels SO PROCEEDINGS OF THE AMERICAN SOCIETY FOR COMPOSITES: THIRTIETH TECHNICAL CONFERENCE LA English DT Proceedings Paper CT 30th Technical Conference of the American-Society-for-Composites CY SEP 28-30, 2015 CL East Lansing, MI SP Amer Soc Composites AB A numerical study on the effect of facesheet-core disbonds on the post-buckling response of curved honeycomb sandwich panels is presented herein. This work was conducted as part of the development of a damage tolerance approach for the next-generation Space Launch System heavy lift vehicle payload fairing. As such, the study utilized full-scale fairing barrel segments as the structure of interest. The panels were composed of carbon fiber reinforced polymer facesheets and aluminum honeycomb core. The panels were analyzed numerically using the finite element method. Facesheet and core nodes in a predetermined circular region were detached to simulate a disbond induced via low-speed impact between the outer mold line facesheet and honeycomb core. Surface-to-surface contact in the disbonded region was invoked to prevent interpenetration of the facesheet and core elements. The diameter of this disbonded region was varied and the effect of the size of the disbond on the post-buckling response was observed. A significant change in the slope of the edge load-deflection response was used to determine the onset of global buckling and corresponding buckling load. C1 [Pineda, E. J.; Myers, D. E.; Bednarcyk, B. A.; Krivanek, T. M.] NASA Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. RP Pineda, EJ (reprint author), NASA Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. NR 31 TC 0 Z9 0 U1 2 U2 2 PU DESTECH PUBLICATIONS, INC PI LANCASTER PA 439 DUKE STREET, LANCASTER, PA 17602-4967 USA BN 978-1-60595-225-3 PY 2015 BP 1637 EP 1656 PG 20 WC Engineering, Mechanical; Materials Science, Composites SC Engineering; Materials Science GA BE7MI UT WOS:000375565100125 ER PT J AU Wang, JT Pineda, EJ Ranatunga, V Smeltzer, SS AF Wang, J. T. Pineda, E. J. Ranatunga, V. Smeltzer, S. S. BE Xiao, X Loos, A Liu, D TI 3D Progressive Damage Modeling for Laminated Composite Based on Crack Band Theory and Continuum Damage Mechanics SO PROCEEDINGS OF THE AMERICAN SOCIETY FOR COMPOSITES: THIRTIETH TECHNICAL CONFERENCE LA English DT Proceedings Paper CT 30th Technical Conference of the American-Society-for-Composites CY SEP 28-30, 2015 CL East Lansing, MI SP Amer Soc Composites ID FIBER-REINFORCED MATERIALS; FAILURE CRITERIA AB A simple continuum damage mechanics (CDM) based 3D progressive damage analysis (PDA) tool for laminated composites was developed and implemented as a user defined material subroutine to link with a commercially available explicit finite element code. This PDA tool uses linear lamina properties from standard tests, predicts damage initiation with an easy-to-implement Hashin-Rotem failure criteria, and in the damage evolution phase, evaluates the degradation of material properties based on the crack band theory and traction-separation cohesive laws. It follows Matzenmiller et al.'s formulation to incorporate the degrading material properties into the damaged stiffness matrix. Since nonlinear shear and matrix stress-strain relations are not implemented, correction factors are used for slowing the reduction of the damaged shear stiffness terms to reflect the effect of these nonlinearities on the laminate strength predictions. This CDM based PDA tool is implemented as a user defined material (VUMAT) to link with the Abaqus/Explicit code. Strength predictions obtained, using this VUMAT, are correlated with test data for a set of notched specimens under tension and compression loads. C1 [Wang, J. T.; Smeltzer, S. S.] NASA Langley Res Ctr, Hampton, VA 23681 USA. [Pineda, E. J.] NASA Glenn Res Ctr, Cleveland, OH 44135 USA. [Ranatunga, V.] Air Force Res Lab, Wright Patterson AFB, OH 45433 USA. RP Wang, JT (reprint author), NASA Langley Res Ctr, Hampton, VA 23681 USA. NR 35 TC 0 Z9 0 U1 0 U2 0 PU DESTECH PUBLICATIONS, INC PI LANCASTER PA 439 DUKE STREET, LANCASTER, PA 17602-4967 USA BN 978-1-60595-225-3 PY 2015 BP 1750 EP 1766 PG 17 WC Engineering, Mechanical; Materials Science, Composites SC Engineering; Materials Science GA BE7MI UT WOS:000375565100134 ER PT J AU Sauti, G Kim, JW Wincheski, RA Antczak, A Campero, JC Luong, HH Shanahan, MH Stelter, CJ Siochi, EJ AF Sauti, G. Kim, J. -W. Wincheski, R. A. Antczak, A. Campero, J. C. Luong, H. H. Shanahan, M. H. Stelter, C. J. Siochi, E. J. BE Xiao, X Loos, A Liu, D TI Structural CNT Composites Part I: Developing a Carbon Nanotube Filament Winder SO PROCEEDINGS OF THE AMERICAN SOCIETY FOR COMPOSITES: THIRTIETH TECHNICAL CONFERENCE LA English DT Proceedings Paper CT 30th Technical Conference of the American-Society-for-Composites CY SEP 28-30, 2015 CL East Lansing, MI SP Amer Soc Composites AB Carbon nanotube (CNT) based materials promise advances in the production of high strength and multifunctional components for aerospace and other applications. Specifically, in tension dominated applications, the latest CNT based filaments are yielding composite properties comparable to or exceeding composites from more established fibers such as Kevlar and carbon fiber. However, for the properties of these materials to be fully realized at the component level, suitable manufacturing processes have to be developed. These materials handle differently from conventional fibers, with different wetting characteristics and behavior under load. The limited availability of bulk forms also requires that the equipment be scaled down accordingly to tailor the process development approach to material availability. Here, the development of hardware and software for filament winding of carbon nanotube based tapes and yarns is described. This hardware features precision guidance of the CNT material and control of the winding tension over a wide range in an open architecture that allows for effective process control and troubleshooting during winding. Use of the filament winder to develop CNT based Composite Overwrapped Pressure Vessels (COPVs) shall also be discussed. C1 [Sauti, G.; Kim, J. -W.; Shanahan, M. H.] Natl Inst Aerosp, Hampton, VA 23666 USA. [Wincheski, R. A.; Luong, H. H.; Stelter, C. J.; Siochi, E. J.] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Antczak, A.] Univ N Carolina, Charlotte, NC 28223 USA. [Campero, J. C.] Univ Texas El Paso, El Paso, TX 79968 USA. RP Sauti, G (reprint author), Natl Inst Aerosp, Hampton, VA 23666 USA. RI Kim, Jae-Woo/A-8314-2008 NR 8 TC 0 Z9 0 U1 0 U2 0 PU DESTECH PUBLICATIONS, INC PI LANCASTER PA 439 DUKE STREET, LANCASTER, PA 17602-4967 USA BN 978-1-60595-225-3 PY 2015 BP 2154 EP 2162 PG 9 WC Engineering, Mechanical; Materials Science, Composites SC Engineering; Materials Science GA BE7MI UT WOS:000375565100167 ER PT J AU Jensen, BD Wise, KE Odegard, GM AF Jensen, B. D. Wise, K. E. Odegard, G. M. BE Xiao, X Loos, A Liu, D TI Fracture of Carbon Nanotube - Amorphous Carbon Composites: Molecular Modeling SO PROCEEDINGS OF THE AMERICAN SOCIETY FOR COMPOSITES: THIRTIETH TECHNICAL CONFERENCE LA English DT Proceedings Paper CT 30th Technical Conference of the American-Society-for-Composites CY SEP 28-30, 2015 CL East Lansing, MI SP Amer Soc Composites ID FILMS; BUNDLES; REAXFF AB Carbon nanotubes (CNTs) are promising candidates for use as reinforcements in next generation structural composite materials because of their extremely high specific stiffness and strength. They cannot, however, be viewed as simple replacements for carbon fibers because there are key differences between these materials in areas such as handling, processing, and matrix design. It is impossible to know for certain that CNT composites will represent a significant advance over carbon fiber composites before these various factors have been optimized, which is an extremely costly and time intensive process. This work attempts to place an upper bound on CNT composite mechanical properties by performing molecular dynamics simulations on idealized model systems with a reactive forcefield that permits modeling of both elastic deformations and fracture. Amorphous carbon (AC) was chosen for the matrix material in this work because of its structural simplicity and physical compatibility with the CNT fillers. It is also much stiffer and stronger than typical engineering polymer matrices. Three different arrangements of CNTs in the simulation cell have been investigated: a single-wall nanotube (SWNT) array, a multi-wall nanotube (MWNT) array, and a SWNT bundle system. The SWNT and MWNT array systems are clearly idealizations, but the SWNT bundle system is a step closer to real systems in which individual tubes aggregate into large assemblies. The effect of chemical crosslinking on composite properties is modeled by adding bonds between the CNTs and AC. The balance between weakening the CNTs and improving fiber-matrix load transfer is explored by systematically varying the extent of crosslinking. It is, of course, impossible to capture the full range of deformation and fracture processes that occur in real materials with even the largest atomistic molecular dynamics simulations. With this limitation in mind, the simulation results reported here provide a plausible upper limit on achievable CNT composite properties and yield some insight on the influence of processing conditions on the mechanical properties of CNT composites. C1 [Jensen, B. D.; Wise, K. E.] NASA, Langley Res Ctr, Adv Mat & Proc Branch, Mail Stop 226, Hampton, VA 23681 USA. [Jensen, B. D.; Odegard, G. M.] Michigan Technol Univ, Dept Mech Engn Engn Mech, Houghton, MI 49931 USA. RP Jensen, BD (reprint author), NASA, Langley Res Ctr, Adv Mat & Proc Branch, Mail Stop 226, Hampton, VA 23681 USA. NR 16 TC 0 Z9 0 U1 1 U2 1 PU DESTECH PUBLICATIONS, INC PI LANCASTER PA 439 DUKE STREET, LANCASTER, PA 17602-4967 USA BN 978-1-60595-225-3 PY 2015 BP 2248 EP 2263 PG 16 WC Engineering, Mechanical; Materials Science, Composites SC Engineering; Materials Science GA BE7MI UT WOS:000375565100173 ER PT J AU Zhao, S Sonta, K Perey, DF Cramer, KE Berger, L AF Zhao, S. Sonta, K. Perey, D. F. Cramer, K. E. Berger, L. BE Xiao, X Loos, A Liu, D TI Non-destructive Evaluation of Bonds between Fiberglass Composites and Metals SO PROCEEDINGS OF THE AMERICAN SOCIETY FOR COMPOSITES: THIRTIETH TECHNICAL CONFERENCE LA English DT Proceedings Paper CT 30th Technical Conference of the American-Society-for-Composites CY SEP 28-30, 2015 CL East Lansing, MI SP Amer Soc Composites AB This study aims to develop a reliable and portable NDE system for service-level adhesive inspection in the automotive industry. To assess the integrity and reliability of an adhesive joint in an automotive composite component, several non-destructive evaluation (NDE) methodologies are correlated to lap shear bond strengths. A glass-fabric-reinforced composite structure was bonded to a metallic structure with a two-part epoxy adhesive. Samples were subsequently cut and tested in shear, and flaws were observed in some areas after lap shear test. Fiberglass-to-metal bonding is the ideal configuration for NDE via thermography using excitation with induction heating, due to the conductive metal and non-conductive glass-fiber-reinforced composites. Excitation can be either by a research-grade induction heater of highly defined frequency and intensity, or by a service-level heater, such as those used for sealing windshields in a body shop. The thermographs thus produced can be captured via a high-resolution infrared camera, with principal component analysis and 2D spatial Laplacian processing. Alternatively, the thermographs can be captured by low resolution thermochromic microencapsulated liquid crystal film imaging, which needs no post-processing and can be very inexpensive. These samples were also examined with phased-array ultrasound. The NDE methods were compared to the lap shear values and to each other for approximate cost, accuracy, and time and level of expertise needed. C1 [Zhao, S.; Berger, L.] Gen Motors R&D Ctr, 30500 Mound Rd, Warren, MI 48092 USA. [Sonta, K.] Gen Motors Engn, Warren, MI 48093 USA. [Perey, D. F.; Cramer, K. E.] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Zhao, S (reprint author), Gen Motors R&D Ctr, 30500 Mound Rd, Warren, MI 48092 USA. NR 13 TC 0 Z9 0 U1 2 U2 2 PU DESTECH PUBLICATIONS, INC PI LANCASTER PA 439 DUKE STREET, LANCASTER, PA 17602-4967 USA BN 978-1-60595-225-3 PY 2015 BP 2427 EP 2437 PG 11 WC Engineering, Mechanical; Materials Science, Composites SC Engineering; Materials Science GA BE7MI UT WOS:000375565100186 ER PT J AU Przekop, A Jegley, DC Rouse, M Lovejoy, AE Wu, HYT AF Przekop, A. Jegley, D. C. Rouse, M. Lovejoy, A. E. Wu, H. -Y. T. BE Xiao, X Loos, A Liu, D TI Nonlinear Analysis and Preliminary Testing Results of a Hybrid Wing Body Center Section Test Article SO PROCEEDINGS OF THE AMERICAN SOCIETY FOR COMPOSITES: THIRTIETH TECHNICAL CONFERENCE LA English DT Proceedings Paper CT 30th Technical Conference of the American-Society-for-Composites CY SEP 28-30, 2015 CL East Lansing, MI SP Amer Soc Composites AB A large test article was recently designed, analyzed, fabricated, and successfully tested up to the representative design ultimate loads to demonstrate that stiffened composite panels with through-the-thickness reinforcement are a viable option for the next generation large transport category aircraft, including non-conventional configurations such as the hybrid wing body. This paper focuses on finite element analysis and test data correlation of the hybrid wing body center section test article under mechanical, pressure and combined load conditions. Good agreement between predictive nonlinear finite element analysis and test data is found. Results indicate that a geometrically nonlinear analysis is needed to accurately capture the behavior of the non-circular pressurized and highly-stressed structure when the design approach permits local buckling. C1 [Przekop, A.; Jegley, D. C.; Rouse, M.; Lovejoy, A. E.] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Wu, H. -Y. T.] Boeing Res & Technol, Huntington Beach, CA 92647 USA. RP Przekop, A (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. NR 22 TC 0 Z9 0 U1 0 U2 0 PU DESTECH PUBLICATIONS, INC PI LANCASTER PA 439 DUKE STREET, LANCASTER, PA 17602-4967 USA BN 978-1-60595-225-3 PY 2015 BP 2528 EP 2547 PG 20 WC Engineering, Mechanical; Materials Science, Composites SC Engineering; Materials Science GA BE7MI UT WOS:000375565100195 ER PT J AU Jegley, D Przekop, A Rouse, M Lovejoy, A Velicki, A Linton, K Wu, HY Baraja, J Thrash, P Hoffman, K AF Jegley, D. Przekop, A. Rouse, M. Lovejoy, A. Velicki, A. Linton, K. Wu, H. -Y. Baraja, J. Thrash, P. Hoffman, K. BE Xiao, X Loos, A Liu, D TI Development of Stitched Composite Structure for Advanced Aircraft SO PROCEEDINGS OF THE AMERICAN SOCIETY FOR COMPOSITES: THIRTIETH TECHNICAL CONFERENCE LA English DT Proceedings Paper CT 30th Technical Conference of the American-Society-for-Composites CY SEP 28-30, 2015 CL East Lansing, MI SP Amer Soc Composites AB NASA has created the Environmentally Responsible Aviation Project to develop technologies which will reduce the impact of aviation on the environment. A critical aspect of this pursuit is the development of a lighter, more robust airframe that will enable the introduction of unconventional aircraft configurations. NASA and The Boeing Company are working together to develop a structural concept that is lightweight and an advancement beyond state-of-the-art composites. The Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) is an integrally stiffened panel design where elements are stitched together and designed to maintain residual load-carrying capabilities under a variety of damage scenarios. With the PRSEUS concept, through-the-thickness stitches are applied through dry fabric prior to resin infusion, and replace fasteners throughout each integral panel. Through-the-thickness reinforcement at discontinuities, such as along flange edges, has been shown to suppress delamination and turn cracks, which expands the design space and leads to lighter designs. The pultruded rod provides stiffening away from the more vulnerable skin surface and improves bending stiffness. A series of building blocks were evaluated to explore the fundamental assumptions related to the capability and advantages of PRSEUS panels. These building blocks addressed tension, compression, and pressure loading conditions. The emphasis of the development work has been to assess the loading capability, damage arrestment features, repairability, post-buckling behavior, and response of PRSEUS flat panels to out-of-plane pressure loading. The results of this building-block program from coupons through an 80%-scale pressure box have demonstrated the viability of a PRSEUS center body for the Hybrid Wing Body (HWB) transport aircraft. This development program shows that the PRSEUS benefits are also applicable to traditional tube-and-wing aircraft, those of advanced configurations, and other structures where weight and through-the-thickness strength are design considerations. An overview of the development of PRSEUS technology for commercial transport aircraft is the subject of this paper. C1 [Jegley, D.; Przekop, A.; Rouse, M.; Lovejoy, A.] NASA, Langley Res Ctr, Mail Stop 190, Hampton, VA 23681 USA. [Velicki, A.; Linton, K.; Wu, H. -Y.; Baraja, J.; Thrash, P.; Hoffman, K.] Boeing Res & Technol, Huntington Beach, CA 92647 USA. RP Jegley, D (reprint author), NASA, Langley Res Ctr, Mail Stop 190, Hampton, VA 23681 USA. NR 26 TC 0 Z9 0 U1 3 U2 3 PU DESTECH PUBLICATIONS, INC PI LANCASTER PA 439 DUKE STREET, LANCASTER, PA 17602-4967 USA BN 978-1-60595-225-3 PY 2015 BP 2548 EP 2566 PG 19 WC Engineering, Mechanical; Materials Science, Composites SC Engineering; Materials Science GA BE7MI UT WOS:000375565100196 ER PT J AU Nordendale, N Goyal, V Lundgren, E Patel, D Farrokh, B Jones, J Fischetti, G Segal, K AF Nordendale, N. Goyal, V. Lundgren, E. Patel, D. Farrokh, B. Jones, J. Fischetti, G. Segal, K. BE Xiao, X Loos, A Liu, D TI Failure Predictions of Out-of-Autoclave Sandwich Joints with Delaminations under Flexure Loads SO PROCEEDINGS OF THE AMERICAN SOCIETY FOR COMPOSITES: THIRTIETH TECHNICAL CONFERENCE LA English DT Proceedings Paper CT 30th Technical Conference of the American-Society-for-Composites CY SEP 28-30, 2015 CL East Lansing, MI SP Amer Soc Composites AB An analysis and a test program was conducted to investigate the damage tolerance of composite sandwich joints. The joints contained a single circular delamination between the face-sheet and the doubler. The coupons were fabricated through out-of-autoclave (OOA) processes, a technology NASA is investigating for joining large composite sections. The four-point bend flexure test was used to induce compression loading into the side of the joint where the delamination was placed. The compression side was chosen since it tends to be one of the most critical loads in launch vehicles. Autoclave cure was used to manufacture the composite sandwich sections, while the doubler was co-bonded onto the sandwich face-sheet using an OOA process after sandwich panels were cured. A building block approach was adopted to characterize the mechanical properties of the joint material, including the fracture toughness between the doubler and facesheet. Twelve four-point-bend samples were tested, six in the sandwich core ribbon orientation and six in sandwich core cross-ribbon direction. Analysis predicted failure initiation and propagation at the pre-delaminated location, consistent with experimental observations. Fracture analyses methods predicted failure loads in close agreement with tests. This investigation demonstrated a strength reduction of 10 percent due to a flaw of significant size compared to the width of the sample. Therefore, concerns of bonding an OOA material to an in-autoclave material was mitigated for the geometries, materials, and load configurations considered. C1 [Nordendale, N.; Goyal, V.; Lundgren, E.; Patel, D.] Aerosp Corp, El Segundo, CA 90245 USA. [Farrokh, B.; Jones, J.; Fischetti, G.; Segal, K.] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. RP Nordendale, N (reprint author), Aerosp Corp, El Segundo, CA 90245 USA. EM Nikolas.norderdale@aero.org NR 5 TC 0 Z9 0 U1 0 U2 0 PU DESTECH PUBLICATIONS, INC PI LANCASTER PA 439 DUKE STREET, LANCASTER, PA 17602-4967 USA BN 978-1-60595-225-3 PY 2015 BP 2656 EP 2675 PG 20 WC Engineering, Mechanical; Materials Science, Composites SC Engineering; Materials Science GA BE7MI UT WOS:000375565100204 ER PT B AU Hossain, MA Hossain, S AF Hossain, Mohammad A. Hossain, Sarzina GP ASME TI Numerical Investigation of Porous Medium Heat Transfer SO PROCEEDINGS OF THE ASME INTERNATIONAL MECHANICAL ENGINEERING CONGRESS AND EXPOSITION, 2014, VOL 8A LA English DT Proceedings Paper CT ASME International Mechanical Engineering Congress and Exposition (IMECE2014) CY NOV 14-20, 2014 CL Montreal, CANADA SP ASME AB This work deals with numerical investigation of porous medium heat transfer for square tube cross flow heat exchanger. The simulation is done for 2D turbulent flow. In order to resolve the flow field, Reynolds Average Navier-stokes (RANS) model is used. Standard k-epsilon model is considered among different RANS model in order to resolve the mean velocity field, pressure drop and temperature distribution. Both average velocity, temperature distribution and pressure drop are calculated for three different cases having three different porosity (phi), permeability (K) and inertial coefficient (beta). The results of three different cases are compared and presented. First the mesh independence test is done by different mesh size. ANSYS Fluent is used for the simulation. A pressured based solver is used with SIMPLE solution scheme, in order to find different flow variables. Finally the Nusselt number (Nu) and surface heat transfer coefficient (h) are determined and presented. C1 [Hossain, Mohammad A.; Hossain, Sarzina] Univ Texas El Paso, NASA, Ctr Space Explorat & Technol Res, Dept Mech Engn, El Paso, TX 79968 USA. RP Hossain, MA (reprint author), Univ Texas El Paso, NASA, Ctr Space Explorat & Technol Res, Dept Mech Engn, El Paso, TX 79968 USA. NR 18 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-4955-2 PY 2015 AR UNSP V08AT10A055 PG 8 WC Thermodynamics; Engineering, Mechanical SC Thermodynamics; Engineering GA BE7JJ UT WOS:000375369300055 ER PT B AU Patel, VK Robinson, F Seyed-Yagoobi, J Didion, J AF Patel, Viral K. Robinson, Franklin Seyed-Yagoobi, Jamal Didion, Jeffrey GP ASME TI LIQUID FILM BOILING HEAT TRANSFER IN THE PRESENCE AND ABSENCE OF GRAVITY SO PROCEEDINGS OF THE ASME INTERNATIONAL MECHANICAL ENGINEERING CONGRESS AND EXPOSITION, 2014, VOL 8B LA English DT Proceedings Paper CT ASME International Mechanical Engineering Congress and Exposition (IMECE2014) CY NOV 14-20, 2014 CL Montreal, CANADA SP ASME AB Liquid film boiling is an effective method of heat removal from a flat surface and has many terrestrial applications. It is an attractive technique for microgravity thermal control but cannot be sustained in the absence of gravity, according to theoretical prediction. However, this has not been experimentally confirmed to date for various reasons such as difficulty of performing experiments in microgravity and the associated cost. This paper presents new terrestrial and microgravity experimental results of liquid film boiling in a radial heat transport device. The microgravity experiments were perfoinied on board a variable gravity parabolic flight. The data were expected to show that absence of gravity results in very high heater surface temperatures and eventual dryout compared to results in the presence of gravity at a given heat flux. However, this only occurred during the transition phase from 1.8-g to 0-g in the parabolic maneuver and the heater temperatures remained normal during the 0-g phase. Despite this, the results still add valuable information, to the overall understanding of the liquid-vapor phase-change process in the absence of gravity. They have also laid the foundation for further experimental work such as using electrohydrodynamic (EFID) conduction pumping to facilitate liquid film boiling in microgravity, which we have presented in another study. C1 [Patel, Viral K.; Seyed-Yagoobi, Jamal] Worcester Polytech Inst, Dept Mech Engn, 100 Inst Rd, Worcester, MA 01609 USA. [Robinson, Franklin; Didion, Jeffrey] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Patel, VK (reprint author), Worcester Polytech Inst, Dept Mech Engn, 100 Inst Rd, Worcester, MA 01609 USA. EM vkpatel@wpi.edu; franklin.l.robinson@nasa.gov; jyagoobi@wpi.edu; jeffrey.r.didion@nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-4956-9 PY 2015 AR UNSP V08BT10A074 PG 7 WC Thermodynamics; Engineering, Mechanical SC Thermodynamics; Engineering GA BE7JK UT WOS:000375370500074 ER PT B AU Saad, MT Miller, SG Marunda, T AF Saad, Messiha T. Miller, Sandi G. Marunda, Torrence GP ASME TI THERMAL CHARACTERIZATION OF IM7/8552-1 CARBON-EPOXY COMPOSITES SO PROCEEDINGS OF THE ASME INTERNATIONAL MECHANICAL ENGINEERING CONGRESS AND EXPOSITION, 2014, VOL 8B LA English DT Proceedings Paper CT ASME International Mechanical Engineering Congress and Exposition (IMECE2014) CY NOV 14-20, 2014 CL Montreal, CANADA SP ASME AB Thermal properties of composite materials such as, thermal conductivity, diffusivity, and specific heat are very important in engineering design process and analysis of aerospace vehicles as well as space systems. These properties are also important in power generation, transportation, and energy storage devices including fuel cells. Thermal conductivity is the property that determines the working temperature levels of the material; it plays a critical role in the performance of materials in high temperature applications, and it is an important parameter in problems involving heat transfer and thermal structures. The objective of this paper is to develop a thermal properties data base for. the carbon fiber-epoxy (IM7/8552-1) composite. The IM7 carbon fiber is a continuous, high performance, intermediate modulus, PAN based fiber. This fiber has been surface treated and can be sized to improve its interlaminar shear properties, handling characteristics, and structural properties. The 8552 is a high performance tough epoxy matrix for use in primary aerospace structures. It exhibits good impact resistance and damage tolerance for a wide range of applications. The IM7/8552-1 is an amine cured unidirectional prepreg. The manufacturer recommended cure cycle for this material was followed, which includes consolidation under vacuum and autoclave pressure. The composite has a service temperature up to 121 degrees C (250 degrees F). The thermal properties of IM7/8552-1 carbon-epoxy have been investigated using experimental methods. The flash method was used to measure the thermal diffusivity of the composite. This method is based on the American Society for Testing and Materials standard, ASTM E1461. In addition, the Differential Scanning Calorimeter was used in accordance with the ASTM E1269 standard to measure the specific heat. The measured thermal diffusivity, specific heat, and density data were used to compute the thermal conductivity of the IM7/8552-1 carbon epoxy composite. C1 [Saad, Messiha T.] Washington State Univ Tricities, Richland, WA USA. [Miller, Sandi G.] NASA Glenn Res Ctr, Cleveland, OH USA. [Marunda, Torrence] North Carolina A&T State Univ, Greensboro, NC USA. RP Saad, MT (reprint author), Washington State Univ Tricities, Richland, WA USA. EM messiha.saad@tricity.wsu.edu NR 14 TC 0 Z9 0 U1 2 U2 2 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-4956-9 PY 2015 AR UNSP V08BT10A091 PG 8 WC Thermodynamics; Engineering, Mechanical SC Thermodynamics; Engineering GA BE7JK UT WOS:000375370500091 ER PT S AU McGraw, M Kolla, P Cook, R Wu, J Lvovich, V Smirnova, A AF McGraw, Michael Kolla, Praveen Cook, Rob Wu, James Lvovich, Vadim Smirnova, Alevtina BE Tatina, R TI COMPARATIVE STUDY OF THERMALLY TREATED SILICON ANODE NANOSTRUCTURES BASED ON POLYACRYLIC ACID AND POLYANILINE FOR LITHIUM ION BATTERY APPLICATION SO PROCEEDINGS OF THE SOUTH DAKOTA ACADEMY OF SCIENCE, VOL 94 SE Proceedings of the South Dakota Academy of Science LA English DT Proceedings Paper CT 100th Annual Meeting of the South Dakota Academy of Science CY APR 10-11, 2015 CL Oacoma, SD SP S Dakota Acad Sci ID ELECTRICAL-CONDUCTIVITY; ELECTRODES; CAPACITY; BINDERS AB A comparative study between a nonconductive thermoplastic, polyacrylic acid (PAA), and an electronic-conducting polymer, polyaniline (PANI), has been conducted related to their function as binders for Silicon Nanoparticle (SiNP)-based anodes in Li-ion battery application. SEM analysis was used to understand the morphological differences associated with dispersion of PAA/PANI with SiNPs. Further, thermogravimetric analysis was conducted in order to understand the thermal degradation and to choose their associated heat-treatment temperatures of 400 degrees C (PAA) and 300 degrees C (PANI). The electrochemical performance of the resultant silicon-based electrodes assembled in Lithium-half-cell configuration was evaluated in terms of their specific capacitance and cycle-stability. The results indicated that PANI-based SiNP anodes heat-treated at 300 degrees C demonstrate the highest specific capacitance and the lowest capacity loss over 10 cycles, which could be attributed to higher electrical conductivity and improved adhesion. C1 [McGraw, Michael; Kolla, Praveen; Smirnova, Alevtina] South Dakota Sch Mines & Technol, Dept Chem & Appl Biol Sci, Rapid City, SD 57701 USA. [Cook, Rob] Zyvex Technol, Rapid City, SD 57701 USA. [Wu, James; Lvovich, Vadim] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Smirnova, A (reprint author), South Dakota Sch Mines & Technol, Dept Chem & Appl Biol Sci, Rapid City, SD 57701 USA. EM Alevtina.smirnova@sdsmt.edu NR 12 TC 0 Z9 0 U1 0 U2 0 PU SOUTH DAKOTA ACAD SCIENCE PI PIERRE PA HCR 531 BOX 97, PIERRE, SD 57501 USA SN 0096-378X J9 PROC S D ACAD SCI JI Proc. South Dak. Acad. Sci. PY 2015 VL 94 BP 253 EP 261 PG 9 WC Multidisciplinary Sciences SC Science & Technology - Other Topics GA BE8FO UT WOS:000376419700020 ER PT S AU Rahn, PH Durkin, TV AF Rahn, Perry H. Durkin, Thomas V. BE Tatina, R TI FERMI'S QUESTION SO PROCEEDINGS OF THE SOUTH DAKOTA ACADEMY OF SCIENCE, VOL 94 SE Proceedings of the South Dakota Academy of Science LA English DT Proceedings Paper CT 100th Annual Meeting of the South Dakota Academy of Science CY APR 10-11, 2015 CL Oacoma, SD SP S Dakota Acad Sci DE Extraterrestrial life; SETI; exoplanet AB There are approximately 4 X 10(11) stars in the Milky Way galaxy and there may be at least as many exoplanets as stars. The probability of intelligent life presently on an exoplanet can be modeled as the product of the following four probabilities: (1) P-hz, that an exoplanet orbits its parent star at a distance (habitable zone) where liquid water could exist, (2) P-dl, that life developed on this exoplanet, (3) P-il, that life evolved into intelligent forms, and (4) P-pt, that this intelligent life presently exists on the exoplanet. The number of extraterrestrial civilizations (ETC) in the Milky Way equals the number of exoplanets (R) times these probabilities: ETC = R (P-hz . P-dl . Pil . P-pt) Despite great uncertainties in the actual probability values for this model, there may be some exoplanets in the Milky Way that meet these criteria. In order to answer Fermi's Question ("Where are they?"), consideration must be given to the fact that the great distance to an exoplanet with intelligent life could essentially preclude any two-way communication. C1 [Rahn, Perry H.] South Dakota Sch Mines & Technol, Dept Geol & Geol Engn, Rapid City, SD 57701 USA. [Durkin, Thomas V.] NASA, Space Grant Consortium, South Dakota Sch Mines & Technol, Rapid City, SD 57701 USA. RP Rahn, PH (reprint author), South Dakota Sch Mines & Technol, Dept Geol & Geol Engn, Rapid City, SD 57701 USA. EM perry.rahn@sdsmt.edu NR 15 TC 0 Z9 0 U1 0 U2 0 PU SOUTH DAKOTA ACAD SCIENCE PI PIERRE PA HCR 531 BOX 97, PIERRE, SD 57501 USA SN 0096-378X J9 PROC S D ACAD SCI JI Proc. South Dak. Acad. Sci. PY 2015 VL 94 BP 329 EP 335 PG 7 WC Multidisciplinary Sciences SC Science & Technology - Other Topics GA BE8FO UT WOS:000376419700028 ER PT B AU Fensholt, R Horion, S Tagesson, T Ehammer, A Grogan, K Tian, F Huber, S Verbesselt, J Prince, SD Tucker, CJ Rasmussen, K AF Fensholt, Rasmus Horion, Stephanie Tagesson, Torbern Ehammer, Andrea Grogan, Kenneth Tian, Feng Huber, Silvia Verbesselt, Jan Prince, Stephen D. Tucker, Compton J. Rasmussen, Kjeld BE Kuenzer, C Dech, S Wagner, W TI Assessment of Vegetation Trends in Drylands from Time Series of Earth Observation Data SO REMOTE SENSING TIME SERIES: REVEALING LAND SURFACE DYNAMICS SE Remote Sensing and Digital Image Processing LA English DT Article; Book Chapter ID HIGH-RESOLUTION RADIOMETER; LAND-SURFACE PHENOLOGY; NET PRIMARY PRODUCTION; SATELLITE SENSOR DATA; LEAF-AREA INDEX; AVHRR-NDVI DATA; SPOT-VEGETATION; AFRICAN SAHEL; MODIS DATA; GLOBAL ASSESSMENT AB This chapter summarizes approaches to the detection of dryland vegetation change and methods for observing spatio-temporal trends from space. An overview of suitable long-term Earth Observation (EO) based datasets for assessment of global dryland vegetation trends is provided and a status map of contemporary greening and browning trends for global drylands is presented. The vegetation metrics suitable for per-pixel temporal trend analysis is discussed, including seasonal parameterisation and the appropriate choice of trend indicators. Recent methods designed to overcome assumptions of long-term linearity in time series analysis (Breaks For Additive Season and Trend(BFAST)) are discussed. Finally, the importance of the spatial scale when performing temporal trend analysis is introduced and a method for image downscaling (Spatial and Temporal Adaptive Reflectance Fusion Model (STARFM)) is presented. C1 [Fensholt, Rasmus; Horion, Stephanie; Tagesson, Torbern; Ehammer, Andrea; Grogan, Kenneth; Tian, Feng; Rasmussen, Kjeld] Univ Copenhagen, Sect Geog, Dept Geosci & Nat Resource Management, Fac Sci, Copenhagen K, Denmark. [Huber, Silvia] DHI GRAS, Copenhagen K, Denmark. [Verbesselt, Jan] Wageningen Univ, Lab Geoinformat Sci & Remote Sensing, NL-6700 AP Wageningen, Netherlands. [Prince, Stephen D.] Univ Maryland, Dept Geog Sci, College Pk, MD 20742 USA. [Tucker, Compton J.] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. RP Fensholt, R (reprint author), Univ Copenhagen, Sect Geog, Dept Geosci & Nat Resource Management, Fac Sci, Copenhagen K, Denmark. EM rf@ign.ku.dk OI Tian, Feng/0000-0002-9686-2769 NR 90 TC 1 Z9 1 U1 0 U2 0 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS BN 978-3-319-15967-6; 978-3-319-15966-9 J9 REMOTE SENS DIGIT IM PY 2015 VL 22 BP 159 EP 182 DI 10.1007/978-3-319-15967-6_8 D2 10.1007/978-3-319-15967-6 PG 24 WC Geography, Physical; Remote Sensing SC Physical Geography; Remote Sensing GA BE7CU UT WOS:000375103900009 ER PT B AU Fensholt, R Horion, S Tagesson, T Ehammer, A Grogan, K Tian, F Huber, S Verbesselt, J Prince, SD Tucker, CJ Rasmussen, K AF Fensholt, Rasmus Horion, Stephanie Tagesson, Torbern Ehammer, Andrea Grogan, Kenneth Tian, Feng Huber, Silvia Verbesselt, Jan Prince, Stephen D. Tucker, Compton J. Rasmussen, Kjeld BE Kuenzer, C Dech, S Wagner, W TI Assessing Drivers of Vegetation Changes in Drylands from Time Series of Earth Observation Data SO REMOTE SENSING TIME SERIES: REVEALING LAND SURFACE DYNAMICS SE Remote Sensing and Digital Image Processing LA English DT Article; Book Chapter ID SEA-SURFACE TEMPERATURE; RAIN-USE EFFICIENCY; PRECIPITATION-USE EFFICIENCY; NORTH-ATLANTIC OSCILLATION; AVHRR NDVI DATA; SAHEL RAINFALL; LAND DEGRADATION; CLIMATE OSCILLATIONS; GLOBAL PRECIPITATION; ECOSYSTEM DYNAMICS AB This chapter summarizes methods of inferring information about drivers of global dryland vegetation changes observed from remote sensing time series data covering from the 1980s until present time. Earth observation (EO) based time series of vegetation metrics, sea surface temperature (SST) (both from the AVHRR (Advanced Very High Resolution Radiometer) series of instruments) and precipitation data (blended satellite/rain gauge) are used for determining the mechanisms of observed changes. EO-based methods to better distinguish between climate and human induced (land use) vegetation changes are reviewed. The techniques presented include trend analysis based on the Rain-Use Efficiency (RUE) and the Residual Trend Analysis (RESTREND) and the methodological challenges related to the use of these. Finally, teleconnections between global sea surface temperature (SST) anomalies and dryland vegetation productivity are illustrated and the associated predictive capabilities are discussed. C1 [Fensholt, Rasmus; Horion, Stephanie; Tagesson, Torbern; Ehammer, Andrea; Grogan, Kenneth; Tian, Feng; Rasmussen, Kjeld] Univ Copenhagen, Sect Geog, Dept Geosci & Nat Resource Management, Fac Sci, Copenhagen K, Denmark. [Huber, Silvia] DHI GRAS, Copenhagen K, Denmark. [Verbesselt, Jan] Wageningen Univ, Lab Geoinformat Sci & Remote Sensing, NL-6700 AP Wageningen, Netherlands. [Prince, Stephen D.] Univ Maryland, Dept Geog Sci, College Pk, MD 20742 USA. [Tucker, Compton J.] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. RP Fensholt, R (reprint author), Univ Copenhagen, Sect Geog, Dept Geosci & Nat Resource Management, Fac Sci, Copenhagen K, Denmark. EM rf@ign.ku.dk OI Tian, Feng/0000-0002-9686-2769 NR 75 TC 3 Z9 3 U1 1 U2 1 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS BN 978-3-319-15967-6; 978-3-319-15966-9 J9 REMOTE SENS DIGIT IM PY 2015 VL 22 BP 183 EP 202 DI 10.1007/978-3-319-15967-6_9 D2 10.1007/978-3-319-15967-6 PG 20 WC Geography, Physical; Remote Sensing SC Physical Geography; Remote Sensing GA BE7CU UT WOS:000375103900010 ER PT B AU Shelhamer, MJ AF Shelhamer, Mark J. BA Salas, E BF Salas, E TI TEAM TRAINING ESSENTIALS A Research-Based Guide INTRODUCTION SO TEAM TRAINING ESSENTIALS: A RESEARCH-BASED GUIDE LA English DT Editorial Material; Book Chapter ID PERFORMANCE; METAANALYSIS; MODEL C1 [Shelhamer, Mark J.] NASA, Human Res Program, New York, NY 10010 USA. RP Shelhamer, MJ (reprint author), NASA, Human Res Program, New York, NY 10010 USA. NR 33 TC 0 Z9 0 U1 1 U2 1 PU ROUTLEDGE PI ABINGDON PA 2 PARK SQ, MILTON PARK, ABINGDON OX14 4RN, OXFORD, ENGLAND BN 978-1-138-81422-6; 978-1-315-74764-4; 978-1-138-81421-9 PY 2015 BP 1 EP 17 PG 17 WC Psychology, Applied SC Psychology GA BD9AA UT WOS:000364491400003 ER PT B AU Shelhamer, MJ AF Shelhamer, Mark J. BA Salas, E BF Salas, E TI TEAM TRAINING ESSENTIALS A Research-Based Guide CONCLUDING REMARKS SO TEAM TRAINING ESSENTIALS: A RESEARCH-BASED GUIDE LA English DT Editorial Material; Book Chapter ID ORGANIZATIONS; SCIENCE C1 [Shelhamer, Mark J.] NASA, Human Res Program, New York, NY 10010 USA. RP Shelhamer, MJ (reprint author), NASA, Human Res Program, New York, NY 10010 USA. NR 13 TC 0 Z9 0 U1 0 U2 0 PU ROUTLEDGE PI ABINGDON PA 2 PARK SQ, MILTON PARK, ABINGDON OX14 4RN, OXFORD, ENGLAND BN 978-1-138-81422-6; 978-1-315-74764-4; 978-1-138-81421-9 PY 2015 BP 123 EP 130 PG 8 WC Psychology, Applied SC Psychology GA BD9AA UT WOS:000364491400009 ER PT B AU Berra, LM Olcmen, S Slater, JW AF Berra, Lee M. Olcmen, Semih Slater, John W. GP ASME TI REDESIGN OF THE B-1B BOMBER INLETS FOR IMPROVED SUPERSONIC PERFORMANCE SO PROCEEDINGS OF THE ASME INTERNATIONAL MECHANICAL ENGINEERING CONGRESS AND EXPOSITION, 2014, VOL 1 LA English DT Proceedings Paper CT ASME International Mechanical Engineering Congress and Exposition (IMECE) CY NOV 14-20, 2014 CL Montreal, CANADA SP ASME AB This paper presents a conceptual study of two alternative inlet concepts for the United States Air Force B-1B bomber to provide for improved supersonic performance with expansion of capabilities to high-altitude, high-speed flight at Mach 2.0. The two inlet concepts are two-dimensional, variable-ramp inlet systems designed to replace the current fixed-geometry, pitot inlets of the B-1B. One inlet incorporates a two-ramp system, while a second inlet incorporates a two-ramp system containing an isentropic contour. The entire inlet system including the supersonic diffuser, throat, cowl lip, and subsonic diffuser sections was designed to maximize the total pressure recovery at the engine fan face to achieve maximum thrust by the engine at Mach 2.0 conditions. Analytic methods implemented into the MATLAB and the NASA SUPIN codes are used to design and analyze the two-dimensional inlet concepts. In addition, high-fidelity WIND-US computational fluid dynamics (CFD) simulations were used to verify the results of the analytic design methods. The results suggest that at Mach 2.0, the total pressure recovery of the inlets could increase from 0.70 to 0.94. The inlet capture area and cowl drag increased; however, the overall improvements resulted in a 98% thrust increase over the existing inlet at the design point. C1 [Berra, Lee M.] US Air Force, Tuscaloosa, AL 35487 USA. [Berra, Lee M.] Univ Alabama, Tuscaloosa, AL 35487 USA. [Olcmen, Semih] Univ Alabama, Dept Aerosp Engn & Mech, Tuscaloosa, AL 35487 USA. [Slater, John W.] NASA John H Glenn Res Ctr, Inlet & Nozzle Branch, Cleveland, OH 44145 USA. RP Berra, LM (reprint author), US Air Force, Tuscaloosa, AL 35487 USA. NR 14 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-4642-1 PY 2015 AR UNSP V001T01A062 PG 11 WC Engineering, Aerospace; Engineering, Mechanical SC Engineering GA BE6PO UT WOS:000374508300061 ER PT S AU Li, SJ Wang, W Qi, HR Ayhan, B Kwan, C Vance, S AF Li, Shuangjiang Wang, Wei Qi, Hairong Ayhan, Bulent Kwan, Chiman Vance, Steven GP IEEE TI LOW-RANK TENSOR DECOMPOSITION BASED ANOMALY DETECTION FOR HYPERSPECTRAL IMAGERY SO 2015 IEEE INTERNATIONAL CONFERENCE ON IMAGE PROCESSING (ICIP) SE IEEE International Conference on Image Processing ICIP LA English DT Proceedings Paper CT IEEE International Conference on Image Processing (ICIP) CY SEP 27-30, 2015 CL Quebec City, CANADA SP Inst Elect & Elect Engineers, IEEE Signal Proc Soc DE Hyperspectral imaging; anomaly detection; low-rank approximation; tensor decomposition ID ALGORITHM; RECOVERY AB Anomaly detection becomes increasingly important in hyper-spectral image analysis, since it can now uncover many material substances which were previously unresolved by multispectral sensors. In this paper, we propose a Low-rank Tensor Decomposition based anomaly Detection (LTDD) algorithm for Hyperspectral Imagery. The HSI data cube is first modeled as a dense low-rank tensor plus a sparse tensor. Based on the obtained low-rank tensor, LTDD further decomposes the low-rank tensor using Tucker decomposition to extract the core tensor which is treated as the "support" of the anomaly spectral signatures. LTDD then adopts an unmixing approach to the reconstructed core tensor for anomaly detection. The experiments based on both simulated and real hyperspectral data sets verify the effectiveness of our algorithm. C1 [Li, Shuangjiang; Wang, Wei; Qi, Hairong] Univ Tennessee, Dept EECS, Knoxville, TN USA. [Ayhan, Bulent; Kwan, Chiman] Signal Proc Inc, Rockville, MD USA. [Vance, Steven] CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Li, SJ (reprint author), Univ Tennessee, Dept EECS, Knoxville, TN USA. NR 24 TC 3 Z9 3 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-4880 BN 978-1-4799-8339-1 J9 IEEE IMAGE PROC PY 2015 BP 4525 EP 4529 PG 5 WC Engineering, Electrical & Electronic; Imaging Science & Photographic Technology SC Engineering; Imaging Science & Photographic Technology GA BE4NP UT WOS:000371977804133 ER PT S AU Berger, K Berger, K Le Callet, P AF Berger, Kai Berger, Kongfeng Le Callet, Patrick GP IEEE TI UHD IMAGE RECONSTRUCTION BY ESTIMATING INTERPOLATION ERROR SO 2015 IEEE INTERNATIONAL CONFERENCE ON IMAGE PROCESSING (ICIP) SE IEEE International Conference on Image Processing ICIP LA English DT Proceedings Paper CT IEEE International Conference on Image Processing (ICIP) CY SEP 27-30, 2015 CL Quebec City, CANADA SP Inst Elect & Elect Engineers, IEEE Signal Proc Soc DE Ultra HDTV; error estimation; tube interpolation; scale invariance; self-similarity ID SUPERRESOLUTION AB With the emerging ultra high definition (UHD) TV technology, the reconstruction of UHD images from transmitted HD images on the receiver's side is of great interests to save bandwidth and be compatible to existing HDTV systems. In this paper, a UHD image reconstruction algorithm is proposed for the UHDTV broadcasting system. A transmitted HD image at the receiver side is first up sampled to UHD resolution, then the error map between the interpolated UHD image and the original UHD image is estimated. The final reconstructed UHD image is the sum of the interpolated UHD image and the estimated UHD error map. There are two steps to estimate the content of the UHD error map: 1) key point detection and prediction estimate the location of the pixels with large error and create a spline tube between two adjacent key points; 2) spline-tube interpolation estimate the error value along the spline tube. Our simulation results on six images show that the proposed reconstruction method performs better than conventional up sampling without estimating the error map. C1 [Berger, Kai] CALTECH, Jet Prop Lab, Pasadena, CA USA. [Berger, Kongfeng; Le Callet, Patrick] LUNAM Univ Nantes, IRCCyN, UMR CNRS 6597, Nantes, France. RP Berger, K (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA USA. NR 19 TC 0 Z9 0 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-4880 BN 978-1-4799-8339-1 J9 IEEE IMAGE PROC PY 2015 BP 4743 EP 4747 PG 5 WC Engineering, Electrical & Electronic; Imaging Science & Photographic Technology SC Engineering; Imaging Science & Photographic Technology GA BE4NP UT WOS:000371977804177 ER PT B AU Schiller, NH Allen, AR Zalewski, BF Beck, BS AF Schiller, Noah H. Allen, Albert R. Zalewski, Bart F. Beck, Benjamin S. GP ASME TI SOUND TRANSMISSION LOSS THROUGH A CORRUGATED-CORE SANDWICH PANEL WITH INTEGRATED ACOUSTIC RESONATORS SO PROCEEDINGS OF THE ASME INTERNATIONAL MECHANICAL ENGINEERING CONGRESS AND EXPOSITION, 2014, VOL 13 LA English DT Proceedings Paper CT ASME International Mechanical Engineering Congress and Exposition (IMECE2014) CY NOV 14-20, 2014 CL Montreal, CANADA SP ASME ID HELMHOLTZ RESONATORS; NOISE-CONTROL AB The goal of this study is to better understand the effect of structurally integrated resonators on the transmission loss of a sandwich panel. The sandwich panel has facesheets over a corrugated core, which creates long aligned chambers that run parallel to the facesheets. When ports are introduced through the facesheet, the long chambers within the core can be used as low-frequency acoustic resonators. By integrating the resonators within the structure they contribute to the static load bearing capability of the panel while also attenuating noise. An analytical model of a panel with embedded resonators is derived and compared with numerical simulations. Predictions show that acoustic resonators can significantly improve the transmission loss of the sandwich panel around the natural frequency of the resonators. In one configuration with 0.813 m long internal chambers, the diffuse field transmission loss is improved by more than 22 dB around 104 Hz. The benefit is achieved with no added mass or volume relative to the baseline structure. The embedded resonators are effective because they radiate sound out-of-phase with the structure. This results in destructive interference, which leads to less transmitted sound power: C1 [Schiller, Noah H.; Allen, Albert R.] NASA, Langley Res Ctr, Hampton, VA 23665 USA. [Zalewski, Bart F.] Zin Technol Inc, Cleveland, OH USA. [Beck, Benjamin S.] Natl Inst Aerosp, Hampton, VA USA. RP Schiller, NH (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. NR 15 TC 0 Z9 0 U1 1 U2 1 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-4962-0 PY 2015 AR V013T16A009 PG 9 WC Acoustics; Engineering, Mechanical SC Acoustics; Engineering GA BE6IX UT WOS:000374202600009 ER PT S AU Pieri, D Diaz, JA AF Pieri, David Andres Diaz, Jorge BE Ravela, S Sandu, A TI In Situ Sampling of Volcanic Emissions with a UAV Sensorweb: Progress and Plans SO DYNAMIC DATA-DRIVEN ENVIRONMENTAL SYSTEMS SCIENCE, DYDESS 2014 SE Lecture Notes in Computer Science LA English DT Proceedings Paper CT 1st International Conference on Dynamic Data-Driven Environmental Systems Science (DyDESS) CY NOV 05-07, 2014 CL Cambridge, MA SP Massachusetts Inst Technol, Dept Earth Atmospher & Planetary Sci DE Unmanned aircraft; UAVs; Volcanoes; SO2; CO2; Diffuse emissions ID COSTA-RICA; PARTICLES; AIRCRAFT; ERUPTION; ALASKA; CLOUD AB A consortium of NASA, commercial, and academic partners, we have begun utilize small UAVs and aerostats for in situ sampling of volcanogenic gases and aerosols, using Turrialba Volcano as natural laboratory. Significant progress has been made over the last several years in utilizing single platforms with a number of newly miniaturized instruments appropriate to aircraft with sub-500 gm payloads. For example, we have been mapping the SO2-water-vapor plume at Turrialba, for comparison with NASA spacecraft-based (e.g., ASTER) data, and are measuring diffuse CO2 emissions over the volcano's flanks, as well as in and near its eruption column. Future work will include devising strategies, platforms, and instrumentation for deployments of multiple UAV formations ("swarms") as 2D and 3D time-series meshes, to better characterize the mass fluxes and dynamics of emissions. We plan to undertake test flights in the United States, as well as at Turrialba and Poas Volcanoes in Costa Rica. Our most immediate aims are to improve characterizations of local emissions for mitigation of proximal volcanic hazards and for validation of abundance retrievals and transport models based on orbital data. Overall, of course, we strive to better understand how volcanoes work, specifically to better constrain estimates of global SO2 and CO2 perennial (diffuse) and event-related (eruptive) emissions-changes in which may foster regional and global climate perturbations. C1 [Pieri, David] CALTECH, Jet Prop Lab, Pasadena, CA USA. [Andres Diaz, Jorge] Univ Costa Rica, Ctr Invest Atom Nucl & Mol Sci CICANUM, GasLab, Sanjose, Costa Rica. RP Pieri, D (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA USA. EM dave.pieri@jpl.nasa.gov NR 23 TC 0 Z9 0 U1 6 U2 6 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 0302-9743 BN 978-3-319-25138-7; 978-3-319-25137-0 J9 LECT NOTES COMPUT SC PY 2015 VL 8964 BP 16 EP 27 DI 10.1007/978-3-319-25138-7_3 PG 12 WC Computer Science, Artificial Intelligence; Computer Science, Interdisciplinary Applications; Computer Science, Software Engineering; Computer Science, Theory & Methods; Robotics SC Computer Science; Robotics GA BE6BS UT WOS:000373824200003 ER PT S AU Kremic, T Cheng, A Hibbitts, K Young, EF AF Kremic, Tibor Cheng, Andrew Hibbitts, Karl Young, Eliot F. BE Ouwehand, L TI PLANETARY SCIENCE WITH BALLOON-BORNE TELESCOPES: A SUMMARY OF THE BOPPS MISSION AND THE PLANETARY SCIENCE THAT MAY BE POSSIBLE LOOKING FORWARD SO EUROPEAN ROCKET AND BALLOON: PROGRAMMES AND RELATED RESEARCH SE ESA Special Publications LA English DT Proceedings Paper CT 22nd ESA Symposium on European Rocket and Balloon Programmes and Related Research CY JUN 07-12, 2015 CL Tromso, NORWAY SP European Space Agcy, Andoya Space Ctr, Ctr Natl Etud Spatiales, Deutsch Zentrums Luft Raumfahrt, Swedish Space Corp, Swedish Natl Space Board, Hsch Luzern AB The National Aeronautics and Space Administration (NASA) and the planetary science community have recently been exploring the potential contributions of stratospheric balloons to the planetary science field. A study that was recently concluded explored the roughly 200 or so science questions raised in the Planetary Decadal Survey report and found that about 45 of those questions are suited to stratospheric balloon based observations. In September of 2014, a stratospheric balloon mission called BOPPS (which stands for Balloon Observation Platform for Planetary Science) was flown out of Fort Sumner, New Mexico. The mission had two main objectives, first, to observe a number of planetary targets including one or more Oort cloud comets and second, to demonstrate the applicability and performance of the platform, instruments, and subsystems for making scientific measurements in support of planetary science objectives. BOPPS carried two science instruments, BIRC and UVVis. BIRC is a cryogenic infrared multispectral imager which can image in the 0.6-5 pm range using an HgCdTe detector. Narrow band filters were used to allow detection of water and CO2 emission features of the observed targets. The UVVis is an imager with the science range of 300 to 600 nm. A main feature of the UVVis instrument is the incorporation of a guide camera and a Fine-Steering Mirror (FSM) system to reduce image jitter to less than 100 milliarcsecond. The BIRC instrument was used to image targets including Oort cloud comets Siding Spring and Jacques, and the dwarf planet 1 Ceres. BOPPS achieved the first ever earth based CO2 observation of a comet and the first images of water and CO2 of an Oort cloud comet (Jacques). It also made the first ever measurement of 1 Ceres at 2.73 pm to refine the shape of the infrared water absorption feature on that body. The UVVis instrument, mounted on its own optics bench, demonstrated the capability for image correction both from atmospheric disturbances as well as some of the residual motion from the gondola that was not addressed by the gondola's coarse pointing systems. The mission met its primary science and engineering objectives. The results of the BOPPS mission will feed into the body of science knowledge, but also feed into future planning for more science from balloon-home platforms. A notional platform called Gondola for High-Altitude Planetary Science (GHAPS) has been explored, and this concept platform can address a number of important decadal questions. This paper provides a summary of the assessment of potential balloon borne observations for planetary science purposes including where potential science contributions can be expected, the necessary performance/characteristics of the platform, and other features required or desired. The BOPPS mission is summarized including descriptions of the main elements and key science and engineering results. The paper then briefly describes GHAPS, and the salient features that can make it a valuable tool for future planetary observations. C1 [Kremic, Tibor] NASA Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. [Cheng, Andrew; Hibbitts, Karl] JHU Appl Phys Lab, Laurel, MD 20723 USA. [Young, Eliot F.] SW Res Inst, Boulder, CO 80302 USA. RP Kremic, T (reprint author), NASA Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. EM Tibor.Kremic@nasa.gov; Andy.Cheng@jhuapl.edu; Karl.Hibbitts@jhuapl.edu; afy@boulder.swri.edu NR 8 TC 0 Z9 0 U1 1 U2 1 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 978-92-9221-294-0 J9 ESA SPEC PUBL PY 2015 VL 730 BP 565 EP 573 PG 9 WC Engineering, Aerospace; Astronomy & Astrophysics SC Engineering; Astronomy & Astrophysics GA BE5YC UT WOS:000373647300077 ER PT B AU Sandroos, A von Alfthan, S Hoilijoki, S Honkonen, I Kempf, Y Pokhotelov, D Palmroth, M AF Sandroos, A. von Alfthan, S. Hoilijoki, S. Honkonen, I. Kempf, Y. Pokhotelov, D. Palmroth, M. BE Pogorelov, NV Audit, E Zank, GP TI Vlasiator: Global Kinetic Magnetospheric Modeling Tool SO NUMERICAL MODELING OF SPACE PLASMA FLOWS: ASTRONUM-2014 SE Astronomical Society of the Pacific Conference Series LA English DT Proceedings Paper CT 9th Annual International Conference on Numerical Modeling of Space Plasma Flows (ASTRONUM-2014) CY JUN 23-27, 2014 CL Long Beach, CA SP Univ Alabama, Ctr Space Plasma & Aeronomic Res, CEA-CNRS-INRIA-UPsud-UVSQ, Maison Simulat ID SIMULATIONS; MAGNETOHYDRODYNAMICS; MAGNETOSHEATH; FORESHOCK AB We present Vlasiator, a novel code based on Vlasov's equation, developed for modeling magnetospheric plasma on a global scale. We have parallelized the code to petascale supercomputers with a hybrid OpenMP-MPI approach to answer the high computational cost of propagating ion distribution functions in six dimensions. The accuracy of the numerical method is demonstrated by comparing simulated wave dispersion plots to analytical results. Simulations of Earth's bow shock region were able to reproduce many well-known plasma phenomena, such as compressional magnetosonic waves in the foreshock region, and mirror mode instability in the magnetosheath. C1 [Sandroos, A.; von Alfthan, S.; Hoilijoki, S.; Kempf, Y.; Palmroth, M.] Finnish Meteorol Inst, POB 503, FI-00101 Helsinki, Finland. [Sandroos, A.] Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. [Hoilijoki, S.; Kempf, Y.] Univ Helsinki, Helsinki, Finland. [Honkonen, I.] NASA Goddard Space Flight Ctr, Greenbelt, MD USA. [Pokhotelov, D.] UCL, Mullard Space Sci Lab, London WC1E 6BT, England. RP Sandroos, A (reprint author), Finnish Meteorol Inst, POB 503, FI-00101 Helsinki, Finland. NR 13 TC 0 Z9 0 U1 0 U2 0 PU ASTRONOMICAL SOC PACIFIC PI SAN FRANCISCO PA 390 ASHTON AVE, SAN FRANCISCO, CA 94112 USA BN 978-1-58381-880-0 J9 ASTR SOC P PY 2015 VL 498 BP 222 EP 228 PG 7 WC Astronomy & Astrophysics; Mathematics, Applied SC Astronomy & Astrophysics; Mathematics GA BE6DR UT WOS:000373970200034 ER PT B AU Parnell, L Vaughan, G Thompson, J Duffy, D Capps, L Steinke, ME Kamath, V AF Parnell, Lynn Vaughan, Garrison Thompson, John Duffy, Daniel Capps, Louis Steinke, Mark E. Kamath, Vinod GP ASME TI THERMODYNAMIC CHARACTERIZATION OF A DIRECT WATER COOLED SERVER RACK RUNNING SYNTHETIC AND REAL HIGH PERFORMANCE COMPUTING WORK LOADS SO INTERNATIONAL TECHNICAL CONFERENCE AND EXHIBITION ON PACKAGING AND INTEGRATION OF ELECTRONIC AND PHOTONIC MICROSYSTEMS, 2015, VOL 1 LA English DT Proceedings Paper CT ASME International Technical Conference and Exhibition on Packaging and Integration of Electronic and Photonic Microsystems (InterPACK) CY JUL 06-09, 2015 CL San Francisco, CA SP ASME AB High performance computing server racks are being engineered to contain significantly more processing capability within the same computer room footprint year after year. The processor density within a single rack is becoming high enough that traditional, inefficient air-cooling of servers is inadequate to sustain HPC workloads. Experiments that characterize the performance of a direct water-cooled server rack in an operating HPC facility are described in this paper. Performance of the rack is reported for a range of cooling water inlet temperatures, flow rates and workloads that include actual and worst-case synthetic benchmarks. Power and temperature measurements of all processors and memory components in the rack were made while extended benchmark tests were conducted throughout the range of cooling variables allowed within an operational HPC facility. Synthetic benchmark results were compared with those obtained on a single server of the same design that had been characterized thermodynamically. Neither actual nor synthetic benchmark performances were affected during the course of the experiments, varying less than 0.13 percent. Power consumption change in the rack was minimal for the entire excursion of coolant temperatures and flow rates. Establishing the characteristics of such a highly energy efficient server rack in situ is critical to determine how the technology might be integrated into an existing heterogeneous, hybrid cooled computing facility i.e., a facility that includes some servers that are air cooled as well as some that are direct water cooled. C1 [Vaughan, Garrison] Informat Technol Coalit Inc, Alexandria, VA USA. [Thompson, John] PTP LLC, Clarksville, MD USA. [Duffy, Daniel] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. [Capps, Louis] NVIDIA Corp, Santa Clara, CA USA. [Steinke, Mark E.; Kamath, Vinod] Lenovo Grp Ltd, Enterprise Business Grp, Morrisville, NC USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-5688-8 PY 2015 AR V001T09A031 PG 7 WC Thermodynamics; Engineering, Mechanical SC Thermodynamics; Engineering GA BE5WB UT WOS:000373517200031 ER PT B AU Bansal, N Lamon, J AF Bansal, Narottam Lamon, Jacques BE Bansal, NP Lamon, J TI CERAMIC MATRIX COMPOSITES MATERIALS, MODELING AND TECHNOLOGY Preface SO CERAMIC MATRIX COMPOSITES: MATERIALS, MODELING AND TECHNOLOGY LA English DT Editorial Material; Book Chapter C1 [Bansal, Narottam] NASA, Glenn Res Ctr, Mat & Struct Div, Cleveland, OH USA. [Lamon, Jacques] UPMC, ENS Cachan Ecole Normale Super, CNRS, LMT, Cachan, France. RP Bansal, N (reprint author), NASA, Glenn Res Ctr, Mat & Struct Div, Cleveland, OH USA. NR 0 TC 1 Z9 1 U1 0 U2 0 PU JOHN WILEY & SONS INC PI HOBOKEN PA 111 RIVER ST, HOBOKEN, NJ 07030 USA BN 978-1-118-83299-8; 978-1-118-23116-6 PY 2015 BP XV EP XVI PG 2 WC Materials Science, Ceramics; Materials Science, Composites SC Materials Science GA BE3XU UT WOS:000371347800001 ER PT B AU DiCarlo, JA AF DiCarlo, James A. BE Bansal, NP Lamon, J TI ADVANCES IN SiC/SiC COMPOSITES FOR AERO-PROPULSION SO CERAMIC MATRIX COMPOSITES: MATERIALS, MODELING AND TECHNOLOGY LA English DT Article; Book Chapter ID ENVIRONMENTAL BARRIER COATINGS; CERAMIC FIBERS; SIC FIBERS; MATRIX; CREEP C1 [DiCarlo, James A.] NASA, Glenn Res Ctr, Mat & Struct Div, Cleveland, OH USA. RP DiCarlo, JA (reprint author), NASA, Glenn Res Ctr, Mat & Struct Div, Cleveland, OH USA. NR 46 TC 3 Z9 3 U1 0 U2 0 PU JOHN WILEY & SONS INC PI HOBOKEN PA 111 RIVER ST, HOBOKEN, NJ 07030 USA BN 978-1-118-83299-8; 978-1-118-23116-6 PY 2015 BP 217 EP 235 PG 19 WC Materials Science, Ceramics; Materials Science, Composites SC Materials Science GA BE3XU UT WOS:000371347800008 ER PT J AU Soebiyanto, RP Clara, WA Jara, J Balmaseda, A Lara, J Moya, ML Palekar, R Widdowson, MA Azziz-Baumgartner, E Kiang, RK AF Soebiyanto, Radina P. Clara, Wilfrido A. Jara, Jorge Balmaseda, Angel Lara, Jenny Moya, Mariel Lopez Palekar, Rakhee Widdowson, Marc-Alain Azziz-Baumgartner, Eduardo Kiang, Richard K. TI Associations between seasonal influenza and meteorological parameters in Costa Rica, Honduras and Nicaragua SO GEOSPATIAL HEALTH LA English DT Article DE Influenza; Central America; Rainfall; Temperature; Humidity ID RELATIVE-HUMIDITY; VIRUS; TRANSMISSION; TEMPERATURE; BANGLADESH; CHILDREN AB Seasonal influenza affects a considerable proportion of the global population each year. We assessed the association between sub-national influenza activity and temperature, specific humidity and rainfall in three Central America countries, i.e. Costa Rica, Honduras and Nicaragua. Using virologic data from each country's national influenza centre, rainfall from the Tropical Rainfall Measuring Mission and air temperature and specific humidity data from the Global Land Data Assimilation System, we applied logistic regression methods for each of the five sub-national locations studied. Influenza activity was represented by the weekly proportion of respiratory specimens that tested positive for influenza. The models were adjusted for the potentially confounding co-circulating respiratory viruses, seasonality and previous weeks' influenza activity. We found that influenza activity was proportionally associated (P<0.05) with specific humidity in all locations [odds ratio (OR) 1.21-1.56 per g/kg], while associations with temperature (OR 0.69-0.81 per degrees C) and rainfall (OR 1.01-1.06 per mm/day) were location-dependent. Among the meteorological parameters, specific humidity had the highest contribution (similar to 3-15%) to the model in all but one location. As model validation, we estimated influenza activity for periods, in which the data was not used in training the models. The correlation coefficients between the estimates and the observed were <= 0.1 in 2 locations and between 0.6-0.86 in three others. In conclusion, our study revealed a proportional association between influenza activity and specific humidity in selected areas from the three Central America countries. C1 [Soebiyanto, Radina P.] Univ Space Res Assoc, Goddard Earth Sci Technol & Res, Columbia, MD USA. [Soebiyanto, Radina P.; Kiang, Richard K.] NASA, Global Change Data Ctr, Goddard Space Flight Ctr, Greenbelt, MD USA. [Clara, Wilfrido A.] Ctr Dis Control & Prevent, Influenza Program, Reg Off Cent Amer Reg, Guatemala City, Guatemala. [Jara, Jorge] Univ Valle Guatemala, Influenza Unit, Ctr Hlth Studies, Guatemala City, Guatemala. [Balmaseda, Angel] Minist Hlth Nicaragua, Natl Virol Lab, Managua, Nicaragua. [Lara, Jenny; Moya, Mariel Lopez] Costa Rican Inst Res & Educ Nutr & Hlth, San Jose, Costa Rica. [Palekar, Rakhee] Pan Amer Hlth Org, Washington, DC USA. [Widdowson, Marc-Alain; Azziz-Baumgartner, Eduardo] Ctr Dis Control & Prevent, Influenza Div, Atlanta, GA USA. RP Kiang, RK (reprint author), NASA, Goddard Space Flight Ctr, Mail Code 610-2, Greenbelt, MD 20771 USA. EM richard.k.kiang@nasa.gov NR 37 TC 0 Z9 0 U1 0 U2 0 PU UNIV NAPLES FEDERICO II PI NAPLES PA FAC VET MED, DEP PATHOLOGY & ANIMAL HEALTH, VET PARASITOLOGY, VIA DELLA VETERINARIA 1, NAPLES, 80137, ITALY SN 1827-1987 EI 1970-7096 J9 GEOSPATIAL HEALTH JI Geospatial Health PY 2015 VL 10 IS 2 BP 144 EP 151 DI 10.4081/gh.2015.372 PG 8 WC Health Care Sciences & Services; Public, Environmental & Occupational Health SC Health Care Sciences & Services; Public, Environmental & Occupational Health GA DG3YF UT WOS:000372006400006 ER PT B AU Kohli, R AF Kohli, Rajiv BE Mittal, KL Jaiswal, R TI Application of Strippable Coatings for Removal of Particulate Contaminants SO PARTICLE ADHESION AND REMOVAL LA English DT Article; Book Chapter DE Strippable coatings; decontamination; mirrors; telescopes; optics; radioactive decontamination; collodion; particles ID OPTICAL-SURFACES; ADHESIVE TAPE; PARTICLES AB The use of strippable coatings is a low-cost, effective method for removal of particle contaminants from the surface of high quality parts and to protect the cleaned parts from surface damage. The coating is applied to the surface by spraying, rolling or brushing. The coating is allowed to cure and then removed by peeling. A wide variety of solvent-and water-based strippable coatings are available for precision cleaning of surfaces and for protecting surfaces that have been cleaned. The coating formulations are designed to entrain the particle contaminants by physical or chemical means. This chapter provides an overview of the types of strippable coatings and their properties, and discusses some of the applications of these coatings for removal of particle contaminants on a variety of surfaces. One successful application has been removal of dust and debris from precision optical surfaces, such as coated lenses and mirrors. Other applications include decontamination of surfaces by removal of hazardous and radioactive contaminants. C1 [Kohli, Rajiv] NASA, Lyndon B Johnson Space Ctr, Aerosp Corp, Houston, TX 77058 USA. RP Kohli, R (reprint author), NASA, Lyndon B Johnson Space Ctr, Aerosp Corp, Houston, TX 77058 USA. EM rajiv.kohli@aero.org NR 118 TC 0 Z9 0 U1 0 U2 0 PU SCRIVENER PUBLISHING LLC PI BEVERLY PA 100 CUMMINGS CENTER, STE 541J, BEVERLY, MA 01915-6106 USA BN 978-1-118-83157-1; 978-1-118-83153-3 PY 2015 BP 411 EP 451 D2 10.1002/9781118831571 PG 41 WC Materials Science, Multidisciplinary SC Materials Science GA BE2TJ UT WOS:000370018300012 ER PT B AU Kohli, R AF Kohli, Rajiv BE Mittal, KL Jaiswal, R TI Supercritical Carbon Dioxide Cleaning: Relevance to Particle Removal SO PARTICLE ADHESION AND REMOVAL LA English DT Article; Book Chapter DE Supercritical CO2 (SCCO2); Hansen solubility parameters; carbon nanotubes; precision cleaning techniques; solvent; tunable density; gas-like viscosity; liquid-like density; surface tension; particles ID EQUATION-OF-STATE; DENSITY-BASED MODELS; TRANSPORT-PROPERTIES; DEVICE FABRICATION; ELEVATED PRESSURES; FLUID APPLICATIONS; CO2; SOLUBILITIES; LIQUID; WATER AB Supercritical carbon dioxide (SCCO2) is an established precision cleaning technique with application in many different industries. The gas-like viscosity and the liquid-like density of CO2 are the key characteristics that allow the process to be tuned to the application. In addition, the very low surface tension of SCCO2 ensures high wettability and makes it very attractive for precision cleaning applications, particularly for intricate parts with complex geometries. The cleaning process is operated at near-ambient temperatures. Although the operating pressures for SCCO2 cleaning are high, this can be compensated for by operating for longer cleaning cycles. SCCO2 cleaning is a batch process. Applications range from cleaning and drying of micro and nanostructures such as carbon nanotubes; terminal sterilization of microbial organisms and food pasteurization; cleaning of metal surfaces, glass, optical elements, silicon wafers, and polymers; precision cleaning and drying of parts with complex geometries and tight spaces; sterilization of medical equipment; garment cleaning; pesticide mitigation in museum collections; and decontamination. C1 [Kohli, Rajiv] NASA, Lyndon B Johnson Space Ctr, Aerosp Corp, Houston, TX 77058 USA. RP Kohli, R (reprint author), NASA, Lyndon B Johnson Space Ctr, Aerosp Corp, Houston, TX 77058 USA. EM rajiv.kohli@aero.org NR 213 TC 0 Z9 0 U1 1 U2 1 PU SCRIVENER PUBLISHING LLC PI BEVERLY PA 100 CUMMINGS CENTER, STE 541J, BEVERLY, MA 01915-6106 USA BN 978-1-118-83157-1; 978-1-118-83153-3 PY 2015 BP 477 EP 518 D2 10.1002/9781118831571 PG 42 WC Materials Science, Multidisciplinary SC Materials Science GA BE2TJ UT WOS:000370018300014 ER PT S AU Campante, TL Barclay, T Swift, JJ Huber, D Adibekyan, VZ Cochran, W Burke, CJ Isaacson, H Quintana, EV Davies, GR Aguirre, VS Ragozzine, D Riddle, R Baranec, C Basu, S Chaplin, WJ Christensen-Dalsgaard, J Metcalfe, TS Bedding, TR Handberg, R Stello, D Brewer, JM Hekker, S Karoff, C Kolbl, R Law, NM Lundkvist, M Miglio, A Rowe, JF Santos, NC Van Laerhoven, C Arentoft, T Elsworth, YP Fischer, DA Kawaler, SD Kjeldsen, H Lund, MN Marcy, GW Sousa, SG Sozzetti, A White, TR AF Campante, T. L. Barclay, T. Swift, J. J. Huber, D. Adibekyan, V. Zh. Cochran, W. Burke, C. J. Isaacson, H. Quintana, E. V. Davies, G. R. Aguirre, V. Silva Ragozzine, D. Riddle, R. Baranec, C. Basu, S. Chaplin, W. J. Christensen-Dalsgaard, J. Metcalfe, T. S. Bedding, T. R. Handberg, R. Stello, D. Brewer, J. M. Hekker, S. Karoff, C. Kolbl, R. Law, N. M. Lundkvist, M. Miglio, A. Rowe, J. F. Santos, N. C. Van Laerhoven, C. Arentoft, T. Elsworth, Y. P. Fischer, D. A. Kawaler, S. D. Kjeldsen, H. Lund, M. N. Marcy, G. W. Sousa, S. G. Sozzetti, A. White, T. R. BE Garcia, RA Ballot, J TI KOI-3158: The oldest known system of terrestrial-size planets SO SPACE PHOTOMETRY REVOLUTION - COROT SYMPOSIUM 3, KEPLER KASC-7 JOINT MEETING SE EPJ Web of Conferences LA English DT Proceedings Paper CT Symposium 3 on Space Photometry Revolution - CoRoT / Kepler KASC-7 Joint Meeting CY JUL 06-11, 2014 CL Toulouse, FRANCE ID CANDIDATES; MASS AB The first discoveries of exoplanets around Sun-like stars have fueled efforts to find ever smaller worlds evocative of Earth and other terrestrial planets in the Solar System. While gas-giant planets appear to form preferentially around metal-rich stars, small planets (with radii less than four Earth radii) can form under a wide range of metallicities. This implies that small, including Earth-size, planets may have readily formed at earlier epochs in the Universe's history when metals were far less abundant. We report Kepler spacecraft observations of KOI-3158, a metal-poor Sun-like star from the old population of the Galactic thick disk, which hosts five planets with sizes between Mercury and Venus. We used asteroseismology to directly measure a precise age of 11.2 +/- 1.0 Gyr for the host star, indicating that KOI-3158 formed when the Universe was less than 20% of its current age and making it the oldest known system of terrestrial-size planets. We thus show that Earth-size planets have formed throughout most of the Universe's 13.8-billion-year history, providing scope for the existence of ancient life in the Galaxy. C1 [Campante, T. L.; Davies, G. R.; Chaplin, W. J.; Handberg, R.; Miglio, A.; Elsworth, Y. P.] Univ Birmingham, Sch Phys & Astron, Birmingham B15 2TT, W Midlands, England. [Campante, T. L.; Davies, G. R.; Aguirre, V. Silva; Chaplin, W. J.; Christensen-Dalsgaard, J.; Metcalfe, T. S.; Bedding, T. R.; Handberg, R.; Stello, D.; Hekker, S.; Karoff, C.; Lundkvist, M.; Miglio, A.; Arentoft, T.; Elsworth, Y. P.; Kjeldsen, H.; Lund, M. N.] Aarhus Univ, SAC, Dept Phys & Astron, DK-8000 Aarhus C, Denmark. [Barclay, T.; Huber, D.; Burke, C. J.; Quintana, E. V.; Rowe, J. F.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Barclay, T.] Bay Area Environm Res Inst, Sonoma, CA 95476 USA. [Swift, J. J.] CALTECH, Dept Astron, Pasadena, CA 91125 USA. [Swift, J. J.] CALTECH, Dept Planetary Sci, Pasadena, CA 91125 USA. [Huber, D.; Burke, C. J.; Quintana, E. V.; Rowe, J. F.] SETI Inst, Mountain View, CA 94043 USA. [Huber, D.; Bedding, T. R.; Stello, D.] Univ Sydney, Sch Phys, Sydney Inst Astron, Sydney, NSW 2006, Australia. [Adibekyan, V. Zh.; Santos, N. C.; Sousa, S. G.] Univ Porto, Ctr Astrofis, P-4150762 Oporto, Portugal. [Adibekyan, V. Zh.; Santos, N. C.; Sousa, S. G.] Univ Porto, Inst Astrofis & Ciencias Espaco, P-4150762 Oporto, Portugal. [Cochran, W.] Univ Texas Austin, Dept Astron, Austin, TX 78712 USA. [Cochran, W.] Univ Texas Austin, McDonald Observ, Austin, TX 78712 USA. [Isaacson, H.; Kolbl, R.; Marcy, G. W.] Univ Calif Berkeley, Dept Astron, Berkeley, CA 94720 USA. [Ragozzine, D.] Florida Inst Technol, Dept Phys & Space Sci, Melbourne, FL 32901 USA. [Riddle, R.] CALTECH, Div Phys Math & Astron, Pasadena, CA 91125 USA. [Baranec, C.] Univ Hawaii, Inst Astron, Hilo, HI 96720 USA. [Basu, S.] Yale Univ, Dept Astron, New Haven, CT 06520 USA. [Metcalfe, T. S.] Space Sci Inst, Boulder, CO 80301 USA. [Brewer, J. M.; Fischer, D. A.] Yale Univ, Dept Phys, New Haven, CT 06511 USA. [Hekker, S.] Max Planck Inst Solar Syst Res, Gottingen, Germany. [Karoff, C.] Aarhus Univ, Dept Geosci, DK-8000 Aarhus C, Denmark. [Law, N. M.] Univ N Carolina, Dept Phys & Astron, Chapel Hill, NC 27599 USA. [Santos, N. C.] Univ Porto, Fac Ciencias, Dept Fis & Astron, P-4169007 Oporto, Portugal. [Van Laerhoven, C.] Univ Arizona, Dept Planetary Sci, Tucson, AZ 85721 USA. [Kawaler, S. D.] Iowa State Univ Sci & Technol, Dept Phys & Astron, Ames, IA 50011 USA. [Sozzetti, A.] Osserv Astron Torino, INAF, I-10025 Pino Torinese, Italy. [White, T. R.] Univ Gottingen, Inst Astrophys, D-37077 Gottingen, Germany. RP Campante, TL (reprint author), Univ Birmingham, Sch Phys & Astron, Birmingham B15 2TT, W Midlands, England. EM campante@bison.ph.bham.ac.uk OI Sozzetti, Alessandro/0000-0002-7504-365X; Lundkvist, Mia Sloth/0000-0002-8661-2571; Brewer, John/0000-0002-9873-1471; Metcalfe, Travis/0000-0003-4034-0416; Karoff, Christoffer/0000-0003-2009-7965; Handberg, Rasmus/0000-0001-8725-4502; Lund, Mikkel Norup/0000-0001-9214-5642 NR 16 TC 0 Z9 0 U1 0 U2 4 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2015 VL 101 AR 02004 DI 10.1051/epjconf/201510102004 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BE5BE UT WOS:000372491300020 ER PT S AU Hambleton, K Kurtz, D Prsa, A Fuller, J Thompson, S AF Hambleton, Kelly Kurtz, Don Prsa, Andrej Fuller, Jim Thompson, Susan BE Garcia, RA Ballot, J TI Heartbeat Stars and The Ringing of Tidal Pulsations SO SPACE PHOTOMETRY REVOLUTION - COROT SYMPOSIUM 3, KEPLER KASC-7 JOINT MEETING SE EPJ Web of Conferences LA English DT Proceedings Paper CT Symposium 3 on Space Photometry Revolution - CoRoT / Kepler KASC-7 Joint Meeting CY JUL 06-11, 2014 CL Toulouse, FRANCE ID MASSIVE BINARY-SYSTEMS; RESONANCE LOCKING; ECCENTRIC ORBITS; DYNAMICAL TIDES; KOI-54; EVOLUTION; MODES AB With the advent of high precision photometry from satellites such as Kepler and CoRoT, a whole new layer of interesting and astounding astronomical objects has been revealed: heartbeat stars are an example of such objects. Heartbeat stars are eccentric ellipsoidal variables that undergo strong tidal interactions when the stars are almost in contact at the time of closest approach. These interactions deform of the stars and cause a notable light curve variation in the form of a tidal pulse. A subset of these objects (similar to 20%) show prominent tidally induced pulsations: pulsations forced by the binary orbit. We now have a fully functional code that models binary star features (using PHOEBE) and stellar pulsations simultaneously, enabling a complete and accurate heartbeat star model to be determined. In this paper we show the results of our new code, which uses EMCEE, a variant of mcmc, to generate a full set of stellar parameters. We further highlight the interesting features of KIC 8164262, including its tidally induced pulsations and resonantly locked pulsations. C1 [Hambleton, Kelly; Kurtz, Don] Univ Cent Lancashire, Jeremiah Horrocks Inst, Fylde Rd, Preston PR1 2HE, Lancs, England. [Hambleton, Kelly; Prsa, Andrej] Villanova Univ, Dept Astrophys & Planetary Sci, Villanova, PA 19085 USA. [Fuller, Jim] CALTECH, Pasadena, CA 91125 USA. [Thompson, Susan] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Thompson, Susan] SETI Inst, Mountain View, CA 94043 USA. RP Hambleton, K (reprint author), Univ Cent Lancashire, Jeremiah Horrocks Inst, Fylde Rd, Preston PR1 2HE, Lancs, England. EM kmhambleton@uclan.ac.uk NR 16 TC 0 Z9 0 U1 1 U2 1 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2015 VL 101 AR 04007 DI 10.1051/epjconf/201510104007 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BE5BE UT WOS:000372491300031 ER PT S AU Oshagh, M Santos, NC Boisse, I Boue, G Ehrenreich, D Haghighipour, N Figueira, P Santerne, A Dumusque, X AF Oshagh, M. Santos, N. C. Boisse, I Boue, G. Ehrenreich, D. Haghighipour, N. Figueira, P. Santerne, A. Dumusque, X. BE Garcia, RA Ballot, J TI Effect of stellar activity on the high precision transit light curve SO SPACE PHOTOMETRY REVOLUTION - COROT SYMPOSIUM 3, KEPLER KASC-7 JOINT MEETING SE EPJ Web of Conferences LA English DT Proceedings Paper CT Symposium 3 on Space Photometry Revolution - CoRoT / Kepler KASC-7 Joint Meeting CY JUL 06-11, 2014 CL Toulouse, FRANCE ID TRANSMISSION SPECTRA AB Stellar activity features such as spots and plages can create difficulties in determining planetary parameters through spectroscopic and photometric observations. The overlap of a transiting planet and a stellar spot, for instance, can produce anomalies in the transit light curve that may lead to inaccurate estimation of the transit duration, depth, and timing. Such inaccuracies can affect the precise derivation of the planet's radius. In this talk we will present the results of a quantitative study on the effects of stellar spots on high precision transit light curves. We show that spot anomalies can lead to the estimate of a planet radius that is 4% smaller than the real value. The effects on the transit duration can also be of the order of 4%, longer or shorter. Depending on the size and distribution of spots, anomalies can also produce transit timing variations with significant amplitudes. For instance, TTVs with signal amplitudes of 200 seconds can be produced by spots as large as the largest sunspot. Finally, we examine the impact of active regions on the transit depth measurements in different wavelengths, in order to probe the impact of this effect on transmission spectroscopy measurements. We show that significant (up to 10%) underestimation/overestimation of the planet-to-star radius ratio can be measured, especially in the short wavelength regime. C1 [Oshagh, M.; Santos, N. C.; Figueira, P.; Santerne, A.] Univ Porto, Ctr Astrofis, Rua Estrelas, P-4150762 Oporto, Portugal. [Oshagh, M.; Santos, N. C.; Figueira, P.; Santerne, A.] Univ Porto, CAUP, Inst Astrofis & Ciencias Espaco, P-4150762 Oporto, Portugal. [Oshagh, M.; Santos, N. C.] Univ Porto, Fac Ciencias, Dept Fis & Astron, P-4169007 Oporto, Portugal. [Boisse, I] Aix Marseille Univ, CNRS, LAM, UMR 7326, F-13388 Marseille 13, France. [Boue, G.] UPMC, Observ Paris, Astron & Syst Dynam, IMCCE,CNRS,UMR 8028, F-75014 Paris, France. [Ehrenreich, D.] Univ Geneva, Observ Geneve, CH-1290 Sauverny, Switzerland. [Haghighipour, N.] Univ Hawaii Manoa, Inst Astron, Honolulu, HI 96822 USA. [Haghighipour, N.] Univ Hawaii Manoa, Astrobiol Inst, NASA, Honolulu, HI 96822 USA. [Dumusque, X.] Harvard Smithsonian Ctr Astrophys, Cambridge, MA 02138 USA. RP Oshagh, M (reprint author), Univ Porto, Ctr Astrofis, Rua Estrelas, P-4150762 Oporto, Portugal. EM moshagh@astro.up.pt RI Figueira, Pedro/J-4916-2013 OI Figueira, Pedro/0000-0001-8504-283X NR 9 TC 2 Z9 2 U1 0 U2 1 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2015 VL 101 AR UNSP 05003 DI 10.1051/epjconf/201510105003 PG 5 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BE5BE UT WOS:000372491300034 ER PT S AU Parmentier, V Guillot, T Showman, AP Fortney, J Marley, M AF Parmentier, Vivien Guillot, Tristan Showman, Adam P. Fortney, Jonathan Marley, Mark BE Garcia, RA Ballot, J TI Characterizing exoplanets atmospheres with space photometry at optical wavelengths SO SPACE PHOTOMETRY REVOLUTION - COROT SYMPOSIUM 3, KEPLER KASC-7 JOINT MEETING SE EPJ Web of Conferences LA English DT Proceedings Paper CT Symposium 3 on Space Photometry Revolution - CoRoT / Kepler KASC-7 Joint Meeting CY JUL 06-11, 2014 CL Toulouse, FRANCE ID HOT JUPITERS; HD 209458B; IRRADIATED ATMOSPHERES; PHASE CURVES; MODEL AB Space photometry such as performed by Kepler and CoRoT provides exoplanets radius and phase curves with an exquisite precision. The phase curve constrains the longitudinal variation of the albedo and shed light on the horizontal distribution of clouds. The planet radius constraints thermal evolution of the planet, potentially unveiling its atmospheric composition. We present how the atmospheric circulation can affect the cloud distribution of three different planets, HD209458b, Kepler-7b and HD189733b based on three-dimensional models and analytical calculations. Then we use an analytical atmospheric model coupled to a state-of-the-art interior evolution code to study the role of TiO in shaping the thermal evolution and final radius of the planet. C1 [Parmentier, Vivien; Guillot, Tristan] Univ Nice Sophia Antipolis, Observ Cote Azur, Lab Lagrange, UMR 7293,CNRS, F-06304 Nice 04, France. [Parmentier, Vivien] Univ Arizona, Lunar & Planetary Lab, Dept Planetary Sci, Tucson, AZ 85721 USA. [Showman, Adam P.] Univ Calif Santa Cruz, Dept Astron & Astrophys, Santa Cruz, CA 95064 USA. [Marley, Mark] NASA, Ames Res Ctr, Mofett Field, CA 94035 USA. RP Parmentier, V (reprint author), Univ Nice Sophia Antipolis, Observ Cote Azur, Lab Lagrange, UMR 7293,CNRS, F-06304 Nice 04, France. EM vivien.parmentier@oca.eu NR 15 TC 0 Z9 0 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2015 VL 101 AR 02002 DI 10.1051/epjconf/201510102002 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BE5BE UT WOS:000372491300018 ER PT S AU Poppenhaeger, K AF Poppenhaeger, K. BE Garcia, RA Ballot, J TI Stellar magnetic activity - Star-Planet Interactions SO SPACE PHOTOMETRY REVOLUTION - COROT SYMPOSIUM 3, KEPLER KASC-7 JOINT MEETING SE EPJ Web of Conferences LA English DT Proceedings Paper CT Symposium 3 on Space Photometry Revolution - CoRoT / Kepler KASC-7 Joint Meeting CY JUL 06-11, 2014 CL Toulouse, FRANCE ID X-RAY-EMISSION; EXTRASOLAR GIANT PLANETS; EARTH-LIKE EXOPLANETS; EJECTION CME ACTIVITY; MAIN-SEQUENCE STARS; IN HABITABLE ZONES; MASS M-STARS; HOT JUPITERS; HOST STARS; ATMOSPHERIC ESCAPE AB Stellar magnetic activity is an important factor in the formation and evolution of exoplanets. Magnetic phenomena like stellar flares, coronal mass ejections, and high-energy emission affect the exoplanetary atmosphere and its mass loss over time. One major question is whether the magnetic evolution of exoplanet host stars is the same as for stars without planets; tidal and magnetic interactions of a star and its close-in planets may play a role in this. Stellar magnetic activity also shapes our ability to detect exoplanets with different methods in the first place, and therefore we need to understand it properly to derive an accurate estimate of the existing exoplanet population. I will review recent theoretical and observational results, as well as outline some avenues for future progress. C1 [Poppenhaeger, K.] Harvard Smithsonian Ctr Astrophys, 60 Garden St, Cambrigde, MA 02138 USA. [Poppenhaeger, K.] NASA, New York, NY USA. RP Poppenhaeger, K (reprint author), Harvard Smithsonian Ctr Astrophys, 60 Garden St, Cambrigde, MA 02138 USA. EM kpoppenhaeger@cfa.harvard.edu OI Poppenhaeger, Katja/0000-0003-1231-2194 NR 66 TC 1 Z9 1 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2015 VL 101 AR 05002 DI 10.1051/epjconf/201510105002 PG 6 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BE5BE UT WOS:000372491300033 ER PT S AU Van Eylen, V Lund, MN Aguirre, VS Arentoft, T Kjeldsen, H Albrecht, S Chaplin, WJ Isaacson, H Pedersen, MG Jessen-Hansen, J Tingley, B Christensen-Dalsgaard, J Aerts, C Campante, TL Bryson, ST AF Van Eylen, Vincent Lund, Mikkel N. Aguirre, Victor Silva Arentoft, Torben Kjeldsen, Hans Albrecht, Simon Chaplin, William J. Isaacson, Howard Pedersen, May G. Jessen-Hansen, Jens Tingley, Brandon Christensen-Dalsgaard, Jorgen Aerts, Conny Campante, Tiago L. Bryson, Steve T. BE Garcia, RA Ballot, J TI What asteroseismology can do for exoplanets SO SPACE PHOTOMETRY REVOLUTION - COROT SYMPOSIUM 3, KEPLER KASC-7 JOINT MEETING SE EPJ Web of Conferences LA English DT Proceedings Paper CT Symposium 3 on Space Photometry Revolution - CoRoT / Kepler KASC-7 Joint Meeting CY JUL 06-11, 2014 CL Toulouse, FRANCE ID STELLAR SPIN; HOST STARS; PLANETARY ORBITS; LIGHT-CURVE; OBLIQUITIES; SYSTEM; MISALIGNMENTS; INCLINATION; CANDIDATES; PARAMETERS AB We describe three useful applications of asteroseismology in the context of exoplanet science: (1) the detailed characterisation of exoplanet host stars; (2) the measurement of stellar inclinations; and (3) the determination of orbital eccentricity from transit duration making use of asteroseismic stellar densities. We do so using the example system Kepler-410 [1]. This is one of the brightest (V = 9.4) Kepler exoplanet host stars, containing a small (2.8 R-circle plus) transiting planet in a long orbit (17.8 days), and one or more additional non-transiting planets as indicated by transit timing variations. The validation of Kepler-410 (KOI-42) was complicated due to the presence of a companion star, and the planetary nature of the system was confirmed after analyzing a Spitzer transit observation as well as ground-based follow-up observations. C1 [Van Eylen, Vincent; Lund, Mikkel N.; Aguirre, Victor Silva; Arentoft, Torben; Kjeldsen, Hans; Albrecht, Simon; Pedersen, May G.; Jessen-Hansen, Jens; Tingley, Brandon; Christensen-Dalsgaard, Jorgen] Aarhus Univ, Dept Phys & Astron, Stellar Astrophys Ctr, Ny Munkegade 120, DK-8000 Aarhus C, Denmark. [Van Eylen, Vincent; Aerts, Conny] Katholieke Univ Leuven, Inst Sterrenkunde, B-3001 Heverlee, Belgium. [Albrecht, Simon] MIT, Dept Phys, Cambridge, MA 02139 USA. [Albrecht, Simon] MIT, Kavli Inst Astrophys & Space Res, Cambridge, MA 02139 USA. [Lund, Mikkel N.] Univ Sydney, Sch Phys, Sydney Inst Astron SIfA, Sydney, NSW 2006, Australia. [Chaplin, William J.; Campante, Tiago L.] Univ Birmingham, Sch Phys & Astron, Birmingham B15 2TT, W Midlands, England. [Isaacson, Howard] Univ Calif Berkeley, Dept Astron, Berkeley, CA 94820 USA. [Bryson, Steve T.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Van Eylen, V (reprint author), Aarhus Univ, Dept Phys & Astron, Stellar Astrophys Ctr, Ny Munkegade 120, DK-8000 Aarhus C, Denmark. EM vincent@phys.au.dk OI Lund, Mikkel Norup/0000-0001-9214-5642 NR 29 TC 1 Z9 1 U1 2 U2 2 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2015 VL 101 AR 02005 DI 10.1051/epjconf/201510102005 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BE5BE UT WOS:000372491300021 ER PT S AU White, TR Aguirre, VS Boyajian, T Creevey, O Huber, D von Braun, K Bedding, TR Elsworth, Y Hekker, S Stello, D Weiss, A AF White, T. R. Aguirre, V. Silva Boyajian, T. Creevey, O. Huber, D. von Braun, K. Bedding, T. R. Elsworth, Y. Hekker, S. Stello, D. Weiss, A. BE Garcia, RA Ballot, J TI Testing Asteroseismic Scaling Relations with Interferometry SO SPACE PHOTOMETRY REVOLUTION - COROT SYMPOSIUM 3, KEPLER KASC-7 JOINT MEETING SE EPJ Web of Conferences LA English DT Proceedings Paper CT Symposium 3 on Space Photometry Revolution - CoRoT / Kepler KASC-7 Joint Meeting CY JUL 06-11, 2014 CL Toulouse, FRANCE ID KEPLER STARS; CHARA ARRAY; PARAMETERS AB The asteroseismic scaling relations for the frequency of maximum oscillation power,.max, and the large frequency separation, Delta nu, provide an easy way to directly determine the masses and radii of stars with detected solar-like oscillations. With the vast amount of data available from the CoRoT and Kepler missions, the convenience of the scaling relations has resulted in their wide-spread use. But how valid are the scaling relations when applied to red giants, which have a substantially different structure than the Sun? Verifying the scaling relations empirically requires independent measurements. We report on the current state and future prospects of interferometric tests of the scaling relations. C1 [White, T. R.] Univ Gottingen, Inst Astrophys, Friedrich Hund Pl 1, D-37077 Gottingen, Germany. [Aguirre, V. Silva; Bedding, T. R.; Elsworth, Y.; Hekker, S.; Stello, D.] Aarhus Univ, Dept Phys & Astron, Stellar Astrophys Ctr, DK-8000 Aarhus C, Denmark. [Boyajian, T.] Yale Univ, Dept Astron, New Haven, CT 06520 USA. [Creevey, O.] Univ Paris 11, CNRS, UMR 8617, Inst Astrophys Spatiale, F-91405 Orsay, France. [Huber, D.] NASA Ames Res Ctr, Moffett Field, CA 94035 USA. [Huber, D.] SETI Inst, Mountain View, CA 94043 USA. [Huber, D.; Bedding, T. R.; Stello, D.] Univ Sydney, Sch Phys, SIfA, Sydney, NSW 2006, Australia. [von Braun, K.; Elsworth, Y.] MPIA, D-69117 Heidelberg, Germany. Univ Birmingham, Sch Phys & Astron, Birmingham B15 2TT, W Midlands, England. [Hekker, S.] Max Planck Inst Sonnensyst Forsch, D-37077 Gottingen, Germany. [Weiss, A.] Max Planck Inst Astrophys, D-85741 Garching, Germany. RP White, TR (reprint author), Univ Gottingen, Inst Astrophys, Friedrich Hund Pl 1, D-37077 Gottingen, Germany. EM twhite@astro.physik.uni-goettingen.de OI Boyajian, Tabetha/0000-0001-9879-9313 NR 10 TC 1 Z9 1 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2015 VL 101 AR 06068 DI 10.1051/epjconf/201510106068 PG 2 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BE5BE UT WOS:000372491300107 ER PT S AU Stevenazzi, S Nghiem, SV Masetti, M AF Stevenazzi, S. Nghiem, S. V. Masetti, M. GP IEEE TI URBAN IMPACTS ON AIR QUALITY OBSERVED WITH REMOTE SENSING AND GROUND STATION DATA FROM THE PO PLAIN FIELD CAMPAIGN SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE NO2; OMI; Ground stations; Urban areas; Po Plain AB The Po Plain area is one of the most urbanized and polluted regions in Europe, with the city of Milan being a major "hot spot" of nitrogen dioxide (NO2) in the world. The Po Plain Experiment Field Campaign has been carried out to identify and understand impacts of urban characteristics on the environment across the Po Plain in Northern Italy. Air quality is investigated with both remote sensing and ground station data. Preliminary results show a moderate correlation between satellite observations and ground-based measurements, highlighting the close relationship between the urban pattern and the distribution of NO2 all over the region. C1 [Stevenazzi, S.; Masetti, M.] Univ Milan, Dipartimento Sci Terra A Desio, Milan, Italy. [Nghiem, S. V.] CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Stevenazzi, S (reprint author), Univ Milan, Dipartimento Sci Terra A Desio, Milan, Italy. RI Masetti, Marco/N-6823-2013; OI MASETTI, MARCO/0000-0001-7961-8046 NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 73 EP 75 PG 3 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696700019 ER PT S AU Nghiem, SV AF Nghiem, S. V. GP IEEE TI GLOBAL MEGA URBANIZATION AND IMPACTS IN THE 2000S SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Urbanization; mega cities; Dense Sampling Method; satellite scatterometer AB The global mega urbanization and impacts in the decade of the 2000s are investigated under an interdisciplinary science research participated by 25 institutions and agencies from five countries in North America and Europe. Among multiple components of the research, the Dense Sampling Method with the Rosette Transform enables a new method to process coarse-resolution satellite scatterometer data into a 1-km posting to delineate urban extent on the basis of physical infrastructures, rather than arbitrary boundaries from political or administrative definitions. Scatterometer data from the QuikSCAT satellite are processed for all 29 mega cities across the world. Results reveal an urban mega agglomeration of connected cities along a swath extending over 450 km from the Pacific coast to the internal land. C1 [Nghiem, S. V.] CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Nghiem, SV (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA USA. NR 2 TC 0 Z9 0 U1 1 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 83 EP 85 PG 3 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696700022 ER PT S AU Milillo, P Perissin, D Lundgren, P Serio, C AF Milillo, Pietro Perissin, Daniele Lundgren, Paul Serio, Carmine GP IEEE TI COSMO-SKYMED VERY SHORT REPEAT-PASS SAR INTERFEROMETRY OVER RURAL AREAS: THE VAL D'AGRI AND POTENZA TEST CASES IN BASILICATA, ITALY. SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE InSAR; rural area; decorrelation; time-series analysis; Basilicata AB Over the last three decades interferometric synthetic aperture radar (InSAR) techniques have attained a fundamental role in surface deformation monitoring. The main importance is given by two key factors: the exploitement of rich SAR data archives and the development of processing techniques able to extract information from these datasets. InSAR time series techniques such as permanent scatterers (PS) or SBAS have proven capable of estimating displacements to with 1 mm precision for targets that show a stable electromagnetic signature. At the same time the availability of SAR constellations with a reduced revisit time, such as the X band COSMO-SkyMed (CSK) and TerraSAR-X/PAZ satellites, has reduced the minimum detectable deformation gradient between two neighboring points and improved the theoretical precision given for a network of selected stable pixels. Independently from the applied processing methodology, the main drawback at X-band is the shorter time interval to temporal decorrelation. This effect can be partially mitigated by a short repeat time acquisitions plan. A technique able to deal with distributed scatterers is fundamental for extending the spatial coverage of the coherent area. In this paper we analyze the potential of X-band COSMO-SkyMed short repeat pass interferometry over a rural area in the southern part of Italy for assessing the capabilities and limitations of the Quasi-PS (QPS) technique in an X-band non-optimal scenario. C1 [Milillo, Pietro; Serio, Carmine] Univ Basilicata, Sch Engn, I-85100 Potenza, Italy. [Milillo, Pietro; Lundgren, Paul] CALTECH, Jet Prop Lab, Pasadena, CA USA. [Milillo, Pietro] CALTECH, Seismol Lab, Pasadena, CA 91125 USA. [Perissin, Daniele] Purdue Univ, Dept Civil Engn, W Lafayette, IN 47907 USA. RP Milillo, P (reprint author), Univ Basilicata, Sch Engn, I-85100 Potenza, Italy. RI Perissin, Daniele/L-5423-2016 OI Perissin, Daniele/0000-0003-4086-8608 NR 17 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 98 EP 101 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696700026 ER PT S AU Osmanoglu, B Rincon, R Lee, S Fatoyinho, T Lagomasino, D AF Osmanoglu, Batuhan Rincon, Rafael Lee, SeungKuk Fatoyinho, Temilola Lagomasino, David GP IEEE TI RADIO FREQUENCY INTERFERENCE DETECTION AND MITIGATION TECHNIQUES: ECOSAR 2014 FLIGHT CAMPAIGN SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE RFI; SAR; Digital Beamforming AB Radio frequency interference (RFI) has strong influence on radar systems, especially for wideband airborne radars operating in the P-band (UHF). EcoSAR is a 435 MHz Synthetic Aperture Radar (SAR) system that employs a wideband digital beamforming architecture for the measurement of science parameters. RFI in EcoSAR measurements, degrades the quality of the SAR data and has to be removed from raw echoes. In this paper, we describe the current methodology used to mitigate RFI with EcoSAR, and provide an example on its performance. We also discuss the advantages and disadvantages of the proposed methods and discuss potential improvements. C1 [Osmanoglu, Batuhan; Lagomasino, David] Univ Space Res Assoc, Columbia, MD USA. [Osmanoglu, Batuhan; Rincon, Rafael; Lee, SeungKuk; Fatoyinho, Temilola; Lagomasino, David] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. RP Osmanoglu, B (reprint author), Univ Space Res Assoc, Columbia, MD USA. NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 124 EP 127 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696700033 ER PT S AU Wolfe, RE Duggan, B Aulenbach, SM Goldstein, JC Tilmes, C Buddenberg, A AF Wolfe, Robert E. Duggan, Brian Aulenbach, Steve M. Goldstein, Justin C. Tilmes, Curt Buddenberg, Andrew GP IEEE TI PROVIDING PROVENANCE TO INSTRUMENTS THROUGH THE US GLOBAL CHANGE INFORMATION SYSTEM SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Semantic Web; Provenance; Global Change; Climate AB The Global Change Information System was created by the US Global Change Research Program to provide specialists and the general public with accessible and usable global change related information. This system uses a relational and semantic web approach to describe the detailed provenance of global change information, such as "in report x, figure y is derived from dataset z". The system supported the development of the US Third National Climate Assessment, which was released in May 2014 and improves our understanding of climate change in the US. Over the last year, a partnership has been developed with the Committee on Earth Observing Satellites and now their database of missions, instruments and observations is being used to provide traceability to the specific platforms and instruments that support the assessment's findings and figures. C1 [Wolfe, Robert E.; Duggan, Brian; Aulenbach, Steve M.; Goldstein, Justin C.] US Global Change Res Program, New York, NY 10010 USA. [Wolfe, Robert E.; Tilmes, Curt] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. [Duggan, Brian; Aulenbach, Steve M.; Goldstein, Justin C.] Univ Corp Atmospher Res, Greenbelt, MD USA. [Buddenberg, Andrew] Natl Climat Ctr, New York, NY USA. RP Wolfe, RE (reprint author), US Global Change Res Program, New York, NY 10010 USA. RI Wolfe, Robert/E-1485-2012 OI Wolfe, Robert/0000-0002-0915-1855 NR 4 TC 1 Z9 1 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 143 EP 145 PG 3 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696700038 ER PT S AU Rincon, R Fatoyinbo, T Lee, S Osmanoglu, B Ranson, J Sun, GQ AF Rincon, Rafael Fatoyinbo, Temilola Lee, SeungKuk Osmanoglu, Batuhan Ranson, Jon Sun, Guoqing GP IEEE TI DIGITAL BEAMFORMING SYNTHETIC APERTURE RADAR (DBSAR): SINGLE-PASS INTERFEROMETRY FOR FOREST STRUCTURE ESTIMATION SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Digital Beamforming; SAR; InSAR AB Digital Beamforming permits the implementation of non-conventional measurement techniques, which can overcome fundamental limitations of conventional radar systems. In SAR systems, this technique can enable three-dimensional measurements using a single radar platform. A split phase center technique is implemented with NASA's digital beamforming SAR. The technique has the potential to provide volume structure estimates in tall forests and glaciers using a single radar platform. C1 [Rincon, Rafael; Fatoyinbo, Temilola; Lee, SeungKuk; Osmanoglu, Batuhan; Ranson, Jon; Sun, Guoqing] NASA, Goddard Space Flight Ctr, Greenblet, MD 20771 USA. [Osmanoglu, Batuhan] Univ Space Res Assoc, Columbia, MD USA. [Sun, Guoqing] Univ Maryland, Baltimore, MD USA. RP Rincon, R (reprint author), NASA, Goddard Space Flight Ctr, Greenblet, MD 20771 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 200 EP 202 PG 3 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696700053 ER PT S AU Riha, L Le Moigne, J El-Ghazawi, T AF Riha, Lubomir Le Moigne, Jacqueline El-Ghazawi, Tarek GP IEEE TI OPTIMIZATION OF SELECTED REMOTE SENSING ALGORITHMS FOR EMBEDDED NVIDIA KEPLER GPU ARCHITECTURE SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE remote sensing; GPU; Tegra K1; ACCA; dimension reduction AB This paper evaluates the potential of embedded Graphic Processing Units in the Nvidia's Tegra K1 for onboard processing. The performance is compared to a general purpose multi-core CPU and full fledge GPU accelerator. This study uses two algorithms: Wavelet Spectral Dimension Reduction of Hyperspectral Imagery and Automated Cloud-Cover Assessment (ACCA) Algorithm. Tegra K1 achieved 51% for ACCA algorithm and 20% for the dimension reduction algorithm, as compared to the performance of the high-end 8-core server Intel Xeon CPU with 13.5 times higher power consumption. C1 [Riha, Lubomir] VSB Tech Univ Ostrava, Natl Supercomp Ctr IT4Innovat, Ostrava, Czech Republic. [Le Moigne, Jacqueline] NASA, Goddard Space Flight Ctr, Software Engn Div, Greenbelt, MD USA. [El-Ghazawi, Tarek] George Washington Univ, High Performance Comp Lab, Ashburn, VA USA. RP Riha, L (reprint author), VSB Tech Univ Ostrava, Natl Supercomp Ctr IT4Innovat, Ostrava, Czech Republic. NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 529 EP 532 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696700134 ER PT S AU Beauchamp, RM Chandrasekar, V Vega, M AF Beauchamp, Robert M. Chandrasekar, V. Vega, Manuel GP IEEE TI NASA D3R LINEAR DEPOLARIZATION RATIO OBSERVATIONS AND A NEW ESTIMATION TECHNIQUE SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE radar; dual-frequency; NASA D3R; linear depolarization ratio; microphysics ID WEATHER RADARS; REFLECTIVITY AB The polarimetric radar parameter, linear depolarization ratio (LDR), provides microphysical insight into a scattering volume, particularly for mixed-phase and ice particles. A new estimator for improved estimation of LDR is presented. The NASA dual-frequency, dual-polarization, Doppler radar (D3R), which was recently upgraded to support operational linear depolarization ratio observations, was used as a testbed for evaluation of the new estimator. With D3R's Ku-band observations, the new LDR estimator is compared to conventional estimators and it is demonstrated that the new estimator is insensitive to attenuation, a number of radar system biases, and has increased immunity to noise for low SNR observations. C1 [Beauchamp, Robert M.; Chandrasekar, V.; Vega, Manuel] Colorado State Univ, Ft Collins, CO 80523 USA. [Vega, Manuel] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. RP Beauchamp, RM (reprint author), Colorado State Univ, Ft Collins, CO 80523 USA. NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 894 EP 897 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696701003 ER PT S AU Jacob, M Salemirad, M Jones, WL Biswas, S Cecil, D AF Jacob, Maria Salemirad, Matin Jones, W. Linwood Biswas, Sayak Cecil, Daniel GP IEEE TI VALIDATION OF RAIN RATE RETRIEVALS FOR THE AIRBORNE HURRICANE IMAGING RADIOMETER (HIRAD) SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Rain Rate; Brightness Temperature; HIRAD; HIWRAP; NEXRAD AB On board of the NASA's Global Hawk (AV1) aircraft there are two microwave, namely: the passive microwave Hurricane Imaging Radiometer (HIRAD), and the active microwave High-altitude Imaging Wind and Rain Airborne Profiler (HIWRAP). This paper presents results from an unplanned rain rate measurement validation opportunity that occurred in 2013, when the Global Hawk aircraft flew over an intense tropical squall-line that was simultaneously observed, by the Tampa NEXRAD meteorological radar. During this experiment, Global Hawk flying at an altitude of 18 km made 3 passes over the rapidly propagating thunderstorm, while the TAMPA NEXRAD perform volume scans on a 5-minute interval. NEXRAD 2D images of rain rate (mm/hr) were obtained at two altitudes (3 km & 6 km), which serve as surface truth for the HIRAD rain rate retrievals. In this paper, results are presented of the three-way inter-comparison of HIRAD Tb, HIWRAP dbZ and NEXRAD rain rate imagery. C1 [Jacob, Maria; Salemirad, Matin; Jones, W. Linwood] Univ Cent Florida, Cent Florida Remote Sensing Lab, Orlando, FL 32816 USA. [Biswas, Sayak; Cecil, Daniel] NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Jacob, M (reprint author), Univ Cent Florida, Cent Florida Remote Sensing Lab, Orlando, FL 32816 USA. EM maria.jacob@conae.gov.ar NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 902 EP 905 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696701005 ER PT S AU Castelletti, D Schroeder, DM Hensley, S Grima, C Ng, G Young, D Gim, Y Bruzzone, L Moussessian, A Blankenship, DD AF Castelletti, D. Schroeder, D. M. Hensley, S. Grima, C. Ng, G. Young, D. Gim, Yonggyu Bruzzone, L. Moussessian, A. Blankenship, D. D. GP IEEE TI CLUTTER DETECTION USING TWO-CHANNEL RADAR SOUNDER DATA SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Radar Sounder; Interferometry; Clutter Detection; Planetary Radar AB Surface clutter can corrupt both Earth and planetary Radar Sounder (RS) observations preventing definitive interpretation of subsurface features, which are often the primary interest of geologists and planetary scientists. Clutter is usually detected by manual or automatic techniques that require ancillary information about the topography of the surface. However, this topography information is not always available. In this paper, we propose a novel method for clutter detection that is independent from ancillary information. This method uses a two channel RS system to exploit the cross-channel interferometric phase difference and is made up three main steps: i) feature extraction and theoretical phase difference estimation, ii) RS interferogram formation and iii) comparison of theoretical and real phase difference distributions. The proposed method has been validated on RS data acquired in Greenland. C1 [Castelletti, D.; Bruzzone, L.] Univ Trento, Dept Informat Engn & Comp Sci, I-38123 Trento, Italy. [Schroeder, D. M.; Hensley, S.; Gim, Yonggyu; Moussessian, A.] CALTECH, Jet Prop Lab, Pasadena, CA USA. [Grima, C.; Ng, G.; Young, D.; Blankenship, D. D.] Univ Texas Austin, Inst Geophys, Austin, TX 78712 USA. RP Castelletti, D (reprint author), Univ Trento, Dept Informat Engn & Comp Sci, I-38123 Trento, Italy. RI Young, Duncan/G-6256-2010 OI Young, Duncan/0000-0002-6866-8176 NR 7 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 1052 EP 1055 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696701043 ER PT S AU Murphy, JM Le Moigne, J AF Murphy, James M. Le Moigne, Jacqueline GP IEEE TI SHEARLET FEATURES FOR REGISTRATION OF REMOTELY SENSED MULTITEMPORAL IMAGES SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Image registration; shearlets; wavelets; multitemporal images; Landsat AB We investigate the role of anisotropic feature extraction methods for automatic image registration of remotely sensed multitemporal images. Building on the classical use of wavelets in image registration, we develop an algorithm based on shearlets, a mathematical generalization of wavelets that offers increased directional sensitivity. Experimental results on multitemporal Landsat images are presented, which indicate superior performance of the shearlet algorithm when compared to classical wavelet algorithms. C1 [Murphy, James M.] Univ Maryland, College Pk, MD 20742 USA. [Murphy, James M.; Le Moigne, Jacqueline] NASA, Goddard Space Flight Ctr, Washington, DC USA. RP Murphy, JM (reprint author), Univ Maryland, College Pk, MD 20742 USA. NR 12 TC 1 Z9 1 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 1084 EP 1087 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696701051 ER PT S AU Polverari, F Marzano, FS Pulvirenti, L Pierdicca, N Hristova-Veleva, SM Turk, FJ AF Polverari, F. Marzano, F. S. Pulvirenti, L. Pierdicca, N. Hristova-Veleva, S. M. Turk, F. J. GP IEEE TI MODELING OCEAN WAVE SURFACE TO SIMULATE SPACEBORNE SCATTEROMETER OBSERVATIONS IN PRESENCE OF RAIN SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Modeling; ocean surface; rain; scatterometry; spectrum; wind ID WIND; SPECTRUM AB Spaceborne scatterometer observations, especially at Ku-band, are affected by rain in several ways and these effects need to be corrected to avoid errors in wind retrievals. In this work we propose a model to derive the surface backscattering coefficient in presence of both wind and rain. Our approach consists in the development of an ocean surface wind wave spectrum accounting for two effects due to raindrops impact on the surface: the rain-induced wave damping and the generation of ring waves. The results show that this extended spectrum is able to model the ocean surface wave modifications due to rain so that it can be used for further study in physically representing the scatterometer observations in presence of both wind and rain. C1 [Polverari, F.; Marzano, F. S.; Pulvirenti, L.; Pierdicca, N.] Univ Roma La Sapienza, DIET, Piazzale Aldo Moro 5, I-00185 Rome, Italy. [Polverari, F.; Marzano, F. S.] Univ Aquila, CETEMPS, I-67100 Laquila, Italy. [Pulvirenti, L.] CIMA Res Fdn, Savona, Italy. [Hristova-Veleva, S. M.; Turk, F. J.] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Polverari, F (reprint author), Univ Roma La Sapienza, DIET, Piazzale Aldo Moro 5, I-00185 Rome, Italy. NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 1203 EP 1206 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696701081 ER PT S AU Hristova-Veleva, SM Rodriguez, E Haddad, Z Stiles, B Turk, FJ AF Hristova-Veleva, S. M. Rodriguez, E. Haddad, Z. Stiles, B. Turk, F. J. GP IEEE TI HADLEY CELL TRENDS AND VARIABILITY AS DETERMINED FROM SCATTEROMETER OBSERVATIONS: HOW RAPIDSCAT WILL HELP ESTABLISHING RELIABLE LONG-TERM RECORD. SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Hadley cell; ocean surface winds; scatterometry AB Recent evidence suggests that the tropics have expanded over the last few decades by a very rough 10 per decade. Until now, understanding the mechanisms of that expansion has been confined to models and proxies because of the unavailability of systematic observations of the large-scale circulation. Scatterometer-derived ocean surface vector winds, provide for the first time, an accurate depiction of the large-scale circulation and allow the study of the Hadley cell evolution through analysis of its surface branch. In this study we determine the extent of the Hadley cell as defined by the subtropical zero-crossing of the zonally-averaged zonal wind component. We use scatterometer observations from a number of missions, covering similar to 13 years. Our analyses reveal seasonal and interannual variability, as well as a long-term trend for expansion of the Hadley cell width. More interestingly, our results show an apparent discontinuity in the signal when the data source changes from one observing system to another. This raises the question about the significance of the unresolved diurnal signal. Indeed, analyses of observations from tandem missions support this notion. Fortunately, the RapidScat mission makes it possible to resolve, for the first time, the details of the diurnal signal. Our preliminary analyses of the RapidScat observations show the presence of a clear semidiurnal signal in the width of the Hadley cell. This helps explain previously found discrepancies. More importantly, this points to a clear need to understand and resolve the diurnal signal before merging wind observations from different missions to form a consistent climate record. C1 [Hristova-Veleva, S. M.; Rodriguez, E.; Haddad, Z.; Stiles, B.; Turk, F. J.] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Hristova-Veleva, SM (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 1211 EP 1214 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696701083 ER PT S AU Bruzzone, L Plaut, JJ Alberti, G Blankenship, DD Bovolo, F Campbell, BA Castelletti, D Gim, Y Ilisei, AM Kofman, W Komatsu, G McKinnon, W Mitri, G Moussessian, A Notarnicola, C Orosei, R Patterson, GW Pettinelli, E Plettemeier, D AF Bruzzone, L. Plaut, J. J. Alberti, G. Blankenship, D. D. Bovolo, F. Campbell, B. A. Castelletti, D. Gim, Y. Ilisei, A. M. Kofman, W. Komatsu, G. McKinnon, W. Mitri, G. Moussessian, A. Notarnicola, C. Orosei, R. Patterson, G. W. Pettinelli, E. Plettemeier, D. GP IEEE TI JUPITER ICY MOON EXPLORER (JUICE): ADVANCES IN THE DESIGN OF THE RADAR FOR ICY MOONS (RIME) SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE radar sounder; ice penetrating radar; radar design; RIME; JUICE; icy moons; Jovian system; planetary exploration AB This paper presents the Radar for Icy Moon Exploration (RIME) that is a fundamental payload in the Jupiter Icy Moon Explorer (JUICE) mission of the European Space Agency (ESA). RIME is a radar sounder aimed to study the subsurface of Jupiter's icy moons Ganymede, Europa and Callisto. The paper illustrates the main goals of RIME, its architecture and parameters and some recent advances in its design. C1 [Bruzzone, L.; Castelletti, D.; Ilisei, A. M.] Univ Trento, Dept Informat Engn & Comp Sci, Trento, Trento, Italy. [Plaut, J. J.; Gim, Y.; Moussessian, A.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. [Alberti, G.] CORISTA, Naples, Italy. [Blankenship, D. D.; Pettinelli, E.] Univ Texas Austin, Inst Geophys, Austin, TX 78712 USA. [Bovolo, F.] Fdn Bruno Kessler, Ctr Informat & Commun Technol, Trento, Trento, Italy. [Campbell, B. A.] Smithsonian Inst, Ctr Earth & Planetary Studies, Washington, DC 20560 USA. [Kofman, W.] Inst Planetol & Astrophys Grenoble IPAG CNRS UJF, Grenoble, France. [Komatsu, G.] Univ G dAnnunzio, Int Res Sch Planetary Sci, Pescara, Italy. [McKinnon, W.] Washington Univ, St Louis, MO USA. [Mitri, G.] Univ Nantes, Lab Planetol & Geodynam, Nantes, France. [Notarnicola, C.] EURAC, Bolzano, Italy. [Orosei, R.] INAF IRA, Bologna, Italy. [Patterson, G. W.] Johns Hopkins Univ, Appl Phys Lab, Laurel, MD USA. Univ Roma Tre, Rome, Italy. [Plettemeier, D.] Tech Univ Dresden, D-01062 Dresden, Germany. RP Bruzzone, L (reprint author), Univ Trento, Dept Informat Engn & Comp Sci, Trento, Trento, Italy. EM lorenzo.bruzzone@ing.unitn.it RI Komatsu, Goro/I-7822-2012; Patterson, Gerald/E-7699-2015 OI Komatsu, Goro/0000-0003-4155-108X; NR 4 TC 1 Z9 1 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 1257 EP 1260 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696701094 ER PT S AU Peral, E Tanelli, S Haddad, Z Sy, O Stephens, G Im, E AF Peral, Eva Tanelli, Simone Haddad, Ziad Sy, Ousmane Stephens, Graeme Im, Eastwood GP IEEE TI RAINCUBE: A PROPOSED CONSTELLATION OF PRECIPITATION PROFILING RADARS IN CUBESAT SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE precipitation; radar; cubesat; weather AB Numerical climate and weather models depend on measurements from space-borne satellites to complete model validation and improvements. Precipitation profiling capabilities are currently limited to a few instruments deployed in Low Earth Orbit (LEO), which cannot provide the temporal resolution necessary to observe the evolution of short time-scale weather phenomena and improve numerical weather prediction models. A constellation of precipitation profiling instruments in LEO would provide this essential capability, but the cost and timeframe of typical satellite platforms and instruments make this solution prohibitive. A new radar instrument architecture that is compatible with low-cost satellite platforms, such as CubeSats and SmallSats, has been designed at JPL that enables constellation missions, which could revolutionize climate science and weather forecasting. C1 [Peral, Eva; Tanelli, Simone; Haddad, Ziad; Sy, Ousmane; Stephens, Graeme; Im, Eastwood] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Peral, E (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. NR 8 TC 1 Z9 1 U1 1 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 1261 EP 1264 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696701095 ER PT S AU Jedlovec, G Bjorgo, E Burn, A AF Jedlovec, Gary Bjorgo, Einar Burn, Anthony GP IEEE TI TRANSITIONING EARTH REMOTE SENSING DATA TO BENEFIT SOCIETY: A PARADIGM FOR A CENTER OF EXCELLENCE SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE remote sensing; transition to application; societal benefit AB A conceptual organization for a Center of Excellence to facilitate the development, transition, and utilization of Earth remote sensing observations for humanitarian applications by the broader international community is presented and discussed. The organization and functionality of the Center of Excellence eliminates many of the current limitations on the broader use of Earth remote sensing data for these applications. Examples of such organizations are presented along with domestic and international applications. C1 [Jedlovec, Gary] NASA, Washington, DC USA. [Bjorgo, Einar] United Nations Inst Training & Res UNITAR, Geneva, Switzerland. [Burn, Anthony] Ctr Adv Sci Space CASIS, Washington, DC USA. RP Jedlovec, G (reprint author), NASA, Washington, DC USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 1273 EP 1275 PG 3 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696701098 ER PT S AU Srivastava, PK O'Neill, P Cosh, M Lang, R Joseph, A AF Srivastava, Prashant K. O'Neill, Peggy Cosh, Michael Lang, Roger Joseph, Alicia GP IEEE TI EVALUATION OF RADAR VEGETATION INDICES FOR VEGETATION WATER CONTENT ESTIMATION USING DATA FROM A GROUND-BASED SMAP SIMULATOR SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Vegetation Water Content; Microwave Polarization Difference Index; Radar; Radiometer; Vegetation Indices ID SOIL-MOISTURE AB Vegetation water content (VWC) is an important component of microwave soil moisture retrieval algorithms. This paper aims to estimate VWC using L band active and passive radar/radiometer datasets obtained from a NASA ground-based Soil Moisture Active Passive (SMAP) simulator known as ComRAD (Combined Radar/Radiometer). Several approaches to derive vegetation information from radar and radiometer data such as HH, HV, VV, Microwave Polarization Difference Index (MPDI), HH/VV ratio, HV/(HH+VV), HV/(HH+HV+VV) and Radar Vegetation Index (RVI) are tested for VWC estimation through a generalized linear model (GLM). The overall analysis indicates that HV radar backscattering could be used for VWC content estimation with highest performance followed by HH, VV, MPDI, RVI, and other ratios. C1 [Srivastava, Prashant K.; O'Neill, Peggy; Joseph, Alicia] NASA, Goddard Space Flight Ctr, Hydrol Sci Lab, Code 617, Greenbelt, MD 20771 USA. [Srivastava, Prashant K.] Univ Maryland, Earth Syst Sci Interdisciplinary Ctr, Baltimore, MD USA. [Cosh, Michael] ARS, Hydrol & Remote Sensing Lab, USDA, Beltsville, MD 20705 USA. [Lang, Roger] George Washington Univ, Dept Elect & Comp Engn, Washington, DC USA. RP O'Neill, P (reprint author), NASA, Goddard Space Flight Ctr, Hydrol Sci Lab, Code 617, Greenbelt, MD 20771 USA. EM Peggy.E.ONeill@nasa.gov NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 1296 EP 1299 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696701104 ER PT S AU Jagdhuber, T Entekhabi, D Hajnsek, I Konings, AG McColl, KA Alemohammad, SH Das, NN Montzka, C AF Jagdhuber, T. Entekhabi, D. Hajnsek, I. Konings, A. G. McColl, K. A. Alemohammad, S. H. Das, N. N. Montzka, C. GP IEEE TI PHYSICALLY-BASED ACTIVE-PASSIVE MODELLING AND RETRIEVAL FOR SMAP SOIL MOISTURE INVERSION ALGORITHM SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE SMAP; active-passive microwave fusion; soil moisture; physical-based retrieval; beta-parameter AB The NASA Soil Moisture Active Passive (SMAP) mission is designed to produce high-resolution (9 km) global mapping of surface soil moisture based on L-band radar and radiometer measurements. The multi-scale measurements are combined using time-series of active passive microwave data to retrieve the statistical regression parameters (alpha, beta) from successive overpasses. In this study, we introduce a physically-based forward model as well as data-based retrieval of the beta-parameter. The forward model stems from analyses of the scattering and loss terms occurring during bare and vegetated soil scattering/emission and allows a physically-based modelling of the beta-parameter. This provides possibilities to analyze the different influences of soil roughness as well as vegetation structure and moisture on the beta-parameter under different environmental conditions. In addition, a physically-based retrieval of beta from one active-passive SMAP acquisition couple is proposed, circumventing lengthy time-series regressions. The key operation enabling a single-pass retrieval of the beta-parameter is the vegetation correction of the backscatter signal. This can be achieved by use of the measured cross-polarized backscatter signal together with an appropriate polarimetric vegetation volume model. C1 [Jagdhuber, T.; Hajnsek, I.] German Aerosp Ctr, Microwaves & Radar Inst, POB 1116, Wessling 82234, Germany. [Entekhabi, D.; Konings, A. G.; McColl, K. A.; Alemohammad, S. H.] MIT, Parsons Lab, Cambridge, MA 02139 USA. [Hajnsek, I.] ETH, Inst Environm Engn, CH-8093 Zurich, Switzerland. [Das, N. N.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. [Montzka, C.] Res Ctr Julich, Inst Bio & Geosci Agrosphere, D-52428 Julich, Germany. RP Jagdhuber, T (reprint author), German Aerosp Ctr, Microwaves & Radar Inst, POB 1116, Wessling 82234, Germany. EM thomas.jagdhuber@dlr.de; darae@mit.edu; irena.hajnsek@dlr.de; konings@mit.edu; kmccoll@mit.edu; hamed_al@mit.edu; narendra.n.das@jpl.nasa.gov; c.montzka@fz-juelich.de RI Alemohammad, Seyed Hamed/F-1292-2014 OI Alemohammad, Seyed Hamed/0000-0001-5662-3643 NR 10 TC 0 Z9 0 U1 1 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 1300 EP 1303 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696701105 ER PT S AU Tilmes, C Privette, AP Chen, J Ramachandran, R Bugbee, KM Wolfe, RE AF Tilmes, Curt Privette, Ana Pinheiro Chen, Jeffrey Ramachandran, Rahul Bugbee, Kaylin M. Wolfe, Robert E. GP IEEE TI LINKING FROM OBSERVATIONS TO DATA TO ACTIONABLE SCIENCE IN THE CLIMATE DATA INITIATIVE SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Information Management; Knowledge Representation; Semantic Web ID PROVENANCE AB A tremendous amount of Earth and Climate related data and information are available from the U.S. Federal government. Among the proposed actions of the President's Climate Action Plan are several efforts to foster the use of existing data to encourage development of additional data products and tools that can be used to improve community resilience and prepare for the impacts of climate change. Building on previous efforts to organize the presentation of this material from Federal web pages and data centers, the Climate Data Initiative is working together with other related efforts to link Earth observation systems through to data resulting from them and on to related web pages, case studies, decision making tools, and other relevant content. Often such information is not located in a single web site, data center, or even a single agency, but distributed across the Federal Government. Linking such information across the breadth of interagency holdings can increase understanding of the complexity of those holdings and their inter-relationships and allow a more cohesive presentation of all of the material. C1 [Tilmes, Curt; Wolfe, Robert E.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Privette, Ana Pinheiro] Climate Data Solut LLC, Asheville, NC 28816 USA. [Chen, Jeffrey] NASA Headquarters, Washington, DC 20456 USA. [Ramachandran, Rahul; Bugbee, Kaylin M.] NASA, Marshall Space Flight Ctr, Huntsville, AL 35811 USA. RP Tilmes, C (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RI Wolfe, Robert/E-1485-2012 OI Wolfe, Robert/0000-0002-0915-1855 NR 7 TC 1 Z9 1 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 1354 EP 1357 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696701118 ER PT S AU Chandrasekar, V Beauchamp, RM Chen, HN Vega, M Schwaller, M Petersen, W Wolff, D AF Chandrasekar, V. Beauchamp, Robert M. Chen, Haonan Vega, Manuel Schwaller, Mathew Petersen, Walter Wolff, David GP IEEE TI DEPLOYMENT AND PERFORMANCE OF NASA D3R DURING GPM IPHEX FIELD CAMPAIGN SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE GPM; ground validation; D3R; dual-polarization; radar; IPHEx; multi-frequency AB In order to investigate how well observations from precipitation-monitoring satellites match up to the best estimate of the true precipitation measured at ground level and how to use the collected precipitation data to evaluate models that describe and predict the hydrology, the Integrated Precipitation and Hydrology Experiment (IPHEx) was conducted in the southern Appalachian Mountains in the eastern United States from May 1 to June 15, 2014. The NASA dual-frequency dual-polarization Doppler radar (D3R), co-located with NASA NPOL radar, was deployed as part of the IPHEx field campaign to characterize precipitation properties at Ku-and Ka-band frequencies. This paper presents the deployment and performance of D3R during the IPHEx field experiment. Sample observations will be presented, with particular attention paid to cross-comparison between D3R and NPOL. C1 [Chandrasekar, V.; Beauchamp, Robert M.; Chen, Haonan; Vega, Manuel; Schwaller, Mathew] Colorado State Univ, Ft Collins, CO 80523 USA. [Vega, Manuel] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. [Petersen, Walter; Wolff, David] NASA, Wallops Flight Facil, Wallops Isl, VA USA. RP Chandrasekar, V (reprint author), Colorado State Univ, Ft Collins, CO 80523 USA. OI Chen, Haonan/0000-0002-9795-3064 NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 2622 EP 2625 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696702182 ER PT S AU Rincon, R Fatoyinbo, T Osmanoglu, B Lee, SK Ranson, KJ Marrero, V Yeary, M AF Rincon, Rafael Fatoyinbo, Temilola Osmanoglu, Batuhan Lee, Seung-Kuk Ranson, K. Jon Marrero, Victor Yeary, Mark GP IEEE TI NEXT GENERATION DIGITAL BEAMFORMING SYNTHETIC APERTURE RADAR (DBSAR-2) SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Digital Beamforming; interferometry SAR; InSAR AB The second generation Digital Beamforming SAR (DBSAR-2) is a state-of-the-art airborne L-band radar being developed at the NASA Goddard Space Flight Center (GSFC). The instrument employs a 16-channel radar architecture characterized by multi-mode operation, software defined waveform generation, digital beamforming, and configurable radar parameters. The instrument has been design to support several disciplines in Earth and Planetary sciences. This technology seeks to establish the Next Generation SAR as a science instrument while setting a path future airborne and spaceborne SAR missions. C1 [Rincon, Rafael; Fatoyinbo, Temilola; Osmanoglu, Batuhan; Lee, Seung-Kuk; Ranson, K. Jon; Marrero, Victor] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. [Osmanoglu, Batuhan] Univ Space Res Assoc, Columbia, MD USA. [Yeary, Mark] Univ Oklahoma, Norman, OK 73019 USA. RP Rincon, R (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. NR 6 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 2774 EP 2777 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696702220 ER PT S AU Kim, DJ Hensley, S Yun, SH AF Kim, Duk-jin Hensley, Scott Yun, Sang-Ho GP IEEE TI ROBUST CHANGE DETECTION IN URBAN AREA USING MULTI-TEMPORAL POLARIMETRIC UAVSAR DATA SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Change detection; polarimetry; UAVSAR; urban; multi-temporal ID IMAGERY AB SAR change detection is useful when emergency situations occurred and weather conditions are unfavourable. In this study, a change detection using multi-temporal polarimetric UAVSAR data was investigated in urban environment. The most robust polarimetric parameter was evaluated, and change detction techniques using maximum likelihood ratio and hyperbolic tanget function were applied to the selected parameters. The comparison results with Google Earth's historical images showed a quite good agreement. A fitting of hyperbolic tangent function to the multi-temporal polarimetric parameters much reduced the false alarm rate, and it also provide whether the building was constructed or destructed and when the the changes occurred. C1 [Kim, Duk-jin; Hensley, Scott; Yun, Sang-Ho] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. [Kim, Duk-jin] Seoul Natl Univ, Sch Earth & Environm Sci, Seoul 151, South Korea. RP Kim, DJ (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. NR 8 TC 0 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 2801 EP 2804 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696702227 ER PT S AU Lee, SK Fatoyinbo, T Lagomasino, D Osmanoglu, B Simard, M Trettin, C Rahman, M Ahmed, M AF Lee, Seung-Kuk Fatoyinbo, Temilola Lagomasino, David Osmanoglu, Batuhan Simard, Marc Trettin, Carl Rahman, Mizanur Ahmed, Miran GP IEEE TI LARGE-SCALE MANGROVE CANOPY HEIGHT MAP GENERATION FROM TANDEM-X DATA BY MEANS OF POL-INSAR TECHNIQUES SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Mangrove; canopy height; Sundarbans; Pol-InSAR; TanDEM-X ID POLARIMETRIC SAR INTERFEROMETRY AB Mangroves are among the most-carbon rich forest in subtropics and tropics, containing on average 1,023 Mg carbon per hectare [1]. In order to better estimate mangrove biomass, carbon dynamics and land coverage changes, mangrove canopy height is a key parameter. However, there is a surprisingly absence of information needed for global-scale mangrove height mapping because of the lack of high spatial resolution data, available spaceborne data sets, and modeling techniques. In recent studies, the first single-pass TanDEM-X data showed a great possibility of mangrove canopy height estimate with accuracies comparable to airborne lidar canopy height model with single- and dual-Pol-InSAR techniques. Based on the method mentioned in [2], we here generated large-scale mangrove canopy height map with a 12-m spatial resolution over Sundarbans, the world largest mangrove forest, from existing global TDX acquisitions. The inversion result for mangrove canopy height was validated against field measurement data; a correlation coefficient of 0.852 and a RMSE of 0.774 m. C1 [Lee, Seung-Kuk; Fatoyinbo, Temilola; Lagomasino, David; Osmanoglu, Batuhan] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Simard, Marc] NASA, Jet Prop Lab, Greenbelt, MD 20771 USA. [Trettin, Carl] US Forest Serv, USDA, Washington, DC USA. [Rahman, Mizanur] Ctr Environm & Geog Informat Serv, Dhaka, Bangladesh. [Ahmed, Miran] Bangladesh Forest Dept, Dhaka, Bangladesh. RP Lee, SK (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. OI Simard, Marc/0000-0002-9442-4562 NR 11 TC 0 Z9 0 U1 3 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 2895 EP 2898 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696702251 ER PT S AU Sainath, K Bringer, A Teixeira, F Hensley, S AF Sainath, K. Bringer, A. Teixeira, F. Hensley, S. GP IEEE TI INSAR COHERENCE DUE TO REMOTE SENSING OF LOW-LOSS, GUIDING PLANAR-LAYERED GEOPHYSICAL MEDIA USING H-POLARIZED MICROWAVES SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Radar interferometry; radar remote sensing; synthetic aperture radar ID RADAR INTERFEROMETRY; PENETRATION AB We propose a planar-layered medium-based radar backscatter model to predict coherence trends, in Interferometric Synthetic Aperture Radar (InSAR) images, manifest when interrogating planar-layered dielectric geophysical subsurfaces. This InSAR coherence model improves upon past ones in two ways: Incorporation of "multi-bounce", arising from the guidance behavior of minimally-attenuating and high-contrast dielectric slabs, as well as azimuthal deviation in antenna pointing. Including the former renders this model especially suitable for analyzing coherence modifications (decorrelation and phase bias) arising from remote sensing of low-attenuating targets (e.g., dry soil), which augments applicability to high-attenuating targets (e.g., wet, salty soils) readily analyzed with many traditional InSAR models. Representing the model's key contributions, we discuss two predicted trends: Namely, in the limit of a perfectly guiding dielectric slab (i.e., zero attenuation and infinite dielectric contrast), the interferometric correlation is inversely proportional to the InSAR perpendicular baseline length and the phase bias linearly diverges. C1 [Sainath, K.; Bringer, A.; Teixeira, F.] Ohio State Univ, Electrosci Lab, Columbus, OH 43212 USA. [Hensley, S.] CALTECH, NASA Jet Prop Lab, Pasadena, CA 91109 USA. RP Sainath, K (reprint author), Ohio State Univ, Electrosci Lab, Columbus, OH 43212 USA. EM sainath.1@osu.edu; shensley@jpl.nasa.gov NR 12 TC 2 Z9 2 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 2979 EP 2982 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696703017 ER PT S AU Jo, MJ Jung, HS Won, JS Lundgren, P AF Jo, Min-Jeong Jung, Hyung-Sup Won, Joong-Sun Lundgren, Paul GP IEEE TI AN EMPIRICAL MODEL FOR MEASUREMENT ACCURACY OF ALONG-TRACK DEFORMATION BY ADVANCED MULTIPLE-APERTURE SAR INTERFEROMETRY FROM COSMO-SKYMED DATASET SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE multiple aperture SAR interferometry; Measurement accuracy; empirical uncertainty model; COSMO-SkyMed; Kamoamoa fissure eruption ID KILAUEA VOLCANO; ERUPTION; HAWAII AB Despite several studies using the multiple-aperture interferometry (MAI) technique, X-band SAR has rarely been applied to MAI-based studies due to their shorter decorrelation timescale. However, the relatively short antenna length and high temporal resolution of the COSMO-SkyMed X-band SAR system provides an opportunity to measure the precise displacement in the along-track direction. In this study, we have assessed the MAI performance in comparison with GPS and established an empirical uncertainty model of MAI measurements with respect to interferometric coherence. It enables us to confirm the difference between theoretical and practical uncertainties of the MAI method. Moreover, this study will be helpful for evaluating the reliability of MAI measurements where GPS data are unavailable. C1 [Jo, Min-Jeong; Won, Joong-Sun] Yonsei Univ, Dept Earth Syst Sci, Seoul 120749, South Korea. [Jung, Hyung-Sup] Univ Seoul, Dept Geoinformat, Seoul, South Korea. [Lundgren, Paul] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Jo, MJ (reprint author), Yonsei Univ, Dept Earth Syst Sci, Seoul 120749, South Korea. EM owen009@yonsei.ac.kr NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 2987 EP 2990 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696703018 ER PT S AU Austerberry, D Gaier, T Kangaslahti, P Lambrigtsen, B McKague, D Ramos, I Ruf, C Tanner, A AF Austerberry, David Gaier, Todd Kangaslahti, Pekka Lambrigtsen, Bjorn McKague, Darren Ramos, Isaac Ruf, Chris Tanner, Alan GP IEEE TI TEST METHODOLOGY FOR THE GEOSTAR CORRELATOR SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE correlator; digital; ASIC; GeoSTAR AB Proposed approaches to the NRC Earth Science Decadal Survey's Precipitation, All-Weather Temperature, and Humidity (PATH) mission involving synthetic aperture arrays require massively parallel, high speed correlators implemented on a geostationary satellite platform. We present testing methodology for a coarse digital correlator chip using a low-power ASIC architecture. The chip was designed in the Electrical Engineering and Computer Science Department of the University of Michigan. These tests precede the integration of the chip into a Geostationary Synthetic Thinned Aperture Array (GeoSTAR) instrument prototype in development at NASA's Jet Propulsion Laboratory. C1 [Austerberry, David; McKague, Darren; Ruf, Chris] Univ Michigan, Ann Arbor, MI 48109 USA. [Gaier, Todd; Kangaslahti, Pekka; Lambrigtsen, Bjorn; Ramos, Isaac; Tanner, Alan] Jet Prop Lab, Pasadena, CA 91109 USA. RP Austerberry, D (reprint author), Univ Michigan, Ann Arbor, MI 48109 USA. RI McKague, Darren/J-2590-2012 OI McKague, Darren/0000-0003-0297-0388 NR 5 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 3473 EP 3476 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696703143 ER PT S AU Bradley, DC Schoenwald, AJ Wong, M Mohammed, PN Piepmeier, JR AF Bradley, Damon C. Schoenwald, Adam J. Wong, Mark Mohammed, Priscilla N. Piepmeier, Jeffrey R. GP IEEE TI WIDEBAND DIGITAL SIGNAL PROCESSING TEST-BED FOR RADIOMETRIC RFI MITIGATION SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Interference; Circularity; Complex Random Process; Radiometer; Digital Receiver; SERDES AB RFI is a persistent and growing problem experienced by spaceborne microwave radiometers. Recent missions such as SMOS, SMAP, and GPM have all detected RFI in L, C, X, and K bands. To proactively deal with this issue, microwave radiometers must include digital back-end processors that generate data products that facilitate the detection and excision of RFI from desired brightness temperature measurements. The wideband digital signal processing testbed is a platform that allows rapid development of various RFI detection and mitigation algorithms using digital hardware akin to that which might be used for final spaceflight implementation. On it, we evaluate an improved version of the SMAP RFI Digital Signal Processor (DSP) that utilizes the new complex signal kurtosis algorithm as opposed to the real signal kurtosis that is used on the SMAP radiometer. In addition, we show how we scale the DSP to operate at 8.3 times the bandwidth of the SMAP radiometer for operation in K-band. C1 [Bradley, Damon C.; Schoenwald, Adam J.; Wong, Mark; Mohammed, Priscilla N.; Piepmeier, Jeffrey R.] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. RP Bradley, DC (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. NR 10 TC 2 Z9 2 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 3489 EP 3492 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696703147 ER PT S AU Delbridge, B Burgmann, R Fielding, E Hensley, S AF Delbridge, Brent Buergmann, Roland Fielding, Eric Hensley, Scott GP IEEE TI KINEMATICS OF THE SLUMGULLION LANDSLIDE FROM UAVSAR DERIVED INTERFEROGRAMS SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE AB In order to measure the response of the Slumgullion landslide to hydraulic forcing, we utilize the unique capabilities of the NASA/JPL's UAVSAR airborne repeat-pass SAR interferometry system to provide surface geodetic measurements with "landslide-wide" spatial coverage. Unlike traditional space-based INSAR we are not restricted to fixed flight tracks or fixed repeat times, allowing for optimal imaging geometries and timing. We combine four look directions chosen based on the landslide geometry and invert for the full 3-D landslide-wide surface de-formation. These observations complement ongoing GPS measurements and in-situ observations of pore-pressure and atmospheric parameters acquired by the U.S. Geological Survey. C1 [Delbridge, Brent; Buergmann, Roland] Univ Calif Berkeley, Berkeley, CA 94720 USA. [Fielding, Eric; Hensley, Scott] NASA, Jet Prop Lab, Pasadena, CA USA. RP Delbridge, B (reprint author), Univ Calif Berkeley, Berkeley, CA 94720 USA. NR 7 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 3842 EP 3845 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696703236 ER PT S AU Middleton, EM Julitta, T Campbell, PE Huemmrich, KF Schickling, A Rossini, M Cogliati, S Landis, DR Alonso, L AF Middleton, Elizabeth M. Julitta, Tommaso Campbell, Petya E. Huemmrich, K. Fred Schickling, Anke Rossini, Micol Cogliati, Sergio Landis, David R. Alonso, Luis GP IEEE TI NOVEL LEAF-LEVEL MEASUREMENTS OF CHLOROPHYLL FLUORESCENCE FOR PHOTOSYNTHETIC EFFICIENCY SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE AB Solar induced chlorophyll fluorescence (SIF) from vegetation can now be obtained from satellites as well as ground-based field studies, at select wavelengths associated with atmospheric features. At the leaf level, full spectrum (650-800 nm) chlorophyll emissions (ChlF) can be measured using specialized instrumentation to support interpretation of these SIF observations. We found that ChlF spectra differ for leaf bottoms versus upper leaf surfaces, potentially affecting within-canopy radiative scattering. Our ChlF measurements for leaves of eight tree species (n=125) obtained during fall 2013 senescence at the Duke Forest in North Carolina, USA and the 2014 growing season (n=72) at the USDA cornfield in Beltsville, MD, USA also demonstrate the benefit of acquiring measurements for both the Red and Far-Red emission peaks. The Red/Far-Red ChlF Ratio was strongly related to both the Photochemical Reflectance Index (PRI) for corn leaves (r=0.76) and tree leaves (r=0.89) and to a PSII Photosynthesis Efficiency parameter (r >= 0.90). C1 [Middleton, Elizabeth M.] NASA, Biospher Sci Lab, Goddard Space Flight Ctr, Greenbelt, MD USA. [Julitta, Tommaso; Rossini, Micol; Cogliati, Sergio] Univ Milano Bicocca, Dept Earth & Environm Sci, Milan, Italy. [Campbell, Petya E.; Huemmrich, K. Fred] Univ Maryland Baltimore Cty, Catonsville, MD USA. [Schickling, Anke] Forschungszentrum Julich, D-52425 Julich, Germany. [Landis, David R.] Global Sci & Technol Inc, Greenbelt, MD USA. [Alonso, Luis] Univ Valencia, Dept Earth Phys & Thermodynam, Valencia, Spain. RP Middleton, EM (reprint author), NASA, Biospher Sci Lab, Goddard Space Flight Ctr, Greenbelt, MD USA. RI Campbell, Petya/L-7486-2013 OI Campbell, Petya/0000-0002-0505-4951 NR 5 TC 0 Z9 0 U1 3 U2 4 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 3878 EP 3881 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696703245 ER PT S AU Golowich, S Lockwood, R Klein, S Thome, K AF Golowich, S. Lockwood, R. Klein, S. Thome, K. GP IEEE TI TOWARD AN OPTICAL FIBER SPECTRAL RADIOMETER FOR SURFACE REFLECTANCE MEASUREMENTS SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Spectral radiometers; vicarious calibration; spectral reflectance measurements AB Vicarious calibration of future space-based spectral imagers will require ground-based measurements of much higher accuracy and precision than current field instruments support. A promising new technology is the use of a multi-mode fiber as the source of dispersion, replacing a grating. It has recently been demonstrated that the wavelength dependent speckle pattern present at the output of a multimode fiber may be exploited to recover the spectrum of the illuminating source, potentially enabling very compact and stable instruments. In this paper, we review our development of a performance model to assess the prospects for developing a field spectral radiometer based on this concept. C1 [Golowich, S.; Lockwood, R.; Klein, S.] MIT, Lincoln Lab, 244 Wood St, Lexington, MA 02420 USA. [Thome, K.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Golowich, S (reprint author), MIT, Lincoln Lab, 244 Wood St, Lexington, MA 02420 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 3902 EP 3905 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696703251 ER PT S AU Xiong, X Fulbright, J Wang, Z Butler, J AF Xiong, X. Fulbright, J. Wang, Z. Butler, J. GP IEEE TI AN OVERVIEW OF S-NPP VIIRS LUNAR CALIBRATION SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE VIIRS; solar diffuser; lunar calibration ID MOON AB The S-NPP VIIRS has operated for more than 3.5 years since its launch in October 2011. The VIIRS reflective solar bands (RSB) calibration is performed by an on-board solar diffuser (SD) and a solar diffuser stability monitor (SDSM). In addition, lunar observations have been used to monitor the RSB on-orbit calibration stability. Since launch, more than 30 lunar calibration events have been scheduled and successfully implemented. This paper provides an overview of S-NPP VIIRS lunar calibration strategies and methodologies. It presents and compares the calibration results derived from regularly scheduled lunar observations with those derived from on-board SD observations. The differences between the solar and lunar calibrations and their likely causes are carefully examined and discussed as an effort for future improvements. C1 [Xiong, X.; Butler, J.] NASA, Sci & Explorat Directorate, GSFC, Greenbelt, MD 20771 USA. [Fulbright, J.; Wang, Z.] Sci Syst & Applicat Inc, Lanham, MD 20706 USA. RP Xiong, X (reprint author), NASA, Sci & Explorat Directorate, GSFC, Greenbelt, MD 20771 USA. NR 7 TC 0 Z9 0 U1 1 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 3910 EP 3913 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696703253 ER PT S AU Hong, L El-Nimri, S Peng, JZ AF Hong, Liang El-Nimri, Salem Peng, Jinzheng GP IEEE TI AQUARIUS FARADAY ROTATION OBSERVATIONS SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Aquarius; L-band; microwave radiometer; Faraday rotation ID L-BAND AB Aquarius is a space-borne 3-beam L-band microwave instrument with its radiometer measuring sea surface salinity and its scatterometer providing ocean roughness corrections for better retrieval. Since polarized signals are used in both salinity and surface wind retrievals, Faraday rotation correction is an important step in calculating both radiometer and scatterometer ocean surface signals. In current ground processing algorithm, data version 3.0, scatterometer Faraday rotation is derived from predictions based on TEC inputs while radiometer Faraday rotation is computed using second and third stokes measurements. Analysis shows general agreement between these two values for all three beams. Discrepancies reside along certain geolocations and vary seasonally. C1 [Hong, Liang; El-Nimri, Salem; Peng, Jinzheng] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Hong, Liang] SAIC, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Peng, Jinzheng] USRA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Hong, L (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RI Hong, Liang/D-3156-2017 OI Hong, Liang/0000-0002-8870-0399 NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 4730 EP 4733 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696704203 ER PT S AU Zuffada, C Li, ZJ Nghiem, SV Lowe, S Shah, R Clarizia, MP Cardellach, E AF Zuffada, Cinzia Li, Zhijin Nghiem, Son V. Lowe, Steve Shah, Rashmi Clarizia, Maria Paola Cardellach, Estel GP IEEE TI THE RISE OF GNSS REFLECTOMETRY FOR EARTH REMOTE SENSING SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE GNSS; sea surface topography; mesoscale ocean; wetland mapping ID OCEAN ALTIMETRY; SYSTEM AB The Global Navigation Satellite System (GNSS) reflectometry, i.e. GNSS-R, is a novel remote-sensing technique first published in [1] that uses GNSS signals reflected from the Earth's surface to infer its surface properties such as sea surface height (SSH), ocean winds, sea-ice coverage, vegetation, wetlands and soil moisture, to name a few. This communication discusses the scientific value of GNSS-R to (a) furthering our understanding of ocean mesoscale circulation toward scales finer than those that existing nadir altimeters can resolve, and (b) mapping vegetated wetlands, an emerging application that might open up new avenues to map and monitor the planet's wetlands for methane emission assessments. Such applications are expected to be demonstrated by the availability of data from GEROS-ISS, an ESA experiment currently in phase A [2], and CyGNSS [3], a NASA mission currently in development. In particular, the paper details the expected error characteristics and the role of filtering played in the assimilation of these data to reduce the altimetric error (when averaging many measurements). C1 [Zuffada, Cinzia; Li, Zhijin; Nghiem, Son V.; Lowe, Steve; Shah, Rashmi] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. [Clarizia, Maria Paola] Univ Michigan, Ann Arbor, MI 48109 USA. [Cardellach, Estel] Inst Ciencies LEspais, Barcelona, Spain. RP Zuffada, C (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. NR 18 TC 1 Z9 1 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 5111 EP 5114 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696705045 ER PT S AU Said, F Soisuvarn, S Katzberg, S Jelenak, Z Chang, PS AF Said, Faozi Soisuvarn, Seubson Katzberg, Steve Jelenak, Zorana Chang, Paul S. GP IEEE TI ESTIMATION OF MAXIMUM HURRICANE WIND SPEED USING SIMULATED CYGNSS MEASUREMENTS SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE AB A hurricane maximum wind retrieval experiment is conducted using CYGNSS (Cyclone Global Navigation Satellite System) tracks simulated over a series of tropical cyclone scenes from the Hurricane Weather Research and Forecasting model (HWRF). This experiment makes use of a forward model relating simulated CYGNSS power-vs-delay waveforms to hurricane maximum winds. The forward model uses synthetic Willoughby modeled storms as 'truth' data. 1148 HWRF storm scenes from the 2010-11 hurricane seasons, from both the Atlantic and Eastern pacific basins, are used as input wind field to the forward model. Retrieved maximum winds are compared to both NHC best-track and HWRF. Results show a definite potential in using the CYGNSS data in retrieving hurricane maximum winds, although the current retrieval performance is hindered due to the symmetrical nature of the modeled Willoughby storms. C1 [Said, Faozi] Global Sci & Technol Inc, Greenbelt, MD 20770 USA. [Said, Faozi; Soisuvarn, Seubson; Jelenak, Zorana; Chang, Paul S.] NOAA, NESDIS, Washington, DC USA. [Soisuvarn, Seubson; Jelenak, Zorana] UCAR, Boulder, CO USA. [Katzberg, Steve] NASA, Langley Res Ctr, Hampton, VA USA. RP Said, F (reprint author), Global Sci & Technol Inc, Greenbelt, MD 20770 USA. RI Jelenak, Zorana/F-5596-2010; Soisuvarn, Seubson/R-8130-2016 OI Jelenak, Zorana/0000-0003-0510-2973; Soisuvarn, Seubson/0000-0002-1373-8974 NR 3 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 5123 EP 5126 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696705048 ER PT S AU Haddad, ZS Kacimi, S Short, D AF Haddad, Ziad S. Kacimi, Sahra Short, David GP IEEE TI A PARAMETRIZATION OF VERTICALLY-VARIABLE HORIZONTAL NON-UNIFORMITY OF RAIN WITHIN THE GPM-DPR BEAMS SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE precipitation; radar; GPM; TRMM ID TRMM PRECIPITATION RADAR AB The "non-uniform beam filling" (NUBF) problem has received much attention in the context of retrieving instantaneous rain amounts from radar measurements because of the non-linearity of the relation between the amount of rain and the signature it leaves in the received echo signals. The non-linearities convert additive white uncertainty into biases in the measured quantities, and the accuracy of any estimate of the biases depends on how detailed a description one can use of the underlying non-uniformity. In this paper, we describe a method that we developed to characterize this non-uniformity in a very similar way to the treatment of Hydrometeor-Size-Distribution variability, by parametrizing it. This should be particularly useful to allow retrieval algorithms to account for NUBF in a more realistic way. C1 [Haddad, Ziad S.; Kacimi, Sahra; Short, David] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Haddad, ZS (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 5131 EP 5133 PG 3 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696705050 ER PT S AU Draper, D Remund, Q Newell, D Krimchansky, S AF Draper, David Remund, Quinn Newell, David Krimchansky, Sergey GP IEEE TI A COMPARISON OF GPM MICROWAVE IMAGER (GMI) HIGH FREQUENCY CHANNEL BRIGHTNESS TEMPERATURES TO THE ADVANCED TECHNOLOGY MICROWAVE SOUNDER (ATMS) SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE microwave atmospheric sounding; cross-calibration AB A direct comparison of top-of-atmosphere brightness temperatures for the 183.31 and 166 GHz channels is given in this paper between the Global Precipitation Measurement (GPM) Microwave Imager (GMI), the Advanced Technology Microwave Sounder (ATMS), and the Microwave Humidity Sounder (MHS) on MetOp-A. As far as is possible, differences in polarization and earth incidence angle are accounted for by properly selecting the data around the GMI incidence angle and rotating the polarization of the dual-pol channels. A sensitivity analysis using a radiative transfer model shows that the comparison should be valid to within +/-0.5K for moist atmospheric conditions. Results are shown before and after antenna pattern corrections applied during the on-orbit calibration/validation period. Except for very dry atmospheric conditions and for convective rain events, the comparison is stable over brightness temperature and atmospheric water content. The GMI brightness temperatures are within about 1K of the ATMS and about 0.5K of MHS on MetOp-A. C1 [Draper, David; Remund, Quinn; Newell, David] Ball Aerosp & Technol Corp, Boulder, CO USA. [Krimchansky, Sergey] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. RP Draper, D (reprint author), Ball Aerosp & Technol Corp, Boulder, CO USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 5146 EP 5149 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696705054 ER PT S AU Newell, D Draper, D Remund, Q Figgins, D Krimchansky, S Wentz, F Meissner, T AF Newell, David Draper, David Remund, Quinn Figgins, Don Krimchansky, Sergey Wentz, Frank Meissner, Thomas GP IEEE TI GPM MICROWAVE IMAGER (GMI) ON-ORBIT PERFORMANCE AND CALIBRATION RESULTS SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE microwave radiometer; calibration AB The Global Precipitation Measurement (GPM) Microwave Imager (GMI) was built and tested by Ball Aerospace and Technologies Corporation (Ball) under a contract with the GPM program at the NASA Goddard Space Flight Center. Ball has supported the initial on-orbit operations to verify calibration performance and provide a final set of operational calibration algorithms. The GMI instrument was launched onboard the GPM spacecraft on February 28th, 2014. GMI was turned on and completed all deployments March 1st, 2014. Spin up and the start of science operations proceeded on March 4th, 2014. GMI has operated nearly continuously since then and has completed a year of successful operation on-orbit. This paper presents the on-orbit performance of the instrument and the results from the calibration activities. C1 [Newell, David; Draper, David; Remund, Quinn; Figgins, Don] Ball Aerosp & Technol Corp, Boulder, CO USA. [Krimchansky, Sergey] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. [Wentz, Frank; Meissner, Thomas] Remote Sensing Syst, Santa Rosa, CA USA. RP Newell, D (reprint author), Ball Aerosp & Technol Corp, Boulder, CO USA. NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 5158 EP 5161 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696705057 ER PT S AU Wilheit, T Berg, W Ebrahimi, H Kroodsma, R McKague, D Payne, V Wang, J AF Wilheit, Thomas Berg, Wesley Ebrahimi, Hamideh Kroodsma, Rachael McKague, Darren Payne, Vivienne Wang, James GP IEEE TI INTERCALIBRATING THE GPM CONSTELLATION USING THE GPM MICROWAVE IMAGER (GMI) SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Calibration; Microwave radiometry; Satellites ID WATER-VAPOR PROFILES; CALIBRATION; RADIOMETERS; RETRIEVAL AB A constellation of disparate radiometers is inherent to the Global Precipitation Measurement (GPM) mission concept. The task of the Intersatellite Calibration Working group is to generate adjustments to make the measurements of all these radiometers physically consistent. A key role of the GPM Microwave Imager (GMI) on the GPM Core satellite is to serve as a transfer standard among the constellation radiometers. The TRMM Microwave Imager (TMI) has served this role during the development phase and for interim corrections early in the GPM mission. The stability of GMI appears to be very good and a physically based calibration has been generated that appears to be accurate at the 1K level or better. C1 [Wilheit, Thomas] Texas A&M Univ, College Stn, TX 77843 USA. [Berg, Wesley] Colorado State Univ, Ft Collins, CO 80523 USA. [Ebrahimi, Hamideh] Univ Cent Florida, Orlando, FL 32816 USA. [Kroodsma, Rachael] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [McKague, Darren] Univ Michigan, Ann Arbor, MI 48109 USA. [Payne, Vivienne] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Wilheit, T (reprint author), Texas A&M Univ, College Stn, TX 77843 USA. RI McKague, Darren/J-2590-2012 OI McKague, Darren/0000-0003-0297-0388 NR 11 TC 2 Z9 2 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 5162 EP 5165 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696705058 ER PT S AU Mladenova, IE Bolten, JD Crow, W de Jeu, R AF Mladenova, Iliana E. Bolten, John. D. Crow, Wade de Jeu, Richard GP IEEE TI EVALUATING THE APPLICATION OF MICROWAVE-BASED VEGETATION OBSERVATIONS IN AN OPERATIONAL SOIL MOISTURE DATA ASSIMILATION SYSTEM SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE data assimilation; soil moisture; observation error; vegetation density; optical depth ID POLARIZATION DIFFERENCE INDEX; OPTICAL DEPTH RETRIEVAL; METHODOLOGY AB A primary operational goal of the United States Department of Agriculture (USDA) is to improve foreign market access for U.S. agricultural products. A large fraction of this crop condition assessment is based on satellite imagery and ground data analysis. The baseline soil moisture estimates that are currently used for this analysis are based on output from the modified Palmer two-layer soil moisture model, updated to assimilate near-real time observations derived from the Soil Moisture Ocean Salinity (SMOS) satellite. The current data assimilation system is based on a 1-D Ensemble Kalman Filter approach, where the observation error is modeled as a function of vegetation density. This allows for offsetting errors in the soil moisture retrievals. The observation error is currently adjusted using Normalized Difference Vegetation Index (NDVI) climatology. In this paper we explore the possibility of utilizing microwave-based vegetation optical depth instead. C1 [Mladenova, Iliana E.; Bolten, John. D.] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. [Mladenova, Iliana E.] UMD Earth Syst Sci Interdisciplinary Ctr, College Pk, MD USA. [Crow, Wade] ARS, USDA, Hydrol & Remote Sensing Lab, Beltsville, MD USA. [de Jeu, Richard] Space Technol Ctr, Transmiss, Noordwijk, Netherlands. RP Mladenova, IE (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. NR 11 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 5190 EP 5193 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696705065 ER PT S AU Swartz, WH Dyrud, LP Lorentz, SR Wu, DL Wiscombe, WJ Papadakis, SJ Huang, PM Reynolds, EL Smith, AW Deglau, DM AF Swartz, William H. Dyrud, Lars P. Lorentz, Steven R. Wu, Dong L. Wiscombe, Warren J. Papadakis, Stergios J. Huang, Philip M. Reynolds, Edward L. Smith, Allan W. Deglau, David M. GP IEEE TI THE RAVAN CUBESAT MISSION: ADVANCING TECHNOLOGIES FOR CLIMATE OBSERVATION SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Radiometers; Carbon nanotubes; Low earth orbit satellites; Global warming; Radiation monitoring ID EARTHS ENERGY AB The Radiometer Assessment using Vertically Aligned Nanotubes (RAVAN) CubeSat mission demonstrates an affordable, accurate radiometer that directly measures Earth-leaving fluxes of total and solar-reflected radiation. The radiometer exploits two key technologies: vertically aligned carbon nanotubes used as the radiometer absorber and a gallium fixed-point blackbody as an internal calibration source. RAVAN will fly on a 3U CubeSat, with a launch likely at the end of 2016. Our ability to understand and predict future climate is limited by our ability to track energy within the Earth system. RAVAN will enable the development of an Earth radiation budget constellation that could provide the global, diurnal measurements needed to significantly advance our understanding of ongoing and future climate change. C1 [Swartz, William H.; Papadakis, Stergios J.; Huang, Philip M.; Reynolds, Edward L.; Deglau, David M.] Johns Hopkins Univ, Appl Phys Lab, Laurel, MD USA. [Dyrud, Lars P.] Charles Stark Draper Lab Inc, Cambridge, MA 02139 USA. [Lorentz, Steven R.; Smith, Allan W.] L1 Stand & Technol Inc, New Windsor, MD USA. [Wu, Dong L.; Wiscombe, Warren J.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Swartz, WH (reprint author), Johns Hopkins Univ, Appl Phys Lab, Laurel, MD USA. RI Wu, Dong/D-5375-2012; Swartz, William/A-1965-2010 OI Swartz, William/0000-0002-9172-7189 NR 4 TC 2 Z9 2 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 5300 EP 5303 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696705093 ER PT S AU Doubleday, J Chien, S Norton, C Wagstaff, K Thompson, DR Bellardo, J Francis, C Baumgarten, E AF Doubleday, Joshua Chien, Steve Norton, Charles Wagstaff, Kiri Thompson, David R. Bellardo, John Francis, Craig Baumgarten, Eric GP IEEE TI AUTONOMY FOR REMOTE SENSING - EXPERIENCES FROM THE IPEX CUBESAT SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE ID VOLCANISM; MODIS AB The Intelligent Payload Experiment (IPEX) is a CubeSat mission to flight validate technologies for onboard instrument processing and autonomous operations for NASA's Earth Science Technologies Office (ESTO). Specifically IPEX is to demonstrate onboard instrument processing and product generation technologies for the Intelligent Payload Module (IPM) of the proposed Hyperspectral Infra-red Imager (HyspIRI) mission concept. Many proposed future missions, including HyspIRI, are slated to produce enormous volumes of data requiring either significant communication advancements or data reduction techniques. IPEX demonstrates several technologies for onboard data reduction, such as computer vision, image analysis, image processing and in general demonstrates general operations autonomy. We conclude this paper with a number of lessons learned through operations of this technology demonstration mission on a novel platform for NASA. C1 [Doubleday, Joshua; Chien, Steve; Norton, Charles; Wagstaff, Kiri; Thompson, David R.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Bellardo, John; Francis, Craig; Baumgarten, Eric] Calif Polytech State Univ San Luis Obispo, San Luis Obispo, CA 93407 USA. RP Doubleday, J (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM joshua.doubleday@jpl.nasa.gov; steve.chien@jpl.nasa.gov; charles.norton@jpl.nasa.gov; kiriwagstaff@jpl.nasa.gov; david.thompson@jpl.nasa.gov; bellardo@calpoly.edu; cfrancis@calpoly.edu NR 20 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 5308 EP 5311 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696705095 ER PT S AU Fields, R Sun, XL Abshire, JB Beck, J Rawlings, RM Sullivan, W Hinkley, D AF Fields, Renny Sun, Xiaoli Abshire, James B. Beck, Jeff Rawlings, Richard M. Sullivan, William, III Hinkley, David GP IEEE TI A LINEAR MODE PHOTON-COUNTING (LMPC) DETECTOR ARRAY IN A CUBESAT TO ENABLE EARTH SCIENCE LIDAR MEASUREMENTS SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Detector; LIDAR; LMPC; CubeSat AB Work is underway to demonstrate a new linear mode photon counting (LMPC) detector in Earth orbit inside a 3U Cubesat. The detector is 16 pixel (2x8) HgCdTe electron Avalanche Photodiode (e-APD) array developed by DRS Technologies, C4ISR Group, Infrared Sensors and Systems (ISS). It has similar to 70% quantum efficiency and single photon level response at wavelengths from 0.4 to 4 microns. The detector will be mounted in a small integrated detector cooler assembly that operates the e-APD at 80K. The LMPC CubeSat is planned for launch into a 450 km x 820 km x 99 degree inclination orbit in July 2016. In space measurements are planned at 1.06, 1.57 and 2.06 microns using internal sources and with ground-to-space experiments. C1 [Fields, Renny; Hinkley, David] Aerosp Corp, El Segundo, CA 90245 USA. [Sun, Xiaoli; Abshire, James B.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Beck, Jeff; Rawlings, Richard M.; Sullivan, William, III] DRS Technol, Grp C4ISR, Dallas, TX 78712 USA. RP Fields, R (reprint author), Aerosp Corp, El Segundo, CA 90245 USA. NR 9 TC 1 Z9 1 U1 1 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 5312 EP 5315 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696705096 ER PT S AU Minchew, B Simons, M Hensley, S Bjornsson, H Palsson, F Milillo, P AF Minchew, Brent Simons, Mark Hensley, Scott Bjoernsson, Helgi Palsson, Finnur Milillo, Pietro GP IEEE TI MULTIPLE GLACIER SURGES OBSERVED WITH AIRBORNE AND SPACEBORNE INTERFEROMETRIC SYNTHETIC APERTURE RADAR SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE ID ICELANDIC GLACIERS; TILL; INSTABILITY; MECHANISM; FLOW C1 [Minchew, Brent; Simons, Mark] CALTECH, Seismol Lab, Pasadena, CA 91125 USA. [Hensley, Scott] CALTECH, Jet Prop Lab, Pasadena, CA USA. [Bjoernsson, Helgi; Palsson, Finnur] Univ Iceland, Inst Earth Sci, Reykjaik, Iceland. [Milillo, Pietro] Univ Basilicata, Sch Engn, I-85100 Potenza, Italy. RP Minchew, B (reprint author), CALTECH, Seismol Lab, Pasadena, CA 91125 USA. NR 21 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 5316 EP 5319 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696705097 ER PT S AU Meissner, T Wentz, F Lagerloef, G Le Vine, D Lee, T AF Meissner, Thomas Wentz, Frank Lagerloef, Gary Le Vine, David Lee, Tong GP IEEE TI ESTIMATE OF UNCERTAINTIES IN THE AQUARIUS SALINITY RETRIEVALS SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Aquarius; Ocean Surface Salinity; Error Characterization Validation AB We present a method for formally assessing random and systematic uncertainties in the Aquarius salinity retrievals. The method is based on performing multiple retrievals by perturbing the various inputs to the retrieval algorithm. This results in calculating the sensitivity of the Aquarius salinity to these inputs. Together with an error model for the uncertainties in the input parameters it is possible to calculate the uncertainty in the retrieved SSS. It is important to distinguish between random uncertainties, which get suppressed when computing weekly or monthly averages and systematic uncertainties, which do not get suppressed by taking averages. We compare the results of the formal uncertainty estimates with uncertainty estimates based on comparing the Aquarius salinities with those from external validation sources finding excellent agreement. C1 [Meissner, Thomas; Wentz, Frank] Remote Sensing Syst, Santa Rosa, CA USA. [Lagerloef, Gary] Earth & Space Res, Seattle, WA USA. [Le Vine, David] NASA, GSFC, Greenbelt, MD USA. [Lee, Tong] JPL, Pasadena, CA USA. RP Meissner, T (reprint author), Remote Sensing Syst, Santa Rosa, CA USA. EM meissner@remss.com NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 5324 EP 5327 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696705099 ER PT S AU Carregal, GR Hartley, T Siqueira, P De Bleser, JW Haynes, MS Esteban-Fernandez, D Millette, T AF Carregal, Gerard Ruiz Hartley, Tom Siqueira, Paul De Bleser, Jan-Willem Haynes, Mark S. Esteban-Fernandez, Daniel Millette, Thomas GP IEEE TI A CALIBRATED 35 GHZ AIRBORNE SCATTEROMETER FOR NASA'S SURFACE WATER AND OCEAN TOPOGRAPHY MISSION SO 2015 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM (IGARSS) SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 26-31, 2015 CL Milan, ITALY SP IEEE DE Airborne radar; millimeter wave radar; scatterometer; radar cross-section AB In this paper, an airborne Ka-band (35 GHz) FMCW scatterometer and its preliminary results are presented. The paper describes the system, the calibration and the data processing needed to study the response of different targets to the scatterometer. The results obtained in the first flights include normalized radar cross-section measurements of inland water bodies and a tree height estimation algorithm. C1 [Carregal, Gerard Ruiz; Hartley, Tom; Siqueira, Paul] Univ Massachusetts, Microwave Remote Sensing Lab, Amherst, MA 01003 USA. [De Bleser, Jan-Willem; Haynes, Mark S.; Esteban-Fernandez, Daniel] CALTECH, Jet Prop Lab, Radar Syst & Instrument Engn, Pasadena, CA USA. [Millette, Thomas] Mt Holyoke Coll, Dept Geog, Hadley, MA USA. RP Carregal, GR (reprint author), Univ Massachusetts, Microwave Remote Sensing Lab, Amherst, MA 01003 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-1-4799-7929-5 J9 INT GEOSCI REMOTE SE PY 2015 BP 5340 EP 5343 PG 4 WC Engineering, Electrical & Electronic; Geosciences, Multidisciplinary; Remote Sensing SC Engineering; Geology; Remote Sensing GA BE4GM UT WOS:000371696705103 ER PT S AU Mehling, JS Holley, J O'Malley, MK AF Mehling, Joshua S. Holley, James O'Malley, Marcia K. GP IEEE TI Leveraging Disturbance Observer Based Torque Control for Improved Impedance Rendering with Series Elastic Actuators SO 2015 IEEE/RSJ INTERNATIONAL CONFERENCE ON INTELLIGENT ROBOTS AND SYSTEMS (IROS) SE IEEE International Conference on Intelligent Robots and Systems LA English DT Proceedings Paper CT IEEE/RSJ International Conference on Intelligent Robots and Systems (IROS) CY SEP 28-OCT 02, 2015 CL Hamburg, GERMANY SP IEEE, RSJ, Univ Hamburg, DFG, RA, New Technol Fdn, SICE, KUKA, DJI, Rethink Robot, BOSCH, Chinese Acad Sci, SIAT, Boozhong, Adept, Automatica, HIT, Ascending Technol, OPTOFORCE, DST Robot, BA Syst, Rainbow Robot, SIA, CLEARPATH Robot, Swiss Natl Ctr Competence Res Robot, SINEVA, Dyson, SICK, Robocept, Force Dimension, Open Unit Robot, Luoyang Natl Univ Sci Park, Fuzhou Univ, Synapticon, Google, Technishce Univ Munchen, iRobot, Echord++, Khalifa Univ, Pan Robot, FESTO, Kinova Robot, SCHUNK, ies ID DESIGN; ROBOT AB The fidelity with which series elastic actuators (SEAs) render desired impedances is important. Numerous approaches to SEA impedance control have been developed under the premise that high-precision actuator torque control is a prerequisite. Indeed, the design of an inner torque compensator has a significant impact on actuator impedance rendering. The disturbance observer (DOB) based torque control implemented in NASA's Valkyrie robot is considered here and a mathematical model of this torque control, cascaded with an outer impedance compensator, is constructed. While previous work has examined the impact a disturbance observer has on torque control performance, little has been done regarding DOBs and impedance rendering accuracy. Both simulation and a series of experiments are used to demonstrate the significant improvements possible in an SEA's ability to render desired dynamic behaviors when utilizing a DOB. Actuator transparency at low impedances is improved, closed loop hysteresis is reduced, and the actuator's dynamic response to both commands and interaction torques more faithfully matches that of the desired model. All of this is achieved by leveraging DOB based control rather than increasing compensator gains, thus making improved SEA impedance control easier to achieve in practice. C1 [Mehling, Joshua S.; Holley, James] NASA, Lyndon B Johnson Space Ctr, Robot Syst Technol Branch, Houston, TX 77058 USA. [Mehling, Joshua S.; O'Malley, Marcia K.] Rice Univ, Dept Mech Engn, Houston, TX 77005 USA. RP Mehling, JS (reprint author), NASA, Lyndon B Johnson Space Ctr, Robot Syst Technol Branch, Houston, TX 77058 USA. EM joshua.s.mehling@nasa.gov; james.j.holley@nasa.gov; omalleym@rice.edu NR 19 TC 2 Z9 2 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-0858 BN 978-1-4799-9994-1 J9 IEEE INT C INT ROBOT PY 2015 BP 1646 EP 1651 PG 6 WC Computer Science, Artificial Intelligence; Robotics SC Computer Science; Robotics GA BE4LI UT WOS:000371885401119 ER PT S AU Meier, D Brockers, R Matthies, L Siegwart, R Weiss, S AF Meier, Daniel Brockers, Roland Matthies, Larry Siegwart, Roland Weiss, Stephan GP IEEE TI Detection and Characterization of Moving Objects with Aerial Vehicles using Inertial-Optical Flow SO 2015 IEEE/RSJ INTERNATIONAL CONFERENCE ON INTELLIGENT ROBOTS AND SYSTEMS (IROS) SE IEEE International Conference on Intelligent Robots and Systems LA English DT Proceedings Paper CT IEEE/RSJ International Conference on Intelligent Robots and Systems (IROS) CY SEP 28-OCT 02, 2015 CL Hamburg, GERMANY SP IEEE, RSJ, Univ Hamburg, DFG, RA, New Technol Fdn, SICE, KUKA, DJI, Rethink Robot, BOSCH, Chinese Acad Sci, SIAT, Boozhong, Adept, Automatica, HIT, Ascending Technol, OPTOFORCE, DST Robot, BA Syst, Rainbow Robot, SIA, CLEARPATH Robot, Swiss Natl Ctr Competence Res Robot, SINEVA, Dyson, SICK, Robocept, Force Dimension, Open Unit Robot, Luoyang Natl Univ Sci Park, Fuzhou Univ, Synapticon, Google, Technishce Univ Munchen, iRobot, Echord++, Khalifa Univ, Pan Robot, FESTO, Kinova Robot, SCHUNK, ies ID TRACKING AB In this paper, we present a novel approach in combining visual and inertial measurements in non-static environments for first order characterization of the metric motion of non-static objects in the scene. Our approach leverages online estimated ego motion states and uses a novel inertialoptical flow (IOF) measurement analysis to identify moving objects and to characterize them in their angular and linear velocities. The novelty of our algorithm lies in the identification and segmentation of consistent optical flow outliers in the so-called kinematic space. These consistent outliers in combination with the IOF information for ego-motion estimation yield a first order estimation of the moving object in full 3D and in metric units. The approach is highly efficient as it only requires matched features in two consecutive images. We evaluate and demonstrate our algorithm in simulations and in real world tests. C1 [Meier, Daniel; Siegwart, Roland] Swiss Fed Inst Technol, ASL, Zurich, Switzerland. [Brockers, Roland; Matthies, Larry; Weiss, Stephan] CALTECH, Mobil & Robot Syst Sect, NASA, Jet Prop Lab, Pasadena, CA 91125 USA. RP Meier, D (reprint author), Swiss Fed Inst Technol, ASL, Zurich, Switzerland. EM danielme@student.ethz.ch; roland.brockers@jpl.nasa.gov; lhm@jpl.nasa.gov; rsiegwart@ethz.ch; stephan.weiss@ieee.org NR 14 TC 1 Z9 1 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-0858 BN 978-1-4799-9994-1 J9 IEEE INT C INT ROBOT PY 2015 BP 2473 EP 2480 PG 8 WC Computer Science, Artificial Intelligence; Robotics SC Computer Science; Robotics GA BE4LI UT WOS:000371885402097 ER PT S AU Smith, LM Quinn, RD Johnson, KA Tuck, WR AF Smith, Lauren M. Quinn, Roger D. Johnson, Kyle A. Tuck, William R. GP IEEE TI The Tri-Wheel: A Novel Wheel-Leg Mobility Concept SO 2015 IEEE/RSJ INTERNATIONAL CONFERENCE ON INTELLIGENT ROBOTS AND SYSTEMS (IROS) SE IEEE International Conference on Intelligent Robots and Systems LA English DT Proceedings Paper CT IEEE/RSJ International Conference on Intelligent Robots and Systems (IROS) CY SEP 28-OCT 02, 2015 CL Hamburg, GERMANY SP IEEE, RSJ, Univ Hamburg, DFG, RA, New Technol Fdn, SICE, KUKA, DJI, Rethink Robot, BOSCH, Chinese Acad Sci, SIAT, Boozhong, Adept, Automatica, HIT, Ascending Technol, OPTOFORCE, DST Robot, BA Syst, Rainbow Robot, SIA, CLEARPATH Robot, Swiss Natl Ctr Competence Res Robot, SINEVA, Dyson, SICK, Robocept, Force Dimension, Open Unit Robot, Luoyang Natl Univ Sci Park, Fuzhou Univ, Synapticon, Google, Technishce Univ Munchen, iRobot, Echord++, Khalifa Univ, Pan Robot, FESTO, Kinova Robot, SCHUNK, ies AB The Tri-Wheel is a novel wheel-leg locomotion concept inspired by work with first responders. Through its two modes of operation-Driving Mode and Tumbling Mode-this mechanism is able to both drive quickly on smooth surfaces at roughly 1.7 times desired speed and climb objects as tall as 67% of the diameter of the mechanism. The unique gearing configuration that facilitates these dual capabilities is described, and testing quantifies that this nonprecision gearing system is roughly 81% efficient in a worst-case scenario of loading. This work introduces the Tri-Wheel concept and provides preliminary testing to validate its predicted operating characteristics. C1 [Smith, Lauren M.] Northrop Grumman, Adv Unmanned Syst, San Diego, CA 92127 USA. [Quinn, Roger D.] Case Western Reserve Univ, Dept Mech & Aerosp Engn, Cleveland, OH 44106 USA. [Johnson, Kyle A.] NASA, SLOPE Lab, Glenn Res Ctr, Cleveland, OH 44135 USA. [Tuck, William R.] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Smith, LM (reprint author), Northrop Grumman, Adv Unmanned Syst, San Diego, CA 92127 USA. EM lauren.m.smith@ngc.com; rdq@case.edu; kyle.a.johnson@nasa.gov; william.r.tuck@nasa.gov NR 19 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-0858 BN 978-1-4799-9994-1 J9 IEEE INT C INT ROBOT PY 2015 BP 4146 EP 4152 PG 7 WC Computer Science, Artificial Intelligence; Robotics SC Computer Science; Robotics GA BE4LI UT WOS:000371885404049 ER PT S AU Degrave, J Caluwaerts, K Dambre, J Wyffels, F AF Degrave, Jonas Caluwaerts, Ken Dambre, Joni Wyffels, Francis GP IEEE TI Developing an Embodied Gait on a Compliant Quadrupedal Robot SO 2015 IEEE/RSJ INTERNATIONAL CONFERENCE ON INTELLIGENT ROBOTS AND SYSTEMS (IROS) SE IEEE International Conference on Intelligent Robots and Systems LA English DT Proceedings Paper CT IEEE/RSJ International Conference on Intelligent Robots and Systems (IROS) CY SEP 28-OCT 02, 2015 CL Hamburg, GERMANY SP IEEE, RSJ, Univ Hamburg, DFG, RA, New Technol Fdn, SICE, KUKA, DJI, Rethink Robot, BOSCH, Chinese Acad Sci, SIAT, Boozhong, Adept, Automatica, HIT, Ascending Technol, OPTOFORCE, DST Robot, BA Syst, Rainbow Robot, SIA, CLEARPATH Robot, Swiss Natl Ctr Competence Res Robot, SINEVA, Dyson, SICK, Robocept, Force Dimension, Open Unit Robot, Luoyang Natl Univ Sci Park, Fuzhou Univ, Synapticon, Google, Technishce Univ Munchen, iRobot, Echord++, Khalifa Univ, Pan Robot, FESTO, Kinova Robot, SCHUNK, ies ID LOCOMOTION; FRAMEWORK AB Incorporating the body dynamics of compliant robots into their controller architectures can drastically reduce the complexity of locomotion control. An extreme version of this embodied control principle was demonstrated in highly compliant tensegrity robots, for which stable gait generation was achieved by using only optimized linear feedback from the robot's sensors to its actuators. The morphology of quadrupedal robots has previously been used for sensing and for control of a compliant spine, but never for gait generation. In this paper, we successfully apply embodied control to the compliant, quadrupedal Oncilla robot. As initial experiments indicated that mere linear feedback does not suffice, we explore the minimal requirements for robust gait generation in terms of memory and nonlinear complexity. Our results show that a memoryless feedback controller can generate a stable trot by learning the desired nonlinear relation between the input and the output signals. We believe this method can provide a very useful tool for transferring knowledge from open loop to closed loop control on compliant robots. C1 [Degrave, Jonas; Dambre, Joni; Wyffels, Francis] Univ Ghent, Elect & Informat Syst ELIS, Sint Pietersnieuwstr 41, B-9000 Ghent, Belgium. [Caluwaerts, Ken] NASA, Ames Res Ctr, Oak Ridge Associated Univ, Mail Stop 269-3, Moffett Field, CA 94035 USA. RP Degrave, J (reprint author), Univ Ghent, Elect & Informat Syst ELIS, Sint Pietersnieuwstr 41, B-9000 Ghent, Belgium. EM Jonas.Degrave@UGent.be NR 24 TC 3 Z9 3 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-0858 BN 978-1-4799-9994-1 J9 IEEE INT C INT ROBOT PY 2015 BP 4486 EP 4491 PG 6 WC Computer Science, Artificial Intelligence; Robotics SC Computer Science; Robotics GA BE4LI UT WOS:000371885404100 ER PT S AU Chakraborti, T Briggs, G Talamadupula, K Zhang, Y Scheutz, M Smith, D Kambhampati, S AF Chakraborti, Tathagata Briggs, Gordon Talamadupula, Kartik Zhang, Yu Scheutz, Matthias Smith, David Kambhampati, Subbarao GP IEEE TI Planning for Serendipity SO 2015 IEEE/RSJ INTERNATIONAL CONFERENCE ON INTELLIGENT ROBOTS AND SYSTEMS (IROS) SE IEEE International Conference on Intelligent Robots and Systems LA English DT Proceedings Paper CT IEEE/RSJ International Conference on Intelligent Robots and Systems (IROS) CY SEP 28-OCT 02, 2015 CL Hamburg, GERMANY SP IEEE, RSJ, Univ Hamburg, DFG, RA, New Technol Fdn, SICE, KUKA, DJI, Rethink Robot, BOSCH, Chinese Acad Sci, SIAT, Boozhong, Adept, Automatica, HIT, Ascending Technol, OPTOFORCE, DST Robot, BA Syst, Rainbow Robot, SIA, CLEARPATH Robot, Swiss Natl Ctr Competence Res Robot, SINEVA, Dyson, SICK, Robocept, Force Dimension, Open Unit Robot, Luoyang Natl Univ Sci Park, Fuzhou Univ, Synapticon, Google, Technishce Univ Munchen, iRobot, Echord++, Khalifa Univ, Pan Robot, FESTO, Kinova Robot, SCHUNK, ies AB Recently there has been a lot of focus on human robot co-habitation issues that are often orthogonal to many aspects of human-robot teaming; e.g. on producing socially acceptable behaviors of robots and de-conflicting plans of robots and humans in shared environments. However, an interesting offshoot of these settings that has largely been overlooked is the problem of planning for serendipity - i.e. planning for stigmergic collaboration without explicit commitments on agents in co-habitation. In this paper we formalize this notion of planning for serendipity for the first time, and provide an Integer Programming based solution for this problem. Further, we illustrate the different modes of this planning technique on a typical Urban Search and Rescue scenario and show a real-life implementation of the ideas on the Nao Robot interacting with a human colleague. C1 [Chakraborti, Tathagata; Zhang, Yu; Kambhampati, Subbarao] Arizona State Univ, Dept Comp Sci, Tempe, AZ 85281 USA. [Briggs, Gordon; Scheutz, Matthias] Tufts Univ, HRI Lab, Medford, MA 02155 USA. [Talamadupula, Kartik] IBM Thomas J Watson Res Ctr, Cognit Learning Dept, Yorktown Hts, NY USA. [Smith, David] NASA, Ames Res Ctr, Autonomous Syst & Robot Intelligent Syst Div, Moffett Field, CA 94035 USA. RP Chakraborti, T (reprint author), Arizona State Univ, Dept Comp Sci, Tempe, AZ 85281 USA. EM tchakra2@asu.edu; qbriggs@cs.tufts.edu; krtalamad@us.ibm.com; yzhan442@asu.edu; mscheutz@cs.tufts.edu; david.smith@nasa.gov; rao@asu.edu NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-0858 BN 978-1-4799-9994-1 J9 IEEE INT C INT ROBOT PY 2015 BP 5300 EP 5306 PG 7 WC Computer Science, Artificial Intelligence; Robotics SC Computer Science; Robotics GA BE4LI UT WOS:000371885405061 ER PT S AU Kim, K Agogino, AK Toghyan, A Moon, D Taneja, L Agogino, AM AF Kim, Kyunam Agogino, Adrian K. Toghyan, Aliakhar Moon, Deaho Taneja, Laqshya Agogino, Alice M. GP IEEE TI Robust Learning of Tensegrity Robot Control for Locomotion through Form-Finding SO 2015 IEEE/RSJ INTERNATIONAL CONFERENCE ON INTELLIGENT ROBOTS AND SYSTEMS (IROS) SE IEEE International Conference on Intelligent Robots and Systems LA English DT Proceedings Paper CT IEEE/RSJ International Conference on Intelligent Robots and Systems (IROS) CY SEP 28-OCT 02, 2015 CL Hamburg, GERMANY SP IEEE, RSJ, Univ Hamburg, DFG, RA, New Technol Fdn, SICE, KUKA, DJI, Rethink Robot, BOSCH, Chinese Acad Sci, SIAT, Boozhong, Adept, Automatica, HIT, Ascending Technol, OPTOFORCE, DST Robot, BA Syst, Rainbow Robot, SIA, CLEARPATH Robot, Swiss Natl Ctr Competence Res Robot, SINEVA, Dyson, SICK, Robocept, Force Dimension, Open Unit Robot, Luoyang Natl Univ Sci Park, Fuzhou Univ, Synapticon, Google, Technishce Univ Munchen, iRobot, Echord++, Khalifa Univ, Pan Robot, FESTO, Kinova Robot, SCHUNK, ies AB Robots based on tensegrity structures have the potential to be robust, efficient and adaptable. While traditionally being difficult to control, recent control strategies for ball-shaped tensegrity robots have successfully enabled punctuated rolling, hill-climbing and obstacle climbing. These gains have been made possible through the use of machine learning and physics simulations that allow controls to be "learned" instead of being engineered in a top-down fashion. While effective in simulation, these emergent methods unfortunately give little insight into how to generalize the learned control strategies and evaluate their robustness. These robustness issues are especially important when applied to physical robots as there exists errors with respect to the simulation, which may prevent the physical robot from actually rolling. This paper describes how the robustness can be addressed in three ways: 1) We present a dynamic relaxation technique that describes the shape of a tensegrity structure given the forces on its cables; 2) We then show how control of a tensegrity robot "ball" for locomotion can be decomposed into finding its shape and then determining the position of the center of mass relative to the supporting polygon for this new shape; 3) Using a multi-step Monte Carlo based learning algorithm, we determine the structural geometry that pushes the center of mass out of the supporting polygon to provide the most robust basic mobility step that can lead to rolling. Combined, these elements will give greater insight into the control process, provide an alternative to the existing physics simulations and offer a greater degree of robustness to bridge the gap between simulation and hardware. C1 [Kim, Kyunam; Toghyan, Aliakhar; Moon, Deaho; Taneja, Laqshya; Agogino, Alice M.] Univ Calif Berkeley, Dept Mech Engn, Berkeley, CA 94720 USA. [Agogino, Adrian K.] Univ Calif Santa Cruz, Santa Cruz, CA 95064 USA. [Agogino, Adrian K.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Kim, K (reprint author), Univ Calif Berkeley, Dept Mech Engn, Berkeley, CA 94720 USA. EM knkim@berkeley.edu; adrian.k.agogino@nasa.gov; aliakbar_toghyan@berkeley.edu; dmoon@berkeley.edu; laqshya_taneja@berkeley.edu; agogino@berkeley.edu NR 20 TC 2 Z9 2 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-0858 BN 978-1-4799-9994-1 J9 IEEE INT C INT ROBOT PY 2015 BP 5824 EP 5831 PG 8 WC Computer Science, Artificial Intelligence; Robotics SC Computer Science; Robotics GA BE4LI UT WOS:000371885405140 ER PT S AU He, YN AF He, Yuning GP IEEE TI Online Detection and Modeling of Safety Boundaries for Aerospace Applications using Active Learning and Bayesian Statistics SO 2015 INTERNATIONAL JOINT CONFERENCE ON NEURAL NETWORKS (IJCNN) SE IEEE International Joint Conference on Neural Networks (IJCNN) LA English DT Proceedings Paper CT International Joint Conference on Neural Networks (IJCNN) CY JUL 12-17, 2015 CL Killarney, IRELAND ID DESIGN AB The behavior of complex aerospace systems is governed by numerous parameters. For safety analysis it is important to understand how the system behaves with respect to these parameter values. In particular, understanding the boundaries between safe and unsafe regions is of major importance. In this paper, we describe a hierarchical Bayesian statistical modeling approach for the online detection and characterization of such boundaries. Our method for classification with active learning uses a particle filter-based model and a boundary-aware metric for best performance. From a library of candidate shapes incorporated with domain expert knowledge, the location and parameters of the boundaries are estimated using advanced Bayesian modeling techniques. The results of our boundary analysis are then provided in a form understandable by the domain expert. We illustrate our approach using a simulation model of a NASA neuro-adaptive flight control system, as well as a system for the detection of separation violations in the terminal airspace. C1 [He, Yuning] NASA, Ames Res Ctr, UARC, Moffett Field, CA 94035 USA. RP He, YN (reprint author), NASA, Ames Res Ctr, UARC, Moffett Field, CA 94035 USA. EM yuning.he@nasa.gov NR 17 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2161-4393 BN 978-1-4799-1959-8 J9 IEEE IJCNN PY 2015 PG 8 WC Computer Science, Artificial Intelligence; Computer Science, Hardware & Architecture; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BE3HR UT WOS:000370730602030 ER PT J AU Chen, PC Rabin, D AF Chen, Peter C. Rabin, Douglas TI Carbon nanotube optical mirrors SO JOURNAL OF ASTRONOMICAL TELESCOPES INSTRUMENTS AND SYSTEMS LA English DT Article DE carbon nanotube epoxy; smart materials; telescope mirror; space optics; active optics ID SMART MATERIALS; COMPOSITES; ACTUATORS; SENSORS AB We report the fabrication of imaging quality optical mirrors with smooth surfaces using carbon nanotubes (CNT) embedded in an epoxy matrix. CNT/epoxy is a multifunctional composite material that has sensing capabilities and can be made to incorporate self-actuation. Moreover, as the precursor is a low density liquid, large and lightweight mirrors can be fabricated by processes such as replication, spincasting, and three-dimensional printing. Therefore, the technology holds promise for the development of a new generation of lightweight, compact " smart" telescope mirrors with figure sensing and active or adaptive figure control. We report on measurements made of optical and mechanical characteristics, active optics experiments, and numerical modeling. We discuss possible paths for future development. (C) The Authors. Published by SPIE under a Creative Commons Attribution 3.0 Unported License. Distribution or reproduction of this work in whole or in part requires full attribution of the original publication, including its DOI. C1 [Chen, Peter C.] Lightweight Telescopes Inc, 5469 Hound Hill Court, Columbia, MD 21045 USA. [Chen, Peter C.] Catholic Univ Amer, Inst Astrophys & Computat Sci, Washington, DC 20064 USA. [Chen, Peter C.] NASA, Goddard Space Flight Ctr, Solar Phys Lab, Greenbelt, MD 20771 USA. [Rabin, Douglas] NASA, Goddard Space Flight Ctr, Heliophys Sci Div, Greenbelt, MD 20771 USA. RP Chen, PC (reprint author), Lightweight Telescopes Inc, 5469 Hound Hill Court, Columbia, MD 21045 USA. EM peter.c.chen@nasa.gov NR 27 TC 0 Z9 0 U1 0 U2 2 PU SPIE-SOC PHOTO-OPTICAL INSTRUMENTATION ENGINEERS PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98225 USA SN 2329-4124 EI 2329-4221 J9 J ASTRON TELESC INST JI J. Astron. Telesc. Instrum. Syst. PD JAN-MAR PY 2015 VL 1 IS 1 AR 014005 DI 10.1117/1.JATIS.1.1.014005 PG 6 WC Engineering, Aerospace; Instruments & Instrumentation; Optics SC Engineering; Instruments & Instrumentation; Optics GA DG2EP UT WOS:000371879500006 ER PT J AU Gersh-Range, J Arnold, WR Stahl, HP AF Gersh-Range, Jessica Arnold, William R., Sr. Stahl, H. Philip TI Edgewise connectivity: an approach to improving segmented primary mirror performance SO JOURNAL OF ASTRONOMICAL TELESCOPES INSTRUMENTS AND SYSTEMS LA English DT Article DE segmented mirror; edgewise connectivity; space telescope; flexibility; stiffness; damping; vibration; disturbance response AB As future astrophysics missions require space telescopes with greater sensitivity and angular resolution, the corresponding increase in the primary mirror diameter presents numerous challenges. Since fairing restrictions limit the maximum diameter of monolithic and deployable segmented mirrors that can be launched, there is a need for on-orbit assembly methods that decouple the mirror diameter from the choice of launch vehicle. In addition, larger mirrors are more susceptible to vibrations and are typically so lightly damped that vibrations could persist for some time if uncontrolled. To address these challenges, we present a segmented mirror architecture in which the segments are connected edgewise by mechanisms analogous to damped springs. These mechanisms can be damped springs, flux-pinning mechanisms, virtual mechanisms, or any other device with the same basic behavior. Using a parametric finite-element model, we show that for low to intermediate stiffnesses, the stiffness and damping contributions from the mechanisms improve both the natural frequency and disturbance response of the segmented mirror. At higher stiffnesses, the mechanisms structurally connect the segments, leading to a segmented mirror that performs comparably to a monolith-or better, depending on the mechanism damping-with the modular design enabling on-orbit assembly and scalability. (C) The Authors. Published by SPIE under a Creative Commons Attribution 3.0 Unported License. Distribution or reproduction of this work in whole or in part requires full attribution of the original publication, including its DOI. C1 [Gersh-Range, Jessica] Cornell Univ, 127 Upson Hall, Ithaca, NY 14853 USA. [Arnold, William R., Sr.] Def Acquisit Inc, Jacobs ESSSA Grp, Huntsville, AL 35806 USA. [Stahl, H. Philip] NASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Gersh-Range, J (reprint author), Cornell Univ, 127 Upson Hall, Ithaca, NY 14853 USA. EM jag389@cornell.edu NR 17 TC 1 Z9 1 U1 0 U2 0 PU SPIE-SOC PHOTO-OPTICAL INSTRUMENTATION ENGINEERS PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98225 USA SN 2329-4124 EI 2329-4221 J9 J ASTRON TELESC INST JI J. Astron. Telesc. Instrum. Syst. PD JAN-MAR PY 2015 VL 1 IS 1 AR 014002 DI 10.1117/1.JATIS.1.1.014002 PG 9 WC Engineering, Aerospace; Instruments & Instrumentation; Optics SC Engineering; Instruments & Instrumentation; Optics GA DG2EP UT WOS:000371879500003 ER PT J AU Gersh-Range, J Arnold, WR Lehner, D Stahl, HP AF Gersh-Range, Jessica Arnold, William R., Sr. Lehner, David Stahl, H. Philip TI Flux-pinning mechanisms for improving cryogenic segmented mirror performance SO JOURNAL OF ASTRONOMICAL TELESCOPES INSTRUMENTS AND SYSTEMS LA English DT Article DE segmented mirror; space telescope; flux pinning; cryogenic; edgewise connectivity; stiffness; damping; flexure ID HIGH-TEMPERATURE SUPERCONDUCTORS; MAGNETIC STIFFNESS; SPACECRAFT; RECONFIGURATION; LEVITATION; ACTUATOR; SAFIR; FORCE AB Although large cryogenic space telescopes may provide a means of answering compelling astrophysics questions, the required increase in the primary mirror diameter presents technical challenges. Larger primaries are more flexible, and cryogenic mirrors are typically very lightly damped-the material damping is negligible, and common damping methods break down. To address these challenges, we propose placing flux-pinning mechanisms along the edges of adjacent mirror segments. These mechanisms consist of a collection of magnets and superconductors, and like flexures, they preferentially allow motion in specific degrees of freedom. Motion in nonpreferred degrees of freedom is resisted by a force analogous to a damped spring force, and the stiffness and damping can be adjusted independently. As an example, we consider simple mechanisms consisting of an inexpensive magnet and a single superconductor. These mechanisms provide increasing resistance as the magnet and superconductor-or mirror segments attached to each-come closer to colliding. These mechanisms, with typical stiffness and damping values on the order of 5000 N/m and 5 kg/s, respectively, also provide modest improvements to the mirror performance. Greater gains can be achieved by using stronger magnets or smaller separations, or by placing nonmagnetic conductive materials near the mechanism. (C) The Authors. Published by SPIE under a Creative Commons Attribution 3.0 Unported License. Distribution or reproduction of this work in whole or in part requires full attribution of the original publication, including its DOI. C1 [Gersh-Range, Jessica] Cornell Univ, 127 Upson Hall, Ithaca, NY 14853 USA. [Arnold, William R., Sr.] Def Acquisit Inc, Jacobs ESSSA Grp, Huntsville, AL 35806 USA. [Lehner, David; Stahl, H. Philip] NASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Gersh-Range, J (reprint author), Cornell Univ, 127 Upson Hall, Ithaca, NY 14853 USA. EM jag389@cornell.edu NR 37 TC 0 Z9 0 U1 0 U2 0 PU SPIE-SOC PHOTO-OPTICAL INSTRUMENTATION ENGINEERS PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98225 USA SN 2329-4124 EI 2329-4221 J9 J ASTRON TELESC INST JI J. Astron. Telesc. Instrum. Syst. PD JAN-MAR PY 2015 VL 1 IS 1 AR 014001 DI 10.1117/1.JATIS.1.1.014001 PG 11 WC Engineering, Aerospace; Instruments & Instrumentation; Optics SC Engineering; Instruments & Instrumentation; Optics GA DG2EP UT WOS:000371879500002 ER PT J AU Hicks, BA Chakrabarti, S Cook, TA AF Hicks, Brian A. Chakrabarti, Supriya Cook, Timothy A. TI Interferometric nulling limits with tip-tilt-piston deformable mirrors and a pinhole spatial filter array SO JOURNAL OF ASTRONOMICAL TELESCOPES INSTRUMENTS AND SYSTEMS LA English DT Article DE spatial filters; wavefront correction; interferometry; exoplanets; high-contrast imaging ID EXTRASOLAR PLANETS; NEARBY STARS; HR 8799; CORONAGRAPH; LIGHT; PHASE; EARTH; IMAGES; PUPILS; DEEP AB We explore the use of hexagonal segment tip-tilt-piston deformable mirrors alone and paired with pinhole spatial filter arrays for high-order wavefront correction of nulling interferometers used for visible light study of exoplanetary systems at 10(7) to 10(10) contrast within regions extending similar to 0.1 to 6 arc s from a parent star. A similar system has been proposed using a single-mode fiber array as an alternative to using multiple deformable mirrors to correct both phase aberrations and balance electric field amplitude, the benefit being drastically reduced component and control complexity. Performance is compared using measured deformable mirror data for hexagonal arrays consisting of a number of rings N-R = 2 to 18, emphasizing the trade between throughput and the additional contrast gained from suppressing wavefront errors introduced by the deformable mirror at spatial frequencies Lambda >= N-R that are otherwise present in the image at corresponding field locations. Taking into account effects of loss of throughput and vignetting, the nulled signal-to-noise ratio is shown to improve for filtered systems in the outer portion of the field of view. Modeled performance shows no significant change in signal-to-noise in the inner field of view. (C) 2015 Society of Photo-Optical Instrumentation Engineers (SPIE) C1 [Hicks, Brian A.] NASA, Postdoctoral Program, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Chakrabarti, Supriya; Cook, Timothy A.] Univ Massachusetts, Ctr Atmospher Res, Lowell, MA 01854 USA. RP Hicks, BA (reprint author), NASA, Postdoctoral Program, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. EM brian.a.hicks@nasa.gov NR 48 TC 0 Z9 0 U1 0 U2 0 PU SPIE-SOC PHOTO-OPTICAL INSTRUMENTATION ENGINEERS PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98225 USA SN 2329-4124 EI 2329-4221 J9 J ASTRON TELESC INST JI J. Astron. Telesc. Instrum. Syst. PD JAN-MAR PY 2015 VL 1 IS 1 AR 019001 DI 10.1117/1JATIS.1.1.019001 PG 10 WC Engineering, Aerospace; Instruments & Instrumentation; Optics SC Engineering; Instruments & Instrumentation; Optics GA DG2EP UT WOS:000371879500010 ER PT J AU Perea, RS Parsons, AM Groza, M Caudel, D Nowicki, SF Burger, A Stassun, KG Peterson, TE AF Perea, Rose Schmitt Parsons, Ann M. Groza, Mike Caudel, David Nowicki, Suzanne F. Burger, Arnold Stassun, Keivan G. Peterson, Todd E. TI Scintillation properties of strontium iodide doped with europium for high-energy astrophysical detectors: nonproportionality as a function of temperature and at high gamma-ray energies SO JOURNAL OF ASTRONOMICAL TELESCOPES INSTRUMENTS AND SYSTEMS LA English DT Article DE scintillator detectors; nonproportionality; gamma-ray detectors; Onsager mechanism; charge carriers; excitons ID NON-PROPORTIONALITY; RESOLUTION AB Strontium iodide doped with europium [SrI2(Eu2+)] is a new scintillator material being developed as an alternative to lanthanum bromide doped with cerium [LaBr3(Ce3+)] for use in high- energy astrophysical detectors. As with all scintillators, the issue of nonproportionality is important because it affects the energy resolution of the detector. We investigate how the nonproportionality of SrI2(Eu2+) changes as a function of temperature from 16 to 60 degrees C by heating the SrI2(Eu2+) scintillator separate from the photomultiplier tube. In a separate experiment, we also investigate the nonproportionality at high energies (up to 6 MeV) of SrI2(Eu2+) at a testing facility located at NASA Goddard Space Flight Center. We find that the nonproportionality increases nearly monotonically as the temperature of the SrI2(Eu2+) scintillator is increased, although there is evidence of nonmonotonic behavior near 40 degrees C, perhaps due to electric charge carriers trapping in the material. We also find that within the energy range of 662 keV to 6.1 MeV, the change in the nonproportionality of SrI2(Eu2+) is similar to 1.5 to 2%. (C) The Authors. Published by SPIE under a Creative Commons Attribution 3.0 Unported License. Distribution or reproduction of this work in whole or in part requires full attribution of the original publication, including its DOI. C1 [Perea, Rose Schmitt; Caudel, David; Burger, Arnold; Stassun, Keivan G.; Peterson, Todd E.] Vanderbilt Univ, Dept Phys & Astron, 2401 Vanderbilt Pl, Nashville, TN 37240 USA. [Perea, Rose Schmitt; Groza, Mike; Caudel, David; Burger, Arnold; Stassun, Keivan G.] Fisk Univ, Dept Life & Phys Sci, Nashville, TN 37208 USA. [Parsons, Ann M.; Nowicki, Suzanne F.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Nowicki, Suzanne F.] NASA, Univ Space Res Assoc, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Peterson, Todd E.] Vanderbilt Univ, Inst Imaging Sci, Nashville, TN 37232 USA. [Peterson, Todd E.] Vanderbilt Univ, Dept Radiol & Radiol Sci, Nashville, TN 37232 USA. RP Perea, RS (reprint author), Vanderbilt Univ, Dept Phys & Astron, 2401 Vanderbilt Pl, Nashville, TN 37240 USA. EM rose.s.perea@vanderbilt.edu NR 25 TC 2 Z9 2 U1 2 U2 2 PU SPIE-SOC PHOTO-OPTICAL INSTRUMENTATION ENGINEERS PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98225 USA SN 2329-4124 EI 2329-4221 J9 J ASTRON TELESC INST JI J. Astron. Telesc. Instrum. Syst. PD JAN-MAR PY 2015 VL 1 IS 1 AR 016002 DI 10.1117/1.JATIS.1.1.016002 PG 7 WC Engineering, Aerospace; Instruments & Instrumentation; Optics SC Engineering; Instruments & Instrumentation; Optics GA DG2EP UT WOS:000371879500009 ER PT J AU Ricker, GR Winn, JN Vanderspek, R Latham, DW Bakos, GA Bean, JL Berta-Thompson, ZK Brown, TM Buchhave, L Butler, NR Butler, RP Chaplin, WJ Charbonneau, D Christensen-Dalsgaard, J Clampin, M Deming, D Doty, J De Lee, N Dressing, C Dunham, EW Endl, M Fressin, F Ge, J Henning, T Holman, MJ Howard, AW Ida, S Jenkins, JM Jernigan, G Johnson, JA Kaltenegger, L Kawai, N Kjeldsen, H Laughlin, G Levine, AM Lin, D Lissauer, JJ MacQueen, P Marcy, G McCullough, PR Morton, TD Narita, N Paegert, M Palle, E Pepe, F Pepper, J Quirrenbach, A Rinehart, SA Sasselov, D Sato, B Seager, S Sozzetti, A Stassun, KG Sullivan, P Szentgyorgyi, A Torres, G Udry, S Villasenor, J AF Ricker, George R. Winn, Joshua N. Vanderspek, Roland Latham, David W. Bakos, Gaspar A. Bean, Jacob L. Berta-Thompson, Zachory K. Brown, Timothy M. Buchhave, Lars Butler, Nathaniel R. Butler, R. Paul Chaplin, William J. Charbonneau, David Christensen-Dalsgaard, Jorgen Clampin, Mark Deming, Drake Doty, John De Lee, Nathan Dressing, Courtney Dunham, Edward W. Endl, Michael Fressin, Francois Ge, Jian Henning, Thomas Holman, Matthew J. Howard, Andrew W. Ida, Shigeru Jenkins, Jon M. Jernigan, Garrett Johnson, John Asher Kaltenegger, Lisa Kawai, Nobuyuki Kjeldsen, Hans Laughlin, Gregory Levine, Alan M. Lin, Douglas Lissauer, Jack J. MacQueen, Phillip Marcy, Geoffrey McCullough, Peter R. Morton, Timothy D. Narita, Norio Paegert, Martin Palle, Enric Pepe, Francesco Pepper, Joshua Quirrenbach, Andreas Rinehart, Stephen A. Sasselov, Dimitar Sato, Bun'ei Seager, Sara Sozzetti, Alessandro Stassun, Keivan G. Sullivan, Peter Szentgyorgyi, Andrew Torres, Guillermo Udry, Stephane Villasenor, Joel TI Transiting Exoplanet Survey Satellite SO JOURNAL OF ASTRONOMICAL TELESCOPES INSTRUMENTS AND SYSTEMS LA English DT Article DE exoplanet; extrasolar planet; photometry; satellite; transits ID KEPLER; PLANETS; STARS; MISSION; SYSTEMS; CATALOG AB The Transiting Exoplanet Survey Satellite (TESS) will search for planets transiting bright and nearby stars. TESS has been selected by NASA for launch in 2017 as an Astrophysics Explorer mission. The spacecraft will be placed into a highly elliptical 13.7-day orbit around the Earth. During its 2-year mission, TESS will employ four wide-field optical charge-coupled device cameras to monitor at least 200,000 main-sequence dwarf stars with I-C approximate to 4-13 for temporary drops in brightness caused by planetary transits. Each star will be observed for an interval ranging from 1 month to 1 year, depending mainly on the star's ecliptic latitude. The longest observing intervals will be for stars near the ecliptic poles, which are the optimal locations for follow-up observations with the James Webb Space Telescope. Brightness measurements of preselected target stars will be recorded every 2 min, and full frame images will be recorded every 30 min. TESS stars will be 10 to 100 times brighter than those surveyed by the pioneering Kepler mission. This will make TESS planets easier to characterize with follow-up observations. TESS is expected to find more than a thousand planets smaller than Neptune, including dozens that are comparable in size to the Earth. Public data releases will occur every 4 months, inviting immediate community-wide efforts to study the new planets. The TESS legacy will be a catalog of the nearest and brightest stars hosting transiting planets, which will endure as highly favorable targets for detailed investigations. (C) The Authors. Published by SPIE under a Creative Commons Attribution 3.0 Unported License. Distribution or reproduction of this work in whole or in part requires full attribution of the original publication, including its DOI. C1 [Ricker, George R.; Winn, Joshua N.; Vanderspek, Roland; Berta-Thompson, Zachory K.; Levine, Alan M.; Seager, Sara; Sullivan, Peter; Villasenor, Joel] MIT, 77 Massachusetts Ave, Cambridge, MA 02139 USA. [Latham, David W.; Buchhave, Lars; Charbonneau, David; Dressing, Courtney; Fressin, Francois; Holman, Matthew J.; Johnson, John Asher; Sasselov, Dimitar; Szentgyorgyi, Andrew; Torres, Guillermo] Harvard Smithsonian Ctr Astrophys, Cambridge, MA 02138 USA. [Bakos, Gaspar A.; Morton, Timothy D.] Princeton Univ, Princeton, NJ 08540 USA. [Bean, Jacob L.] Univ Chicago, Chicago, IL 60611 USA. [Brown, Timothy M.] Las Cumbres Observ Global Telescope, Goleta, CA 93117 USA. [Buchhave, Lars] Univ Copenhagen, DK-1165 Copenhagen, Denmark. [Butler, Nathaniel R.] Arizona State Univ, Tempe, AZ 85004 USA. [Butler, R. Paul] Carnegie Inst Sci, Dept Terr Magnetism, Washington, DC 20015 USA. [Chaplin, William J.] Univ Birmingham, Birmingham B15 2TT, W Midlands, England. [Chaplin, William J.; Christensen-Dalsgaard, Jorgen; Kjeldsen, Hans] Univ Aarhus, Stellar Astrophys Ctr, DK-8000 Aarhus, Denmark. [Clampin, Mark; Rinehart, Stephen A.] NASA, Goddard Space Flight Ctr, Green Belt, MD 20771 USA. [Deming, Drake] Univ Maryland, College Pk, MD 20742 USA. [Doty, John] Noqsi Aerosp Ltd, Pine, CO 80470 USA. [De Lee, Nathan] No Kentucky Univ, Highland Hts, KY 41099 USA. [De Lee, Nathan; Paegert, Martin; Pepper, Joshua; Stassun, Keivan G.] Vanderbilt Univ, Nashville, TN 37235 USA. [Dunham, Edward W.] Lowell Observ, Flagstaff, AZ 86001 USA. [Endl, Michael; MacQueen, Phillip] McDonald Observ, Austin, TX 78712 USA. [Ge, Jian] Univ Florida, Gainesville, FL 32611 USA. [Henning, Thomas; Kaltenegger, Lisa] Max Planck Inst Astron, D-69117 Heidelberg, Germany. [Howard, Andrew W.] Univ Hawaii, Manoa, HI 96822 USA. [Ida, Shigeru; Kawai, Nobuyuki; Sato, Bun'ei] Tokyo Inst Technol, Tokyo 1528851, Japan. [Jenkins, Jon M.; Lissauer, Jack J.] NASA, Ames Res Ctr, Mountain View, CA 94035 USA. [Jernigan, Garrett] Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. [Laughlin, Gregory; Lin, Douglas] UCO, Lick Observ, Santa Cruz, CA 95064 USA. [Marcy, Geoffrey] Univ Calif Berkeley, Berkeley, CA 94720 USA. [McCullough, Peter R.] Space Telescope Sci Inst, Baltimore, MD 21218 USA. [McCullough, Peter R.] Johns Hopkins Univ, Baltimore, MD 21218 USA. [Narita, Norio] Natl Astron Observ Japan, Tokyo 1818588, Japan. [Palle, Enric] Inst Astrofis Canarias, E-38205 San Cristobal la Laguna, Tenerife, Spain. [Pepe, Francesco; Udry, Stephane] Observ Geneva, CH-1290 Versoix, Switzerland. [Pepper, Joshua] Lehigh Univ, Bethlehem, PA 18015 USA. [Quirrenbach, Andreas] Heidelberg Univ, Zentrum Astron, Landessternwarte, D-69117 Heidelberg, Germany. [Sozzetti, Alessandro] INAF, Osservatorio Astrofis Torino, I-10025 Turin, Italy. [Stassun, Keivan G.] Fisk Univ, Nashville, TN 37208 USA. RP Ricker, GR (reprint author), MIT, 77 Massachusetts Ave, Cambridge, MA 02139 USA. EM grr@space.mit.edu NR 33 TC 93 Z9 93 U1 6 U2 12 PU SPIE-SOC PHOTO-OPTICAL INSTRUMENTATION ENGINEERS PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98225 USA SN 2329-4124 EI 2329-4221 J9 J ASTRON TELESC INST JI J. Astron. Telesc. Instrum. Syst. PD JAN-MAR PY 2015 VL 1 IS 1 AR 014003 DI 10.1117/1.JATIS.1.1.014003 PG 10 WC Engineering, Aerospace; Instruments & Instrumentation; Optics SC Engineering; Instruments & Instrumentation; Optics GA DG2EP UT WOS:000371879500004 ER PT S AU Szafir, D Mutlu, B Fong, T AF Szafir, Daniel Mutlu, Bilge Fong, Terrence GP ACM TI Communicating Directionality in Flying Robots SO PROCEEDINGS OF THE 2015 ACM/IEEE INTERNATIONAL CONFERENCE ON HUMAN-ROBOT INTERACTION (HRI'15) SE ACMIEEE International Conference on Human-Robot Interaction LA English DT Proceedings Paper CT 10th Annual ACM/IEEE International Conference on Human-Robot Interaction (HRI) CY MAR 02-05, 2015 CL Portland, OR SP IEEE, ACM, ACM SIGCHI, ACM SIGART, IEEE Robot & Automat Soc, AAAI, HFES, ACM SIGAI DE Robot design; signaling intent; free-flyers; micro air vehicles (MAVs) ID VISUAL-PERCEPTION; MOTION; TIMES AB Small flying robots represent a rapidly emerging family of robotic technologies with aerial capabilities that enable unique forms of assistance in a variety of collaborative tasks. Such tasks will necessitate interaction with humans in close proximity, requiring that designers consider human perceptions regarding robots flying and acting within human environments. We explore the design space regarding explicit robot communication of flight intentions to nearby viewers. We apply design constraints to robot flight behaviors, using biological and airplane flight as inspiration, and develop a set of signaling mechanisms for visually communicating directionality while operating under such constraints. We implement our designs on two commercial flyers, requiring little modification to the base platforms, and evaluate each signaling mechanism, as well as a no-signaling baseline, in a user study in which participants were asked to predict robot intent. We found that three of our designs significantly improved viewer response time and accuracy over the baseline and that the form of the signal offered tradeoffs in precision, generalizability, and perceived robot usability. C1 [Szafir, Daniel; Mutlu, Bilge] Univ Wisconsin, 1210 W Dayton St, Madison, WI 53706 USA. [Fong, Terrence] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Szafir, D (reprint author), Univ Wisconsin, 1210 W Dayton St, Madison, WI 53706 USA. EM dszafir@cs.wisc.edu; bilge@cs.wisc.edu; terry.fong@nasa.gov NR 38 TC 8 Z9 8 U1 0 U2 0 PU ASSOC COMPUTING MACHINERY PI NEW YORK PA 1515 BROADWAY, NEW YORK, NY 10036-9998 USA SN 2167-2121 BN 978-1-4503-2882-1 J9 ACMIEEE INT CONF HUM PY 2015 BP 19 EP 26 DI 10.1145/2696454.2696475 PG 8 WC Computer Science, Artificial Intelligence; Computer Science, Theory & Methods; Engineering, Electrical & Electronic; Robotics SC Computer Science; Engineering; Robotics GA BE4NU UT WOS:000371986600004 ER PT S AU Ryoo, MS Fuchs, TJ Xia, L Aggarwa, JK Matthies, L AF Ryoo, M. S. Fuchs, Thomas J. Xia, Lu Aggarwa, J. K. Matthies, Larry GP ACM TI Robot-Centric Activity Prediction from First-Person Videos: What Will They Do to Me? SO PROCEEDINGS OF THE 2015 ACM/IEEE INTERNATIONAL CONFERENCE ON HUMAN-ROBOT INTERACTION (HRI'15) SE ACMIEEE International Conference on Human-Robot Interaction LA English DT Proceedings Paper CT 10th Annual ACM/IEEE International Conference on Human-Robot Interaction (HRI) CY MAR 02-05, 2015 CL Portland, OR SP IEEE, ACM, ACM SIGCHI, ACM SIGART, IEEE Robot & Automat Soc, AAAI, HFES, ACM SIGAI DE Activity recognition; first-person videos; human-robot interaction AB In this paper, we present a core technology to enable robot recognition of human activities during human-robot interactions. In particular, we propose a methodology for early recognition of activities from robot-centric videos (i.e., first-person videos) obtained from a robot's viewpoint during its interaction with humans. Early recognition, which is also known as activity prediction, is an ability to infer an ongoing activity at its early stage. We present an algorithm to recognize human activities targeting the camera from streaming videos, enabling the robot to predict intended activities of the interacting person as early as possible and take fast reactions to such activities (e.g., avoiding harmful events targeting itself before they actually occur). We introduce the novel concept of 'onset' that efficiently summarizes pre-activity observations, and design a recognition approach to consider event history in addition to visual features from first-person videos. We propose to represent an onset using a cascade histogram of time series gradients, and we describe a novel algorithmic setup to take advantage of such onset for early recognition of activities. The experimental results clearly illustrate that the proposed concept of onset enables better/earlier recognition of human activities from first-person videos collected with a robot. C1 [Ryoo, M. S.; Fuchs, Thomas J.; Matthies, Larry] CALTECH, Jet Prop Lab, Pasadena, CA USA. [Xia, Lu] Amazon Com Inc, Seattle, WA USA. [Xia, Lu; Aggarwa, J. K.] Univ Texas Austin, Dept ECE, Austin, TX 78712 USA. RP Ryoo, MS (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA USA. EM mryoo@jpl.nasa.gov NR 20 TC 5 Z9 5 U1 0 U2 0 PU ASSOC COMPUTING MACHINERY PI NEW YORK PA 1515 BROADWAY, NEW YORK, NY 10036-9998 USA SN 2167-2121 BN 978-1-4503-2882-1 J9 ACMIEEE INT CONF HUM PY 2015 BP 295 EP 302 DI 10.1145/2696454.2696462 PG 8 WC Computer Science, Artificial Intelligence; Computer Science, Theory & Methods; Engineering, Electrical & Electronic; Robotics SC Computer Science; Engineering; Robotics GA BE4NU UT WOS:000371986600040 ER PT S AU Arumugam, DD AF Arumugam, Darmindra D. GP IEEE TI Multi-axis single-anchor vs. single-axis multi-anchors in long-range 2D MQS positioning SO 2015 IEEE INTERNATIONAL SYMPOSIUM ON ANTENNAS AND PROPAGATION & USNC/URSI NATIONAL RADIO SCIENCE MEETING SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE International Symposium on Antennas and Propagation / USNC/URSI National North American Radio Science Meeting CY JUL 19-24, 2015 CL Vancouver, CANADA SP Inst Elect & Elect Engineers, IEEE Antennas & Propagat Soc, USNC, URSI DE Electromagnetic fields; magnetoquasistatics; radio position measurement; radio tracking ID IMAGE THEORY AB Recent developments have enabled single-anchor long-range two-dimensional (2D) positioning using low-frequency magnetoquasistatic fields. The approach of using a single-anchor for 2D position and orientation sensing results in significantly simplified systems and setup when compared to previous multi-anchor systems. The various advantages of single-anchor systems over multi-anchor systems include accurate closed-form inverted solutions, substantially simplified system setup and calibration, no relative ground truth needs, and ability to easily perform low-latency or real-time sensing with simple systems. C1 [Arumugam, Darmindra D.] CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Arumugam, DD (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA USA. EM Darminda.D.Arumugam@jpl.nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4799-7815-1 J9 IEEE ANTENNAS PROP PY 2015 BP 165 EP 166 PG 2 WC Telecommunications SC Telecommunications GA BE3YW UT WOS:000371401400081 ER PT S AU Arumugam, DD AF Arumugam, Darmindra D. GP IEEE TI Magnetoquasistatic position measurement above earth using the exact integral solutions SO 2015 IEEE INTERNATIONAL SYMPOSIUM ON ANTENNAS AND PROPAGATION & USNC/URSI NATIONAL RADIO SCIENCE MEETING SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE International Symposium on Antennas and Propagation / USNC/URSI National North American Radio Science Meeting CY JUL 19-24, 2015 CL Vancouver, CANADA SP Inst Elect & Elect Engineers, IEEE Antennas & Propagat Soc, USNC, URSI DE Electromagnetic fields; magnetoquasistatics; radio position measurement; radio tracking AB Measurements of the magnetoquasistatic coupling between a co-polarized vertical emitting and receiving coil, both located above earth, is compared to calculations using complex image theory and the exact integral solutions along a direction perpendicular to the surface normal axes of the loops. Inverting the theoretical expressions of the exact integral solution to estimate distance from measured fields resulted in an RMS error of 0.089 m for distances between 1.3-29.4 m, which corresponds to a 21.9% reduction in RMS distance error over complex image theory. C1 [Arumugam, Darmindra D.] CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Arumugam, DD (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA USA. EM Darmindra.D.Arumugam@jpl.nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4799-7815-1 J9 IEEE ANTENNAS PROP PY 2015 BP 554 EP 555 PG 2 WC Telecommunications SC Telecommunications GA BE3YW UT WOS:000371401400270 ER PT S AU Cannon, BL Vanhille, KJ Sadowy, GA AF Cannon, Benjamin L. Vanhille, Kenneth J. Sadowy, Gregory A. GP IEEE TI Microfabricated Dual-Polarized, W-band Antenna Architecture for Scalable Line Array Feed SO 2015 IEEE INTERNATIONAL SYMPOSIUM ON ANTENNAS AND PROPAGATION & USNC/URSI NATIONAL RADIO SCIENCE MEETING SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE International Symposium on Antennas and Propagation / USNC/URSI National North American Radio Science Meeting CY JUL 19-24, 2015 CL Vancouver, CANADA SP Inst Elect & Elect Engineers, IEEE Antennas & Propagat Soc, USNC, URSI AB Scalable antenna arrays that support active, electronic scanning at W-band are of interest for future remote sensing missions such as the proposed Aerosol, Cloud and Ecosystems (ACE) mission. An intermediate step towards an electronically scanned solution is demonstrated. A dual-polarized passive, 2x8 element 94 GHz array is microfabricated in the Nuvotronics proprietary PolyStrata process. Feed networks are located behind the footprint of the array to permit scalable tiling to form larger arrays. Measured S-parameters are presented, demonstrating 2:1 VSWR bandwidth of over 8%, and 45 dB isolation between transmit and cross-polarized receive channel. Measured radiation patterns demonstrate excellent agreement with simulation predictions and repeatability between units. C1 [Cannon, Benjamin L.; Vanhille, Kenneth J.] Nuvotronics LLC, Durham, NC USA. [Sadowy, Gregory A.] CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Cannon, BL (reprint author), Nuvotronics LLC, Durham, NC USA. EM bcannon@nuvotronics.com NR 3 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4799-7815-1 J9 IEEE ANTENNAS PROP PY 2015 BP 615 EP 616 PG 2 WC Telecommunications SC Telecommunications GA BE3YW UT WOS:000371401400300 ER PT S AU Zemba, MJ Morse, JR Nessel, JA AF Zemba, Michael J. Morse, Jacquelynne R. Nessel, James A. GP IEEE TI Long-Term Trends in Space-Ground Atmospheric Propagation Measurements SO 2015 IEEE INTERNATIONAL SYMPOSIUM ON ANTENNAS AND PROPAGATION & USNC/URSI NATIONAL RADIO SCIENCE MEETING SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE International Symposium on Antennas and Propagation / USNC/URSI National North American Radio Science Meeting CY JUL 19-24, 2015 CL Vancouver, CANADA SP Inst Elect & Elect Engineers, IEEE Antennas & Propagat Soc, USNC, URSI AB Propagation measurement campaigns are critical to characterizing the atmospheric behavior of a location and efficiently designing space-ground links. However, as global climate change affects weather patterns, the long-term trends of propagation data may be impacted over periods of decades or longer. Particularly, at high microwave frequencies (10 GHz and above), rain plays a dominant role in the attenuation statistics, and it has been observed that rain events over the past 50 years have trended toward increased frequency, intensity, and rain height. In the interest of quantifying the impact of these phenomena on long-term trends in propagation data, this paper compares two 20 GHz measurement campaigns both conducted at NASA's White Sands facility in New Mexico. The first is from the Advanced Communication Technology Satellite (ACTS) propagation campaign from 1994 - 1998, while the second is amplitude data recorded during a site test interferometer (STI) phase characterization campaign from 2009 - 2014. C1 [Zemba, Michael J.; Morse, Jacquelynne R.; Nessel, James A.] NASA, Glenn Res Ctr, Adv High Frequency Branch, Cleveland, OH USA. RP Zemba, MJ (reprint author), NASA, Glenn Res Ctr, Adv High Frequency Branch, Cleveland, OH USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4799-7815-1 J9 IEEE ANTENNAS PROP PY 2015 BP 1003 EP 1004 PG 2 WC Telecommunications SC Telecommunications GA BE3YW UT WOS:000371401401057 ER PT S AU Gonzalez-Ovejero, D Chattopadhyay, G Maci, S AF Gonzalez-Ovejero, David Chattopadhyay, Goutam Maci, Stefano GP IEEE TI Efficient Analysis of Metasurfaces in a Planar Layered Medium SO 2015 IEEE INTERNATIONAL SYMPOSIUM ON ANTENNAS AND PROPAGATION & USNC/URSI NATIONAL RADIO SCIENCE MEETING SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE International Symposium on Antennas and Propagation / USNC/URSI National North American Radio Science Meeting CY JUL 19-24, 2015 CL Vancouver, CANADA SP Inst Elect & Elect Engineers, IEEE Antennas & Propagat Soc, USNC, URSI AB Gaussian ring basis functions (GRBFs) are proposed for the method of moments (MoM) analysis of metasurfaces (MTSs) in a planar layered medium. We solve the relevant integral equation for the homogenized problem, accounting for the MTS layers as impedance boundary conditions. The closed-form spectra of the GRBFs allows an efficient computation of the MoM impedance matrix using the spectral-domain approach and asymptotic expansions. Moreover, these basis functions represent the global evolution of the surface current density in an effective manner, which leads to a significant reduction of the number of unknowns. C1 [Gonzalez-Ovejero, David; Chattopadhyay, Goutam] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Maci, Stefano] Univ Siena, Dept Informat Engn & Math, I-53100 Siena, Italy. RP Gonzalez-Ovejero, D (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM david.gonzalez@jpl.nasa.gov; goutam.chattopadhyay@jpl.nasa.gov; macis@dii.unisi.it OI Gonzalez Ovejero, David/0000-0002-2552-0649 NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4799-7815-1 J9 IEEE ANTENNAS PROP PY 2015 BP 1082 EP 1083 PG 2 WC Telecommunications SC Telecommunications GA BE3YW UT WOS:000371401401095 ER PT S AU Mackenzie, AI AF Mackenzie, Anne I. GP IEEE TI Microwave Band Gaps Produced by Varying Numbers of Mushroom Metamaterial Cells SO 2015 IEEE INTERNATIONAL SYMPOSIUM ON ANTENNAS AND PROPAGATION & USNC/URSI NATIONAL RADIO SCIENCE MEETING SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE International Symposium on Antennas and Propagation / USNC/URSI National North American Radio Science Meeting CY JUL 19-24, 2015 CL Vancouver, CANADA SP Inst Elect & Elect Engineers, IEEE Antennas & Propagat Soc, USNC, URSI ID ANTENNA AB Surface wave transmission at X-band frequencies through mushroom metamaterials was measured for different sizes of mushroom arrays fabricated on high-permittivity circuit boards. For arrays of width 1, 2, 3, and 26 cells, the band gap increased in frequency and depth as the number of cells increased. The maximum filtering effect was 22 dB. This study demonstrates the necessity of careful simulation or measurement to ensure that the desired band gap is achieved with finite band gap arrays. C1 [Mackenzie, Anne I.] NASA, Langley Res Ctr, Electromagnet & Sensors Branch, Hampton, VA 23665 USA. RP Mackenzie, AI (reprint author), NASA, Langley Res Ctr, Electromagnet & Sensors Branch, Hampton, VA 23665 USA. EM anne.mackenzie-1@nasa.gov NR 3 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4799-7815-1 J9 IEEE ANTENNAS PROP PY 2015 BP 1102 EP 1103 PG 2 WC Telecommunications SC Telecommunications GA BE3YW UT WOS:000371401401105 ER PT S AU Santos, JP Rahmat-Samii, Y Chamberlain, NF Hodges, RE AF Santos, Jean Paul Rahmat-Samii, Yahya Chamberlain, Neil F. Hodges, Richard E. GP IEEE TI Single Feed Circularly Polarized Half E-Shaped Array: a Compact Assembly for Dual-Band Direct-to-Earth Communications in Mars Rovers SO 2015 IEEE INTERNATIONAL SYMPOSIUM ON ANTENNAS AND PROPAGATION & USNC/URSI NATIONAL RADIO SCIENCE MEETING SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE International Symposium on Antennas and Propagation / USNC/URSI National North American Radio Science Meeting CY JUL 19-24, 2015 CL Vancouver, CANADA SP Inst Elect & Elect Engineers, IEEE Antennas & Propagat Soc, USNC, URSI ID PATCH ANTENNAS AB Establishing reliable and direct communications links from Earth to Mars rovers, also known as Direct-to-Earth (DTE) communications, is a complex and challenging antenna design problem. With the possibility of diminished UHF relay assets for the upcoming Mars 2020 mission, supporting such a technology requires a high performance antenna array system in order to enable substantial return of valuable scientific data. We propose a novel X-band single feed circularly polarized antenna subarray comprised of half E-shaped elements, optimized using Particle Swarm Optimization. The subarray architecture is modular, fed by a waveguide feed network, enabling high power handling capability. The subarray was prototyped and measured, showing good agreement between simulation and measurements. The design achieves excellent dual-band characteristics for uplink and downlink frequencies and is able to satisfy the required NASA DTE challenging system-level requirements. C1 [Santos, Jean Paul; Rahmat-Samii, Yahya] Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90024 USA. [Chamberlain, Neil F.; Hodges, Richard E.] CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Santos, JP (reprint author), Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90024 USA. EM jpsant2006@ucla.edu; rahmat@ee.ucla.edu; neil.f.chamberlain@jpl.nasa.gov; richard.e.hodges@jpl.nasa.gov NR 4 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4799-7815-1 J9 IEEE ANTENNAS PROP PY 2015 BP 1694 EP 1695 PG 2 WC Telecommunications SC Telecommunications GA BE3YW UT WOS:000371401401395 ER PT S AU Rahmat-Samii, Y Kovitz, JM Amaro, LR AF Rahmat-Samii, Yahya Kovitz, Joshua M. Amaro, Luis R. GP IEEE TI Normalized Plane Wave Spectra: Quantification of Measured Near-Field Distributions for the ISS-RapidScat using Measured Far-field Patterns SO 2015 IEEE INTERNATIONAL SYMPOSIUM ON ANTENNAS AND PROPAGATION & USNC/URSI NATIONAL RADIO SCIENCE MEETING SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE International Symposium on Antennas and Propagation / USNC/URSI National North American Radio Science Meeting CY JUL 19-24, 2015 CL Vancouver, CANADA SP Inst Elect & Elect Engineers, IEEE Antennas & Propagat Soc, USNC, URSI AB The International Space Station Rapid Scatterometer (ISS-RapidScat) instrument was recently developed and launched to sense ocean winds. This recent addition to the ISS significantly improves the detection and sensing capabilities of the current satellite constellation. An important consideration in this antenna is the interference generated towards nearby space vehicles and humans due to its relatively high RF power output. To avoid this issue, our work aims to characterize the antenna's near-field distribution, whose knowledge could aid in blanker circuit design to shut off the RF power for certain time slots during the scan period. A generalized and customized procedure using Spectral Domain analysis, i.e. plane wave spectra, is proposed to predict the absolute near-field values in V/m for a given radiated power and measured far-field patterns. C1 [Rahmat-Samii, Yahya; Kovitz, Joshua M.] Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90024 USA. [Amaro, Luis R.] CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Rahmat-Samii, Y (reprint author), Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90024 USA. EM rahmat@ee.ucla.edu; jmkovitz@ucla.edu; luis.r.amaro@jpl.nasa.gov NR 3 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4799-7815-1 J9 IEEE ANTENNAS PROP PY 2015 BP 1702 EP 1703 PG 2 WC Telecommunications SC Telecommunications GA BE3YW UT WOS:000371401401399 ER PT S AU Novak, MH Volakis, JL Miranda, FA AF Novak, Markus H. Volakis, John L. Miranda, Felix A. GP IEEE TI Wideband Array for C, X, and Ku-Band Applications with 5.3:1 Bandwidth SO 2015 IEEE INTERNATIONAL SYMPOSIUM ON ANTENNAS AND PROPAGATION & USNC/URSI NATIONAL RADIO SCIENCE MEETING SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE International Symposium on Antennas and Propagation / USNC/URSI National North American Radio Science Meeting CY JUL 19-24, 2015 CL Vancouver, CANADA SP Inst Elect & Elect Engineers, IEEE Antennas & Propagat Soc, USNC, URSI ID ANTENNA AB Planar arrays that exploit strong intentional coupling between elements have allowed for very wide bandwidths in low-profile configurations. However, such designs also require complex impedance matching networks that must also be very compact. For many space applications, typically occurring at C-, X-, Ku-, and most recently at Ka-band, such designs require specialized and expensive fabrication techniques. To address this issue, a novel ultra-wideband array is presented, using a simplified feed network to reduce fabrication cost. The array operates from 3.5-18.5 GHz with VSWR<2.4 at broadside, and is of very low profile, having a total height of lambda/10 at the lowest frequency of operation. Validation is provided using a 64-element prototype array, fabricated using common Printed Circuit Board (PCB) technology. The low size, weight, and cost of this array make it attractive for space-borne applications. C1 [Novak, Markus H.; Volakis, John L.] Ohio State Univ, ECE Dept, ElectroSci Lab, Columbus, OH 43210 USA. [Miranda, Felix A.] NASA Glenn Res Ctr, Adv High Frequency Branch, Cleveland, OH USA. RP Novak, MH (reprint author), Ohio State Univ, ECE Dept, ElectroSci Lab, Columbus, OH 43210 USA. NR 6 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4799-7815-1 J9 IEEE ANTENNAS PROP PY 2015 BP 1995 EP 1996 PG 2 WC Telecommunications SC Telecommunications GA BE3YW UT WOS:000371401402034 ER PT S AU Lambert, KM Miranda, FA Romanofsky, RR Durham, TE Vanhille, KJ AF Lambert, Kevin M. Miranda, Felix A. Romanofsky, Robert R. Durham, Timothy E. Vanhille, Kenneth J. GP IEEE TI Antenna Characterization for the Wideband Instrument for Snow Measurements (WISM) SO 2015 IEEE INTERNATIONAL SYMPOSIUM ON ANTENNAS AND PROPAGATION & USNC/URSI NATIONAL RADIO SCIENCE MEETING SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE International Symposium on Antennas and Propagation / USNC/URSI National North American Radio Science Meeting CY JUL 19-24, 2015 CL Vancouver, CANADA SP Inst Elect & Elect Engineers, IEEE Antennas & Propagat Soc, USNC, URSI AB Experimental characterization of the antenna for the Wideband Instrument for Snow Measurement (WISM) under development for the NASA Earth Science Technology Office (ESTO) Instrument Incubator Program (IIP), is discussed. A current sheet antenna, consisting of a small, 6x6 element, dual-linear polarized array with integrated beamformer, feeds an offset parabolic reflector, enabling WISM operation over an 8 to 40 GHz frequency band. An overview of the test program implemented for both the feed and the reflector antenna is given along with select results for specific frequencies utilized by the radar and radiometric sensors of the WISM. C1 [Lambert, Kevin M.] Vantage Partners LLC, Cleveland, OH USA. [Miranda, Felix A.; Romanofsky, Robert R.] NASA Glenn Res Ctr, Cleveland, OH USA. [Durham, Timothy E.] Harris Corp, Melbourne, FL 32919 USA. [Vanhille, Kenneth J.] Nuvotronics LLC, Durham, NC USA. RP Lambert, KM (reprint author), Vantage Partners LLC, Cleveland, OH USA. EM felix.a.miranda@nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4799-7815-1 J9 IEEE ANTENNAS PROP PY 2015 BP 1997 EP 1998 PG 2 WC Telecommunications SC Telecommunications GA BE3YW UT WOS:000371401402035 ER PT S AU Durham, TE Vanhille, KJ Trent, CR Lambert, KM Miranda, FA AF Durham, Timothy E. Vanhille, Kenneth J. Trent, Christopher R. Lambert, Kevin M. Miranda, Felix A. GP IEEE TI Design of an 8-40 GHz Antenna for the Wideband Instrument for Snow Measurements (WISM) SO 2015 IEEE INTERNATIONAL SYMPOSIUM ON ANTENNAS AND PROPAGATION & USNC/URSI NATIONAL RADIO SCIENCE MEETING SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE International Symposium on Antennas and Propagation / USNC/URSI National North American Radio Science Meeting CY JUL 19-24, 2015 CL Vancouver, CANADA SP Inst Elect & Elect Engineers, IEEE Antennas & Propagat Soc, USNC, URSI AB Measurement of land surface snow remains a significant challenge in the remote sensing arena. Developing the tools needed to remotely measure Snow Water Equivalent (SWE) is an important priority. The Wideband Instrument for Snow Measurements (WISM) is being developed to address this need. WISM is an airborne instrument comprised of a dual-frequency (X-and Ku-band) Synthetic Aperture Radar (SAR) and dual-frequency (K-and Ka-band) radiometer. A unique feature of this instrument is that all measurement bands share a common antenna aperture consisting of an array-feed reflector that covers the entire bandwidth. This paper covers the design and fabrication of the wideband array feed, which is based on tightly coupled dipole arrays. Implementation using a relatively new multi-layer microfabrication process results in a small, 6x6-element, dual-linear polarized array with beamformer that operates from 8 to 40 GHz. C1 [Durham, Timothy E.; Trent, Christopher R.] Harris Corp, Melbourne, FL 32919 USA. [Vanhille, Kenneth J.] Nuvotronics LLC, Durham, NC USA. [Lambert, Kevin M.] Vantage Partners LLC, Cleveland, OH USA. [Miranda, Felix A.] NASA Glenn Res Ctr, Cleveland, OH USA. RP Durham, TE (reprint author), Harris Corp, Melbourne, FL 32919 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4799-7815-1 J9 IEEE ANTENNAS PROP PY 2015 BP 1999 EP 2000 PG 2 WC Telecommunications SC Telecommunications GA BE3YW UT WOS:000371401402036 ER PT S AU Hodges, RE Radway, MJ Toorian, A Hoppe, DJ Shah, B Kalman, AE AF Hodges, Richard E. Radway, Matthew J. Toorian, Armen Hoppe, Daniel J. Shah, Biren Kalman, Andrew E. GP IEEE TI ISARA - Integrated Solar Array and Reflectarray CubeSat Deployable Ka-band Antenna SO 2015 IEEE INTERNATIONAL SYMPOSIUM ON ANTENNAS AND PROPAGATION & USNC/URSI NATIONAL RADIO SCIENCE MEETING SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE International Symposium on Antennas and Propagation / USNC/URSI National North American Radio Science Meeting CY JUL 19-24, 2015 CL Vancouver, CANADA SP Inst Elect & Elect Engineers, IEEE Antennas & Propagat Soc, USNC, URSI AB The Integrated Solar Array and Reflectarray Antenna (ISARA) is a new deployable antenna designed to fit into a standard CubeSat bus. It does not occupy payload volume, provides spacecraft prime power and imposes only a modest impact on overall mass. Measured data indicates that the 3 panel configuration achieves 33.5 dB gain at 26 GHz. Measured radiation patterns are in good agreement with calculations. C1 [Hodges, Richard E.; Radway, Matthew J.; Toorian, Armen; Hoppe, Daniel J.; Shah, Biren] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Kalman, Andrew E.] Pumpkin Inc, San Francisco, CA 94112 USA. RP Hodges, RE (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Richard.E.Hodges@jpl.nasa.gov; aek@pumpkinine.com NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4799-7815-1 J9 IEEE ANTENNAS PROP PY 2015 BP 2141 EP 2142 PG 2 WC Telecommunications SC Telecommunications GA BE3YW UT WOS:000371401402101 ER PT S AU Chahat, N Sauder, J Thomson, M Hodges, R Rahmat-Samii, Y AF Chahat, Nacer Sauder, Jonathan Thomson, Mark Hodges, Richard Rahmat-Samii, Yahya GP IEEE TI CubeSat Deployable Ka-band Reflector Antenna for Deep Space Missions SO 2015 IEEE INTERNATIONAL SYMPOSIUM ON ANTENNAS AND PROPAGATION & USNC/URSI NATIONAL RADIO SCIENCE MEETING SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE International Symposium on Antennas and Propagation / USNC/URSI National North American Radio Science Meeting CY JUL 19-24, 2015 CL Vancouver, CANADA SP Inst Elect & Elect Engineers, IEEE Antennas & Propagat Soc, USNC, URSI AB While CubeSats have thus far been used exclusively in Low Earth Orbit (LEO), NASA is now investigating the possibility to deploy CubeSats beyond LEO to carry out scientific experiments in Deep Space. Such CubeSats require a high-gain antenna that fits in a constrained and limited volume. This paper introduces a 42.8 dBi gain deployable Ka-band antenna folding in a 1.5U stowage volume suitable for 3U and 6U class CubeSats. C1 [Chahat, Nacer; Sauder, Jonathan; Thomson, Mark; Hodges, Richard] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Rahmat-Samii, Yahya] Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90024 USA. RP Chahat, N (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM nacer.e.chahat@jpl.nasa.gov; rahmat@ee.ucla.edu NR 6 TC 2 Z9 2 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4799-7815-1 J9 IEEE ANTENNAS PROP PY 2015 BP 2185 EP 2186 PG 2 WC Telecommunications SC Telecommunications GA BE3YW UT WOS:000371401402122 ER PT S AU Simons, RN AF Simons, Rainee N. GP IEEE TI Link Analysis of High Throughput Spacecraft Communication Systems for Future Science Missions SO 2015 IEEE INTERNATIONAL SYMPOSIUM ON ANTENNAS AND PROPAGATION & USNC/URSI NATIONAL RADIO SCIENCE MEETING SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE International Symposium on Antennas and Propagation / USNC/URSI National North American Radio Science Meeting CY JUL 19-24, 2015 CL Vancouver, CANADA SP Inst Elect & Elect Engineers, IEEE Antennas & Propagat Soc, USNC, URSI AB NASA's plan to launch several spacecrafts into low Earth Orbit (LEO) to support science missions in the next ten years and beyond requires down link throughput on the order of several terabits per day. The ability to handle such a large volume of data far exceeds the capabilities of current systems. This paper proposes two solutions, first, a high data rate link between the LEO spacecraft and ground via relay satellites in geostationary orbit (GEO). Second, a high data rate direct to ground link from LEO. Next, the paper presents results from computer simulations carried out for both types of links taking into consideration spacecraft transmitter frequency, EIRP, and waveform; elevation angle dependent path loss through Earth's atmosphere, and ground station receiver G/T. C1 [Simons, Rainee N.] NASA Glenn Res Ctr, MS 54-1,21000 Brookpk Rd, Cleveland, OH 44135 USA. RP Simons, RN (reprint author), NASA Glenn Res Ctr, MS 54-1,21000 Brookpk Rd, Cleveland, OH 44135 USA. EM Rainee.N.Simons@nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4799-7815-1 J9 IEEE ANTENNAS PROP PY 2015 BP 2187 EP 2188 PG 2 WC Telecommunications SC Telecommunications GA BE3YW UT WOS:000371401402123 ER PT S AU Jamnejad, V AF Jamnejad, Vahraz GP IEEE TI Magnetometer Boom Blockage Effects on Performance of Reflector Antenna of Europa Habitability Mission SO 2015 IEEE INTERNATIONAL SYMPOSIUM ON ANTENNAS AND PROPAGATION & USNC/URSI NATIONAL RADIO SCIENCE MEETING SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE International Symposium on Antennas and Propagation / USNC/URSI National North American Radio Science Meeting CY JUL 19-24, 2015 CL Vancouver, CANADA SP Inst Elect & Elect Engineers, IEEE Antennas & Propagat Soc, USNC, URSI AB the objective of this study is to provide a parametric analysis of the effects of the Magnetometer Boom of the Europa spacecraft on the performance of the 0.8m-diameter High Gain Antenna (HGA) at 8- and 32-GHz frequencies with circular polarization, used for gravity studies. Specifically of interest, are the changes in the phase of the main beam region of the antenna patterns. For the purpose of this study, the antenna and Boom parameters (dimensions and distances) are approximated. EM Analysis is performed using the GRASP software. Only first order strut effects are included. Input data files for GRASP for parametric study of the antenna and Boom in various representative positions are obtained using a MATLAB program. A number of antenna gain amplitude and phase plots have been obtained and compared with no-struts interference case. Worst case scenarios are identified and presented. C1 [Jamnejad, Vahraz] CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Jamnejad, V (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA USA. EM Vahraz.jamnejad@jpl.nasa.gov NR 0 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4799-7815-1 J9 IEEE ANTENNAS PROP PY 2015 BP 2191 EP 2192 PG 2 WC Telecommunications SC Telecommunications GA BE3YW UT WOS:000371401402125 ER PT S AU Host, NK Chen, CC Volakis, JL Miranda, FA AF Host, Nicholas K. Chen, Chi-Chih Volakis, John L. Miranda, Felix A. GP IEEE TI Ku-Band Traveling Wave Slot Array Using Simple Scanning Control SO 2015 IEEE INTERNATIONAL SYMPOSIUM ON ANTENNAS AND PROPAGATION & USNC/URSI NATIONAL RADIO SCIENCE MEETING SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE International Symposium on Antennas and Propagation / USNC/URSI National North American Radio Science Meeting CY JUL 19-24, 2015 CL Vancouver, CANADA SP Inst Elect & Elect Engineers, IEEE Antennas & Propagat Soc, USNC, URSI AB This paper introduces a feeding concept aimed at simplifying the backend (phase shifters) of traditional phased arrays. As an alternative to traditional phased arrays, we employ a traveling wave array (TWA) using a single feedline whose propagation constant is controlled via a single, small mechanical movement without a need for phase shifters to enable scanning. Specifically, a dielectric plunger is positioned within a parallel plate waveguide (PPW) transmission line (TL) that feeds the TWA. By adjusting the position of the dielectric plunger within the PPW feeding the TWA, beam steering is achieved. A 20 element array is designed at 13GHz shown to give stable realized gain across the angular range of -25 degrees <= theta <= 25 degrees. A proof of concept array is fabricated and measured to demonstrate and validate the concept's operation. C1 [Host, Nicholas K.] Johns Hopkins Univ APL, Laurel, MD USA. [Chen, Chi-Chih; Volakis, John L.] Ohio State Univ ESL, Columbus, OH USA. [Miranda, Felix A.] NASA John Glenn Res Ctr, Cleveland, OH USA. RP Host, NK (reprint author), Johns Hopkins Univ APL, Laurel, MD USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4799-7815-1 J9 IEEE ANTENNAS PROP PY 2015 BP 2477 EP 2478 PG 2 WC Telecommunications SC Telecommunications GA BE3YW UT WOS:000371401402255 ER PT S AU May, RD Beierle, C Hong, MG Loparo, KA AF May, Ryan D. Beierle, Connor Hong, Mingguo Loparo, Kenneth A. GP IEEE TI Highly Distributed State Estimation for a DC Spacecraft Power System SO 2015 IEEE POWER & ENERGY SOCIETY GENERAL MEETING SE IEEE Power and Energy Society General Meeting PESGM LA English DT Proceedings Paper CT General Meeting of the IEEE-Power-and-Energy-Society CY JUL 26-30, 2015 CL Denver, CO SP IEEE Power & Energy Soc DE state estimation; software agents; microgrids; power system control; distributed optimization AB To enable the development of an autonomous power control system comprised of highly-distributed software agents, a distributed implementation of a power system state estimator must be developed. The estimator uses agents located at each bus to estimate the local state and boundary conditions that are then communicated to neighboring agents. Using an iterative approach, the agents can compute a near-optimal state estimate using only local information and the communicated boundary conditions. The algorithm is implemented and tested against a subset of the International Space Station's power system. The results are compared and validated with those of a centralized state estimator. C1 [May, Ryan D.] Vantage Partners LLC, Cleveland, OH USA. [Beierle, Connor] NASA Glenn Res Ctr, Cleveland, OH USA. [Hong, Mingguo; Loparo, Kenneth A.] Case Western Reserve Univ, Cleveland, OH 44106 USA. RP May, RD (reprint author), Vantage Partners LLC, Cleveland, OH USA. EM ryan.d.may@nasa.gov; cbeierle@stanford.edu; mingguo.hong@case.edu; kal4@case.edu NR 10 TC 0 Z9 0 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1944-9925 BN 978-1-4673-8040-9 J9 IEEE POW ENER SOC GE PY 2015 PG 5 WC Energy & Fuels; Engineering, Electrical & Electronic SC Energy & Fuels; Engineering GA BE3YU UT WOS:000371397500104 ER PT J AU Moore, JP AF Moore, Jason P. GP IEEE TI Shape Sensing Using Multi-core Fiber SO 2015 OPTICAL FIBER COMMUNICATIONS CONFERENCE AND EXHIBITION (OFC) LA English DT Proceedings Paper CT Optical Fiber Communications Conference and Exhibition (OFC) CY MAR 22-26, 2015 CL Los Angeles, CA AB A method of converting multi-core fiber strain and twist measurements into three dimensional shape measurements using Frenet-Serret equations adapted to the treatment of a multi-core optical fiber as a Kirchhoff elastic rod is presented. C1 [Moore, Jason P.] NASA, Langley Res Ctr, Hampton, VA 23692 USA. RP Moore, JP (reprint author), NASA, Langley Res Ctr, Hampton, VA 23692 USA. EM jason.p.moore@nasa.gov NR 6 TC 0 Z9 0 U1 2 U2 4 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-55752-937-4 PY 2015 PG 3 WC Engineering, Electrical & Electronic; Optics; Telecommunications SC Engineering; Optics; Telecommunications GA BE3MS UT WOS:000370976400125 ER PT S AU Bauer, FH Dennehy, N AF Bauer, Frank H. Dennehy, Neil BE Gravseth, IJ TI LOOKING BACK AND LOOKING FORWARD: REPRISING THE PROMISE AND PREDICTING THE FUTURE OF FORMATION FLYING AND SPACEBORNE GPS NAVIGATION SYSTEMS SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB A retrospective consideration of two 15-year old Guidance, Navigation and Control (GN&C) technology 'vision' predictions will be the focus of this paper. A look back analysis and critique of these late 1990s technology roadmaps outlining the future vision, for two then nascent, but rapidly emerging, GN&C technologies will be performed. Specifically, these two GN&C technologies were: 1) multi-spacecraft formation flying and 2) the spaceborne use and exploitation of global positioning system (GPS) signals to enable formation flying. This paper reprises the promise of formation flying and spaceborne GPS as depicted in the cited 19991 and 19982 papers. It will discuss what happened to cause that promise to be unfulfilled and the reasons why the envisioned formation flying dream has yet to become a reality. The recent technology trends over the past few years will then be identified and a renewed government interest in spacecraft formation flying/cluster flight will be highlighted. The authors will conclude with a reality-tempered perspective, 15 years after the initial technology roadmaps were published, predicting a promising future of spacecraft formation flying technology development over the next decade. C1 [Bauer, Frank H.] FBauer Aerosp Consulting Serv, Silver Spring, MD 20905 USA. [Dennehy, Neil] NASA Langley Res Ctr, NASA Engn Safety Ctr, Guidance Nav & Control, Hampton, VA 23681 USA. RP Bauer, FH (reprint author), FBauer Aerosp Consulting Serv, Silver Spring, MD 20905 USA. EM fhbauer@verizon.net; cornelius.j.dennehy@nasa.gov NR 20 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 109 EP 132 PG 24 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600009 ER PT S AU Schier, JS AF Schier, James S. BE Gravseth, IJ TI NASA'S SPACE NAVIGATION ROADMAPS SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB In 2012, the National Research Council's document "NASA Space Technology Roadmaps and Priorities: Restoring NASA's Technological Edge and Paving the Way for a New Era in Space" identified a number of navigation technology developments. High priority navigation technologies required to support anticipated future missions included: 1. Onboard Autonomous Navigation and Maneuvering (OANM); and 2. Timekeeping and Time Distribution. Top technical challenges included "Autonomous and Accurate Navigation" for both absolute and relative navigation enabling autonomous rendezvous and docking as well as precision entry, descent, and landing. In 2014, NASA updated this analysis by defining specific Design Reference Missions (DRM) through 2040 for science, exploration, and aeronautics and evaluating the capabilities needed to enable or enhance each of these DRMs. The Space Communications and Navigation Program is refining its technology investments and long range architecture plans based on this update. This paper will present the results of investment decisions being made now and preliminary results of architecture studies currently in progress that will define future space Position, Navigation, and Timing (PNT) capabilities. This will include advances in optical tracking, hybrid RF/optical systems, atomic clocks, and Global Positioning System. C1 [Schier, James S.] NASA, Human Explorat & Operat Mission Directorate, Space Commun & Nav SCaN Off, 300 E St SW, Washington, DC 20546 USA. RP Schier, JS (reprint author), NASA, Human Explorat & Operat Mission Directorate, Space Commun & Nav SCaN Off, 300 E St SW, Washington, DC 20546 USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 157 EP 168 PG 12 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600012 ER PT S AU Riedel, JE Aung, M AF Riedel, Joseph E. Aung, MiMi BE Gravseth, IJ TI ONBOARD GUIDANCE, NAVIGATION, AND CONTROL TECHNOLOGY ASSESSMENT FOR FUTURE PLANETARY SCIENCE MISSIONS SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB This paper presents an evaluation of the onboard GN&C capabilities and technologies needed for future missions pursuing NASA's planetary science goals. In particular, this assessment covers attitude estimation and control in general, as well as the estimation and control of vehicle flight paths when flight path and attitude dynamics are strongly coupled or performed primarily onboard (as is the case during certain critical phases, such as entry, descent, and landing, in some planetary missions). This work first surveys the technologies, appraises their applicability to future NASA planetary missions, and then quantitatively assesses priorities for NASA based on likely need, relevance and optionally cost. C1 [Riedel, Joseph E.; Aung, MiMi] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Riedel, JE (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 51 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 185 EP 218 PG 34 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600014 ER PT S AU Johnson, L AF Johnson, Les BE Gravseth, IJ TI ADVANCES IN PROPELLANTLESS IN-SPACE PROPULSION TECHNOLOGIES SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO ID ELECTRIC SAIL AB In order to implement the next generation of robotic space missions affordably and with reasonable flight times, improvements in in-space propulsion must be achieved. For robotic exploration and science missions, increased efficiencies of future propulsion systems are critical to reduce overall life-cycle costs. Some future missions being proposed, including outer solar system rendezvous and sample return missions, will require 2 to 3 times more total change in velocity over their mission lives than can be achieved with chemical rockets or electric propulsion systems. Some of the most promising technologies for enabling these ambitious missions use the environment of space itself for energy and propulsion and are generically called, "propellantless" because they do not require onboard fuel to achieve thrust. An overview of the state-of-the-art propellantless propulsion technologies such as solar sails, electric sails, and electrodynamic tethers will be provided. C1 [Johnson, Les] NASA, George C Marshall Space Flight Ctr, Adv Concepts Off, 4601 Martin Rd, Huntsville, AL 35812 USA. RP Johnson, L (reprint author), NASA, George C Marshall Space Flight Ctr, Adv Concepts Off, 4601 Martin Rd, Huntsville, AL 35812 USA. NR 19 TC 0 Z9 0 U1 2 U2 2 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 305 EP 311 PG 7 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600022 ER PT S AU Houts, MG Mitchell, DP Kim, T AF Houts, Michael G. Mitchell, Doyce P. Kim, Tony BE Gravseth, IJ TI GUIDANCE, NAVIGATION, AND CONTROL CONSIDERATIONS FOR NUCLEAR THERMAL PROPULSION SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB The fundamental capability of Nuclear Thermal Propulsion (NTP) is game changing for space exploration. A first generation NTP system could provide high thrust at a specific impulse above 900 s, roughly double that of state of the art chemical engines. Characteristics of fission and NTP indicate that useful first generation systems will provide a foundation for future systems with extremely high performance. The role of a first generation NTP in the development of advanced nuclear propulsion systems could be analogous to the role of the DC-3 in the development of advanced aviation. Progress made under the NTP project could also help enable high performance fission power systems and Nuclear Electric Propulsion (NEP). Guidance, navigation, and control of NTP may have some unique but manageable characteristics. C1 [Houts, Michael G.] NASA, George C Marshall Space Flight Ctr, Technol Dev & Transfer Off, ZP30, Huntsville, AL 35812 USA. [Mitchell, Doyce P.] Technol Dev & Transfer Off, Nucl Thermal Prop Project, Huntsville, AL 35812 USA. [Kim, Tony] Technol Dev & Transfer Off, Nucl Thermal Prop, Huntsville, AL 35812 USA. RP Houts, MG (reprint author), NASA, George C Marshall Space Flight Ctr, Technol Dev & Transfer Off, ZP30, Huntsville, AL 35812 USA. NR 1 TC 0 Z9 0 U1 1 U2 1 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 323 EP 331 PG 9 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600024 ER PT S AU Sorgenfrei, M Nehrenz, M Thomas, RE AF Sorgenfrei, Matt Nehrenz, Matt Thomas, Robert E. BE Gravseth, IJ TI ON THE IMPLEMENTATION OF MICROELECTROSPRAY PROPULSION SYSTEMS IN CUBESAT-CLASS SPACECRAFT SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB The integration of propulsion systems into CubeSat-class spacecraft is a key enabling technology for future science missions that require high levels of pointing stability or which operate beyond low Earth orbit. One promising technology for these very small spacecraft is microelectrospray propulsion (MEP) systems, due in part to their compact size and high specific impulse. While MEP systems display a number of ideal traits for spacecraft momentum management and low thrust translational maneuvers, much of the hardware is at a relatively low technology readiness level (TRL). NASA Ames Research Center and Glenn Research Center (GRC) have recently initiated a campaign to increase the TRL of candidate MEP systems for future flight projects. This test campaign is motivated by the performance requirements of a six-cube CubeSat operating in deep space, for which the MEP system will support detumble and momentum management. This paper will describe the candidate deep space mission, the software architecture required to drive the MEP system in a flight-like manner, and the test campaign that will be undertaken at GRC, including some preliminary test results. C1 [Sorgenfrei, Matt] NASA, Ames Res Ctr, Intelligent Syst Div, Stinger Ghaffarian Technol, Moffett Field, CA 94035 USA. [Nehrenz, Matt] NASA, Ames Res Ctr, Mission Design Div, Emergent Space Syst, Moffett Field, CA 94035 USA. [Thomas, Robert E.] NASA, Glenn Res Ctr, Space Prop Syst Branch, Cleveland, OH 44135 USA. RP Sorgenfrei, M (reprint author), NASA, Ames Res Ctr, Intelligent Syst Div, Stinger Ghaffarian Technol, Moffett Field, CA 94035 USA. NR 9 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 333 EP 344 PG 12 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600025 ER PT S AU Freesland, D Carter, D Chapel, J Clapp, B Howat, J Krimchansky, A AF Freesland, Doug Carter, Delano Chapel, Jim Clapp, Brian Howat, John Krimchansky, Alexander BE Gravseth, IJ TI GOES-R DUAL ISOLATION SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB The Geostationary Operational Environmental Satellite-R Series (GOES-R) is the first of the next generation geostationary weather satellites, scheduled for delivery in late 2015. GOES-R represents a quantum increase in Earth and solar weather observation capabilities, with 4 times the resolution, 5 times the observation rate, and 3 times the number of spectral bands for Earth observations. With the improved resolution, comes the instrument suite's increased sensitive to disturbances over a broad spectrum 0-512 Hz. Sources of disturbance include reaction wheels, thruster firings for station keeping and momentum management, gimbal motion, and internal instrument disturbances. To minimize the impact of these disturbances, the baseline design includes an Earth Pointed Platform (EPP), a stiff optical bench to which the two nadir pointed instruments are collocated together with the Guidance Navigation & Control (GN&C) star trackers and Inertial Measurement Units (IMUs). The EPP is passively isolated from the spacecraft bus with Honeywell D-Strut isolators providing attenuation for frequencies above similar to 5 Hz in all six degrees-of-freedom. A change in Reaction Wheel Assembly (RWA) vendors occurred very late in the program. To reduce the risk of RWA disturbances impacting performance, a secondary passive isolation system manufactured by Moog CSA Engineering was incorporated under each of the six 160 Nms RWAs, tuned to provide attenuation at frequencies above similar to 50 Hz. Integrated wheel and isolator testing was performed on a Kistler table at NASA Goddard Space Flight Center. High fidelity simulations were conducted to evaluate jitter performance for four topologies: 1) hard mounted no isolation, 2) EPP isolation only, 2) RWA isolation only, and 4) dual isolation. Simulation results demonstrate excellent performance relative to the pointing stability requirements, with dual isolated Line of Sight (LOS) jitter < 1 mu rad. C1 [Freesland, Doug] ACS Engn Corp, Columbia, MD 21046 USA. [Carter, Delano] Thearality Inc, Glendale, AZ 85318 USA. [Chapel, Jim; Clapp, Brian] Lockheed Martin Space Syst, Denver, CO 80201 USA. [Howat, John] Moog CSA Engn, Mountain View, CA 94043 USA. [Krimchansky, Alexander] NASA, Goddard Space Flight Ctr, NASA GOES R Flight Project, Greenbelt, MD 20771 USA. RP Freesland, D (reprint author), ACS Engn Corp, Columbia, MD 21046 USA. EM douglas.c.freesland@nasa.gov; delano.r.carter@nasa.gov; jim.d.chapel@lmco.com; brian.clapp@lmco.com; jhowat@moog.com; alexander.krimchansky@nasa.gov NR 8 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 359 EP 371 PG 13 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600027 ER PT S AU Bhatt, S Svecz, A Alaniz, A Jang, JW Nguyen, L Spanos, P AF Bhatt, Sagar Svecz, Andrew Alaniz, Abran Jang, Jiann-Woei Nguyen, Louis Spanos, Pol BE Gravseth, IJ TI THERMALLY-CONSTRAINED FUEL-OPTIMAL ISS MANEUVERS SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB Optimal Propellant Maneuvers (OPMs) are now being used to rotate the International Space Station (ISS) and have saved hundreds of kilograms of propellant over the last two years. The savings are achieved by commanding the ISS to follow a pre-planned attitude trajectory optimized to take advantage of environmental torques. The trajectory is obtained by solving an optimal control problem. Prior to use on orbit, OPM trajectories are screened to ensure a static sun vector (SSV) does not occur during the maneuver. The SSV is an indicator that the ISS hardware temperatures may exceed thermal limits, causing damage to the components. In this paper, thermally-constrained fuel-optimal trajectories are presented that avoid an SSV and can be used throughout the year while still reducing propellant consumption significantly. C1 [Bhatt, Sagar; Alaniz, Abran; Jang, Jiann-Woei] Charles Stark Draper Lab Inc, 17629 El Camino Real,Suite 470, Houston, TX 77058 USA. [Svecz, Andrew] Rice Univ, Mech Engn, Houston, TX 77005 USA. [Nguyen, Louis] NASA Johnson Space Ctr, Houston, TX 77058 USA. [Spanos, Pol] Rice Univ, Engn, Houston, TX 77005 USA. RP Bhatt, S (reprint author), Charles Stark Draper Lab Inc, 17629 El Camino Real,Suite 470, Houston, TX 77058 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 455 EP 465 PG 11 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600033 ER PT S AU Davis, N DeWeese, K Vess, M O'Donnell, JR Welter, G AF Davis, Nikesha DeWeese, Keith Vess, Melissa O'Donnell, James R., Jr. Welter, Gary BE Gravseth, IJ TI GLOBAL PRECIPITATION MEASUREMENT MISSION LAUNCH AND COMMISSIONING SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB During launch and early operation of the Global Precipitation Measurement (GPM) Mission, the Guidance, Navigation, and Control (GN&C) analysis team encountered four main on-orbit anomalies. These include: (1) unexpected shock from Solar Array deployment, (2) momentum buildup from the Magnetic Torquer Bars (MTBs) phasing errors, (3) transition into Safehold due to albedo induced Course Sun Sensor (CSS) anomaly, and (4) a flight software error that could cause a Safehold transition due to a Star Tracker occultation. This paper will discuss ways GN&C engineers identified the anomalies and tracked down the root causes. Flight data and GN&C on-board models will be shown to illustrate how each of these anomalies were investigated and mitigated before causing any harm to the spacecraft. On May 29, 2014, GPM was handed over to the Mission Flight Operations Team after a successful commissioning period. Currently, GPM is operating nominally on orbit, collecting meaningful scientific data that will significantly improve our understanding of the Earth's climate and water cycle. C1 [Davis, Nikesha; DeWeese, Keith; Vess, Melissa; O'Donnell, James R., Jr.] NASA, Goddard Space Flight Ctr, Attitude Control Syst Engn Branch, Greenbelt, MD 20771 USA. [Welter, Gary] NASA, Goddard Space Flight Ctr, Flight Software Syst Branch, Greenbelt, MD 20771 USA. RP Davis, N (reprint author), NASA, Goddard Space Flight Ctr, Attitude Control Syst Engn Branch, Greenbelt, MD 20771 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 467 EP 478 PG 12 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600034 ER PT S AU Peters, SF Collins, SM Vanelli, CA Robinson, ML Montgomery, JF Johnson, SC AF Peters, Stephen F. Collins, Steven M. Vanelli, C. Anthony Robinson, Matthew L. Montgomery, James F. Johnson, Shawn C. BE Gravseth, IJ TI THREE MID-MISSION IMPROVEMENTS TO MARS SCIENCE LABORATORY SURFACE ATTITUDE ESTIMATION ACCURACY SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB Of all the contributions to attitude and pointing error in the Curiosity rover on Mars, only those from clock drift and gyroscope propagation increase over time. A single update on sol 647 to the onboard model of planetary motion both corrected for accumulated clock drift error and compensated for future clock drift. A flight software update on sol 481 added an accelerometer-only mode for updating attitude, eliminating accumulation of gyroscope propagation error when updating attitude during arm activities. The adoption of an operational pattern of following each drive with an accelerometer-based correction to attitude eliminated the roll and pitch components of gyroscope propagation error accumulated during drives. With these three improvements, only the yaw component of gyroscope propagation error grows from sol to sol. C1 [Peters, Stephen F.; Robinson, Matthew L.] CALTECH, NASA Jet Prop Lab, Mobil & Robot Syst, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Collins, Steven M.; Vanelli, C. Anthony; Montgomery, James F.; Johnson, Shawn C.] CALTECH, NASA Jet Prop Lab, Guidance & Control, Pasadena, CA 91109 USA. RP Peters, SF (reprint author), CALTECH, NASA Jet Prop Lab, Mobil & Robot Syst, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 491 EP 498 PG 8 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600036 ER PT S AU Wright, CA Bhatt, S Woffinden, D Strube, M D'Souza, C AF Wright, Cinnamon A. Bhatt, Sagar Woffinden, David Strube, Matthew D'Souza, Chris BE Gravseth, IJ TI LINEAR COVARIANCE ANALYSIS FOR PROXIMITY OPERATIONS AROUND ASTEROID 2008 EV5 SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO ID SPACECRAFT; TRACTOR AB The NASA initiative to collect an asteroid, the Asteroid Robotic Redirect Mission (ARRM), is currently investigating the option of retrieving a boulder from an asteroid, demonstrating planetary defense with an enhanced gravity tractor technique, and returning it to a lunar orbit. Techniques for accomplishing this are being investigated by the Satellite Servicing Capabilities Office (SSCO) at NASA GSFC in collaboration with JPL, NASA JSC, LaRC, and Draper Laboratory, Inc. Two critical phases of the mission are the descent to the boulder and the Enhanced Gravity Tractor demonstration. A linear covariance analysis is done for these phases to assess the feasibility of these concepts with the proposed design of the sensor and actuator suite of the Asteroid Redirect Vehicle (ARV). The sensor suite for this analysis includes a wide field of view camera, LiDAR, and an IMU. The proposed asteroid of interest is currently the C-type asteroid 2008 EV5, a carbonaceous chondrite that is of high interest to the scientific community. This paper presents an overview of the linear covariance analysis techniques and simulation tool, provides sensor and actuator models, and addresses the feasibility of descending to the surface of the asteroid within allocated requirements as well as the possibility of maintaining a halo orbit to demonstrate the Enhanced Gravity Tractor technique. C1 [Wright, Cinnamon A.] NASA, Goddard Space Flight Ctr, Nav & Miss Design Branch, Code 595, Greenbelt, MD 20771 USA. [Bhatt, Sagar; Woffinden, David] Charles Stark Draper Lab Inc, Houston, TX 77058 USA. [Strube, Matthew] NASA, Goddard Space Flight Ctr, Components & Hardware Syst Branch, Greenbelt, MD 20771 USA. [D'Souza, Chris] NASA, Johnson Space Ctr, Houston, TX 77058 USA. RP Wright, CA (reprint author), NASA, Goddard Space Flight Ctr, Nav & Miss Design Branch, Code 595, Greenbelt, MD 20771 USA. NR 16 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 537 EP 548 PG 12 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600040 ER PT S AU Deininger, WD Mitchell, S Enger, S Unruh, B Sjauwenwa, WK McGuire, ML AF Deininger, William D. Mitchell, Scott Enger, Scott Unruh, Bryce Sjauwenwa, Waldy K. McGuire, Melissa L. BE Gravseth, IJ TI SEP-ENABLED ESPA-CLASS SATELLITE FOR NEAR-EARTH APPLICATIONS SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB Ball Aerospace & Technologies Corp. participated in a Space Act Agreement with NASA GRC to determine the feasibility of accommodating Solar Electric Propulsion (SEP) on an ESPA-class spacecraft. The BCP-100 bus was used as the baseline to leverage its flight heritage (STPSat-2 and STPSat-3, with GPIM under development). The study approach focused on minimizing changes to the existing bus design by modifying only what was necessary to accommodate the SEP system (structures, thermal and harnessing). This approach maintains high heritage and minimizes the amount of non-recurring engineering required for the bus. High heritage components are also selected for the 200 W SEP system including an off-the-shelf xenon tank, Hall effect thruster and cathode, and xenon feed control, allowing future development funding to be focused on a PPU compatible with the existing BCP-100 low voltage (28 V) power bus. The results of the study show a BCP-100 can be modified to accommodate meaningful SEP capability while meeting the mass and volume constraints for an ESPA launch. The Hall thruster SEP system produces similar to 1500 m/s Delta V with 20 kg of xenon propellant. This paper summarizes the BCP-100 design and capabilities, status of the heritage flight and in-development programs and summarizes how the BCP-100 is adapted to include SEP. Mission options starting in both LEO and GTO were explored and are discussed. C1 [Deininger, William D.] Ball Aerosp & Technol Corp, Mission Syst Engn, 1600 Commerce St, Boulder, CO 80301 USA. [Mitchell, Scott] Ball Aerosp & Technol Corp, Syst Engn, Boulder, CO 80301 USA. [Enger, Scott] Ball Aerosp & Technol Corp, Power Syst Engn, Boulder, CO 80301 USA. [Unruh, Bryce] Ball Aerosp & Technol Corp, Civil Space & Technol, Business Dev, Boulder, CO 80301 USA. [Sjauwenwa, Waldy K.; McGuire, Melissa L.] NASA, Mission Architecture & Anal Branch, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Deininger, WD (reprint author), Ball Aerosp & Technol Corp, Mission Syst Engn, 1600 Commerce St, Boulder, CO 80301 USA. EM wdeining@ball.com; senger@ball.com; bunruh@ball.com; waldy.k.sjauw@nasa.gov; melis-sa.l.mcguire@nasa.gov NR 40 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 549 EP 560 PG 12 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600041 ER PT S AU Orr, JS Powers, JF Yang, HQ AF Orr, Jeb S. Powers, Joseph F. Yang, Hong Q. BE Gravseth, IJ TI LATTICE BOLTZMANN METHOD FOR SPACECRAFT PROPELLANT SLOSH SIMULATION SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO ID EQUATION-OF-STATE; MULTIPHASE FLOWS; MODEL AB A scalable computational approach to the simulation of propellant tank sloshing dynamics in microgravity is presented. In this work, we use the lattice Boltzmann equation (LBE) to approximate the behavior of two-phase, single-component isothermal flows at very low Bond numbers. Through the use of a non-ideal gas equation of state and a modified multiple relaxation time (MRT) collision operator, the proposed method can simulate thermodynamically consistent phase transitions at temperatures and density ratios consistent with typical spacecraft cryogenic propellants, for example, liquid oxygen. Determination of the tank forces and moments relies upon the global momentum conservation of the fluid domain, and a parametric wall wetting model allows tuning of the free surface contact angle. Development of the interface is implicit and no interface tracking approach is required. Numerical examples illustrate the method's application to predicting bulk fluid motion including lateral propellant slosh in low-g conditions. C1 [Powers, Joseph F.] NASA, Control Syst Design & Anal Branch, Marshall Space Flight Ctr, Huntsville, AL 35812 USA. [Yang, Hong Q.] CFD Res Corp, Jacobs ESSSA Grp, Huntsville, AL 35806 USA. EM jeb.orr@nasa.gov; Joseph.F.Powers@nasa.gov; hong.q.yang@nasa.gov NR 20 TC 0 Z9 0 U1 2 U2 3 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 563 EP 574 PG 12 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600042 ER PT S AU Scarritt, SK Fill, T Robinson, S AF Scarritt, Sara K. Fill, Thomas Robinson, Shane BE Gravseth, IJ TI ADVANCES IN ORION'S ON-ORBIT GUIDANCE AND TARGETING SYSTEM ARCHITECTURE SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB NASA's manned spaceflight programs have a rich history of advancing onboard guidance and targeting technology. In order to support future missions, the guidance and targeting architecture for the Orion Multi-Purpose Crew Vehicle must be able to operate in complete autonomy, without any support from the ground. Orion's guidance and targeting system must be sufficiently flexible to easily adapt to a wide array of undecided future missions, yet also not cause an undue computational burden on the flight computer. This presents a unique design challenge from the perspective of both algorithm development and system architecture construction. The present work shows how Orion's guidance and targeting system addresses these challenges. On the algorithm side, the system advances the state-of-the-art by: (1) steering burns with a simple closed-loop guidance strategy based on Shuttle heritage, and (2) planning maneuvers with a cutting-edge two-level targeting routine. These algorithms are then placed into an architecture designed to leverage the advantages of each and ensure that they function in concert with one another. The resulting system is characterized by modularity and simplicity. As such, it is adaptable to the on-orbit phases of any future mission that Orion may attempt. C1 [Scarritt, Sara K.; Robinson, Shane] NASA, Aerosci & Flight Mech Div, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. [Fill, Thomas] Charles Stark Draper Lab, Strateg & Space Guidance & Control Grp, Cambridge, MA 02139 USA. RP Scarritt, SK (reprint author), NASA, Aerosci & Flight Mech Div, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. NR 25 TC 1 Z9 1 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 619 EP 631 PG 13 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600046 ER PT S AU Miller, CJ Orr, JS Hanson, CE Gilligan, ET AF Miller, Christopher J. Orr, Jeb S. Hanson, Curtis E. Gilligan, Eric T. BE Gravseth, IJ TI AIRBORNE SIMULATION OF LAUNCH VEHICLE DYNAMICS SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB In this paper we present a technique for approximating the short-period dynamics of an exploration-class launch vehicle during flight test with a high-performance surrogate aircraft in relatively benign endoatmospheric flight conditions. The surrogate vehicle relies-upon a nonlinear dynamic inversion scheme with proportional-integral feedback to drive a subset of the aircraft states into coincidence with the states of a time-varying reference model that simulates the unstable rigid body dynamics, servodynamics, and parasitic elastic and sloshing dynamics of the launch vehicle. The surrogate aircraft flies a constant pitch rate trajectory to approximate the boost phase gravity turn ascent, and the aircraft's closed-loop bandwidth is sufficient to simulate the launch vehicle's fundamental lateral bending and sloshing modes by exciting the rigid body dynamics of the aircraft. A novel control allocation scheme is employed to utilize the aircraft's relatively fast control effectors in inducing various failure modes for the purposes of evaluating control system performance. Sufficient dynamic similarity is achieved such that the control system under evaluation is configured for the full-scale vehicle with no changes to its parameters, and pilot-control system interaction studies can be performed to characterize the effects of guidance takeover during boost. High-fidelity simulation and flight-test results are presented that demonstrate the efficacy of the design in simulating the Space Launch System (SLS) launch vehicle dynamics using the National Aeronautics and Space Administration (NASA) Armstrong Flight Research Center Fullscale Advanced Systems Testbed (FAST), a modified F/A-18 airplane (McDonnell Douglas, now The Boeing Company, Chicago, Illinois), over a range of scenarios designed to stress the SLS's Adaptive Augmenting Control (AAC) algorithm. C1 [Miller, Christopher J.; Hanson, Curtis E.] NASA, Flight Controls & Dynam, Armstrong Flight Res Ctr, Edwards AFB, CA 93523 USA. [Gilligan, Eric T.] NASA, Control Syst Design & Anal Branch, Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Miller, CJ (reprint author), NASA, Flight Controls & Dynam, Armstrong Flight Res Ctr, Edwards AFB, CA 93523 USA. EM jeb.orr@nasa.gov NR 10 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 633 EP 644 PG 12 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600047 ER PT S AU Strube, M Henry, R Skelton, E Van Eepoel, J Gill, N McKenna, R AF Strube, Matthew Henry, Ross Skelton, Eugene Van Eepoel, John Gill, Nat McKenna, Reed BE Gravseth, IJ TI RAVEN: AN ON-ORBIT RELATIVE NAVIGATION DEMONSTRATION USING INTERNATIONAL SPACE STATION VISITING VEHICLES SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB Since the last Hubble Servicing Mission five years ago, the Satellite Servicing Capabilities Office (SSCIO) at the NASA Goddard Space Flight Center (GsFc) has been focusing on maturing the technologies necessary to robotically service orbiting legacy assets spacecraft not necessarily designed for in-flight service. Raven, sscO's next orbital experiment to the International Space Station (Iss), is a real-time autonomous relative navigation system that will mature the estimation algorithms required for rendezvous and proximity operations for a satellite-servicing mission. Raven will fly as a hosted payload as part of the Space Test Program's STP-H5 mission, which will be mounted on an external ExPRESS Logistics Carrier (ELC) and will image the many visiting vehicles arriving and departing from the ISS as targets for observation. Raven will host multiple sensors: a visible camera with a variable field of view lens, a long-wave infrared camera, and a short-wave flash lidar. This sensor suite can be pointed via a two-axis gimbal to provide a wide field of regard to track the visiting vehicles as they make their approach. Various real-time vision processing algorithms will produce range, bearing, and six degree of freedom pose measurements that will be processed in a relative navigation filter to produce an optimal relative state estimate. In this overview paper, we will cover top-level requirements, experimental concept of operations, system design, and the status of Raven integration and test activities. C1 [Strube, Matthew; Henry, Ross; Van Eepoel, John; Gill, Nat] NASA, GSFC, Code 596, Greenbelt, MD 20771 USA. [Skelton, Eugene] Lockheed Martin Space Syst Co, Greenbelt, MD 20771 USA. [McKenna, Reed] Solo Effects LLC, Logan, UT 84321 USA. RP Strube, M (reprint author), NASA, GSFC, Code 596, Greenbelt, MD 20771 USA. NR 15 TC 0 Z9 0 U1 1 U2 2 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 659 EP 672 PG 14 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600049 ER PT S AU Foster, CW Blaschak, JM Eldridge, EA Brazzel, JP Spehar, PT AF Foster, Christopher W. Blaschak, Johnathan M. Eldridge, Erin A. Brazzel, Jack P. Spehar, Peter T. BE Gravseth, IJ TI DESIGN AND PRELIMINARY TESTING OF THE INTERNATIONAL DOCKING ADAPTER'S PERIPHERAL DOCKING TARGET SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB The International Docking Adapter's Peripheral Docking Target (PDT) was designed to allow a docking spacecraft to judge its alignment relative to the docking system. The PDT was designed to be compatible with relative sensors using visible cameras, thermal imagers, or Light Detection and Ranging (LIDAR) technologies. The conceptual design team tested prototype designs and materials to determine the contrast requirements for the features. This paper will discuss the design of the PDT, the methodology and results of the tests, and the conclusions pertaining to PDT design that were drawn from testing. C1 [Foster, Christopher W.; Blaschak, Johnathan M.; Eldridge, Erin A.] Jacobs Engn, Aerosci & Flight Mech Sect, 2224 Bay Area Blvd, Houston, TX 77058 USA. [Brazzel, Jack P.; Spehar, Peter T.] NASA, GN&C Autonomous Flight Syst Branch, Johnson Space Ctr, Houston, TX 77058 USA. RP Foster, CW (reprint author), Jacobs Engn, Aerosci & Flight Mech Sect, 2224 Bay Area Blvd, Houston, TX 77058 USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 711 EP 723 PG 13 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600053 ER PT S AU Starek, JA Barbee, B Pavone, M AF Starek, Joseph A. Barbee, Brent Pavone, Marco BE Gravseth, IJ TI A SAMPLING-BASED APPROACH TO SPACECRAFT AUTONOMOUS MANEUVERING WITH SAFETY SPECIFICATIONS SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO ID ALGORITHMS; GUIDANCE AB This paper presents a method for safe spacecraft autonomous maneuvering that leverages robotic motion planning techniques to spacecraft control. Specifically, the scenario we consider is an in-plane rendezvous of a chaser spacecraft in proximity to a target spacecraft at the origin of the Clohessy-Wiltshire-Hill frame. The trajectory for the chaser spacecraft is generated in a receding-horizon fashion by executing a sampling-based robotic motion planning algorithm named Fast Marching Trees (FMT*), which efficiently grows a tree of trajectories over a set of probabilistically-drawn samples in the state space. To enforce safety, the tree is only grown over actively safe samples, from which there exists a one-burn collision avoidance maneuver that circularizes the spacecraft orbit along a collision-free coasting arc and that can be executed under potential thruster failures. The overall approach establishes a provably-correct framework for the systematic encoding of safety specifications into the spacecraft trajectory generation process and appears promising for real-time implementation on orbit. Simulation results are presented for a two-fault tolerant spacecraft during autonomous approach to a single client in Low Earth Orbit. C1 [Starek, Joseph A.; Pavone, Marco] Stanford Univ, Dept Aeronaut & Astronaut, Durand Bldg,496 Lomita Mall,Room 009, Stanford, CA 94305 USA. [Barbee, Brent] NASA, Nav & Mission Design Branch, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Starek, JA (reprint author), Stanford Univ, Dept Aeronaut & Astronaut, Durand Bldg,496 Lomita Mall,Room 009, Stanford, CA 94305 USA. NR 23 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 725 EP 737 PG 13 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600054 ER PT S AU Scheeres, DJ Van Wal, S Tardivel, S AF Scheeres, D. J. Van Wal, S. Tardivel, S. BE Gravseth, IJ TI FLYBY-ONLY SCIENCE OPERATIONS FOR AN ASTEROID EXPLORATION MISSION SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO ID 1999 KW4; SIMULATION AB Orbital operations at small bodies can be challenging for mission planning purposes due to the large uncertainties in a target asteroids shape, size, mass and rotation rate. Even if these are known based on ground observations, the overall environment may also be challenging from an orbit stability point of view, especial for a binary asteroid. For an asteroid with a sufficiently small total size and mass, however, orbital mechanics approaches can be eschewed in favor of performing multiple flybys of the body at low speeds, performing a "turn around" maneuver every few days to revisit the body. In this paper this mission approach is explored in more detail, and in terms of observations and gravity field measurements of the central body. Considerations will also be explored for the deployment of surface packages using such an approach. It will be shown that this approach to mission operations at small asteroids forms another possible close proximity solution in addition to the already explored orbital and hovering approaches used by the NEAR and Hayabusa missions, respectively. C1 [Scheeres, D. J.; Van Wal, S.] Univ Colorado, Dept Aerosp Engn Sci, Boulder, CO 80309 USA. [Tardivel, S.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Scheeres, DJ (reprint author), Univ Colorado, Dept Aerosp Engn Sci, Boulder, CO 80309 USA. EM scheeres@colorado.edu; scheeres@colorado.edu NR 13 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 771 EP 786 PG 16 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600057 ER PT S AU Bhaskaran, S Broschart, S Han, D Mastrodemos, N Owen, B Roundhill, I Rush, B Smith, J Surovik, D Budnik, F Companys, V AF Bhaskaran, Shyam Broschart, Stephen Han, Don Mastrodemos, Nick Owen, Bill Roundhill, Ian Rush, Brian Smith, Jonathon Surovik, David Budnik, Frank Companys, Vicente BE Gravseth, IJ TI ROSETTA NAVIGATION AT COMET CHURYUMOV-GERASIMENKO SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB On August 6, 2014, the European Space Agency's Rosetta mission arrived at comet Churyumov-Gerasimenko to mark a new era in comet exploration. After a series of orbits which took it progressively closer to the nucleus, the Philae lander was released from the Rosetta orbiter and touched down on the surface of the comet on November 12, 2014. Navigation of Rosetta, including the landing of Philae, was especially challenging due to several factors, including the use of terrain-relative optical navigation, the central body being a highly irregularly shaped object with unknown mass distribution, and an unknown coma environment. The responsibility for mission design and navigation of Rosetta resides with the Flight Dynamics group at the European Space Operations Center; through a collaborative arrangement, navigation specialists at the Jet Propulsion Laboratory also performed a parallel effort to reconstruct the spacecraft's orbit from approach through the Philae landing. In this paper, we describe JPL's methods and results in determining the orbit of Rosetta and the Philae lander. C1 [Bhaskaran, Shyam] CALTECH, Outer Planet Nav Grp, Nav & Mission Design Sect, Jet Prop Lab, MS 301-820,4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Smith, Jonathon] CALTECH, Nav & Mission Design Sect, Jet Prop Lab, Pasadena, CA 91109 USA. [Surovik, David] Univ Colorado, Colorado Ctr Astrodynam Res, Boulder, CO 80309 USA. [Companys, Vicente] European Space Technol Ctr, Darmstadt, Germany. RP Bhaskaran, S (reprint author), CALTECH, Outer Planet Nav Grp, Nav & Mission Design Sect, Jet Prop Lab, MS 301-820,4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 10 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 787 EP 801 PG 15 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600058 ER PT S AU Mastrodemos, N Rush, BP Owen, WM AF Mastrodemos, Nickolaos Rush, Brian P. Owen, William M., Jr. BE Gravseth, IJ TI OPTICAL NAVIGATION FOR THE ROSETTA MISSION SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB JPL's participation in ESA's Rosetta mission to comet 67P/Churyumov-Gerasimenko includes a parallel navigation effort in which JPL conducts navigation operations along with ESA and compares orbit solutions and estimated cometary parameters. Optical navigation, begun during approach to the comet and continuing through the orbit phases, is an integral part of that effort. We describe the optical navigation operations, methodology and key results for star-relative image processing during approach, and landmark tracking on orbit. C1 [Mastrodemos, Nickolaos; Rush, Brian P.; Owen, William M., Jr.] CALTECH, Opt Nav Grp, Mission Design & Nav Sect, Jet Prop Lab, MS 264-820, Pasadena, CA 91109 USA. RP Mastrodemos, N (reprint author), CALTECH, Opt Nav Grp, Mission Design & Nav Sect, Jet Prop Lab, MS 264-820, Pasadena, CA 91109 USA. EM mastrode@jpl.nasa.gov; brush@jpl.nasa.gov; wmo@jpl.nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 803 EP 819 PG 17 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600059 ER PT S AU Berry, K Antreasian, P Moreau, MC May, A Sutter, B AF Berry, Kevin Antreasian, Peter Moreau, Michael C. May, Alex Sutter, Brian BE Gravseth, IJ TI OSIRIS-REX TOUCH-AND-GO (TAG) NAVIGATION PERFORMANCE SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB The Origins Spectral Interpretation Resource Identification Security Regolith Explorer (OSIRIS-REx) mission is a NASA New Frontiers mission launching in 2016 to rendezvous with the near-Earth asteroid (101955) Bennu in late 2018. Following an extensive campaign of proximity operations activities to characterize the properties of Bennu and select a suitable sample site, OSIRIS-REx will fly a Touch-And-Go (TAG) trajectory to the asteroid's surface to obtain a regolith sample. The paper summarizes the mission design of the TAG sequence, the propulsive maneuvers required to achieve the trajectory, and the sequence of events leading up to the TAG event. The paper also summarizes the Monte-Carlo simulation of the TAG sequence and presents analysis results that demonstrate the ability to conduct the TAG within 25 meters of the selected sample site and +/-2 cm/s of the targeted contact velocity. The paper describes some of the challenges associated with conducting precision navigation operations and ultimately contacting a very small asteroid. C1 [Berry, Kevin; Moreau, Michael C.] NASA, GSFC, Code 595,8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Antreasian, Peter] KinetX Inc, Space Nav & Flight Dynam SNAFD Practice, Simi Valley, CA 93065 USA. [May, Alex; Sutter, Brian] Lockheed Martin Space Syst Co, Syst Engn, Littleton, CO 80125 USA. RP Berry, K (reprint author), NASA, GSFC, Code 595,8800 Greenbelt Rd, Greenbelt, MD 20771 USA. NR 7 TC 0 Z9 0 U1 2 U2 2 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 833 EP 844 PG 12 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600061 ER PT S AU Broschart, SB Abrahamson, M Bhaskaran, S Fahnestock, EG Karimi, RR Lantoine, G Pavlak, TA Chappaz, L AF Broschart, Stephen B. Abrahamson, Matthew Bhaskaran, Shyam Fahnestock, Eugene G. Karimi, Reza R. Lantoine, Gregory Pavlak, Thomas A. Chappaz, Loic BE Gravseth, IJ TI THE SMALL-BODY DYNAMICS TOOLKIT AND ASSOCIATED CLOSE-PROXIMITY NAVIGATION ANALYSIS TOOLS AT JPL SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO ID SPACECRAFT; POLYHEDRON; ASTEROIDS; BODIES AB Over the past several years, an ecosystem of MATLAB-based tools has been developing at NASA's Jet Propulsion Laboratory (JPL) for early-mission analysis of encounter-phase navigation at primitive bodies. These tools increasingly draw from a common implementation of capabilities known as the Small-Body Dynamics Toolkit (SBDT). Fundamentally, the SBDT provides support for trajectory integration and geometric analysis of the environment, providing force models (gravity, solar pressure, comet outgassing), equations of motion, polyhedron shape utilities, altitude calculations, occultation checking, and more. Using the capabilities of the SBDT; analysis tools for mapping performance analysis (PB-CAGE), navigation performance analysis (AutoNAV), and trajectory design space characterization (SBMCT) have been developed. This paper provides a brief overview of the SBDT and these associated analysis tools. C1 [Broschart, Stephen B.; Abrahamson, Matthew; Bhaskaran, Shyam; Fahnestock, Eugene G.; Karimi, Reza R.; Lantoine, Gregory; Pavlak, Thomas A.] CALTECH, Mission Design & Nav Sect, Jet Prop Lab, M-S 301-121,4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Chappaz, Loic] Purdue Univ, Sch Aeronaut & Astronaut, W Lafayette, IN 47906 USA. RP Broschart, SB (reprint author), CALTECH, Mission Design & Nav Sect, Jet Prop Lab, M-S 301-121,4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 29 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 859 EP 870 PG 12 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600063 ER PT S AU Barth, A Marnich, H Hoelscher, B AF Barth, Andrew Marnich, Harvey Hoelscher, Brian BE Gravseth, IJ TI POST-FLIGHT ANALYSIS OF THE GUIDANCE, NAVIGATION AND CONTROL PERFORMANCE DURING ORION EXPLORATION FLIGHT TEST 1 SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB The first test flight of the Orion Multi-Purpose Crew Vehicle presented additional challenges for guidance, navigation and control as compared to a typical re-entry from the International Space Station or other Low Earth Orbit. An elevated re-entry velocity and steeper flight path angle were chosen to achieve aero-thermal flight test objectives. New IMU's, a GPS receiver, and baro altimeters were flight qualified to provide the redundant navigation needed for human space flight. The guidance and control systems must manage the vehicle lift vector in order to deliver the vehicle to a precision, coastal, water landing, while operating within aerodynamic load, reaction control system, and propellant constraints. Extensive pre-flight six degree-of-freedom analysis was performed that showed mission success for the nominal mission as well as in. the presence of sensor and effector failures. Post-flight reconstruction analysis of the test flight is presented in this paper to show whether that all performance metrics were met and establish how well the pre-flight analysis predicted the in-flight performance. C1 [Barth, Andrew] Lockheed Martin Corp, Explorat & Mission Support, POB 58487,Mail Code H3B, Houston, TX 77258 USA. [Marnich, Harvey] Lockheed Martin Corp, Littleton, CO 80125 USA. [Hoelscher, Brian] NASA, Integrated GN&C Branch, JSC, Houston, TX 77058 USA. RP Barth, A (reprint author), Lockheed Martin Corp, Explorat & Mission Support, POB 58487,Mail Code H3B, Houston, TX 77258 USA. NR 0 TC 1 Z9 1 U1 2 U2 2 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 931 EP 943 PG 13 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600068 ER PT S AU Tibbetts, BR Blood, E Sell, S Benton, J AF Tibbetts, Brian R. Blood, Eric Sell, Steve Benton, Jeff BE Gravseth, IJ TI GLN-MAC INITIALIZATION APPROACH AND NAVIGATION SOLUTION AS APPLIED TO LDSD SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB The recent Low Density Supersonic Decelerator (LDSD) Supersonic Flight Dynamics Test (SFDT) vehicle flew from the Pacific Missile Range Facility (PMRF) on Kauai,Hawaii. This SFDT flight tested two entry technologies, a 6-meter supersonic inflatable aerodynamic decelerator (SIAD), which was deployed at Mach 4, and a supersonic disksail parachute, which was deployed at Mach 2.75. In order to test these entry technologies in Mars-relevant conditions, the technologies must fly through a representative mach and dynamic pressure regime. To accomplish that, the test vehicle was hoisted under a balloon up to an altitude of 36 km. At this point, the test vehicle separated from the balloon and began its primary mission under its own propulsion. A critical aspect of meeting the test conditions was to deploy the technologies at the correct velocities, to within 30m/s. Several challenges existed to accomplish this level of accuracy, including initialization of the IMU (GLN-MAC) while in a pendulum-motion under the balloon, the use of a magnetometer in a untested configuration for heading, and loss of GPS solutions at vehicle spin-up, requiring ded-reckoned navigation throughout the flight. This paper describes the challenges and our solutions to initialization, producing a navigated velocity for event triggering, operations, and the in-flight performance of the system. C1 [Tibbetts, Brian R.; Sell, Steve; Benton, Jeff] Orbital Sci Corp, Wallops Flight Facil, F-10,Room N231, Wallops Isl, VA 23337 USA. [Blood, Eric] CALTECH, EDL Syst Grp, Pasadena, CA 91109 USA. [Blood, Eric] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Tibbetts, BR (reprint author), Orbital Sci Corp, Wallops Flight Facil, F-10,Room N231, Wallops Isl, VA 23337 USA. NR 1 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 945 EP 956 PG 12 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600069 ER PT S AU Collins, SM Essmiller, JC Hines, EK San Martin, AM Serricchio, F AF Collins, Steven M. Essmiller, John C. Hines, Erisa K. San Martin, A. Miguel Serricchio, Frederick BE Gravseth, IJ TI MSL CRUISE ATTITUDE CONTROL FLIGHT EXPERIENCE AND IMPLICATIONS FOR MARS 2020 SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB The spectacular landing of the Mars Science Laboratory "Curiosity" rover in August 2012 was made possible by the near perfect delivery of the vehicle to the planned entry conditions after a 8-month interplanetary cruise. Using a spin-stabilized attitude control architecture based on the earlier Mars Exploration Rovers and Mars Pathfinder missions, MSL executed 4 trajectory corrections, 22 turns to maintain power and communications and 18 turns in support of in-flight alignments and calibrations. To enable use of a guided, lifting entry, cruise ACS was also called on to perform a high-reliability precision initialization of the entry vehicle's onboard inertial navigation system just before landing. Along with other surprises, cruise operations were complicated by an early problem with the spacecraft flight computer which prevented use of the onboard star scanner for the first few months of flight. During this important period, ACS activities were accomplished using a combination of sun-only modes and ground based attitude determination. This paper outlines the MSL cruise attitude control system and relates our flight experience during operations, describing some of the challenges faced during the mission and the techniques and system features used to over-come them. We also present a performance assessment and several lessons learned with relevance. to Mars 2020 and other future missions using the MPF/MER/MSL cruise architecture. C1 [Collins, Steven M.; Essmiller, John C.; Hines, Erisa K.; San Martin, A. Miguel; Serricchio, Frederick] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Collins, SM (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 957 EP 967 PG 11 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600070 ER PT S AU Peters, SF Vanelli, CA Allen, WC Collins, SM Montgomery, JF Sklyanskiy, E AF Peters, Stephen F. Vanelli, C. Anthony Allen, William C. Collins, Steven M. Montgomery, James F. Sklyanskiy, Evgeniy BE Gravseth, IJ TI AVOIDING HIGH-GAIN ANTENNA OCCLUSIONS AND FLOPS IN MARS SCIENCE LABORATORY SURFACE OPERATIONS SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB A rover occlusion is a part of the spacecraft which blocks the high-gain antenna's view of the Earth, interfering with communication. A flop is a change of kinematic solution in the middle of an Earth track, temporarily breaking the communications link. When the Mars Science Laboratory rover is level and the Earth is near the horizon, the Earth is occluded for 55 percent of rover headings. When the rover is level and the Earth is near zenith, a flop is required to continue tracking for 44 percent of rover headings. These constraints and two tools used in everyday tactical operations to help rover planners choose unoccluded, flop-free end-of-drive headings are described. C1 [Peters, Stephen F.] CALTECH, Mobil & Robot Syst, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Vanelli, C. Anthony; Collins, Steven M.; Montgomery, James F.; Sklyanskiy, Evgeniy] CALTECH, Guidance & Control, Jet Prop Lab, Pasadena, CA 91109 USA. [Allen, William C.] CALTECH, Spacecraft Mech Engn, Jet Prop Lab, Pasadena, CA 91109 USA. RP Peters, SF (reprint author), CALTECH, Mobil & Robot Syst, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 1 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 983 EP 991 PG 9 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600072 ER PT S AU Peters, SF AF Peters, Stephen F. BE Gravseth, IJ TI AN ERROR BUDGET FOR POINTING AT SURFACE FEATURES FROM CLOSE RANGE SO GUIDANCE, NAVIGATION, AND CONTROL 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 38th Annual AAS Rocky Mountain Section Guidance and Control Conference CY JAN 30-FEB 04, 2015 CL Breckenridge, CO AB Spacecraft instrument pointing performance is often characterized by a single number: radial angular error, three sigma. In support of the spacecraft design process, pointing error budgets allocate allowable contributions to this error from the sensors, actuators, and portions of spacecraft structure that affect pointing accuracy. When pointing the Mars Science Laboratory ChemCam Laser-Induced Breakdown Spectrometer at a surface feature, the error of interest is the distance of the laser spot from the feature on the surface. The footprint of error on the surface depends not only on the overall radial angular error, but also on the distance to the surface feature. Translational distortions within the spacecraft also affect the error footprint. The effective origin of error is defined, and a mathematical formulation for computing pointing error budgets in terms of radial distances from a surface feature is presented. C1 [Peters, Stephen F.] CALTECH, Mobil & Robot Syst, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Peters, SF (reprint author), CALTECH, Mobil & Robot Syst, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-621-0 J9 ADV ASTRONAUT SCI PY 2015 VL 154 BP 993 EP 1002 PG 10 WC Automation & Control Systems; Engineering, Aerospace SC Automation & Control Systems; Engineering GA BE4FR UT WOS:000371649600073 ER PT S AU Vu, TT Rongione, N Rahmani, A AF Vu, Thanh T. Rongione, Nicolas Rahmani, Amir GP IEEE TI Minimalist Control Design of Canard-Actuated Micro-Projectiles SO IEEE SOUTHEASTCON 2015 SE IEEE SoutheastCon-Proceedings LA English DT Proceedings Paper CT IEEE Southeast Conference (IEEE SoutheastCon) CY APR 09-12, 2015 CL Fort Lauderdale, FL SP IEEE DE ballistics; micro-projectiles; canard-actuated control; minimalist control; smart munitions AB A minimal control law is designed for a canard controlled smart projectile. This system allows for an envelope of down and cross range targeting capability for a set initial firing state. The controller relies on limited aerodynamic data with initial firing conditions in order to avoid the need for complicated electronics and sensors. First range and lateral control are shown to be achieved independently, and then they were combined to demonstrate full 3D control. A 6DoF simulation is used to show the effectiveness of the proposed algorithm. Sensitivity analysis to variations in initial conditions are carried out using Monte Carlo simulations. With a 5 m/s muzzle velocity, a 95% confidence predefined target landing is achieved with -0.236% +/- 0.792% lateral and -0.352% +/- 0.185% range error. C1 [Vu, Thanh T.; Rongione, Nicolas] Univ Miami, Coll Engn, Coral Gables, FL 33146 USA. [Rahmani, Amir] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Vu, TT (reprint author), Univ Miami, Coll Engn, Coral Gables, FL 33146 USA. EM t.vu3@umiami.edu; n.rongione@umiami.edu; a.rahmani@gmail.com NR 9 TC 0 Z9 0 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1091-0050 BN 978-1-4673-7300-5 J9 IEEE SOUTHEASTCON PY 2015 PG 5 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BE3YR UT WOS:000371393800186 ER PT J AU Zwally, HJ Li, J Robbins, JW Saba, JL Yi, DH Brenner, AC AF Zwally, H. Jay Li, Jun Robbins, John W. Saba, Jack L. Yi, Donghui Brenner, Anita C. TI Mass gains of the Antarctic ice sheet exceed losses SO JOURNAL OF GLACIOLOGY LA English DT Article DE Antarctic glaciology; ice and climate; ice-sheet mass balance; surface mass budget ID SEA-LEVEL RISE; FIRN COMPACTION; EAST ANTARCTICA; TEMPERATURE-VARIATIONS; ELEVATION CHANGES; LAKE VOSTOK; ACCUMULATION; GREENLAND; BALANCE; RADAR AB Mass changes of the Antarctic ice sheet impact sea-level rise as climate changes, but recent rates have been uncertain. Ice, Cloud and land Elevation Satellite (ICESat) data (2003-08) show mass gains from snow accumulation exceeded discharge losses by 82 +/- 25 Gt a(-1), reducing global sea-level rise by 0.23 mm a(-1). European Remote-sensing Satellite (ERS) data (1992-2001) give a similar gain of 112 +/- 61 Gt a(-1). Gains of 136 Gt a(-1) in East Antarctica (EA) and 72 Gt a(-1) in four drainage systems (WA2) in West Antarctic (WA) exceed losses of 97 Gt a(-1) from three coastal drainage systems (WA1) and 29 Gt a(-1) from the Antarctic Peninsula (AP). EA dynamic thickening of 147 Gt a(-1) is a continuing response to increased accumulation (>50%) since the early Holocene. Recent accumulation loss of 11 Gt a(-1) in EA indicates thickening is not from contemporaneous snowfall increases. Similarly, the WA2 gain is mainly (60 Gt a-1) dynamic thickening. In WA1 and the AP, increased losses of 66 +/- 16 Gt a(-1) from increased dynamic thinning from accelerating glaciers are 50% offset by greater WA snowfall. The decadal increase in dynamic thinning in WA1 and the AP is approximately one-third of the long-term dynamic thickening in EA and WA2, which should buffer additional dynamic thinning for decades. C1 [Zwally, H. Jay] NASA, Goddard Space Flight Ctr, Cryospher Sci Lab, Greenbelt, MD 20771 USA. [Zwally, H. Jay] Univ Maryland, Earth Syst Sci Interdisciplinary Ctr, College Pk, MD 20742 USA. [Li, Jun; Yi, Donghui] SGT Inc, NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. [Robbins, John W.] Craig Technol, NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. [Saba, Jack L.] Sci Syst & Applicat Inc, NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. [Brenner, Anita C.] Sigma Space Corp, Lanham, MD USA. RP Zwally, HJ (reprint author), NASA, Goddard Space Flight Ctr, Cryospher Sci Lab, Greenbelt, MD 20771 USA. EM jayzwallyice@verizon.net FU NASA's Project Science funding FX We thank D.H. Bromwich and J.P. Nicolas for assistance and advice on the reanalysis data, J.T.M. Lenaerts and M.R. van den Broeke for providing their SMB data for comparison, E. Ivins and P. Whitehouse for providing their GIA model results, A. Ridout for providing the Envisat SSH data, and S. Farrell for discussions about Arctic SSH measurements. In memoriam, we deeply appreciate the pioneering work of Seymour Laxon and Katharine Giles on measuring SSH in the Arctic from satellite altimetry. We also thank J. DiMarzio, D. Hancock and many others in the ICESat Project support group. This research was supported by NASA's Project Science funding. NR 62 TC 15 Z9 15 U1 3 U2 14 PU CAMBRIDGE UNIV PRESS PI CAMBRIDGE PA EDINBURGH BLDG, SHAFTESBURY RD, CB2 8RU CAMBRIDGE, ENGLAND SN 0022-1430 EI 1727-5652 J9 J GLACIOL JI J. Glaciol. PY 2015 VL 61 IS 230 BP 1019 EP 1036 DI 10.3189/2015JoG15J071 PG 18 WC Geography, Physical; Geosciences, Multidisciplinary SC Physical Geography; Geology GA DF9AW UT WOS:000371653600001 ER PT J AU Li, J Zwally, HJ AF Li, Jun Zwally, H. Jay TI Response times of ice-sheet surface heights to changes in the rate of Antarctic firn compaction caused by accumulation and temperature variations SO JOURNAL OF GLACIOLOGY LA English DT Article DE polar firn ID MASS-BALANCE; INTERANNUAL VARIATIONS; ELEVATION CHANGES; GREENLAND SUMMIT; DENSIFICATION; MODEL AB Variations in accumulation rate A(s)(t) and temperature T-s(t) at the surface of firn cause changes in the rate of firn compaction (FC) and surface height H(t) that do not involve changes in mass, and therefore need to be accounted for in deriving mass changes from measured H(t). As the effects of changes in A(s)(t) and T-s(t) propagate into the firn, the FC rate is affected with a highly variable and complex response time. The H(t) during measurement periods depend on the history of A(s)(t) and T-s(t) prior to the measurements. Consequently, knowledge of firn response times to climate perturbations is important to estimate the required length of the time series of A(s)(t) and T-s(t) used in FC models. We use our numerical FC model, which is time-dependent on both temperature and accumulation rate, to examine the response times of both H(t) and the rates of change dH(t)/dt to variations in A(s)(t) and T-s(t) using sample perturbations and climate data for selected sites in Antarctica. Our results show that the response times for dH(t)/dt, which are of particular interest, are much shorter than the responses of H(t). Typical response times of dH(t)/dt are from several years to <20 years. The response times are faster in warmer and higher-accumulation areas such as Byrd Station, West Antarctica (4 years), and slower in colder and lower-accumulation areas such as Vostok, East Antarctica (18 years). The response times to temperature are much faster (0.9 year at Byrd and 2.2 years at Vostok), but the corresponding height changes persist much longer. The associated variations in firn density are significantly preserved in the density depth profiles. For typical fluctuations of surface weather, the Ts(()t) from satellite observations since 1982 and A(s)(t) from meteorological data since 1979 are essentially of sufficient length to correct for FC height changes for measurements beginning in 1992. C1 [Li, Jun] SGT Inc, NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. [Zwally, H. Jay] NASA, Goddard Space Flight Ctr, Lab Cryospher Sci, Greenbelt, MD 20771 USA. RP Li, J (reprint author), SGT Inc, NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. EM jun.li@nasa.gov NR 24 TC 1 Z9 1 U1 5 U2 7 PU INT GLACIOL SOC PI CAMBRIDGE PA LENSFIELD RD, CAMBRIDGE CB2 1ER, ENGLAND SN 0022-1430 EI 1727-5652 J9 J GLACIOL JI J. Glaciol. PY 2015 VL 61 IS 230 BP 1037 EP 1047 DI 10.3189/2015JoG14J182 PG 11 WC Geography, Physical; Geosciences, Multidisciplinary SC Physical Geography; Geology GA DF9AW UT WOS:000371653600002 ER PT S AU Seubert, J Ely, T AF Seubert, Jill Ely, Todd BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI UTILIZATION OF THE DEEP SPACE ATOMIC CLOCK FOR EUROPA GRAVITATIONAL TIDE RECOVERY SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB Estimation of Europa's gravitational tide can provide strong evidence of the existence of a subsurface liquid ocean. Due to limited close approach tracking data, a Europa flyby mission suffers strong coupling between the gravity solution quality and tracking data quantity and quality. This work explores utilizing Low Gain Antennas with the Deep Space Atomic Clock (DSAC) to provide abundant high accuracy uplink-only radiometric tracking data. DSAC's performance, expected to exhibit an Allan Deviation of less than 3e-15 at one day, provides long-term stability and accuracy on par with the Deep Space Network ground clocks, enabling one-way radiometric tracking data with accuracy equivalent to that of its two-way counterpart. The feasibility of uplink-only Doppler tracking via the coupling of LGAs and DSAC and the expected Doppler data quality are presented. Violations of the Kalman filter's linearization assumptions when state perturbations are included in the flyby analysis results in poor determination of the Europa gravitational tide parameters. B-plane targeting constraints are statistically determined, and a solution to the linearization issues via pre-flyby approach orbit determination is proposed and demonstrated. C1 [Seubert, Jill; Ely, Todd] CALTECH, Jet Prop Lab, Deep Space Atom Clock Technol Demonstrat Mission, MS 301-141C,4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Seubert, J (reprint author), CALTECH, Jet Prop Lab, Deep Space Atom Clock Technol Demonstrat Mission, MS 301-141C,4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Jill.Tombasco@jpl.nasa.gov; Todd.A.Ely@jpl.nasa.gov NR 16 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 367 EP 384 PN I-III PG 18 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200023 ER PT S AU White, J Dutta, S Striepe, S AF White, Joseph Dutta, Soumyo Striepe, Scott BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI SFDT-1 CAMERA POINTING AND SUN-EXPOSURE ANALYSIS AND FLIGHT PERFORMANCE SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB The Supersonic Flight Dynamics Test (SFDT) vehicle was developed to advance and test technologies of NASA's Low Density Supersonic Decelerator (LDSD) Technology Demonstration Mission. The first flight test (SFDT-1) occurred on June 28, 2014. In order to optimize the usefulness of the camera data, analysis was performed to optimize parachute visibility in the camera field of view during deployment and inflation and to determine the probability of sun-exposure issues with the cameras given the vehicle heading and launch time. This paper documents the analysis, results and comparison with flight video of SFDT-1. C1 [White, Joseph] Analyt Mech Associates Inc, 21 Enterprise Pkwy,Suite 300, Hampton, VA 23666 USA. [Dutta, Soumyo; Striepe, Scott] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP White, J (reprint author), Analyt Mech Associates Inc, 21 Enterprise Pkwy,Suite 300, Hampton, VA 23666 USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 489 EP 505 PN I-III PG 17 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200030 ER PT S AU Dutta, S Bowes, AL Striepe, SA Davis, JL Queen, EM Blood, EM Ivanov, MC AF Dutta, Soumyo Bowes, Angela L. Striepe, Scott A. Davis, Jody L. Queen, Eric M. Blood, Eric M. Ivanov, Mark C. BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI SUPERSONIC FLIGHT DYNAMICS TEST 1-POST-FLIGHT ASSESSMENT OF SIMULATION PERFORMANCE SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB NASA's Low Density Supersonic Decelerator (LDSD) project conducted its first Supersonic Flight Dynamics Test (SFDT-1) on June 28, 2014. Program to Optimize Simulated Trajectories II (POST2) was one of the flight dynamics codes used to simulate and predict the flight performance and Monte Carlo analysis was used to characterize the potential flight conditions experienced by the test vehicle. This paper compares the simulation predictions with the reconstructed trajectory of SFDT-1. Additionally, off-nominal conditions seen during flight are modeled in post-flight simulations to find the primary contributors that reconcile the simulation with flight data. The results of these analyses are beneficial for the pre-flight simulation and targeting of the follow-on SFDT flights currently scheduled for summer 2015. C1 [Dutta, Soumyo; Bowes, Angela L.; Striepe, Scott A.; Davis, Jody L.; Queen, Eric M.] NASA, Langley Res Ctr, Hampton, VA 23665 USA. [Blood, Eric M.; Ivanov, Mark C.] CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Dutta, S (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. EM soumyo.dutta@nasa.gov; angela.bowes@nasa.gov; scott.a.striepe@nasa.gov; jody.l.davis@nsa.gov; eric.m.queen@nasa.gov; eric.blood@jpl.nasa.gov; mark.c.ivanov@jpl.nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 507 EP 522 PN I-III PG 16 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200031 ER PT S AU Kutty, P Karlgaard, CD Blood, EM O'Farrell, C Ginn, JM Schoenenberger, M Dutta, S AF Kutty, Prasad Karlgaard, Christopher D. Blood, Eric M. O'Farrell, Clara Ginn, Jason M. Schoenenberger, Mark Dutta, Soumyo BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI SUPERSONIC FLIGHT DYNAMICS TEST: TRAJECTORY, ATMOSPHERE, AND AERODYNAMICS RECONSTRUCTION SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB The Supersonic Flight Dynamics Test is a full-scale flight test of a Supersonic Inflatable Aerodynamic Decelerator, which is part of the Low Density Supersonic Decelerator technology development project. The purpose of the project is to develop and mature aerodynamic decelerator technologies for landing large mass payloads on the surface of Mars. The technologies include a Supersonic Inflatable Aerodynamic Decelerator and Supersonic Parachutes. The first Supersonic Flight Dynamics Test occurred on June 28th, 2014 at the Pacific Missile Range Facility. This test was used to validate the test architecture for future missions. The flight was a success and, in addition, was able to acquire data on the aerodynamic performance of the supersonic inflatable decelerator. This paper describes the instrumentation, analysis techniques, and acquired flight test data utilized to reconstruct the vehicle trajectory, atmosphere, and aerodynamics. The results of the reconstruction show significantly higher lofting of the trajectory, which can partially be explained by off-nominal booster motor performance. The reconstructed vehicle force and moment coefficients fall well within pre-flight predictions. A parameter identification analysis indicates that the vehicle displayed greater aerodynamic static stability than seen in pre-flight computational predictions and ballistic range tests. C1 [Kutty, Prasad; Karlgaard, Christopher D.] Analyt Mech Associates Inc, Hampton, VA USA. [Blood, Eric M.; Ginn, Jason M.] CALTECH, Jet Prop Lab, EDL & Adv Technol, Pasadena, CA USA. [O'Farrell, Clara] CALTECH, Jet Prop Lab, EDL Guidance & Control Syst, Pasadena, CA USA. [Schoenenberger, Mark; Dutta, Soumyo] NASA, Langley Res Ctr, Atmospher Flight & Entry Syst Branch, Hampton, VA 23665 USA. RP Kutty, P (reprint author), Analyt Mech Associates Inc, Hampton, VA USA. NR 29 TC 0 Z9 0 U1 1 U2 1 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 523 EP 539 PN I-III PG 17 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200032 ER PT S AU Bowes, AL Davis, JL Dutta, S Striepe, SA Ivanov, MC Powell, RW White, J AF Bowes, Angela L. Davis, Jody L. Dutta, Soumyo Striepe, Scott A. Ivanov, Mark C. Powell, Richard W. White, Joseph BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI LDSD POST2 SIMULATION AND SFDT-1 PRE-FLIGHT LAUNCH OPERATIONS ANALYSES SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB The Low-Density Supersonic Decelerator (LDSD) Project's first Supersonic Flight Dynamics Test (SFDT-1) occurred June 28, 2014. Program to Optimize Simulated Trajectories II (POST2) was utilized to develop trajectory simulations characterizing all SFDT-1 flight phases from drop to splashdown. These POST2 simulations were used to validate the targeting parameters developed for SFDT-1, predict performance and understand the sensitivity of the vehicle and nominal mission designs, and to support flight test operations with trajectory performance and splashdown location predictions for vehicle recovery. This paper provides an overview of the POST2 simulations developed for LDSD and presents the POST2 simulation flight dynamics support during the SFDT-1 launch, operations, and recovery. C1 [Bowes, Angela L.; Davis, Jody L.; Dutta, Soumyo; Striepe, Scott A.] NASA, Langley Res Ctr, MS 489, Hampton, VA 23681 USA. [Ivanov, Mark C.] CALTECH, Jet Prop Lab, Pasadena, CA USA. [Powell, Richard W.; White, Joseph] Analyt Mech Associates Inc, Hampton, VA 23666 USA. RP Bowes, AL (reprint author), NASA, Langley Res Ctr, MS 489, Hampton, VA 23681 USA. EM angela.bowes@nasa.gov; jody.l.davis@nasa.gov; soumyo.dutta@nasa.gov; scott.a.striepe@nasa.gov; mark.c.ivanov@jpl.nasa.gov; richard.w.powell@nasa.gov; joseph.white@nasa.gov NR 16 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 541 EP 554 PN I-III PG 14 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200033 ER PT S AU Jesick, M AF Jesick, Mark BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI MARS DOUBLE-FLYBY FREE RETURNS SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID EARTH; OPTIMIZATION; TRAJECTORIES; ASSIST; CYCLER AB A subset of Earth-originating Mars double-flyby ballistic trajectories is documented. The subset consists of those trajectories that, after the first Mars flyby, perform a half-revolution transfer with Mars before returning to Earth. This class of free returns is useful for both human and robotic Mars missions because of its low geocentric energy at departure and arrival, and because of its extended stay time in the vicinity of Mars. Ballistic opportunities are documented over Earth departure dates ranging from 2015 through 2100. The mission is viable over three or four consecutive Mars synodic periods and unavailable for the next four, with the pattern repeating approximately every 15 years. Over the remainder of the century, a minimum Earth departure hyperbolic excess speed of 3.16 km/s, a minimum Earth atmospheric entry speed of 11.47 km/s, and a minimum flight time of 904 days are observed. The algorithm used to construct these trajectories is presented along with several examples. C1 [Jesick, Mark] CALTECH, Jet Prop Lab, Inner Planet Nav Grp, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Jesick, M (reprint author), CALTECH, Jet Prop Lab, Inner Planet Nav Grp, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM jesick@jpl.nasa.gov NR 30 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 695 EP 714 PN I-III PG 20 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200043 ER PT S AU Lugo, RA Ozoroski, TA Van Norman, JW Arney, DC Dec, JA Jones, CA Zumwalt, CH AF Lugo, Rafael A. Ozoroski, Thomas A. Van Norman, John W. Arney, Dale C. Dec, John A. Jones, Christopher A. Zumwalt, Carlie H. BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI HIGH ALTITUDE VENUS OPERATIONS CONCEPT TRAJECTORY DESIGN, MODELING, AND SIMULATION SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB A trajectory design and analysis that describes aerocapture, entry, descent, and inflation of manned and unmanned High Altitude Venus Operation Concept (HAVOC) lighter-than-air missions is presented. Mission motivation, concept of operations, and notional entry vehicle designs are presented. The initial trajectory design space is analyzed and discussed before investigating specific trajectories that are deemed representative of a feasible Venus mission. Under the project assumptions, while the high-mass crewed mission will require further research into aerodynamic decelerator technology, it was determined that the unmanned robotic mission is feasible using current technology. C1 [Lugo, Rafael A.; Ozoroski, Thomas A.; Van Norman, John W.] Analyt Mech Associates Inc, Hampton, VA 23666 USA. [Arney, Dale C.; Jones, Christopher A.] NASA, Langley Res Ctr, Space Mission Anal Branch, Hampton, VA 23681 USA. [Dec, John A.] NASA, Langley Res Ctr, Struct & Thermal Syst Branch, Hampton, VA 23681 USA. [Zumwalt, Carlie H.] NASA, Langley Res Ctr, Atmospher Flight & Entry Syst Branch, Hampton, VA 23681 USA. RP Lugo, RA (reprint author), Analyt Mech Associates Inc, Hampton, VA 23666 USA. NR 13 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 729 EP 748 PN I-III PG 20 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200045 ER PT S AU Genova, AL Yang, FY Perez, AD Galal, KF Faber, NT Mitchell, S Landin, B Datta, A Burns, JO AF Genova, Anthony L. Yang, Fan Yang Perez, Andres Dono Galal, Ken F. Faber, Nicolas T. Mitchell, Scott Landin, Brett Datta, Abhirup Burns, Jack O. BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI TRAJECTORY DESIGN FROM GTO TO NEAR-EQUATORIAL LUNAR ORBIT FOR THE DARK AGES RADIO EXPLORER (DARE) SPACECRAFT SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID MOON; FARSIDE AB The trajectory design for the Dark Ages Radio Explorer (DARE) mission concept involves launching the DARE spacecraft into a geosynchronous transfer orbit (GTO) as a secondary payload. From GTO, the spacecraft then transfers to a lunar orbit that is stable (i.e., no station-keeping maneuvers are required with minimum perilune altitude always above 40 km) and allows for more than 1,000 cumulative hours for science measurements in the radio-quiet region located on the lunar farside. C1 [Genova, Anthony L.] NASA, Ames Res Ctr, Mission Design Div, Moffett Field, CA 94035 USA. [Yang, Fan Yang] NASA, Ames Res Ctr, Mission Design Div, Sci & Technol Corp, Moffett Field, CA 94035 USA. [Perez, Andres Dono] NASA, Ames Res Ctr, Mission Design Div, USRA, Moffett Field, CA 94035 USA. [Galal, Ken F.] NASA, Ames Res Ctr, Programs & Projects Div, Moffett Field, CA 94035 USA. [Faber, Nicolas T.] NASA, Ames Res Ctr, Mission Design Div, SGT, Moffett Field, CA 94035 USA. [Mitchell, Scott] Ball Aerosp & Technol Corp, Boulder, CO 80301 USA. [Landin, Brett] Univ Colorado, Atmospher & Space Phys Lab, Boulder, CO 80303 USA. [Datta, Abhirup] Univ Colorado, Ctr Astrophys & Space Astron, Boulder, CO 80303 USA. [Burns, Jack O.] Univ Colorado, Dept Astrophys & Planetary Sci, Boulder, CO 80309 USA. [Burns, Jack O.] NASA, Ames Res Ctr, Lunar Sci Inst, Moffett Field, CA 94035 USA. RP Genova, AL (reprint author), NASA, Ames Res Ctr, Mission Design Div, Moffett Field, CA 94035 USA. NR 12 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 799 EP 813 PN I-III PG 15 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200049 ER PT S AU Strange, N Landau, D Longuski, J AF Strange, Nathan Landau, Damon Longuski, James BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI REDIRECTION OF ASTEROIDS ONTO EARTH-MARS CYCLERS SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society (AAS)/American Institute of Aeronautics and Astronautics Space (AIAA) Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID TRAJECTORIES AB NASA is currently studying an Asteroid Redirect Mission (ARM) that would capture either an entire small asteroid or a boulder from a larger asteroid and place it in orbit around the Moon using a Solar Electric Propulsion (SEP) vehicle. This asteroid redirection capability could also be used in future missions to redirect asteroids onto Earth-Mars cyclers where the asteroidal material could be used to provide water, propellant, structural material, and radiation shielding material. This last application is especially interesting as it may provide an economical solution to the problem of protecting astronauts from radiation on journeys to Mars. C1 [Strange, Nathan; Landau, Damon] CALTECH, Jet Prop Lab, Mission Concepts Sect, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Longuski, James] Purdue Univ, Sch Aeronaut & Astronaut, W Lafayette, IN 47907 USA. RP Strange, N (reprint author), CALTECH, Jet Prop Lab, Mission Concepts Sect, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 30 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 937 EP 948 PN I-III PG 12 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200057 ER PT S AU Zanetti, R D'Souza, CN AF Zanetti, Renato D'Souza, Christopher N. BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI OBSERVABILITY ANALYSIS AND FILTER DESIGN FOR THE ORION EARTH-MOON ATTITUDE FILTER SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID SPACECRAFT ATTITUDE; KALMAN; REPRESENTATIONS; NAVIGATION AB The Orion attitude navigation design is presented, together with justification of the choice of states in the filter and an analysis of the observability of its states while processing star tracker measurements. The analysis shows that when the gyro biases and scale factors drift at different rates and are modeled as first-order Gauss-Markov processes, the states are observable so long as the time constants are not the same for both sets of states. These results are used to finalize the design of the attitude estimation algorithm and the attitude calibration maneuvers. C1 [Zanetti, Renato; D'Souza, Christopher N.] NASA, Aerosci & Flight Mech Div, Johnson Space Ctr EG6, 2101 NASA Pkwy, Houston, TX 77058 USA. RP Zanetti, R (reprint author), NASA, Aerosci & Flight Mech Div, Johnson Space Ctr EG6, 2101 NASA Pkwy, Houston, TX 77058 USA. NR 15 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 1131 EP 1148 PN I-III PG 18 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200068 ER PT S AU Babiarz, C Carter, D Freesland, D Todirita, M Kronenwetter, J Kim, K Tadikonda, K Chu, D AF Babiarz, Craig Carter, Delano Freesland, Douglas Todirita, Monica Kronenwetter, Jeff Kim, Kevin Tadikonda, Kumar Chu, Donald BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI ASSESSING GOES-R MAGNETOMETER ACCURACY SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB The Geostationary Operational Environmental Satellite (GOES-R) will have two magnetometers on a long boom to monitor the geomagnetic field and space weather. There are several sources of measurement error including spacecraft field, bias, misalignment, scale factor and sensor non-orthogonality. This paper is a first attempt at estimating overall system accuracy using simulation and covariance analyses. It also proposes calibration procedures for post-launch test and routine operations. The results suggest that small annual maneuvers would be highly advantageous for maintaining accuracy. C1 [Babiarz, Craig] Univ Illinois, Aerosp Engn, Urbana, IL 61801 USA. [Carter, Delano] NASA, Goddard Space Flight Ctr, Thearal, Greenbelt, MD 20771 USA. [Freesland, Douglas] NASA, Goddard Space Flight Ctr, ACS Engn, Greenbelt, MD 20771 USA. [Todirita, Monica] NASA, Goddard Space Flight Ctr, NOAA, Greenbelt, MD 20771 USA. [Kronenwetter, Jeff; Chu, Donald] NASA, Goddard Space Flight Ctr, Chesapeake Aerosp, Greenbelt, MD 20771 USA. [Kim, Kevin] NASA, Goddard Space Flight Ctr, Bast Technol, Greenbelt, MD 20771 USA. [Tadikonda, Kumar] NASA, Goddard Space Flight Ctr, CSE, Greenbelt, MD 20771 USA. RP Babiarz, C (reprint author), Univ Illinois, Aerosp Engn, Urbana, IL 61801 USA. NR 3 TC 0 Z9 0 U1 1 U2 1 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 1241 EP 1248 PN I-III PG 8 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200074 ER PT S AU Englander, JA Vavrina, MA Ghosh, AR AF Englander, Jacob A. Vavrina, Matthew A. Ghosh, Alexander R. BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI MULTI-OBJECTIVE HYBRID OPTIMAL CONTROL FOR MULTIPLE-FLYBY LOW-THRUST MISSION DESIGN SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID GRAVITY-ASSIST TRAJECTORIES; GENETIC ALGORITHM; AUTOMATED DESIGN; OPTIMIZATION AB Preliminary design of low-thrust interplanetary missions is a highly complex process. The mission designer must choose discrete parameters such as the number of flybys, the bodies at which those flybys are performed, and in some cases the final destination. In addition, a time-history of control variables must be chosen that defines the trajectory. There are often many thousands, if not millions, of possible trajectories to be evaluated. The customer who commissions a trajectory design is not usually interested in a point solution, but rather the exploration of the trade space of trajectories between several different objective functions. This can be a very expensive process in terms of the number of human analyst hours required. An automated approach is therefore very desirable. This work presents such an approach by posing the mission design problem as a multi-objective hybrid optimal control problem. The method is demonstrated on a hypothetical mission to the main asteroid belt. C1 [Englander, Jacob A.] NASA, Goddard Space Flight Ctr, Nav & Mission Design Branch, Greenbelt, MD 20771 USA. [Vavrina, Matthew A.] Ai Solut Inc, Lanham, MD 20706 USA. [Ghosh, Alexander R.] Univ Illinois, Dept Aerosp Engn, Champaign, IL 61820 USA. RP Englander, JA (reprint author), NASA, Goddard Space Flight Ctr, Nav & Mission Design Branch, Greenbelt, MD 20771 USA. NR 38 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 1251 EP 1270 PN I-III PG 20 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200075 ER PT S AU Beeson, R Englander, JA Hughes, SP Schadegg, M AF Beeson, Ryne Englander, Jacob A. Hughes, Steven P. Schadegg, Maximilian BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI AN AUTOMATIC MEDIUM TO HIGH FIDELITY LOW-THRUST GLOBAL TRAJECTORY TOOL-CHAIN; EMTG-GMAT SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB Solving the global optimization, low-thrust, multiple-flyby interplanetary trajectory problem with high-fidelity dynamical models requires an unreasonable amount of computational resources. A better approach, and one that is demonstrated in this paper, is a multi-step process whereby the solution of the aforementioned problem is solved at a medium-fidelity and this solution is used as an initial guess for a higher-fidelity solver. The framework presented in this work uses two tools developed by NASA Goddard Space Flight Center (GSFC): the Evolutionary Mission Trajectory Generator (EMTG) and the General Mission Analysis Tool (GMAT). EMTG is a medium to medium-high fidelity low-thrust interplanetary global optimization solver, which now has the capability to automatically generate GMAT script files for seeding a high-fidelity solution using GMAT's local optimization capabilities. An overview of the analysis tools is presented along with a discussion of the autonomy of the tool-chain. Current capabilities are highlighted with increasingly difficult problems; the final problem being the recreation of the interplanetary trajectory for the DAWN mission. C1 [Beeson, Ryne] Univ Illinois, Aerosp Engn, 104 S Wright St, Urbana, IL 61801 USA. [Englander, Jacob A.; Hughes, Steven P.] NASA, Goddard Space Flight Ctr, Nav & Mission Design Branch, Greenbelt, MD 20771 USA. [Schadegg, Maximilian] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Beeson, R (reprint author), Univ Illinois, Aerosp Engn, 104 S Wright St, Urbana, IL 61801 USA. NR 18 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 1287 EP 1303 PN I-III PG 17 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200077 ER PT S AU Vavrina, MA Englander, JA Ghosh, AR AF Vavrina, Matthew A. Englander, Jacob A. Ghosh, Alexander R. BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI COUPLED LOW-THRUST TRAJECTORY AND SYSTEMS OPTIMIZATION VIA MULTI-OBJECTIVE HYBRID OPTIMAL CONTROL SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID ELECTRIC-PROPULSION; GENETIC ALGORITHM; MISSIONS; SPACECRAFT AB The optimization of low-thrust trajectories is tightly coupled with the spacecraft hardware. Trading trajectory characteristics with system parameters to identify viable solutions and determine mission sensitivities across discrete hardware configurations is labor intensive. Local, independent optimization runs can sample the design space, but a global exploration that resolves the relationships between the system variables across multiple objectives enables a full mapping of the optimal solution space. A multi-objective, hybrid optimal control algorithm is formulated using a multi-objective genetic algorithm as an outer-loop systems optimizer around a global trajectory optimizer. The coupled problem is solved simultaneously to generate Pareto-optimal solutions in a single execution. The automated approach is demonstrated on two interplanetary boulder return missions. C1 [Vavrina, Matthew A.] Ai Solut Inc, 10001 Derekwood Ln Suite 215, Lanham, MD 20706 USA. [Englander, Jacob A.] NASA, Goddard Space Flight Ctr, Nav & Mission Design Branch, Greenbelt, MD 20771 USA. [Ghosh, Alexander R.] Univ Illinois, Dept Aerosp Engn, Champaign, IL 61820 USA. RP Vavrina, MA (reprint author), Ai Solut Inc, 10001 Derekwood Ln Suite 215, Lanham, MD 20706 USA. NR 43 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 1321 EP 1340 PN I-III PG 20 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200079 ER PT S AU Reiter, JA Nicholas, AK Spencer, DB AF Reiter, Jason A. Nicholas, Austin K. Spencer, David B. BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI OPTIMIZATION OF MANY-REVOLUTION, ELECTRIC-PROPULSION TRAJECTORIES WITH ENGINE SHUTOFF CONSTRAINTS SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB Many-revolution, solar-electric-propulsion trajectories are difficult to computationally optimize. One of the most significant, unsolved problems with optimizing low-orbit trajectories using feedback control is eclipse constraints. Employing a new forward-looking feedback control technique, however, allows for an optimization of the trajectory including the effects of eclipses or any other arbitrary engine shutoff periods. The control law applies weightings to the optimal thrusting angles based on the spacecraft's relative instantaneous efficiency over one revolution, which includes the effect of the engine shutoffs. This method also facilitates simple exploration of the propellant versus time trade space in the presence of engine shutoff constraints. C1 [Reiter, Jason A.; Spencer, David B.] Penn State Univ, Dept Aerosp Engn, 229 Hammond Bldg, University Pk, PA 16802 USA. [Nicholas, Austin K.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Reiter, JA (reprint author), Penn State Univ, Dept Aerosp Engn, 229 Hammond Bldg, University Pk, PA 16802 USA. NR 3 TC 0 Z9 0 U1 1 U2 1 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 1721 EP 1734 PN I-III PG 14 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200105 ER PT S AU Thomas, ASW Ocampo, CA Landau, DF AF Thomas, Andrew S. W. Ocampo, Cesar A. Landau, Damon F. BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI A CREWED MARS EXPLORATION ARCHITECTURE USING FLY-BY AND RETURN TRAJECTORIES SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID MISSIONS AB Sustainable human Mars exploration strategies are presented that use Mars fly-by and return trajectories. Three mission models are considered that differ in the number of transit habitats and the type of fly-by and return trajectories used. Earth-Mars-Earth and Earth-Mars-Mars-Earth fly-by and return trajectories form the basis for these architectures. The strategies assume the existence and operation of the Space Launch System and the Orion spacecraft with no reliance or requirement for new technology development. The capability for hyperbolic rendezvous and complex orbital operations at Mars is needed. Advantages of the proposed strategies include, smaller transit habitats since they are only occupied for fractions of the overall mission time, lower propellant requirements since the interplanetary transit habitats need not be inserted into or taken out of Mars orbit, and some limited abort opportunities. The strategies can be used in a stair step approach that facilitates a logical sequence of fly-by, orbital, Mars moons or surface missions. Representative solutions and selected mission performance data are presented for missions in the 2020-2050 time frame bracketing 15 complete Earth-Mars synodic cycles. C1 [Thomas, Andrew S. W.] NASA, Explorat Branch, Astronaut Off, Johnson Space Ctr, 1120 NASA Pkwy, Houston, TX 77058 USA. [Ocampo, Cesar A.] Odyssey Space Res LLC, Houston, TX 77058 USA. [Landau, Damon F.] CALTECH, Jet Prop Lab, Project Syst Engn & Formulat, Pasadena, CA 91109 USA. RP Thomas, ASW (reprint author), NASA, Explorat Branch, Astronaut Off, Johnson Space Ctr, 1120 NASA Pkwy, Houston, TX 77058 USA. NR 24 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 1821 EP 1840 PN I-III PG 20 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200111 ER PT S AU Chappaz, L Broschart, SB Lantoine, G Howell, K AF Chappaz, Loic Broschart, Stephen B. Lantoine, Gregory Howell, Kathleen BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI ORBITAL PERTURBATION ANALYSIS NEAR BINARY ASTEROID SYSTEMS SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID DYNAMICS AB Current estimates indicate that approximately sixteen percent of the known near-Earth asteroid population may be binaries. Within the context of exploring the dynamical behavior of a spacecraft orbiting or moving near such systems, a first step in the analysis is an assessment of the perturbing effect that dominates the dynamics of the spacecraft. The relative strength of several perturbations, including the perturbation that arises from the existence of a binary system, rather than a single body system, is compared by exploiting 'zonal maps'. Such a map is useful in determining the type of orbit that is practical in support of a given mission scenario. C1 [Chappaz, Loic; Howell, Kathleen] Purdue Univ, Sch Aeronaut & Astronaut, 701 W Stadium Ave, W Lafayette, IN 47906 USA. [Broschart, Stephen B.; Lantoine, Gregory] CALTECH, Jet Prop Lab, Mission Design & Nav Sect, Pasadena, CA 91109 USA. RP Chappaz, L (reprint author), Purdue Univ, Sch Aeronaut & Astronaut, 701 W Stadium Ave, W Lafayette, IN 47906 USA. NR 16 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 1877 EP 1896 PN I-III PG 20 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200114 ER PT S AU Olson, C Russell, RP Bhaskaran, S AF Olson, Corwin Russell, Ryan P. Bhaskaran, Shyam BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI SPIN STATE ESTIMATION OF TUMBLING SMALL BODIES SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID EXPLORATION; POLYHEDRON; MISSION AB It is expected that a non-trivial percentage of small bodies that future missions may visit are tumbling in non-principal axis rotation. An Extended Kalman Filter (EKF) Simultaneous Localization and Mapping (SLAM) method is used to estimate the small body spin state with optical landmark measurements, as well-as the spacecraft position, velocity, attitude, and surface landmark locations. An example scenario based on the Rosetta mission is used, with a tumbling small body. The SLAM method proves effective, with order of magnitude decreases in the spacecraft and small body spin state errors after less than a quarter of the comet characterization phase. Initial small body angular velocity errors can be several times larger than the true rates, and the SLAM method will still converge (effectively having no apriori knowledge of the angular velocity). It is also observed that higher levels of tumbling in the small body increase the spin state angular velocity estimation errors and decrease the moments of inertia error, as expected. C1 [Olson, Corwin; Russell, Ryan P.] Univ Texas Austin, Dept Aerosp Engn & Engn Mech, 1 Univ Stn, Austin, TX 78712 USA. [Bhaskaran, Shyam] CALTECH, Jet Prop Lab, Mission Design & Nav Sect, Outer Planet Nav Grp, Pasadena, CA 91191 USA. RP Olson, C (reprint author), Univ Texas Austin, Dept Aerosp Engn & Engn Mech, 1 Univ Stn, Austin, TX 78712 USA. NR 32 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 1897 EP 1914 PN I-III PG 18 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200115 ER PT S AU Pavlak, TA Broschart, SB Lantoine, G AF Pavlak, Thomas A. Broschart, Stephen B. Lantoine, Gregory BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI QUANTIFYING MAPPING ORBIT PERFORMANCE IN THE VICINITY OF PRIMITIVE BODIES SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID SOLAR-RADIATION PRESSURE; SATELLITE DYNAMICS; TERMINATOR ORBITS; HAYABUSA; SPACECRAFT; ASTEROIDS AB Predicting and quantifying the capability of mapping orbits in the vicinity of primitive bodies is challenging given the complex orbit geometries that exist and the irregular shape of the bodies themselves. This paper employs various quantitative metrics to characterize the performance and relative effectiveness of various types of mapping orbits including terminator, quasi-terminator, hovering, ping-pong, and conic-like trajectories. Metrics of interest include surface area coverage, lighting conditions, and the variety of viewing angles achieved. The metrics discussed in this investigation are intended to enable mission designers and project stakeholders to better understand the implications of candidate mapping orbits during preliminary mission formulation activities. C1 [Pavlak, Thomas A.; Broschart, Stephen B.; Lantoine, Gregory] CALTECH, Jet Prop Lab, Mission Design & Nav Sect, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Pavlak, TA (reprint author), CALTECH, Jet Prop Lab, Mission Design & Nav Sect, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 24 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 1915 EP 1934 PN I-III PG 20 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200116 ER PT S AU Tardivel, S Scheeres, DJ AF Tardivel, Simon Scheeres, Daniel J. BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI ACCURATE DEPLOYMENT OF LANDERS TO DYNAMICALLY CHALLENGING ASTEROIDS SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm DE Asteroid; Astrodynamics; Lander AB This paper investigates the ballistic deployment of lenders to dynamically challenging asteroids, in the context of the current NASA Discovery mission proposal BASiX. Dynamically challenging asteroids are fast rotators, where the amended gravitational acceleration almost vanishes near the equator. In the studied architecture, a mothership flies-by the asteroid at high altitude and releases the lander on a ballistic trajectory towards its landing site. Given fixed constraints and GNC capabilities, the landing time and spread can be reduced manyfold with fine adjustments of the lander's orbit parameters such as the radius of periapse, the inclination, or the argument of periapse. C1 [Tardivel, Simon] CALTECH, Jet Prop Lab, M-S-1709,4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Scheeres, Daniel J.] Univ Colorado, Dept Aerosp Engn Sci, Boulder, CO 80309 USA. RP Tardivel, S (reprint author), CALTECH, Jet Prop Lab, M-S-1709,4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM simon.tardivel@jpl.nasa.gov; scheeres@colorado.edu NR 18 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 1935 EP 1954 PN I-III PG 20 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200117 ER PT S AU Lantukh, D Russell, RP Broschart, SB AF Lantukh, Demyan Russell, Ryan P. Broschart, Stephen B. BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI HELIOTROPIC ORBITS AT ASTEROIDS: ZONAL GRAVITY PERTURBATIONS AND APPLICATION AT BENNU SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID EVEN HARMONICS; SATELLITES; OBLATENESS; DENSITY; MOTION; DUST AB Analytical inclusion of high degree zonal gravity harmonics and solar radiation pressure enables heliotropic orbits to be found at irregular primitive bodies like Bennu, the target of the OSIRIS-REx mission. Heliotropic orbits provide long-lifetime, low-altitude orbits in the presence of these significant perturbations. Using a constrained, doubly-averaged disturbing potential in the Lagrange Planetary Equations yields inclined heliotropic orbits as well as a method for assessing the likelihood of a heliotropic orbit existing in an uncertain environment. The existence of heliotropic orbits is shown to be robust to uncertainty in the gravity parameters of a model of Bennu, and an example orbit shows how heliotropic orbits persist in the presence of other gravity perturbations as well. C1 [Lantukh, Demyan; Russell, Ryan P.] Univ Texas Austin, Dept Aerosp Engn & Engn Mech, Austin, TX 78712 USA. [Broschart, Stephen B.] CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Lantukh, D (reprint author), Univ Texas Austin, Dept Aerosp Engn & Engn Mech, Austin, TX 78712 USA. NR 21 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 1981 EP 1991 PN I-III PG 11 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200120 ER PT S AU Ellison, DH Conway, BA Englander, JA AF Ellison, Donald H. Conway, Bruce A. Englander, Jacob A. BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI NUMERICAL COMPUTATION OF A CONTINUOUS-THRUST STATE TRANSITION MATRIX INCORPORATING ACCURATE HARDWARE AND EPHEMERIS MODELS SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID GRAVITY-ASSIST TRAJECTORIES; ANALYTICAL GRADIENTS; OPTIMIZATION AB A significant body of work exists showing that providing a nonlinear programming (NLP) solver with analytical expressions for the problem constraint gradients substantially increases the speed of program execution and can also improve the robustness of convergence, especially for local optimizers. Calculation of these derivatives is often accomplished through the computation of the spacecraft's state transition matrix (STM). If the two-body gravitational model is employed, as is often done in the context of preliminary design, closed-form expressions for these derivatives may be provided. If a high-fidelity dynamics model, that might include perturbing forces such as the gravitational effects from multiple third bodies and solar radiation pressure, is used then these STM's must be computed numerically. We present a method for the numerical computation of the state transition matrix including analytical expressions for a state propagation matrix that incorporate an accurate spacecraft solar electric power hardware model and a full ephemeris model. An adaptive-step embedded eighth order Dormand-Prince numerical integrator is discussed and a method for the computation of the time of flight derivatives in this framework is presented. The use of these numerically calculated derivatives offer a substantial improvement over finite differencing in the context of a global optimizer. Specifically, the inclusion of these STM's into the low-thrust mission design tool chain in use at NASA Goddard Spaceflight Center allows for an increased preliminary mission design cadence. C1 [Ellison, Donald H.; Conway, Bruce A.] Univ Illinois, Dept Aerosp Engn, 104 South Wright St,Mail Code 236, Urbana, IL USA. [Englander, Jacob A.] NASA, Goddard Space Flight Ctr, Nav & Mission Design Branch, Washington, DC USA. RP Ellison, DH (reprint author), Univ Illinois, Dept Aerosp Engn, 104 South Wright St,Mail Code 236, Urbana, IL USA. NR 31 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 2393 EP 2412 PN I-III PG 20 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200145 ER PT S AU Folta, D Dichmann, D Clark, P Haapala, A Howell, K AF Folta, David Dichmann, Donald Clark, Pamela Haapala, Amanda Howell, Kathleen BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI LUNAR CUBE TRANSFER TRAJECTORY OPTIONS SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID DESIGN AB Numerous Earth-Moon trajectory and lunar orbit options are available for Cubesat missions. Given the limited Cubesat injection infrastructure, transfer trajectories are contingent upon the modification of an initial condition of the injected or deployed orbit. Additionally, these transfers can be restricted by the selection or designs of Cubesat subsystems such as propulsion or communication. Nonetheless, many trajectory options can be considered which have a wide range of transfer durations, fuel requirements, and final destinations. Our investigation of potential trajectories highlights several options including deployment from low Earth orbit (LEO), geostationary transfer orbits (GTO), and higher energy direct lunar transfers and the use of longer duration Earth-Moon dynamical systems. For missions with an intended lunar orbit, much of the design process is spent optimizing a ballistic capture while other science locations such as Sun-Earth libration or heliocentric orbits may simply require a reduced Delta-V imparted at a convenient location along the trajectory. C1 [Folta, David; Dichmann, Donald] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Clark, Pamela] Catholic Univ, Inst Astrophys & Computat Sci, Washington, DC 20064 USA. [Haapala, Amanda; Howell, Kathleen] Purdue Univ, Sch Aeronaut & Astronaut, W Lafayette, IN 47907 USA. RP Folta, D (reprint author), NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. NR 32 TC 0 Z9 0 U1 1 U2 1 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 2523 EP 2542 PN I-III PG 20 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200154 ER PT S AU Mortari, D de Dilectis, F Zanetti, R AF Mortari, Daniele de Dilectis, Francesco Zanetti, Renato BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI POSITION ESTIMATION USING IMAGE DERIVATIVE SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB This paper describes an image processing algorithm to process Moon and/or Earth images. The theory presented is based on the fact that Moon hard edge points are characterized by the highest values of the image derivative. Outliers are eliminated by two sequential filters. Moon center and radius are then estimated by nonlinear least-squares using circular sigmoid functions. The proposed image processing has been applied and validated using real and synthetic Moon images. C1 [Mortari, Daniele; de Dilectis, Francesco] Texas A&M Univ, Aerosp Engn, 746C HR Bright Bldg, College Stn, TX 77843 USA. [Zanetti, Renato] NASA, Lyndon B Johnson Space Ctr, Aerosci & Flight Mech Div, Houston, TX 77058 USA. RP Mortari, D (reprint author), Texas A&M Univ, Aerosp Engn, 746C HR Bright Bldg, College Stn, TX 77843 USA. EM MORTARI@TAMU.EDU; F.DE.DILECTIS@NEO.TAMU.EDU NR 6 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 2613 EP 2632 PN I-III PG 20 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200159 ER PT S AU Laing, J Myers, J Ward, D Lamb, R AF Laing, Jason Myers, Jessica Ward, Douglas Lamb, Rivers BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI OPERATIONAL CHALLENGES IN TDRS POST-MANEUVER ORBIT DETERMINATION SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB The GSFC Flight Dynamics Facility (FDF) is responsible for daily and post maneuver orbit determination for the Tracking and Data Relay Satellite System (TDRSS). The most stringent requirement for this orbit determination is 75 meters total position accuracy (3-sigma) predicted over one day for Terra's onboard navigation systems. To maintain an accurate solution onboard Terra, a solution is generated and provided by the FDF four hours after a TDRS maneuver. A number of factors present challenges to this support, such as maneuver prediction uncertainty and potentially unreliable tracking from User satellites. Reliable support is provided by comparing an Extended Kalman Filter (estimated using ODTK) against a Batch Least Squares system (estimated using GTDS). C1 [Laing, Jason; Myers, Jessica; Ward, Douglas] Omitron Inc, GSFC Flight Dynam Facil, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Lamb, Rivers] NASA, Goddard Space Flight Ctr, Flight Dynam Facil, Greenbelt, MD 20771 USA. RP Laing, J (reprint author), Omitron Inc, GSFC Flight Dynam Facil, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 2695 EP 2712 PN I-III PG 18 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200164 ER PT S AU Jones, D Lam, T Trawny, N Lee, C AF Jones, Drew Lam, Try Trawny, Nikolas Lee, Clifford BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI USING ONBOARD TELEMETRY FOR MAVEN ORBIT DETERMINATION SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID AEROBRAKING AB Determining the state of Mars orbiting spacecraft has traditionally been achieved using radiometric tracking data, often with data before and after an atmospheric drag pass. This paper describes our approach and results for supplementing radiometric observables with on-board telemetry measurements to improve the reconstructed trajectory estimate for the Mars Atmosphere and Volatile Evolution Mission (MAVEN). Uncertainties in Mars atmospheric models, combined with non-continuous tracking degrade navigation accuracy, making MAVEN a key candidate for using on-board telemetry data to help complement its orbit determination process. The successful demonstration of using telemetry data to improve the accuracy of ground based orbit determination could reduce cost (DSN tracking time) and enhance the performance of future NASA missions. In addition, it presents an important stepping stone to autonomous on-board aerobraking and aerocapture. C1 [Jones, Drew; Lam, Try; Trawny, Nikolas; Lee, Clifford] CALTECH, Jet Prop Lab, M-S 264-282,4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Jones, D (reprint author), CALTECH, Jet Prop Lab, M-S 264-282,4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM drew.r.jones@jpl.nasa.gov; try.lam@jpl.nasa.gov; nikolas.trawny@jpl.nasa.gov; clifford.lee@jpl.nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 2715 EP 2729 PN I-III PG 15 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200165 ER PT S AU Carpenter, JR Mashiku, AK AF Carpenter, J. Russell Mashiku, Alinda K. BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI CAUCHY DRAG ESTIMATION FOR LOW EARTH ORBITERS SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB Recent work on minimum variance estimators based on Cauchy distributions appears relevant to orbital drag estimation. Samples from Cauchy distributions, which are part of a class of heavy-tailed distributions, are characterized by long stretches of fairly small variation, punctuated by large variations that are many times larger than could be expected from a Gaussian. Such behavior can occur when solar storms perturb the atmosphere. In this context, the present work describes an embedding of the scalar Idan-Speyer Cauchy Estimator to estimate density corrections, within an Extended Kalman Filter that estimates the state of a low Earth orbiter. In contrast to the baseline Kalman approach, the larger formal errors of the present approach fully and conservatively bound the predictive error distribution, even in the face of unanticipated density disturbances of hundreds of percent. C1 [Carpenter, J. Russell; Mashiku, Alinda K.] NASA, Goddard Space Flight Ctr, Code 595, Greenbelt, MD 20771 USA. RP Carpenter, JR (reprint author), NASA, Goddard Space Flight Ctr, Code 595, Greenbelt, MD 20771 USA. NR 8 TC 1 Z9 1 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 2731 EP 2746 PN I-III PG 16 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200166 ER PT S AU Ely, TA Seubert, J AF Ely, Todd A. Seubert, Jill BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI ONE-WAY RADIOMETRIC NAVIGATION WITH THE DEEP SPACE ATOMIC CLOCK SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB The Deep Space Atomic Clock (DSAC) mission is developing a small mercury ion atomic clock with Allan deviation of less than le-14 at one day (current estimates similar to 3e-15) for a yearlong space demonstration in 2016. DSAC's stability yields one-way radiometric tracking data with better accuracy than current two-way tracking data and enables transitioning to more efficient and flexible one-way deep space navigation. This study discusses the potential for one-way radiometric navigation using DSAC, including those navigation uses that are immediately enabled, and those that require additional infrastructure and flight system development for full realization. C1 [Ely, Todd A.] CALTECH, Jet Prop Lab, Deep Space Atom Clock Technol Demonstrat Mission, MS 301-121,4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Seubert, Jill] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Ely, TA (reprint author), CALTECH, Jet Prop Lab, Deep Space Atom Clock Technol Demonstrat Mission, MS 301-121,4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Todd.A.Ely@jpl.nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 2799 EP 2816 PN I-III PG 18 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200170 ER PT S AU Kam, A Plice, L Galal, K Hawkins, A Policastri, L Loucks, M Carrico, J Nickel, C Lebois, R Sherman, R AF Kam, Arlen Plice, Laura Galal, Ken Hawkins, Alisa Policastri, Lisa Loucks, Michel Carrico, John, Jr. Nickel, Craig Lebois, Ryan Sherman, Ryan BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI LADEE FLIGHT DYNAMICS: OVERVIEW OF MISSION DESIGN AND OPERATIONS SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB The Lunar Atmosphere and Dust Environment Explorer (LADEE) mission set out on September 7, 2013 to observe the lunar exosphere at low altitudes. This mission overview from a flight dynamics perspective addresses solid rocket dispersions in the first use of the Minotaur V, science orbit maintenance for over 5 months, high precision past and predicted orbit estimation, the automated approach to calculating over 40,000 attitude waypoints, and strong teamwork at an intense operational pace. The unique flight dynamics solutions for the near-circular, near-equatorial orbit in non-uniform lunar gravity resulted in a successful mission from both engineering and scientific standpoints. C1 [Kam, Arlen] OneWeb, Toronto, ON, Canada. [Kam, Arlen] Stinger Ghaffarian Technol Inc, Houston, TX USA. [Plice, Laura] NASA, Ames Res Ctr, Metis Technol Solut, Moffett Field, CA 94035 USA. [Galal, Ken] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Hawkins, Alisa; Carrico, John, Jr.] Google Inc, Mountain View, CA USA. [Hawkins, Alisa] Aerosp Corp, Toronto, ON, Canada. [Policastri, Lisa; Carrico, John, Jr.; Nickel, Craig; Lebois, Ryan; Sherman, Ryan] Appl Def Solut, Columbia, MD USA. [Loucks, Michel] Space Explorat Engn Corp, Friday Harbor, WA USA. RP Kam, A (reprint author), OneWeb, Toronto, ON, Canada. EM akam@oneweb.net; alisahawkins@google.com; JCarrico@google.com NR 16 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 2835 EP 2853 PN I-III PG 19 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200172 ER PT S AU Galal, K Nickel, C Sherman, R AF Galal, Ken Nickel, Craig Sherman, Ryan BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI ATTITUDE DESIGN FOR THE LADEE MISSION SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB This paper summarizes attitude design and operations support provided to satisfy the numerous pointing requirements and constraints of the successfully completed LADEE mission. STK scripts used to automate the modeling of more than a dozen LADEE pointing profiles and a graphical tool used to design custom maneuver attitudes that satisfied communication and star tracker occlusions constraints are described. Also, provided is an overview of how a set of rules and conventions and long-term constraint violation predictions were used to establish keep-out time-frames for particular attitude profiles in order to manage the complexity of this design challenge. C1 [Galal, Ken] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Nickel, Craig; Sherman, Ryan] Appl Def Solut, Columbia, MD USA. RP Galal, K (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 2895 EP 2913 PN I-III PG 19 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200175 ER PT S AU Woodburn, J Policastri, L Owens, B AF Woodburn, James Policastri, Lisa Owens, Brandon BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI GENERATION OF SIMULATED TRACKING DATA FOR LADEE OPERATIONAL READINESS TESTING SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB Operational Readiness Tests were an important part of the pre-launch preparation for the LADEE mission. The generation of simulated tracking data to stress the Flight Dynamics System and the Flight Dynamics Team was important for satisfying the testing goal of demonstrating that the software and the team were ready to fly the operational mission. The simulated tracking was generated in a manner to incorporate the effects of errors in the baseline dynamical model, errors in maneuver execution and phenomenology associated with various tracking system based components. The ability of the mission team to overcome these challenges in a realistic flight dynamics scenario indicated that the team and Flight Dynamics System were ready to fly the LADEE mission. C1 [Woodburn, James] Analyt Graph Inc, 220 Valley Creek Blvd, Exton, PA 19341 USA. [Policastri, Lisa] Appl Def Solut, Columbia, MD 21044 USA. [Owens, Brandon] SGT Inc, NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Woodburn, J (reprint author), Analyt Graph Inc, 220 Valley Creek Blvd, Exton, PA 19341 USA. NR 13 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 2915 EP 2934 PN I-III PG 20 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200176 ER PT S AU Loucks, M Plice, L Cheke, D Maunder, C Reich, B AF Loucks, Michel Plice, Laura Cheke, Daniel Maunder, Cary Reich, Brian BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI TRADE STUDIES IN LADEE TRAJECTORY DESIGN SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB The Lunar Atmosphere and Dust Environment Explorer (LADEE) mission design challenge was a "design to capabilities" approach in a tightly constrained trade space. Several trade studies defined feasible trajectory designs and launch opportunities. One trade study selected the insertion orbit and identified usable combinations of transfer orbit plane and arrival nodes per launch block. The next trade study assessed each monthly launch period by day with three-sigma launch energy dispersions against several parameters including delta-v budget, lunar orbit beta angle, and maximum shadow duration. In the final trade study, detailed technical and operational considerations dictated the daily launch windows. C1 [Loucks, Michel] Space Explorat Engn Corp, 687 Chinook Way, Friday Harbor, WA 98250 USA. [Plice, Laura] NASA, Ames Res Ctr, Metis Technol Solut, Moffett Field, CA 94035 USA. [Cheke, Daniel; Maunder, Cary; Reich, Brian] Orbital Sci Corp, Minotaur V Launch Team, Chandler, AZ 85248 USA. RP Loucks, M (reprint author), Space Explorat Engn Corp, 687 Chinook Way, Friday Harbor, WA 98250 USA. EM loucks@see.com; laura.plice@nasa.goy NR 6 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 2935 EP 2954 PN I-III PG 20 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200177 ER PT S AU Loucks, M Plice, L Cheke, D Maunder, C Reich, B AF Loucks, Michel Plice, Laura Cheke, Daniel Maunder, Cary Reich, Brian BE Furfaro, R Cassotto, S Trask, A Zimmer, S TI THE LADEE TRAJECTORY AS FLOWN SO SPACEFLIGHT MECHANICS 2015, PTS I-III SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT 25th American-Astronautical-Society/American Institute of Aeronautics and Astronautics Space Flight Mechanics Meeting CY JAN 11-15, 2015 CL Williamsburg, VA SP Amer Astronaut Soc, Space Flight Mech Tech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB The LADEE spacecraft launched on a Minotaur-V launch vehicle from Wallops Flight Facility on 7 September 2013 at 3:27 UTC as planned into a 6.4 day orbit. After three cis-lunar phasing maneuvers, LADEE achieved lunar orbit on 6 October 2013, and entered a 232 x 247 km commissioning orbit on 13 October 2013. LADEE performed many successful maneuvers to execute the baseline science mission plus an extended mission through April of 2014. Final maneuvers executed in early April led to a planned lunar impact on 18 April 2014. C1 [Loucks, Michel] Space Explorat Engn Corp, 687 Chinook Way, Friday Harbor, WA 98250 USA. [Plice, Laura] NASA, Ames Res Ctr, Metis Technol Solut, Moffett Field, CA 94035 USA. [Cheke, Daniel; Maunder, Cary; Reich, Brian] Orbital Sci Corp, Minotaur V Launch Team, Chandler, AZ 85248 USA. RP Loucks, M (reprint author), Space Explorat Engn Corp, 687 Chinook Way, Friday Harbor, WA 98250 USA. EM loucks@see.com; laura.plice@nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-623-4 J9 ADV ASTRONAUT SCI PY 2015 VL 155 BP 2955 EP 2970 PN I-III PG 16 WC Engineering, Aerospace SC Engineering GA BE4FK UT WOS:000371647200178 ER PT S AU Arbabi, A Horie, Y Bagheri, M Faraon, A AF Arbabi, Amir Horie, Yu Bagheri, Mahmood Faraon, Andrei GP IEEE TI Simultaneous and Complete Control of Light Polarization and Phase using High Contrast Transmitarrays SO 2015 CONFERENCE ON LASERS AND ELECTRO-OPTICS (CLEO) SE Conference on Lasers and Electro-Optics LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics (CLEO) CY MAY 10-15, 2015 CL San Jose, CA AB We report an efficient dielectric metasurface platform for complete control over polarization and phase of light with subwavelength spatial resolution. Using this platform, we experimentally demonstrate polarization switchable phase holograms and vector beam generators. C1 [Arbabi, Amir; Horie, Yu; Faraon, Andrei] CALTECH, TJ Watson Lab Appl Phys, 1200 E Calif Blvd, Pasadena, CA 91125 USA. [Bagheri, Mahmood] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Arbabi, A (reprint author), CALTECH, TJ Watson Lab Appl Phys, 1200 E Calif Blvd, Pasadena, CA 91125 USA. EM amir@caltech.edu NR 5 TC 0 Z9 0 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2160-9020 BN 978-1-55752-968-8 J9 CONF LASER ELECTR PY 2015 PG 2 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BE3EW UT WOS:000370627102495 ER PT S AU Beyer, AD Briggs, RM Marsili, F Cohen, JD Meenehan, SM Painter, OJ Shaw, MD AF Beyer, Andrew D. Briggs, Ryan M. Marsili, Francesco Cohen, Justin D. Meenehan, Sean M. Painter, Oskar J. Shaw, Matthew D. GP IEEE TI Waveguide-Coupled Superconducting Nanowire Single-Photon Detectors SO 2015 CONFERENCE ON LASERS AND ELECTRO-OPTICS (CLEO) SE Conference on Lasers and Electro-Optics LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics (CLEO) CY MAY 10-15, 2015 CL San Jose, CA ID EFFICIENCY AB We have demonstrated WSi-based superconducting nanowire single-photon detectors coupled to SiNx waveguides with integrated ring resonators. This photonics platform enables the implementation of robust and efficient photon-counting detectors with fine spectral resolution near 1550 nm. C1 [Beyer, Andrew D.; Briggs, Ryan M.; Marsili, Francesco; Shaw, Matthew D.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Cohen, Justin D.; Meenehan, Sean M.; Painter, Oskar J.] CALTECH, Thomas J Watson Sr Lab Appl Phys, Pasadena, CA 91125 USA. RP Beyer, AD (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM andrew.d.beyer@jpl.nasa.gov NR 7 TC 0 Z9 0 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2160-9020 BN 978-1-55752-968-8 J9 CONF LASER ELECTR PY 2015 PG 2 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BE3EW UT WOS:000370627102113 ER PT S AU Borgentun, C Forouhar, S Frez, C Briggs, R Bagheri, M Fradet, M AF Borgentun, Carl Forouhar, Siamak Frez, Clifford Briggs, Ryan Bagheri, Mahmood Fradet, Mathieu GP IEEE TI Double-Ridge Interband Cascade Lasers for High-Power Spectroscopy in the Mid-Infrared SO 2015 CONFERENCE ON LASERS AND ELECTRO-OPTICS (CLEO) SE Conference on Lasers and Electro-Optics LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics (CLEO) CY MAY 10-15, 2015 CL San Jose, CA AB Lasers employing a new double-ridge waveguide design emit 18 mW at 3.57 mu m and 20 mW at 3.37 mu m. The top ridge confines the optical mode while the bottom ridge limits lateral current spreading. C1 [Borgentun, Carl; Forouhar, Siamak; Frez, Clifford; Briggs, Ryan; Bagheri, Mahmood; Fradet, Mathieu] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Borgentun, C (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM siamak.forouhar@jpl.nasa.gov NR 5 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2160-9020 BN 978-1-55752-968-8 J9 CONF LASER ELECTR PY 2015 PG 2 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BE3EW UT WOS:000370627102330 ER PT S AU Le Jeannic, H Huang, K Ruaudel, J Verma, VB Shaw, MD Marsili, F Nam, SW Wu, E Zeng, H Jeong, YC Filip, R Morin, O Laurat, J AF Le Jeannic, H. Huang, K. Ruaudel, J. Verma, V. B. Shaw, M. D. Marsili, F. Nam, S. W. Wu, E. Zeng, H. Jeong, Y. -C. Filip, R. Morin, O. Laurat, J. GP IEEE TI Efficient Optical Generation of Large-Amplitude Schrodinger Cat States with Minimal Resources SO 2015 CONFERENCE ON LASERS AND ELECTRO-OPTICS (CLEO) SE Conference on Lasers and Electro-Optics LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics (CLEO) CY MAY 10-15, 2015 CL San Jose, CA AB We demonstrate a protocol enabling the generation of large coherent state superpositions with unprecedented preparation rate. It is optimally using expensive non-Gaussian resources to build up only the core non-Gaussian part of the state. (C) 2015 Optical Society of America C1 [Le Jeannic, H.; Huang, K.; Ruaudel, J.; Jeong, Y. -C.; Morin, O.; Laurat, J.] ENS PSL Res Univ, UPMC Sorbonne Univ, CNRS, Lab Kastler Brossel,Coll France, 4 Pl Jussieu, F-75005 Paris, France. [Huang, K.; Wu, E.; Zeng, H.] E China Normal Univ, State Key Lab Precis Spect, Shanghai 200062, Peoples R China. [Verma, V. B.; Nam, S. W.] NIST, Boulder, CO 80305 USA. [Shaw, M. D.; Marsili, F.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. [Filip, R.] Palacky Univ, Dept Opt, Olomouc 77146, Czech Republic. RP Le Jeannic, H (reprint author), ENS PSL Res Univ, UPMC Sorbonne Univ, CNRS, Lab Kastler Brossel,Coll France, 4 Pl Jussieu, F-75005 Paris, France. EM hanna.lejeannic@lkb.upmc.fr NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2160-9020 BN 978-1-55752-968-8 J9 CONF LASER ELECTR PY 2015 PG 2 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BE3EW UT WOS:000370627103079 ER PT S AU Marsili, F Cunnane, DP Briggs, RM Beyer, AD Shaw, MD Karasik, BS Wolak, MA Acharya, N Xi, XX AF Marsili, Francesco Cunnane, Daniel P. Briggs, Ryan M. Beyer, Andrew D. Shaw, Matthew D. Karasik, Boris S. Wolak, M. A. Acharya, N. Xi, X. X. GP IEEE TI Superconducting Nanowire Detectors Based on MgB2 SO 2015 CONFERENCE ON LASERS AND ELECTRO-OPTICS (CLEO) SE Conference on Lasers and Electro-Optics LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics (CLEO) CY MAY 10-15, 2015 CL San Jose, CA AB We fabricated and characterized the optical response of MgB2 nanowires with critical temperature T-C = 33 K. The devices showed optical response at 4 K and sub-nanosecond relaxation time. The detectors responded to the simultaneous absorption of three photons, but not to single photons. C1 [Marsili, Francesco; Cunnane, Daniel P.; Briggs, Ryan M.; Beyer, Andrew D.; Shaw, Matthew D.; Karasik, Boris S.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Wolak, M. A.; Acharya, N.; Xi, X. X.] Temple Univ, Dept Phys, Philadelphia, PA 19122 USA. RP Marsili, F (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM francesco.marsili.dr@jpl.nasa.gov NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2160-9020 BN 978-1-55752-968-8 J9 CONF LASER ELECTR PY 2015 PG 2 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BE3EW UT WOS:000370627100161 ER PT S AU Murphy, RP Grein, ME Gudmundsen, TJ McCaughan, A Najafi, F Berggren, KK Marsili, F Dauler, EA AF Murphy, Ryan P. Grein, Matthew E. Gudmundsen, Theodore J. McCaughan, Adam Najafi, Faraz Berggren, Karl K. Marsili, Francesco Dauler, Eric A. GP IEEE TI Saturated Photon Detection Efficiency in NbN Superconducting Photon Detectors SO 2015 CONFERENCE ON LASERS AND ELECTRO-OPTICS (CLEO) SE Conference on Lasers and Electro-Optics LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics (CLEO) CY MAY 10-15, 2015 CL San Jose, CA AB In this work, we demonstrate saturated photon detection efficiency with narrow NbN nanowires and SNAPs to boost the signal-to-noise ratio, and we demonstrate a stabilizing choke inductance that is part of the optically-active area. C1 [Murphy, Ryan P.; Grein, Matthew E.; Gudmundsen, Theodore J.; Dauler, Eric A.] MIT, Lincoln Lab, 244 Wood St, Lexington, MA 02420 USA. [McCaughan, Adam; Najafi, Faraz; Berggren, Karl K.] MIT, Elect Res Lab, Cambridge, MA 02139 USA. [Marsili, Francesco] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Murphy, RP (reprint author), MIT, Lincoln Lab, 244 Wood St, Lexington, MA 02420 USA. EM ryan.murphy@ll.mit.edu NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2160-9020 BN 978-1-55752-968-8 J9 CONF LASER ELECTR PY 2015 PG 2 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BE3EW UT WOS:000370627100159 ER PT S AU Najafi, F Mower, J Harris, N Bellei, F Dane, A Lee, C Hu, X Mouradian, S Schroder, T Kharel, P Marsili, F Assefa, S Berggren, KK Englund, D AF Najafi, F. Mower, J. Harris, N. Bellei, F. Dane, A. Lee, C. Hu, X. Mouradian, S. Schroeder, T. Kharel, P. Marsili, F. Assefa, S. Berggren, K. K. Englund, D. GP IEEE TI Low-jitter single-photon detector arrays integrated with silicon and aluminum nitride photonic chips SO 2015 CONFERENCE ON LASERS AND ELECTRO-OPTICS (CLEO) SE Conference on Lasers and Electro-Optics LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics (CLEO) CY MAY 10-15, 2015 CL San Jose, CA AB We present progress on a scalable scheme for integration of single-photon detectors with silicon and aluminum nitride photonic circuits. We assemble arrays of low-jitter waveguideintegrated single-photon detectors and show up to 24% system detection efficiency. (C) 2015 Optical Society of America C1 [Najafi, F.; Mower, J.; Harris, N.; Bellei, F.; Dane, A.; Lee, C.; Hu, X.; Mouradian, S.; Schroeder, T.; Berggren, K. K.; Englund, D.] MIT, Elect Res Lab, 50 Vassar St, Cambridge, MA 02139 USA. [Kharel, P.] Columbia Univ, Dept Elect Engn, New York, NY 10027 USA. [Marsili, F.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. [Assefa, S.] IBM Corp, Thomas J Watson Res Ctr, Yorktown Hts, NY 10598 USA. RP Berggren, KK (reprint author), MIT, Elect Res Lab, 50 Vassar St, Cambridge, MA 02139 USA. EM berggren@mit.edu; englund@mit.edu NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2160-9020 BN 978-1-55752-968-8 J9 CONF LASER ELECTR PY 2015 PG 2 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BE3EW UT WOS:000370627100157 ER PT S AU Shaw, MD Marsili, F Beyer, AD Stern, JA Resta, GV Ravindran, P Chang, S Bardin, J Russell, DS Gin, JW Patawaran, FD Verma, VB Mirin, RP Nam, SW Farr, WH AF Shaw, M. D. Marsili, F. Beyer, A. D. Stern, J. A. Resta, G. V. Ravindran, P. Chang, S. Bardin, J. Russell, D. S. Gin, J. W. Patawaran, F. D. Verma, V. B. Mirin, R. P. Nam, S. W. Farr, W. H. GP IEEE TI Arrays of WSi Superconducting Nanowire Single Photon Detectors for Deep-Space Optical Communications SO 2015 CONFERENCE ON LASERS AND ELECTRO-OPTICS (CLEO) SE Conference on Lasers and Electro-Optics LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics (CLEO) CY MAY 10-15, 2015 CL San Jose, CA AB We have developed 64-pixel free-space-coupled arrays of WSi SNSPDs as a pathfinder for the ground detector in a deep-space optical communication system. Our receiver prototype was used to close a real-time deep-space optical communication link at 47 Mbps. C1 [Shaw, M. D.; Marsili, F.; Beyer, A. D.; Stern, J. A.; Resta, G. V.; Russell, D. S.; Gin, J. W.; Patawaran, F. D.; Farr, W. H.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Verma, V. B.; Mirin, R. P.; Nam, S. W.] NIST, Boulder, CO 80305 USA. [Ravindran, P.; Chang, S.; Bardin, J.] Univ Massachusetts, Amherst, MA 01003 USA. RP Shaw, MD (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM mattshaw@jpl.nasa.gov NR 4 TC 0 Z9 0 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2160-9020 BN 978-1-55752-968-8 J9 CONF LASER ELECTR PY 2015 PG 2 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BE3EW UT WOS:000370627101109 ER PT S AU Spuler, S Repasky, K Morley, B Moen, D Weckwerth, T Hayman, M Nehrir, A AF Spuler, Scott Repasky, Kevin Morley, Bruce Moen, Drew Weckwerth, Tammy Hayman, Matt Nehrir, Amin GP IEEE TI Advances in Diode-Laser-Based Lidar for Profiling Atmospheric Water Vapor SO 2015 CONFERENCE ON LASERS AND ELECTRO-OPTICS (CLEO) SE Conference on Lasers and Electro-Optics LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics (CLEO) CY MAY 10-15, 2015 CL San Jose, CA AB The design of an advanced diode laser based differential absorption lidar (DIAL) is discussed which is capable of measuring water vapor profiles over a wide range of atmospheric conditions. The instrument was field tested for 50 days and the results were compared to collocated instrumentation. (C) 2014 Optical Society of America C1 [Spuler, Scott; Morley, Bruce; Weckwerth, Tammy; Hayman, Matt] Natl Ctr Atmospher Res, Earth Observing Lab, POB 3000, Boulder, CO 80307 USA. [Repasky, Kevin; Moen, Drew] Montana State Univ, Elect & Comp Engn, Bozeman, MT 59717 USA. [Nehrir, Amin] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Spuler, S (reprint author), Natl Ctr Atmospher Res, Earth Observing Lab, POB 3000, Boulder, CO 80307 USA. EM spuler@ucar.edu NR 5 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2160-9020 BN 978-1-55752-968-8 J9 CONF LASER ELECTR PY 2015 PG 2 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BE3EW UT WOS:000370627100111 ER PT S AU Strekalov, DV AF Strekalov, Dmitry V. GP IEEE TI Nonlinear and Quantum Optics with Whispering Gallery Resonators SO 2015 CONFERENCE ON LASERS AND ELECTRO-OPTICS (CLEO) SE Conference on Lasers and Electro-Optics LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics (CLEO) CY MAY 10-15, 2015 CL San Jose, CA AB Whispering Gallery Mode resonators made from optically nonlinear crystals have small mode volume and extremely high quality factor which makes them ideal for various nonlinear conversion process at low power, ultimately at single photon level. (c) 2014 Optical Society of America C1 [Strekalov, Dmitry V.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Strekalov, DV (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM dmitry.v.strekalov@jpl.nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2160-9020 BN 978-1-55752-968-8 J9 CONF LASER ELECTR PY 2015 PG 2 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BE3EW UT WOS:000370627102340 ER PT S AU Jiang, H Hawkcs, EW Arutyunov, V Tims, J Fuller, C King, JP Seubert, C Chang, HL Parness, A Cutkosky, MR AF Jiang, Hao Hawkcs, Elliot W. Arutyunov, Vladimir Tims, Jacob Fuller, Christine King, Jonathan P. Seubert, Carl Chang, Herrick L. Parness, Aaron Cutkosky, Mark R. GP IEEE TI Scaling Controllable Adhesives to Grapple Floating Objects in Space SO 2015 IEEE INTERNATIONAL CONFERENCE ON ROBOTICS AND AUTOMATION (ICRA) SE IEEE International Conference on Robotics and Automation ICRA LA English DT Proceedings Paper CT IEEE International Conference on Robotics and Automation (ICRA) CY MAY 26-30, 2015 CL Seattle, WA SP IEEE AB As the number of rocket bodies and other debris in Earth's orbit increases, the need to capture and remove this space junk becomes essential to protect new satellites. A low cost solution may include gecko-inspired directional adhesives, which require almost no compressive preload to generate adhesion and are therefore suitable for surface grasping in space where objects are free floating. Current individual adhesive units with a pair of opposed pads achieve a limit of 13N normal to the surface. Instead of using a single large unit to generate high levels of adhesion, using multiple small gripper units is desirable to prevent single-point failures and to conform to higher curvatures. For this strategy to succeed, it is essential to distribute the overall force evenly, to minimize the overall preload normal to the surface, and to prevent local failures from propagating over the array. We present two load sharing mechanisms. The first uses nearly-constant force springs in parallel. The second uses a tendon and pulleys in series. Both allow a 4-unit gripper to maintain the same adhesive stress as a single unit. A normal adhesive load to compressive preload ratio of 100:1 is demonstrated. Zero gravity experiments and air bearing floor experiments demonstrate the gripper's functionality in a simulated space environment. Design considerations are discussed for further scaling, with the trade-offs among load sharing, suitability for different surfaces, and failure sensitivity. C1 [Jiang, Hao; Hawkcs, Elliot W.; Cutkosky, Mark R.] Stanford Univ, Dept Mech Engn, Stanford, CA 94305 USA. [Arutyunov, Vladimir; Tims, Jacob; Fuller, Christine; King, Jonathan P.; Seubert, Carl; Chang, Herrick L.; Parness, Aaron] CALTECH, Jet Prop Lab, NASA, Pasadena, CA 91109 USA. RP Jiang, H (reprint author), Stanford Univ, Dept Mech Engn, Stanford, CA 94305 USA. EM jianghao@stanford.edu; Aaron.Parness@jpl.nasa.gov NR 22 TC 3 Z9 3 U1 0 U2 2 PU IEEE COMPUTER SOC PI LOS ALAMITOS PA 10662 LOS VAQUEROS CIRCLE, PO BOX 3014, LOS ALAMITOS, CA 90720-1264 USA SN 1050-4729 BN 978-1-4799-6923-4 J9 IEEE INT CONF ROBOT PY 2015 BP 2828 EP 2835 PG 8 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic; Robotics SC Automation & Control Systems; Computer Science; Engineering; Robotics GA BE3MR UT WOS:000370974902124 ER PT S AU Sabelhaus, AP Bruce, J Caluwaerts, K Manovi, P Firoozi, RF Dobi, S Agogino, AM SunSpira, V AF Sabelhaus, Andrew P. Bruce, Jonathan Caluwaerts, Ken Manovi, Pavlo Firoozi, Roya Fallah Dobi, Sarah Agogino, Alice M. SunSpira, Vytas GP IEEE TI System Design and Locomotion of SUPERball, an Untethered Tensegrity Robot SO 2015 IEEE INTERNATIONAL CONFERENCE ON ROBOTICS AND AUTOMATION (ICRA) SE IEEE International Conference on Robotics and Automation ICRA LA English DT Proceedings Paper CT IEEE International Conference on Robotics and Automation (ICRA) CY MAY 26-30, 2015 CL Seattle, WA SP IEEE AB The Spherical Underactuated Planetary Exploration Robot ball (SUPERball) is an ongoing project within NASA Ames Research Center's Intelligent Robotics Group and the Dynamic Tensegrity Robotics Lab (DTRL). The current SUPERball is the first full prototype of this tensegrity robot platform, eventually destined for space exploration missions. This work, building on prior published discussions of individual components, presents the fully-constructed robot. Various design improvements are discussed, as well as testing results of the sensors and actuators that illustrate system performance. Basic low-level motor position controls are implemented and validated against sensor data, which show SUPERball to be uniquely suited for highly dynamic state trajectory tracking. Finally, SUPERball is shown in a simple example of locomotion. This implementation of a basic motion primitive shows SUPERball in untethered control. C1 [Sabelhaus, Andrew P.; Bruce, Jonathan; Caluwaerts, Ken; Manovi, Pavlo; Dobi, Sarah; SunSpira, Vytas] NASA, Ames Intelligent Robot Grp, Moffett Field, CA 94035 USA. [Sabelhaus, Andrew P.; Bruce, Jonathan; Caluwaerts, Ken; Manovi, Pavlo; Dobi, Sarah; SunSpira, Vytas] NASA, Dynam Tensegr Robot Lab, Moffett Field, CA 94035 USA. [Sabelhaus, Andrew P.; Firoozi, Roya Fallah; Dobi, Sarah; Agogino, Alice M.] Univ Calif Berkeley, Dept Mech Engn, Berkeley, CA 94720 USA. [Bruce, Jonathan; Manovi, Pavlo] Univ Calif Santa Cruz, Dept Comp Engn, Santa Cruz, CA 95064 USA. [Caluwaerts, Ken] Oak Ridge Associated Univ, Oak Ridge, TN 37830 USA. [Caluwaerts, Ken] Univ Ghent, Elect & Informat Syst Dept, B-9000 Ghent, Belgium. [SunSpira, Vytas] SGT Inc, Greenbelt, MD 20770 USA. RP Sabelhaus, AP (reprint author), NASA, Ames Intelligent Robot Grp, Moffett Field, CA 94035 USA. EM apsabelhaus@berkeley.edu; jbruce@soe.ucsc.edu; ken.caluwaerts@nasa.gov; pavlomanovi@soe.ucsc.edu; royafiroozi@berkeley.edu; sarahdobi@berkeley.edu; agogino@berkeley.edu; vytas.sunspiral@nasa.gov NR 23 TC 5 Z9 5 U1 0 U2 3 PU IEEE COMPUTER SOC PI LOS ALAMITOS PA 10662 LOS VAQUEROS CIRCLE, PO BOX 3014, LOS ALAMITOS, CA 90720-1264 USA SN 1050-4729 BN 978-1-4799-6923-4 J9 IEEE INT CONF ROBOT PY 2015 BP 2867 EP 2873 PG 7 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic; Robotics SC Automation & Control Systems; Computer Science; Engineering; Robotics GA BE3MR UT WOS:000370974902130 ER PT S AU Cunningham, C Nesnas, I Whittaker, WL AF Cunningham, Chris Nesnas, Issa Whittaker, William L. GP IEEE TI Terrain Traversability Prediction by Imaging Thermal Transients SO 2015 IEEE INTERNATIONAL CONFERENCE ON ROBOTICS AND AUTOMATION (ICRA) SE IEEE International Conference on Robotics and Automation ICRA LA English DT Proceedings Paper CT IEEE International Conference on Robotics and Automation (ICRA) CY MAY 26-30, 2015 CL Seattle, WA SP IEEE ID INERTIA AB The inability of current robotic perception techniques to adequately detect non-geometric terrain hazards is a primary cause of failure for robots operating in natural terrain on Mars, the Moon, and Earth. Classical approaches detect surface appearance but do not measure the underlying mechanical properties that determine wheel-terrain interaction. Diurnal temperature variations of a granular material, however, are strongly correlated with both its surface appearance and subsurface geophysical properties. This paper presents a technique for determining relative differences in looseness and traversability of granular terrain through analysis of thermal imagery. Terrain compaction and traversability are predicted by estimating a material's thermal inertia from observations of thermal transients. Results from a set of experiments in sandy terrain demonstrate the ability of this approach to differentiate between safe, compact and hazardous, loose terrain. C1 [Cunningham, Chris; Whittaker, William L.] Carnegie Mellon Univ, Inst Robot, Pittsburgh, PA 15213 USA. [Nesnas, Issa] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Cunningham, C (reprint author), Carnegie Mellon Univ, Inst Robot, Pittsburgh, PA 15213 USA. EM ccunningham@cmu.edu; issa.a.nesnas@jpl.nasa.gov; red@cmu.edu NR 25 TC 1 Z9 1 U1 0 U2 0 PU IEEE COMPUTER SOC PI LOS ALAMITOS PA 10662 LOS VAQUEROS CIRCLE, PO BOX 3014, LOS ALAMITOS, CA 90720-1264 USA SN 1050-4729 BN 978-1-4799-6923-4 J9 IEEE INT CONF ROBOT PY 2015 BP 3947 EP 3952 PG 6 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic; Robotics SC Automation & Control Systems; Computer Science; Engineering; Robotics GA BE3MR UT WOS:000370974903140 ER PT S AU Hebert, P Ma, J Borders, J Aydemir, A Bajracharya, M Hudson, N Shankar, K Karumanchi, S Douillard, B Burdick, J AF Hebert, Paul Ma, Jeremy Borders, James Aydemir, Alper Bajracharya, Max Hudson, Nicolas Shankar, Krishna Karumanchi, Sisir Douillard, Bertrand Burdick, Joel GP IEEE TI Supervised Remote Robot with Guided Autonomy and Teleoperation (SURROGATE): A Framework for Whole-Body Manipulation SO 2015 IEEE INTERNATIONAL CONFERENCE ON ROBOTICS AND AUTOMATION (ICRA) SE IEEE International Conference on Robotics and Automation ICRA LA English DT Proceedings Paper CT IEEE International Conference on Robotics and Automation (ICRA) CY MAY 26-30, 2015 CL Seattle, WA SP IEEE AB The use of the cognitive capabilties of humans to help guide the autonomy of robotics platforms in what is typically called "supervised-autonomy" is becoming more commonplace in robotics research. The work discussed in this paper presents an approach to a human-in-the-loop mode of robot operation that integrates high level human cognition and commanding with the intelligence and processing power of autonomous systems. Our framework for a " Supervised Remote Robot with Guided Autonomy and Teleoperation" (SURROGATE) is demonstrated on a robotic platform consisting of a pan-tilt perception head, two 7-DOF arms connected by a single 7-DOF torso, mounted on a tracked-wheel base. We present an architecture that allows high-level supervisory commands and intents to be specified by a user that are then interpreted by the robotic system to perform whole body manipulation tasks autonomously. We use a concept of "behaviors" to chain together sequences of "actions" for the robot to perform which is then executed real time. C1 [Hebert, Paul; Ma, Jeremy; Borders, James; Aydemir, Alper; Bajracharya, Max; Hudson, Nicolas; Karumanchi, Sisir; Douillard, Bertrand] CALTECH, Jet Prop Lab, Pasadena, CA USA. [Shankar, Krishna; Burdick, Joel] CALTECH, Pasadena, CA 91125 USA. RP Hebert, P (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA USA. NR 17 TC 1 Z9 1 U1 0 U2 0 PU IEEE COMPUTER SOC PI LOS ALAMITOS PA 10662 LOS VAQUEROS CIRCLE, PO BOX 3014, LOS ALAMITOS, CA 90720-1264 USA SN 1050-4729 BN 978-1-4799-6923-4 J9 IEEE INT CONF ROBOT PY 2015 BP 5509 EP 5516 PG 8 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic; Robotics SC Automation & Control Systems; Computer Science; Engineering; Robotics GA BE3MR UT WOS:000370974905066 ER PT S AU Hart, S Dinh, P Hambuchen, K AF Hart, Stephen Dinh, Paul Hambuchen, Kimberly GP IEEE TI The Affordance Template ROS Package for Robot Task Programming SO 2015 IEEE INTERNATIONAL CONFERENCE ON ROBOTICS AND AUTOMATION (ICRA) SE IEEE International Conference on Robotics and Automation ICRA LA English DT Proceedings Paper CT IEEE International Conference on Robotics and Automation (ICRA) CY MAY 26-30, 2015 CL Seattle, WA SP IEEE AB This paper introduces the Affordance Template ROS package for quickly programming, adjusting, and executing robot applications in the ROS RViz environment. This package extends the capabilities of RViz interactive markers [1] by allowing an operator to specify multiple end-effector waypoint locations and grasp poses in object-centric coordinate frames and to adjust these waypoints in order to meet the run-time demands of the task (specifically, object scale and location). The Affordance Template package stores task specifications in a robot-agnostic JSON description format such that it is trivial to apply a template to a new robot. As such, the Affordance Template package provides a robot-generic ROS tool appropriate for building semi-autonomous, manipulation-based applications. Affordance Templates were developed by the NASA-JSC DARPA Robotics Challenge (DRC) team and have since successfully been deployed on multiple platforms including the NASA Valkyrie and Robonaut 2 humanoids, the University of Texas Dreamer robot and the Willow Garage PR2. In this paper, the specification and implementation of the affordance template package is introduced and demonstrated through examples for wheel (valve) turning, pick-and-place, and drill grasping, evincing its utility and flexibility for a wide variety of robot applications. C1 [Hart, Stephen] TRACLabs Inc, Houston, TX 77058 USA. [Dinh, Paul] Oceaneering Space Syst, Houston, TX 77058 USA. [Hambuchen, Kimberly] NASA, Johnson Space Ctr, Houston, TX 77058 USA. RP Hart, S (reprint author), TRACLabs Inc, Houston, TX 77058 USA. EM swhart@traclabs.com; paul.dinh@nasa.gov; kimberly.a.hambuchen@nasa.gov NR 26 TC 5 Z9 5 U1 0 U2 0 PU IEEE COMPUTER SOC PI LOS ALAMITOS PA 10662 LOS VAQUEROS CIRCLE, PO BOX 3014, LOS ALAMITOS, CA 90720-1264 USA SN 1050-4729 BN 978-1-4799-6923-4 J9 IEEE INT CONF ROBOT PY 2015 BP 6227 EP 6234 PG 8 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic; Robotics SC Automation & Control Systems; Computer Science; Engineering; Robotics GA BE3MR UT WOS:000370974906025 ER PT B AU Shuping, RY Krzaczek, R Vacca, WD Charcos-Llorens, M Reach, WT Alles, R Clarke, M Melchiorri, R Radomski, J Shenoy, S Sandel, D Omelian, EB AF Shuping, R. Y. Krzaczek, R. Vacca, W. D. Charcos-Llorens, M. Reach, W. T. Alles, R. Clarke, M. Melchiorri, R. Radomski, J. Shenoy, S. Sandel, D. Omelian, E. B. BE Taylor, AR Rosolowsky, E TI Overview of the SOFIA Data Processing System: A Generalized System for Manual and Automatic Data Processing at the SOFIA Science Center SO ASTRONOMICAL DATA ANALYSIS SOFTWARE AND SYSTEMS: XXIV SE Astronomical Society of the Pacific Conference Series LA English DT Proceedings Paper CT 24th International Conference on Astronomical Data Analysis Software and Systems, ADASS XXIV CY OCT 05-09, 2014 CL Univ Calgary, Calgary, CANADA SP Anglo-Australian Observ, Cybera Inc, Univ Calgary, European Space Agcy, European So Observ, Infrared Process & Anal Ctr, Natl Opt Astron Observ, Smithsonian Astrophys Observ, Space Telescope Sci Inst HO Univ Calgary AB The Stratospheric Observatory for Infrared Astronomy (SOFIA) is an airborne astronomical observatory comprised of a 2.5-meter telescope mounted in the aft section of a Boeing 747SP aircraft. During routine operations, several instruments will be available to the astronomical community including cameras and spectrographs in the near- to far-IR. Raw data obtained in-flight require a significant amount of processing to correct for background emission (from both the telescope and atmosphere), remove instrumental artifacts, correct for atmospheric absorption, and apply both wavelength and flux calibration. In general, this processing is highly specific to the instrument and telescope. In order to maximize the scientific output of the observatory, the SOFIA Science Center must provide these post-processed data sets to Guest Investigators in a timely manner. To meet this requirement, we have designed and built the SOFIA Data Processing System (DPS): an in-house set of tools and services that can be used in both automatic ("pipeline") and manual modes to process data from a variety of instruments. Here we present an overview of the DPS concepts and architecture, as well as operational results from the first two SOFIA observing cycles (2013-2014). C1 [Shuping, R. Y.] Space Sci Inst, 4750 Walnut St,Suite 250, Boulder, CO 80301 USA. [Shuping, R. Y.; Krzaczek, R.; Vacca, W. D.; Charcos-Llorens, M.; Reach, W. T.; Alles, R.; Clarke, M.; Melchiorri, R.; Radomski, J.; Shenoy, S.; Sandel, D.] NASA, USRA SOFIA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Krzaczek, R.] Rochester Inst Technol, Carlson Ctr Imaging Sci, Rochester, NY 14623 USA. [Omelian, E. B.] NASA, Orbital Sci Corp, TSD, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Shuping, RY (reprint author), Space Sci Inst, 4750 Walnut St,Suite 250, Boulder, CO 80301 USA. EM rshuping@spacescience.org NR 2 TC 0 Z9 0 U1 0 U2 0 PU ASTRONOMICAL SOC PACIFIC PI SAN FRANCISCO PA 390 ASHTON AVE, SAN FRANCISCO, CA 94112 USA BN 978-1-58381-875-6; 978-1-58381-874-9 J9 ASTR SOC P PY 2015 VL 495 BP 351 EP 354 PG 4 WC Astronomy & Astrophysics; Computer Science, Information Systems; Computer Science, Interdisciplinary Applications SC Astronomy & Astrophysics; Computer Science GA BE3OY UT WOS:000371098000074 ER PT B AU Clarke, M Vacca, WD Shuping, RY AF Clarke, Melanie Vacca, William D. Shuping, Ralph Y. BE Taylor, AR Rosolowsky, E TI Redux: A Common Interface for SOFIA Data Reduction Pipelines SO ASTRONOMICAL DATA ANALYSIS SOFTWARE AND SYSTEMS: XXIV SE Astronomical Society of the Pacific Conference Series LA English DT Proceedings Paper CT 24th International Conference on Astronomical Data Analysis Software and Systems, ADASS XXIV CY OCT 05-09, 2014 CL Univ Calgary, Calgary, CANADA SP Anglo-Australian Observ, Cybera Inc, Univ Calgary, European Space Agcy, European So Observ, Infrared Process & Anal Ctr, Natl Opt Astron Observ, Smithsonian Astrophys Observ, Space Telescope Sci Inst HO Univ Calgary ID SPECTROGRAPH AB We have developed a common user interface for running the data reduction software for multiple instruments for the Stratospheric Observatory for Infrared Astronomy (SOFIA). This interface, called Redux, provides a GUI for processing the data from three instruments (EXES, FORCAST, and FLITECAM) in their various modes (imaging and spectroscopy), and is currently being adapted to run a fourth (HAWC+). Redux can also be run without the GUI, in order to automatically process data in a non-interactive pipeline mode. By separating the interface from the pipeline reduction algorithms, Redux provides a standardized means of controlling the pipelines. This shields the user from the diversity of the individual software packages and formats and simplifies code maintenance and re-use. Redux is now an important element in the SOFIA Data Processing System, an overview of which is given in Shuping et al. (2014). Here, we describe the design and development of Redux. C1 [Clarke, Melanie; Vacca, William D.] NASA, Univ Space Res Assoc, Ames Res Ctr, Moffett Field, CA 94035 USA. [Shuping, Ralph Y.] Space Sci Inst, Boulder, CO 80301 USA. RP Clarke, M (reprint author), NASA, Univ Space Res Assoc, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 10 TC 1 Z9 1 U1 0 U2 0 PU ASTRONOMICAL SOC PACIFIC PI SAN FRANCISCO PA 390 ASHTON AVE, SAN FRANCISCO, CA 94112 USA BN 978-1-58381-875-6; 978-1-58381-874-9 J9 ASTR SOC P PY 2015 VL 495 BP 355 EP 358 PG 4 WC Astronomy & Astrophysics; Computer Science, Information Systems; Computer Science, Interdisciplinary Applications SC Astronomy & Astrophysics; Computer Science GA BE3OY UT WOS:000371098000075 ER PT B AU Krzaczek, R Shuping, R Charcos-Llorens, M Alles, R Vacca, W AF Krzaczek, Robert Shuping, Ralph Charcos-Llorens, Miguel Alles, Rosemary Vacca, William BE Taylor, AR Rosolowsky, E TI Automated and Scalable Data Reduction in the SOFIA Data Processing System SO ASTRONOMICAL DATA ANALYSIS SOFTWARE AND SYSTEMS: XXIV SE Astronomical Society of the Pacific Conference Series LA English DT Proceedings Paper CT 24th International Conference on Astronomical Data Analysis Software and Systems, ADASS XXIV CY OCT 05-09, 2014 CL Univ Calgary, Calgary, CANADA SP Anglo-Australian Observ, Cybera Inc, Univ Calgary, European Space Agcy, European So Observ, Infrared Process & Anal Ctr, Natl Opt Astron Observ, Smithsonian Astrophys Observ, Space Telescope Sci Inst HO Univ Calgary AB In order to provide suitable data products to general investigators and other end users in a timely manner, the Stratospheric Observatory for Infrared Astronomy (SOFIA) has developed a framework supporting the automated execution of data processing pipelines for the various instruments, called the Data Processing System (DPS), see Shuping et al. (2014) for overview). The primary requirement is to process all data collected from a flight within eight hours, allowing data quality assessments and inspections to be made the following day. The raw data collected during a flight requires processing by a number of different software packages and tools unique to each combination of instrument and mode of operation, much of it developed in-house, in order to create data products for use by investigators and other end-users. The requirement to deliver these data products in a consistent, predictable, and performant manner presents a significant challenge for the observatory. Herein we present aspects of the DPS that help to achieve these goals. We discuss how it supports data reduction software written in a variety of languages and environments, its support for new versions and live upgrades to that software and other necessary resources (e.g., calibrations), its accommodation of sudden processing loads through the addition (and eventual removal) of computing resources, and close with an observation of the performance achieved in the first two observing cycles of SOFIA. C1 [Krzaczek, Robert] Rochester Inst Technol, Chester F Carlson Ctr Imaging Sci, 1 Lomb Mem Dr, Rochester, NY 14623 USA. [Shuping, Ralph] Space Sci Inst, Boulder, CO 80301 USA. [Charcos-Llorens, Miguel; Alles, Rosemary; Vacca, William] NASA, Univ Space Res Assoc, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Krzaczek, R (reprint author), Rochester Inst Technol, Chester F Carlson Ctr Imaging Sci, 1 Lomb Mem Dr, Rochester, NY 14623 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU ASTRONOMICAL SOC PACIFIC PI SAN FRANCISCO PA 390 ASHTON AVE, SAN FRANCISCO, CA 94112 USA BN 978-1-58381-875-6; 978-1-58381-874-9 J9 ASTR SOC P PY 2015 VL 495 BP 363 EP 366 PG 4 WC Astronomy & Astrophysics; Computer Science, Information Systems; Computer Science, Interdisciplinary Applications SC Astronomy & Astrophysics; Computer Science GA BE3OY UT WOS:000371098000077 ER EF