FN Thomson Reuters Web of Science™ VR 1.0 PT B AU Wolpert, DH MacLennan, BJ AF Wolpert, DH MacLennan, BJ BE Wang, PP TI A computationally universal field computer that is purely linear SO PROCEEDINGS OF THE FIFTH JOINT CONFERENCE ON INFORMATION SCIENCES, VOLS 1 AND 2 LA English DT Proceedings Paper CT 5th Joint Conference on Information Sciences (JCIS 2000) CY FEB 27-MAR 03, 2000 CL ATLANTIC CITY, NJ SP Assoc Intelligent Machinery, Machine Intelligent & Fussy Log Lab, Elsevier Publishing Co, Inc, Informat Sci Journal, USA Res Off AB A field computer is a (spatial) continuum-limit neural net (MacLennan 1987). We investigate field computers whose temporal dynamics is also continuum-limit, being governed by an integro-differential equation. We prove that even when they are purely linear, such systems are computationally universal. The "trick" used to get such universal (and therefore in general nonlinear) behavior is quite similar to the way nonlinear macroscopic physics arises from the purely linear microscopic physics of Schrodinger's equation: one interprets the system in a non-linear way. In this paper, we show that simply using a unary code for the interpretation suffices. See Wolpert and MacLennan (1993) for full details and additional material. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Wolpert, DH (reprint author), NASA, Ames Res Ctr, MS 269-1, Moffett Field, CA 94035 USA. NR 2 TC 0 Z9 0 U1 1 U2 1 PU ASSOC INTELLIGENT MACHINERY PI DURHAM PA PO BOX 90291, DURHAM, NC 27708-0291 USA BN 0-9643456-9-2 PY 2000 BP 782 EP 785 PG 4 WC Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BV66Q UT WOS:000179698300193 ER PT B AU Mack, M Lapir, GM Berkovich, S AF Mack, M Lapir, GM Berkovich, S BE Wang, PP TI Approximate matching as a key technique in organization of natural and artificial intelligence SO PROCEEDINGS OF THE FIFTH JOINT CONFERENCE ON INFORMATION SCIENCES, VOLS 1 AND 2 LA English DT Proceedings Paper CT 5th Joint Conference on Information Sciences (JCIS 2000) CY FEB 27-MAR 03, 2000 CL ATLANTIC CITY, NJ SP Assoc Intelligent Machinery, Machine Intelligent & Fussy Log Lab, Elsevier Publishing Co, Inc, Informat Sci Journal, USA Res Off C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Mack, M (reprint author), NASA, Goddard Space Flight Ctr, Code 585,Code 933, Greenbelt, MD 20771 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU ASSOC INTELLIGENT MACHINERY PI DURHAM PA PO BOX 90291, DURHAM, NC 27708-0291 USA BN 0-9643456-9-2 PY 2000 BP 851 EP 854 PG 4 WC Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BV66Q UT WOS:000179698300212 ER PT B AU Zak, M AF Zak, M BE Wang, PP TI Reflexive biodynamics for immune inspired computing SO PROCEEDINGS OF THE FIFTH JOINT CONFERENCE ON INFORMATION SCIENCES, VOLS 1 AND 2 LA English DT Proceedings Paper CT 5th Joint Conference on Information Sciences (JCIS 2000) CY FEB 27-MAR 03, 2000 CL ATLANTIC CITY, NJ SP Assoc Intelligent Machinery, Machine Intelligent & Fussy Log Lab, Elsevier Publishing Co, Inc, Informat Sci Journal, USA Res Off C1 CALTECH, Jet Prop Lab, Ultracomp Grp, Pasadena, CA 91105 USA. RP Zak, M (reprint author), CALTECH, Jet Prop Lab, Ultracomp Grp, M-S 126-347, Pasadena, CA 91105 USA. NR 9 TC 0 Z9 0 U1 0 U2 0 PU ASSOC INTELLIGENT MACHINERY PI DURHAM PA PO BOX 90291, DURHAM, NC 27708-0291 USA BN 0-9643456-9-2 PY 2000 BP 920 EP 922 PG 3 WC Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BV66Q UT WOS:000179698300230 ER PT B AU Bellutta, P Manduchi, R Matthies, L Owens, K Rankin, A AF Bellutta, P Manduchi, R Matthies, L Owens, K Rankin, A GP IEEE IEEE TI Terrain perception for DEMO III SO PROCEEDINGS OF THE IEEE INTELLIGENT VEHICLES SYMPOSIUM 2000 LA English DT Proceedings Paper CT IEEE Intelligent Vehicles Symposium CY OCT 03-05, 2000 CL DEARBORN, MI SP IEEE, IEEE, Intelligent Transportat Syst Council DE autonomous navigation; obstacle detection; stereo vision; color classification AB The Demo III program has as ifs primary focus the development of autonomous mobility for a smalt rugged cross country vehicle. Enabling vision based terrain perception technology classification of scene geometry and material is currently under development at JPL. In this paper we report recent progress on both stereo-based obstacle detection and terrain cover color-based classification. Our experiments show that the integration of geometric description and ter rain cover characterization may be the key to enabling successful autonomous navigation in cross-country vegetated terrain. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM bellutta@telerobotics.jpl.nasa.gov; manduchi@telerobotics.jpl.nasa.gov; lhm@telerobotics.jpl.nasa.gov; kowens@telerobotics.jpl.nasa.gov; arankin@telerobotics.jpl.nasa.gov NR 7 TC 38 Z9 46 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 0-7803-6363-9 PY 2000 BP 326 EP 331 DI 10.1109/IVS.2000.898363 PG 6 WC Engineering, Electrical & Electronic; Transportation Science & Technology SC Engineering; Transportation GA BR43P UT WOS:000166402100056 ER PT B AU Filman, RE Lee, DD AF Filman, RE Lee, DD BE Arabnia, HR TI Managing distributed systems with smart subscriptions SO PROCEEDINGS OF THE INTERNATIONAL CONFERENCE ON PARALLEL AND DISTRIBUTED PROCESSING TECHNIQUES AND APPLICATIONS, VOLS I-V LA English DT Proceedings Paper CT International Conference on Parallel and Distributed Processing Techniques and Applications (PDPTA 2000) CY JUN 26-29, 2000 CL LAS VEGAS, NV SP Comp Sci Res, Educ & Applicat Press, Informat Processing Soc Japan, SIGMPS, Int Technol Inst, Java High Performance Comp Res Grp, Korea Informat Processing Soc, World Sci & Engn Soc DE publish-and-subscribe; events; managing distributed applications; subscription languages; event channels; event matching algorithms AB We describe an event-based, publish-and-subscribe system based on using "smart subscriptions" to recognize weakly structured events. We present a hierarchy of subscription languages (propositional, predicate, temporal and agent) of increasing expressability and computational complexity, and several algorithms (Sig, Memo, Lattice, Compile and RETE) for efficiently recognizing event matches. We have applied this system to implementing and managing distributed applications. C1 NASA, Adv Comp Sci Res Inst, Ames Res Ctr, Moffett Field, CA 94305 USA. RP Filman, RE (reprint author), NASA, Adv Comp Sci Res Inst, Ames Res Ctr, Mail Stop 269-1, Moffett Field, CA 94305 USA. NR 14 TC 0 Z9 0 U1 0 U2 0 PU C S R E A PRESS PI ATHENS PA 115 AVALON DR, ATHENS, GA 30606 USA BN 1-892512-52-1 PY 2000 BP 853 EP 859 PG 7 WC Computer Science, Hardware & Architecture; Computer Science, Information Systems; Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BR82C UT WOS:000167676300116 ER PT S AU Lindner, JL Gilbert, JA AF Lindner, JL Gilbert, JA GP SEM SEM TI A panoramic system for vibration analysis SO PROCEEDINGS OF THE SEM IX INTERNATIONAL CONGRESS ON EXPERIMENTAL MECHANICS SE PROCEEDINGS OF THE INTERNATIONAL CONGRESS ON EXPERIMENTAL MECHANICS LA English DT Proceedings Paper CT SEM 9th International Congress on Experimental Mechanics CY JUN 05-08, 2000 CL ORLANDO, FL SP British Soc Strain Measurement, Chinese Soc Mech Engineers, Japan Soc Mech Engineers Mat & Mech Div, Machinery Failure Pervent Technol Soc, Korean Soc, Mech Engineers, Mat & Fracture Div, SEM Republic China Local Sect, Shock & Vibrat Informat Analy Ctr, strain Soc South Africa AB This paper describes a method for capturing time-average holograms using a panoramic imaging system. It includes the development of the phase-displacement relation required to analyze the interference fringe patterns, and a discussion of the modulation in the sensitivity vector across the inner walls of an aluminum ring and a turbopump liner. C1 NASA, George C Marshall Space Flight Ctr, Struct & Dynam Lab, Huntsville, AL 35812 USA. RP Lindner, JL (reprint author), NASA, George C Marshall Space Flight Ctr, Struct & Dynam Lab, Huntsville, AL 35812 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU SOC EXPERIMENTAL MECHANICS INC PI BETHEL PA 7 SCHOOL ST, BETHEL, CT 06801 USA SN 1046-672X BN 0-91205-369-0 J9 P INT CONG EXPERIT M PY 2000 BP 26 EP 29 PG 2 WC Engineering, Mechanical; Mechanics; Physics, Applied SC Engineering; Mechanics; Physics GA BU51C UT WOS:000176203100008 ER PT S AU Reeder, JR Glaessgen, EH AF Reeder, JR Glaessgen, EH GP SEM SEM TI Debouding of stitched composite joints under fatigue loading SO PROCEEDINGS OF THE SEM IX INTERNATIONAL CONGRESS ON EXPERIMENTAL MECHANICS SE PROCEEDINGS OF THE INTERNATIONAL CONGRESS ON EXPERIMENTAL MECHANICS LA English DT Proceedings Paper CT SEM 9th International Congress on Experimental Mechanics CY JUN 05-08, 2000 CL ORLANDO, FL SP British Soc Strain Measurement, Chinese Soc Mech Engineers, Japan Soc Mech Engineers Mat & Mech Div, Machinery Failure Pervent Technol Soc, Korean Soc, Mech Engineers, Mat & Fracture Div, SEM Republic China Local Sect, Shock & Vibrat Informat Analy Ctr, strain Soc South Africa AB The effect of stitches on the fatigue failure of a single lap joint configuration has been investigated. The experimental study investigated two different lengths of lap joints when subjected to fatigue loading at 70% of the static ultimate load. The number of cycles to failure of both the stitched and unstitched specimens where about the same for the two cases. This shows that an observed factor of 2.6 increase in static strength translated into similar increase in load for a given number of cycles to failure. Additionally, stitching significantly changed the pattern of damage growth to failure. X-rays taken periodically during the fatigue tests indicate that the stitches do an effective job of slowing debond growth. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Reeder, JR (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU SOC EXPERIMENTAL MECHANICS INC PI BETHEL PA 7 SCHOOL ST, BETHEL, CT 06801 USA SN 1046-672X BN 0-91205-369-0 J9 P INT CONG EXPERIT M PY 2000 BP 187 EP 190 PG 4 WC Engineering, Mechanical; Mechanics; Physics, Applied SC Engineering; Mechanics; Physics GA BU51C UT WOS:000176203100051 ER PT S AU Swanson, GR Arakere, NK AF Swanson, GR Arakere, NK GP SEM SEM TI Fatigue failure of space shuttle main engine turbine blades SO PROCEEDINGS OF THE SEM IX INTERNATIONAL CONGRESS ON EXPERIMENTAL MECHANICS SE PROCEEDINGS OF THE INTERNATIONAL CONGRESS ON EXPERIMENTAL MECHANICS LA English DT Proceedings Paper CT SEM 9th International Congress on Experimental Mechanics CY JUN 05-08, 2000 CL ORLANDO, FL SP British Soc Strain Measurement, Chinese Soc Mech Engineers, Japan Soc Mech Engineers Mat & Mech Div, Machinery Failure Pervent Technol Soc, Korean Soc, Mech Engineers, Mat & Fracture Div, SEM Republic China Local Sect, Shock & Vibrat Informat Analy Ctr, strain Soc South Africa AB Experimental validation of finite element modeling of single crystal turbine blades is presented. Experimental results from uniaxial high cycle fatigue (HCF) test specimens and full scale Space Shuttle Main Engine test firings with the High Pressure Fuel Turbopump Alternate Turbopump (HPFTP/AT) provide the data used for the validation. The conclusions show the significant contribution of the crystal orientation within the blade on the resulting life of the component, that the analysis can predict this variation, and that experimental testing demonstrates it. C1 NASA, George C Marshall Space Flight Ctr, Struct Mech Team, Huntsville, AL 35812 USA. RP Swanson, GR (reprint author), NASA, George C Marshall Space Flight Ctr, Struct Mech Team, ED22, Huntsville, AL 35812 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU SOC EXPERIMENTAL MECHANICS INC PI BETHEL PA 7 SCHOOL ST, BETHEL, CT 06801 USA SN 1046-672X BN 0-91205-369-0 J9 P INT CONG EXPERIT M PY 2000 BP 492 EP 495 PG 4 WC Engineering, Mechanical; Mechanics; Physics, Applied SC Engineering; Mechanics; Physics GA BU51C UT WOS:000176203100134 ER PT B AU Singleterry, RC Thibeault, SA AF Singleterry, RC Thibeault, SA GP ANS ANS TI Air and spacecraft shielding materials optimization analysis SO PROCEEDINGS OF THE TOPICAL MEETING ON RADIATION PROTECTION FOR OUR NATIONAL PRIORITIES: MEDICINE, THE ENVIRONMENT, AND THE LEGACY LA English DT Proceedings Paper CT 6th Radiation Protection and Shielding Topical Conference CY SEP 17-21, 2000 CL SPOKANE, WA SP Amer Nucl Soc, Radiat Protect & Shield Div, Hlth Phys Soc Columbia Chapter AB Various candidate aircraft and spacecraft materials were analyzed and compared in a simulated solar proton event using the High-energy Monte Carlo N-Particle transport code (MCNPX) with an maximum energy to 3 GeV. Some of the materials have been tested in particle beams, and others seemed reasonable to analyze in this manner before deciding to test them. The two metal alloys analyzed are actual materials being designed into or used in aircraft and spacecraft today. The aluminum alloy in most simulated vehicle layups produced excess neutrons over polymer based materials that are reflected back into the environment, which for aircraft is of little importance, but for habitats and spacecraft where extravehicular activities occur, can pose an increased risk to astronauts of radiation induced illness or cancers. The extent of this risk needs to be investigated further. The transmission properties of these layups were not as dramatic for aluminum alloy based layups, but the polymer based layups consistently transmit fewer neutrons than the aluminum based layups. These results must be considered in any design of an aircraft, spacecraft, or habitat. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Singleterry, RC (reprint author), NASA, Langley Res Ctr, Mail Stop 188B,8 W Taylor St, Hampton, VA 23681 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU AMER NUCLEAR SOC PI LA GRANGE PARK PA 555 N KENSINGTON AVE, LA GRANGE PARK, IL 60525 USA BN 0-89448-649-7 PY 2000 BP 478 EP 486 PG 5 WC Environmental Sciences; Nuclear Science & Technology SC Environmental Sciences & Ecology; Nuclear Science & Technology GA BT24D UT WOS:000172402600070 ER PT J AU Holst, TL AF Holst, TL TI Transonic flow computations using nonlinear potential methods SO PROGRESS IN AEROSPACE SCIENCES LA English DT Review ID APPROXIMATE-FACTORIZATION SCHEMES; MULTIOBJECTIVE GENETIC ALGORITHM; AERODYNAMIC SHAPE DESIGN; SMALL-DISTURBANCE THEORY; FINITE-ELEMENT METHOD; AIRCRAFT CONFIGURATIONS; FLUID-DYNAMICS; ROTOR FLOWS; WING-DESIGN; FREE-WAKE AB This presentation describes the state of transonic flow simulation using nonlinear potential methods for external-aerodynamic applications. The presentation begins with a review of the various potential equation forms (with emphasis on the full potential equation) and includes a discussion of pertinent mathematical characteristics and all derivation assumptions. Impact of the derivation assumptions on simulation accuracy, especially with respect to shock wave capture, is discussed. Key characteristics of all numerical algorithm types used for solving nonlinear potential equations, including steady, unsteady, space marching, and design methods, are described. Both spatial discretization and iteration scheme characteristics are examined. Numerical results for various aerodynamic applications are included throughout the presentation to highlight key discussion points. The presentation ends with concluding remarks and recommendations for future work. Overall, nonlinear potential solvers are efficient, highly developed and routinely used in the aerodynamic design environment for cruise conditions. Published by Elsevier Science Ltd. All rights reserved. C1 NASA, Ames Res Ctr, Computat Phys & Simulat Branch, Moffett Field, CA 94035 USA. RP NASA, Ames Res Ctr, Computat Phys & Simulat Branch, Mail Stop T27B-1, Moffett Field, CA 94035 USA. EM tholst@mail.arc.nasa.gov NR 386 TC 14 Z9 15 U1 0 U2 7 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0376-0421 J9 PROG AEROSP SCI JI Prog. Aeosp. Sci. PD JAN PY 2000 VL 36 IS 1 BP 1 EP 61 DI 10.1016/S0376-0421(99)00010-X PG 61 WC Engineering, Aerospace SC Engineering GA 285KQ UT WOS:000085388600001 ER PT J AU Kalkhoran, IM Smart, MK AF Kalkhoran, IM Smart, MK TI Aspects of shock wave-induced vortex breakdown SO PROGRESS IN AEROSPACE SCIENCES LA English DT Review ID WING-TIP VORTICES; NUMERICAL-SIMULATION; MACH-3 STREAM; OBLIQUE; DISTORTION; MODEL AB In this article, we discuss supersonic vortex breakdown when sufficiently strong streamwise vortices encounter otherwise planar, normal and oblique shock fronts as well as solid surfaces placed in their passages. The dramatic destruction of a streamwise vortex during supersonic vortex interactions reveals a vortex breakdown similar in many ways to the well-documented incompressible vortex bursting. The main features of supersonic vortex breakdown include formation of a spherically blunt-nosed conical shock, and a vortex core, which upon crossing the apex of the conical shock expands into a subsonic turbulent conical region. A notable characteristic of the supersonic vortex breakdown is the formation of an entropy-shear layer separating an inner subsonic zone containing the burst structure from the surrounding supersonic flow. Numerical, experimental, and analytical studies of shuck wave/vortex interactions are discussed and results from wind tunnel studies involving head-on collision of supersonic vortices with solid surfaces are presented. (C) 2000 Elsevier Science Ltd. All rights reserved. C1 Polytech Univ, Dept Mech Aerosp & Mfg Engn, Brooklyn, NY 11201 USA. NASA, Langley Res Ctr, Hyperson Airbreathing Prop Branch, Hampton, VA 23681 USA. RP Kalkhoran, IM (reprint author), Polytech Univ, Dept Mech Aerosp & Mfg Engn, 6 Metrotech Ctr, Brooklyn, NY 11201 USA. RI Smart, Michael/C-8823-2013 NR 36 TC 19 Z9 23 U1 0 U2 2 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0376-0421 J9 PROG AEROSP SCI JI Prog. Aeosp. Sci. PD JAN PY 2000 VL 36 IS 1 BP 63 EP 95 DI 10.1016/S0376-0421(99)00011-1 PG 33 WC Engineering, Aerospace SC Engineering GA 285KQ UT WOS:000085388600002 ER PT J AU Bellan, J AF Bellan, J TI Supercritical (and subcritical) fluid behavior and modeling: drops, streams, shear and mixing layers, jets and sprays SO PROGRESS IN ENERGY AND COMBUSTION SCIENCE LA English DT Article; Proceedings Paper CT 1st Mediterranean Combustion Symposium (MCS-99) CY JUN 20-25, 1999 CL ANTALYA, TURKEY SP Combust Inst, Int Ctr Heat & Mass Transfer DE supercritical fluids; fluid behavior at high pressure; microgravity drop experiments ID ROCKET CHAMBER PRESSURES; LOX DROPLET; VAPORIZATION; COMBUSTION; HYDROGEN; ENVIRONMENTS; EVAPORATION; FUELS; HEAT AB A critical review of recent investigations in the realm of supercritical (and subcritical) fluid behavior is presented with the goal of obtaining a perspective on the peculiarities of high pressure observations. Experiments with drops, isolated or in groups, streams, shear and mixing layers, jets and sprays are tabulated and discussed as a precursor to forming a conceptual picture of fluid comportment, The physics of fluid behavior in the supercritical and subcritical regimes is discussed, and major differences between the observations in these two regimes are identified and explained. A variety of supercritical fluid models is then examined in the context of drop studies, and salient aspects of fluid behavior are identified. In particular, a model that has been validated with microgravity drop experiments is described and summarized; in this validated model, the differences in subcritical/supercritical comportment are interpreted in terms of lengths scales and it is this difference that is responsible for the traditional Lewis number expression no longer portraying the ratio of heat to mass transfer in supercritical fluids; instead, an effective Lewis number is recommended that gives a realistic estimate of the ratio of these length scales. Furthermore, the application of various fluid models to the description of supercritical fluid in various geometric configurations is discussed for conditions relevant to liquid rocket, Diesel and gas turbine engines. Such preliminary simulations performed with the validated fluid model have already reproduced some specific experimental features of supercritical fluid jet disintegration. Finally, comments are offered regarding future areas of research. Published by Elsevier Science Ltd. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Bellan, J (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS125-109, Pasadena, CA 91109 USA. NR 100 TC 106 Z9 111 U1 4 U2 31 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0360-1285 J9 PROG ENERG COMBUST JI Prog. Energy Combust. Sci. PY 2000 VL 26 IS 4-6 BP 329 EP 366 DI 10.1016/S0360-1285(00)00008-3 PG 38 WC Thermodynamics; Energy & Fuels; Engineering, Chemical; Engineering, Mechanical SC Thermodynamics; Energy & Fuels; Engineering GA 341AM UT WOS:000088568900003 ER PT J AU Aiken, J Rees, N Hooker, S Holligan, P Bale, A Robins, D Moore, G Harris, R Pilgrim, D AF Aiken, J Rees, N Hooker, S Holligan, P Bale, A Robins, D Moore, G Harris, R Pilgrim, D TI The Atlantic Meridional Transect: overview and synthesis of data SO PROGRESS IN OCEANOGRAPHY LA English DT Review ID EQUATORIAL PACIFIC-OCEAN; NORTH-ATLANTIC; PHYTOPLANKTON PHOTOSYNTHESIS; WATER MASSES; SEAWIFS; VARIABILITY; CIRCULATION; CLIMATE; JGOFS; IRON AB The Atlantic Meridional Transect programme uses the twice-annual passage of the RRS James Clark Ross between the UK and the Falkland Islands. before and after the Antarctic research programme in the Austral Summer (see Aiken, J., & Bale, A. J. (2000). An introduction to the Atlantic Meridional Transect (AMT) Programme. Progress in Oceanography, this issue). This paper examines the scientific rationale for a spatially-extensive time and space series programme and reviews the relevant physical and biological oceanography of the Atlantic Ocean. The main scientific observations from the research programme are reported. These are set in the context of historical and contemporary observations pertinent to the principal objectives, of the cruise, notably the satellite remotely sensed observations of ocean properties. The extent to which the programme goals have been realised by the research to date is assessed and discussed. New bio-optical signatures, which can be related to productivity parameters, have been derived. These can be used to interpret remotely sensed observations of ocean colour in terms of productivity and production processes such as the air/sea exchange of biogenic gases, which relate to the issues of climate change and the sustainability of marine ecosystems. (C) 2000 Elsevier Science Ltd. All rights reserved. C1 CCMS Plymouth Marine Lab, Plymouth PL1 3DH, Devon, England. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Southampton Oceanog Ctr, Southampton, Hants, England. Univ Plymouth, Plymouth PL4 8AA, Devon, England. RP Aiken, J (reprint author), CCMS Plymouth Marine Lab, Prospect Pl,W Hoe, Plymouth PL1 3DH, Devon, England. EM ja@ccms.ac.uk RI Hooker, Stanford/E-2162-2012 NR 48 TC 70 Z9 70 U1 0 U2 10 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0079-6611 J9 PROG OCEANOGR JI Prog. Oceanogr. PY 2000 VL 45 IS 3-4 BP 257 EP 312 DI 10.1016/S0079-6611(00)00005-7 PG 56 WC Oceanography SC Oceanography GA 318PW UT WOS:000087293900002 ER PT J AU Hooker, SB Rees, NW Aiken, J AF Hooker, SB Rees, NW Aiken, J TI An objective methodology for identifying oceanic provinces SO PROGRESS IN OCEANOGRAPHY LA English DT Review ID CIRCULATION; SURFACE AB An objective methodology for identifying oceanic provinces in hydrographic data is presented, although, the technique is sufficiently general so as to be applicable to a variety of data sets. The sub- and near-surface temperature (T) and salinity (S) of the Atlantic Ocean were measured on two Atlantic Meridional Transect (AMT) cruises covering approximately 100 degrees of latitude and 50 degrees of longitude. The cruises covered the boreal autumn and austral spring (AMT-1) and the boreal spring and austral autumn (AMT-2) during 1995 and 1996, respectively. There are distinct patterns of change in T-S from 50 degrees N to 50 degrees S for both sub- and nearsurface measurements, although this study concentrates primarily on the latter. Near-surface density (sigma(t)) encapsulates the variations in T-S. The position of localized extrema in the sigma(t) first spatial derivative locates the change in bulk T-S properties and, hence, the extent of a physical province. The province identification methodology is validated by comparing the results obtained using in situ density, a mixed layer depth space series constructed from expendable bathythermograph profiles, and climatological density. Additional validation of the methodology is achieved by intercomparing different in situ data sources between the two cruise periods. The comparisons show the near-surface measurements are indicative of the mixed layer and that the AMT-1 and AMT-2 cruises are representative of the corresponding climatological months. A simple scheme for investigating how far a province extends away from the cruise track uses the climatological data in concert with a T-S description of each province from the AMT along-track observations to produce a two-dimensional map of the geographical extent of each province. Although exceptions between the province extents and the basic circulation of the Atlantic Ocean occur, the majority of the provinces have the correct shape and extent, that is, their edges follow the flow fields associated with the currents that bound them and they extend over an appropriate area. The province identification methodology is sensitive and reliable enough to investigate temporal differences in oceanic provinces, which means it might be useful for parameterizing global budget calculations in numerical models. (C) 2000 Elsevier Science Ltd. All rights reserved. C1 NASA, Goddard Space Flight Ctr, Lab Hydrospher Proc, Oceans & Ice Branch, Greenbelt, MD 20771 USA. CCMS Plymouth Marine Lab, Plymouth, Devon, England. RP Hooker, SB (reprint author), NASA, Goddard Space Flight Ctr, Lab Hydrospher Proc, Oceans & Ice Branch, Code 971, Greenbelt, MD 20771 USA. RI Hooker, Stanford/E-2162-2012 NR 14 TC 38 Z9 39 U1 1 U2 10 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0079-6611 J9 PROG OCEANOGR JI Prog. Oceanogr. PY 2000 VL 45 IS 3-4 BP 313 EP 338 DI 10.1016/S0079-6611(00)00006-9 PG 26 WC Oceanography SC Oceanography GA 318PW UT WOS:000087293900003 ER PT J AU Hooker, SB McClain, CR AF Hooker, SB McClain, CR TI The calibration and validation of SeaWiFS data SO PROGRESS IN OCEANOGRAPHY LA English DT Review ID ZONE COLOR SCANNER; QUALITY MONITOR SQM; OCEAN-COLOR; ATMOSPHERIC CORRECTION; FIELD RADIOMETERS; IMAGERY; SENSORS; PHYTOPLANKTON; ALGORITHM; PIGMENT AB The Sea-viewing Wide Field-of-view Sensor (SeaWiFS) is the successor ocean color imaging system to the Nimbus-7 Coastal Zone Color Scanner (CZCS). The SeaWiFS calibration and validation effort includes spacecraft, atmospheric, sea surface, subsurface (or in situ), plus laboratory and data analysis components which require pre- and postlaunch activities. The most important goals of this effort are to produce water-leaving radiances with an uncertainty of 5% in clear-water regions and chlorophyll a concentrations within +/-35% over the range of 0.05-50 mg m(-3). The first objective requires field instruments with a calibration and measurement capability on the order of 1%; because these challenging in situ measurements will be acquired from a variety of field instruments over the five-year mission interval, a measurement assurance program is required. This program consists of several activities: an accurate pre launch characterization and calibration of the SeaWiFS instrument; a Marine Optical Buoy (MOBY) rotation in clear water to provide a water-leaving radiance time series for postlaunch vicarious calibration: the SeaWiFS Bio-Optical Archive and Storage System (SeaBASS) to hold the relevant data; clearly defined SeaWiFS Ocean Optics Protocols (SOOP) for established data collection methodologies; annual SeaWiFS Intercalibration Round-Robin Experiments (SIRREXs) for intercomparing field and calibration equipment, and training scientific personnel; direct comparison to a national standard laboratory using the SeaWiFS Transfer Radiometer (SXR); a portable field source, called the SeaWiFS Quality Monitor (SQM), for monitoring the temporal stability of the calibration of field instruments; a highly accurate atmospheric correction algorithm designed for the SeaWiFS instrument response functions; bio-optical algorithms that encompass a broad range of bio-optical provinces; and satellite data processing, duality control, and analysis procedures for monitoring the postlaunch performance of the sensor and the validity of the derived products. The culmination of many of these activities is the deployment of the instruments and methodologies on Atlantic Meridional Transect (AMT) cruises between England and the Falkland Islands, a 13 000 km voyage spanning more than 100 degrees of latitude, with a calibration and measurement accuracy that is on the order of 1%. The AMT Program is the primary product validation activity supported by the SeaWiFS Project The AMT cruises also serve as a testbed for new technology development and have demonstrated that high quality bio-optical data can be routinely provided to the Project in near-real time. (C) 2000 Elsevier Science Ltd. All rights reserved. C1 NASA, Goddard Space Flight Ctr, Lab Hydrospher Proc, Greenbelt, MD 20771 USA. RP Hooker, SB (reprint author), NASA, Goddard Space Flight Ctr, Lab Hydrospher Proc, SeaWiFS Project Code 970-2, Greenbelt, MD 20771 USA. RI Hooker, Stanford/E-2162-2012 NR 91 TC 166 Z9 181 U1 2 U2 21 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0079-6611 J9 PROG OCEANOGR JI Prog. Oceanogr. PY 2000 VL 45 IS 3-4 BP 427 EP 465 DI 10.1016/S0079-6611(00)00012-4 PG 39 WC Oceanography SC Oceanography GA 318PW UT WOS:000087293900009 ER PT S AU Hsu, F Azarm, MA AF Hsu, F Azarm, MA BE Kondo, S Furuta, K TI Evaluation of failure dependency through simulation studies SO PSAM 5: PROBABILISTIC SAFETY ASSESSMENT AND MANAGEMENT, VOLS 1-4 SE FRONTIERS SCIENCE SERIES LA English DT Proceedings Paper CT 5th International Conference on Probabilistic Safety Assessment and Management CY NOV 27-DEC 01, 2000 CL OSAKA, JAPAN SP Amer Inst Chem Engineers, Amer Nucl Soc, Architectural Inst Japan, Atom Energy Soc Japan AB In an earlier study, we have developed a new perspective on the basic concept of dependent failures where the definition of dependency is based on clustering in failure times of similar components, and the detection of failure dependency was based oil failure time statistics. Specific measurements were also defined as dependent failure indicators, which steamed off the concept of the Minimal Cycle Duration (MCD) among failure times of similar components. In validating the proposed new method, a simulation approach was developed in this study to evaluate not only its capability of detecting failure dependency, but also to assess the effect of triggering events on clustering of failures and its impact oil the unavailability of nuclear safety systems. Another objective of the simulation studies was to generate failure times for multiple components which resemble different levels of statistical dependency induced by triggering events, and imposes the local failure rate changes across redundant components. A computer modeling scheme and the software CLUSTER, was developed using Monte-Carlo methods. Simulations were performed for a set of 2 and 4 similar components to show that the effect of clustering is more pronounced as more components are affected. Throughout the simulation studies, repair was assumed to be instantaneous. C1 NASA, Lyndon B Johnson Space Ctr, Sci Applicat Int Corp, Houston, TX 77058 USA. RP Hsu, F (reprint author), NASA, Lyndon B Johnson Space Ctr, Sci Applicat Int Corp, Houston, TX 77058 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU UNIVERSAL ACADEMY PRESS, INC PI TOKYO PA C P O BOX 235, TOKYO, 100-8691, JAPAN SN 0915-8502 BN 4-946443-64-9 J9 FRONT SCI SERIES PY 2000 IS 34 BP 3 EP 12 PG 10 WC Computer Science, Artificial Intelligence; Engineering, Civil; Engineering, Electrical & Electronic; Operations Research & Management Science; Nuclear Science & Technology SC Computer Science; Engineering; Operations Research & Management Science; Nuclear Science & Technology GA BT17N UT WOS:000172150100001 ER PT B AU Harding, AK Strickman, MS Gwinn, C McCulloch, P Moffet, D AF Harding, AK Strickman, MS Gwinn, C McCulloch, P Moffet, D BE Kramer, M Wex, N Wielebinski, R TI RXTE observations of the Vela pulsar: The X-ray-optical connection SO PULSAR ASTRONOMY - 2000 AND BEYOND: IAU COLLOQUIUM 177 SE ASTRONOMICAL SOCIETY OF THE PACIFIC CONFERENCE SERIES LA English DT Proceedings Paper CT 177th IAU Colloquium on Pulsar Astronomy - 2000 and Beyond CY AUG 30-SEP 03, 1999 CL BONN, GERMANY SP Int Astronom Union, Deutsch Forschgsgemein, Max Planck Inst Radioastronom, Max Planck Inst Ecxtraterrest Phys AB We report on our analysis of a 300 ks observation of the Vela pulsar with the Rossi X-Ray Timing Explorer (RXTE). The double-peaked, pulsed emission at 2 - 30 keV, which we had previously detected during a 93 ks observation, is confirmed with much improved statistics. There is now clear evidence, both in the spectrum and the light curve, that the emission in the RXTE band is a blend of two separate components. The spectrum of the harder component connects smoothly with the OSSE, COMPTEL and EGRET spectrum and the peaks in the light curve are in phase coincidence with those of the high-energy light curve. The spectrum of the softer component is consistent with an extrapolation to the pulsed optical flux, and the second RXTE pulse is in phase coincidence with the second optical peak. In addition, Eve see a peak in the 2-8 keV RXTE pulse profile at the radio phase. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Harding, AK (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RI Harding, Alice/D-3160-2012 NR 9 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 1-58381-029-3 J9 ASTR SOC P PY 2000 VL 202 BP 331 EP 334 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BQ44S UT WOS:000088366000107 ER PT B AU Marshall, FE Gotthelf, EV Middleditch, J Wang, QD Zhang, W AF Marshall, FE Gotthelf, EV Middleditch, J Wang, QD Zhang, W BE Kramer, M Wex, N Wielebinski, R TI Intensive X-ray monitoring of the 16ms Crab-like pulsar PSR J0537-6910 SO PULSAR ASTRONOMY - 2000 AND BEYOND: IAU COLLOQUIUM 177 SE Astronomical Society of the Pacific Conference Series LA English DT Proceedings Paper CT 177th IAU Colloquium on Pulsar Astronomy - 2000 and Beyond CY AUG 30-SEP 03, 1999 CL BONN, GERMANY SP Int Astronom Union, Deutsch Forschgsgemein, Max Planck Inst Radioastronom, Max Planck Inst Ecxtraterrest Phys ID SUPERNOVA REMNANT N157B; TORQUE EVOLUTION; YOUNG PULSARS; GLITCHES; ROSAT AB The recently discovered pulsar PSR J0537-6910 is the most rapidly rotating young pulsar known. This latest example of a Crab-like pulsar, located in the supernova remnant N157B in the Large Magellanic Cloud, is rotating twice as fast as the Crab pulsar. With a characteristic age of 5000 years, it is also the oldest known example of a Crab-like pulsar and was likely rotating close to the maximum rate for a neutron star when it was born. Here we report preliminary results from an intensive monitoring campaign of X-ray observations acquired with the Rossi Xray Timing Explorer that began in January 1999. These observation have revealed a large glitch event in the pulse timing during the first six month of our campaign, consistent with those suggested by sparse observations dating back to 1993. The current evolution of the rotation rate of PSR J0537-6910 provides a unique probe of the internal structure of neutron stars and constraints on possible pulsar emission mechanisms. C1 NASA, Goddard Space Flight Ctr, High Energy Phys Lab, Greenbelt, MD 20771 USA. RP NASA, Goddard Space Flight Ctr, High Energy Phys Lab, Greenbelt, MD 20771 USA. EM frank.marshall@gsfc.nasa.gov; evg@astro.columbia.edu RI Zhang, William/D-3535-2012 NR 12 TC 2 Z9 2 U1 0 U2 0 PU ASTRONOMICAL SOC PACIFIC PI SAN FRANCISCO PA 390 ASHTON AVE, SAN FRANCISCO, CA 94112 USA BN 1-58381-029-3 J9 ASTR SOC P PY 2000 VL 202 BP 335 EP 340 PG 6 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BQ44S UT WOS:000088366000108 ER PT B AU Zhang, B Harding, AK AF Zhang, B Harding, AK BE Kramer, M Wex, N Wielebinski, R TI A full polar cap cascade model: pulsar gamma-ray and X-ray luminosities SO PULSAR ASTRONOMY - 2000 AND BEYOND: IAU COLLOQUIUM 177 SE ASTRONOMICAL SOCIETY OF THE PACIFIC CONFERENCE SERIES LA English DT Proceedings Paper CT 177th IAU Colloquium on Pulsar Astronomy - 2000 and Beyond CY AUG 30-SEP 03, 1999 CL BONN, GERMANY SP Int Astronom Union, Deutsch Forschgsgemein, Max Planck Inst Radioastronom, Max Planck Inst Ecxtraterrest Phys AB We propose a full polar cap cascade model which includes the curvature and inverse Compton emission of the primary particles, and both synchrotron radiation and inverse Compton of the higher generation pairs. Such a full cascade model can reproduce both the L-gamma proportional to (L-sd)(1/2) and the L-x similar to 10(-3) L-sd dependences observed from the known spin-powered pulsars. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Zhang, B (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RI Harding, Alice/D-3160-2012 NR 4 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 1-58381-029-3 J9 ASTR SOC P PY 2000 VL 202 BP 481 EP 482 PG 2 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BQ44S UT WOS:000088366000153 ER PT S AU Zak, M Meyers, RE Deacon, K AF Zak, M Meyers, RE Deacon, K BE Donkor, E Pirich, AR TI Quantum Decision-Maker theory and simulation SO QUANTUM COMPUTING SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Quantum Computing CY APR 26-27, 2000 CL ORLANDO, FL SP SPIE AB A quantum device simulating the human decision making process is introduced. It consists of quantum recurrent nets generating stochastic processes which represent the motor dynamics, and of classical neural nets describing the evolution of probabilities of these processes which represent the mental dynamics. The autonomy of the decision making process is achieved by a feedback from the mental to motor dynamics which changes the stochastic matrix based upon the probability distribution. This feedback replaces unavailable external information by an internal knowledge-base stored in the mental model in the form of probability distributions. As a result, the coupled motor-mental dynamics is described by a nonlinear version of Markov chains which can decrease entropy without an external source of information. Applications to common sense based decisions as well as to evolutionary games are discussed. An example exhibiting self-organization is computed using quantum computer simulation. Force on force and mutual aircraft engagements using the quantum decision maker dynamics are considered. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Zak, M (reprint author), CALTECH, Jet Prop Lab, MS 126-347, Pasadena, CA 91109 USA. NR 5 TC 0 Z9 0 U1 1 U2 3 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3673-9 J9 P SOC PHOTO-OPT INS PY 2000 VL 4047 BP 97 EP 112 DI 10.1117/12.391958 PG 16 WC Computer Science, Theory & Methods; Optics; Physics, Mathematical SC Computer Science; Optics; Physics GA BQ79D UT WOS:000089527000010 ER PT J AU Joiner, J Rokke, L AF Joiner, J Rokke, L TI Variational cloud-clearing with TOVS data SO QUARTERLY JOURNAL OF THE ROYAL METEOROLOGICAL SOCIETY LA English DT Article DE variational assimilation; cloud clearing; TOVS ID OPERATIONAL VERTICAL SOUNDER; NONLINEAR OPTIMAL ESTIMATION; RADIATIVE-TRANSFER; DATA ASSIMILATION; TIROS-N; RADIANCES; SATELLITE; TEMPERATURE; INVERSION; OZONE AB A number of studies have shown that the use of passive microwave and infrared satellite observations in data assimilation systems can increase forecast skill. Considerable effort has been expended over the past two decades, particularly with the TIROS Operational Vertical Sounder (TOVS), to achieve this result. The positive impact on forecast skill is a result of more rigorous treatment of quality control, improvements in systematic error correction schemes, and advances in data assimilation systems. Yet, there still remains potential for improving the use of satellite data, particularly cloud-contaminated observations, in data assimilation. Here, we use a one-dimensional variational framework (1DVAR) as a first step towards improving the treatment of cloudy data by cloud-clearing. Cloud-clearing is a procedure that removes cloud radiative effects through comparison of partly cloudy adjacent pixels. The 1DVAR approach simultaneously extracts cloud-clearing parameters and information about the atmospheric and surface state from microwave and infrared observations. The variational framework ensures that the state estimate is consistent with all available measurements. The 1DVAR cloud-clearing approach can also be extended to three or four dimensions (3DVAR, 4DVAR). Our TOVS cloud-clearing implementation allows for complex cloud structures, including multiple cloud layers with wavelength-dependent radiative properties. We present preliminary results of our 1DVAR cloud-clearing implementation with TOVS. The results suggest that there is useful information in the cloud-cleared data. C1 NASA, Data Assimilat Off, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Joiner, J (reprint author), NASA, Data Assimilat Off, Goddard Space Flight Ctr, Code 910-3, Greenbelt, MD 20771 USA. RI Joiner, Joanna/D-6264-2012; Rokke, Laurie/I-5642-2015 OI Rokke, Laurie/0000-0002-5696-7240 NR 42 TC 23 Z9 23 U1 1 U2 1 PU ROYAL METEOROLOGICAL SOC PI READING PA 104 OXFORD ROAD, READING, BERKS, ENGLAND RG1 7LJ SN 0035-9009 J9 Q J ROY METEOR SOC JI Q. J. R. Meteorol. Soc. PD JAN PY 2000 VL 126 IS 563 BP 725 EP 748 DI 10.1256/smsqj.56315 PN B PG 24 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 297NF UT WOS:000086088400015 ER PT J AU Jouzel, J Hoffmann, G Koster, RD Masson, V AF Jouzel, J Hoffmann, G Koster, RD Masson, V TI Water isotopes in precipitation: data/model comparison for present-day and past climates SO QUATERNARY SCIENCE REVIEWS LA English DT Article; Proceedings Paper CT 1st PAGES Open Science Meeting CY APR 19-23, 1998 CL UNIV LONDON, LONDON, ENGLAND HO UNIV LONDON ID GENERAL-CIRCULATION MODEL; LAST GLACIAL MAXIMUM; ICE CORE RECORDS; DEUTERIUM EXCESS; ANTARCTIC PRECIPITATION; UNITED-STATES; GCM ANALYSIS; TEMPERATURE; GREENLAND; SNOW AB Variations of HDO and H-2 O-18 concentrations are observed in precipitation both on a geographical and on a temporal basis. These variations, resulting from successive isotopic fractionation processes at each phase change of water during its atmospheric cycle, are well documented through the IAEA/WMO network. Isotope concentrations are, in middle and high latitudes, linearly related to the annual mean temperature at the precipitation site. Paleoclimatologists have used this relationship to infer paleotemperatures from isotope paleodata extractable from ice cores, deep groundwater and other such sources. For this application to be valid, however, the spatial relationship must also hold in time at a given location as the location undergoes a series of climatic changes. Progress in water isotope modeling aimed at examining and evaluating this assumption has been recently reviewed (Jouzel et al., 1997) with a focus on polar regions and, more specifically, on Greenland. We extend this review in comparing the results of two different isotopic AGCMs (NASA/GISS and ECHAM) and in examining, with a more global perspective, the validity of the above assumption, i.e. the equivalence of the spatial and temporal isotope-temperature relationships. These results confirm the dominating role of local temperature changes on the paleo isotope signal in most regions. However, the exact calibration of this valuable paleothermometer is biased by, for example, the seasonality of precipitation and other factors. We forced the two models by the climatic boundary conditions of the mild-holocene at 6 kyr BP which only slightly differs from today's climate. The isotope response on this weak forcing is quite heterogeneous. The only robust common response is the intensification of the hydrological cycle in low latitudes and, therefore, isotopically more depleted precipitation in the tropics and subtropics. We also examine recent progress made in modeling: the relationship between the conditions prevailing in moisture source regions for precipitation and the deuterium excess of that precipitation. (C) 1999 Elsevier Science Ltd. All rights reserved. C1 CEA Saclay, CNRS, UMR 1572, Lab Sci Climat & Environm, F-91191 Gif Sur Yvette, France. NASA, Hydrol Sci Branch, Lab Hydrospher Proc, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Jouzel, J (reprint author), CEA Saclay, CNRS, UMR 1572, Lab Sci Climat & Environm, Orme Merisiers, F-91191 Gif Sur Yvette, France. RI Koster, Randal/F-5881-2012; Masson-Delmotte, Valerie/G-1995-2011 OI Koster, Randal/0000-0001-6418-6383; Masson-Delmotte, Valerie/0000-0001-8296-381X NR 68 TC 117 Z9 131 U1 2 U2 33 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0277-3791 J9 QUATERNARY SCI REV JI Quat. Sci. Rev. PD JAN PY 2000 VL 19 IS 1-5 BP 363 EP 379 DI 10.1016/S0277-3791(99)00069-4 PG 17 WC Geography, Physical; Geosciences, Multidisciplinary SC Physical Geography; Geology GA 268PV UT WOS:000084425500023 ER PT J AU Rind, D AF Rind, D TI Relating paleoclimate data and past temperature gradients: Some suggestive rules SO QUATERNARY SCIENCE REVIEWS LA English DT Article; Proceedings Paper CT 1st PAGES Open Science Meeting CY APR 19-23, 1998 CL UNIV LONDON, LONDON, ENGLAND HO UNIV LONDON ID LAST GLACIAL MAXIMUM; MIDDLE PLIOCENE CLIMATE; JOINT INVESTIGATIONS; MODEL AB Understanding tropical sensitivity is perhaps the major concern confronting researchers, for both past and future climate change issues. Tropical data has been beset by contradictions, and many techniques applicable to the extratropics are either unavailable or fraught with uncertainty when applied at low latitudes. Paleoclimate data, if interpreted within the context of the latitudinal temperature gradient data they imply, can be used to estimate what did happen to tropical temperatures in the past, and provide a first guess for what might happen in the future. The approach is made possible by the modeling result that atmospheric dynamical changes, and the climate impacts they produce, respond primarily to temperature gradient changes. Here we review some "rules" obtained from GCM experiments with different sea surface temperature gradients and different forcing, that can be used to relate paleoclimate reconstructions to the likely temperature gradient changes they suggest. Published by Elsevier Science Ltd. C1 NASA, Goddard Space Flight Ctr, Inst Space Studies, New York, NY 10025 USA. RP Rind, D (reprint author), NASA, Goddard Space Flight Ctr, Inst Space Studies, 2880 Broadways, New York, NY 10025 USA. NR 26 TC 28 Z9 28 U1 0 U2 0 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0277-3791 J9 QUATERNARY SCI REV JI Quat. Sci. Rev. PD JAN PY 2000 VL 19 IS 1-5 BP 381 EP 390 DI 10.1016/S0277-3791(99)00070-0 PG 10 WC Geography, Physical; Geosciences, Multidisciplinary SC Physical Geography; Geology GA 268PV UT WOS:000084425500024 ER PT J AU Ziemke, JR Chandra, S Herman, J Varotsos, C AF Ziemke, JR Chandra, S Herman, J Varotsos, C TI Erythemal weighted ultraviolet trends over northern latitudes SO RADIATION PROTECTION DOSIMETRY LA English DT Article; Proceedings Paper CT International Workshop on Ultraviolet Radiation Exposure, Measurement and Protection CY OCT 18-20, 1999 CL ST CATHERINES COLL, OXFORD, ENGLAND SP Natl Radiol Protect Board, WHO, Int Commiss Non-ionizing Radiat Protect, Fed Minist Environm, Nat Conservat & Nucl Safety, Dept Hlth, Hlth & Safety Execut HO ST CATHERINES COLL ID STRATOSPHERIC OZONE DEPLETION; B RADIATION; WINTER; HEMISPHERE AB This study examines the distribution of long-term trends in ground-level erythemally-weighted ultraviolet-B (UVB, wavelengths 290-320 nm) exposures in the northern latitudes for the period 1979-1991 using measurements from the Nimbus 7 total ozone mapping spectrometer (TOMS) instrument. Zonal mean erythemal UV data show similar to 3-7% per decade increases in the mid-to-high latitudes. Analysis of the horizontal patterns in trends around summer months indicates that most of the regional increases (exceeding 6% per decade) in the northern hemisphere in the latitude range 30 degrees-40 degrees N originate from the Pacific and Atlantic oceanic regions. Increases (also exceeding 6% per decade) in latitudes 40 degrees-60 degrees appear to originate from the North American and Asian continents and also central Europe. Trends over the east Asian continent in high latitudes indicate increases exceeding 10% per decade for May-August. C1 Software Corp Amer, Beltsville, MD 20705 USA. NASA, Goddard Space Flight Ctr, Atmospher Chem & Dynam Branch, Greenbelt, MD 20771 USA. Univ Athens, Dept Appl Phys, Athens 15784, Greece. RP Ziemke, JR (reprint author), Software Corp Amer, Beltsville, MD 20705 USA. RI Varotsos, Costas/H-6257-2013; OI Varotsos, Costas/0000-0001-7215-3610; Herman, Jay/0000-0002-9146-1632 NR 17 TC 2 Z9 2 U1 1 U2 1 PU NUCLEAR TECHNOLOGY PUBL PI ASHFORD PA PO BOX 7, ASHFORD TN23 1YW, KENT, ENGLAND SN 0144-8420 J9 RADIAT PROT DOSIM JI Radiat. Prot. Dosim. PY 2000 VL 91 IS 1-3 BP 157 EP 160 PG 4 WC Environmental Sciences; Public, Environmental & Occupational Health; Nuclear Science & Technology; Radiology, Nuclear Medicine & Medical Imaging SC Environmental Sciences & Ecology; Public, Environmental & Occupational Health; Nuclear Science & Technology; Radiology, Nuclear Medicine & Medical Imaging GA 361KR UT WOS:000089722700031 ER PT J AU Yasuda, H Fujitaka, K AF Yasuda, H Fujitaka, K TI Responses of TLD Mg2SiO4 : Tb and radiophotoluminescent glass to heavy charged particles and space radiation SO RADIATION PROTECTION DOSIMETRY LA English DT Article ID DOSE-EQUIVALENT; FLIGHT AB The LET dependences of thermoluminescence dosemeters of Mg2SiO4:Tb (TLMS) and radiophotoluminescent glass dosemeters (RPLG) were examined using high energy, heavy ion beams. TLMS kept its efficiency below 10 keV.mu m(-1) and decreased almost linearly with the logarithm of LET for higher LET particles. The efficiency of RPLG decreased more gradually than TLMS although its reduction was observed at a lower LET region around 0.5 keV.mu m(-1). Accordingly, the ratio of TLMS to RPLG value showed a maximum peak around 20 keV.mu m(-1) of LET. The results obtained with both dosemeters in the 10 day space mission in the Russian space station Mir showed that not only dose level but also radiation quality were varying considerably in the Mir Core Module. C1 Natl Inst Radiol Sci, Inage Ku, Chiba 2638555, Japan. NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Yasuda, H (reprint author), Natl Inst Radiol Sci, Inage Ku, Chiba 2638555, Japan. NR 16 TC 22 Z9 22 U1 1 U2 1 PU NUCLEAR TECHNOLOGY PUBL PI ASHFORD PA PO BOX 7, ASHFORD, KENT, ENGLAND TN23 1YW SN 0144-8420 J9 RADIAT PROT DOSIM JI Radiat. Prot. Dosim. PY 2000 VL 87 IS 2 BP 115 EP 119 PG 5 WC Environmental Sciences; Public, Environmental & Occupational Health; Nuclear Science & Technology; Radiology, Nuclear Medicine & Medical Imaging SC Environmental Sciences & Ecology; Public, Environmental & Occupational Health; Nuclear Science & Technology; Radiology, Nuclear Medicine & Medical Imaging GA 281GX UT WOS:000085151100007 PM 11543154 ER PT J AU Yasuda, H Fujitaka, K AF Yasuda, H Fujitaka, K TI Glow curves from beryllium oxide exposed to high energy heavy ions SO RADIATION PROTECTION DOSIMETRY LA English DT Article ID DOSE MEASUREMENT AB Ceramic chips of beryllium oxide were exposed to high energy heavy ion beams (He, C, Ne, Ar, and Fe) and the glow curves were analysed. Two comparable peaks at around 203 degrees C and 355 degrees C were found and each peak height showed a different LET dependence. The low temperature peak height (I,) increased remarkably with LET to about 10 keV.mu m(-1) and the relative efficiency normalised to that of (137)Cs gamma rays took a maximum factor of 1.3. The high temperature peak height (I,) decreased almost linearly with the logarithm of LET. The ratio of I, to I, decreased exponentially up to 100 keV.mu m(-1). These results show a possibility that the glow curve of BeO can be utilised for the evaluation of radiation quality where high LET particles are mixed, as in space. C1 Natl Inst Radiol Sci, Chiba 2638555, Japan. NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Yasuda, H (reprint author), Natl Inst Radiol Sci, Chiba 2638555, Japan. NR 19 TC 4 Z9 4 U1 0 U2 0 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0144-8420 J9 RADIAT PROT DOSIM JI Radiat. Prot. Dosim. PY 2000 VL 87 IS 3 BP 203 EP 206 PG 4 WC Environmental Sciences; Public, Environmental & Occupational Health; Nuclear Science & Technology; Radiology, Nuclear Medicine & Medical Imaging SC Environmental Sciences & Ecology; Public, Environmental & Occupational Health; Nuclear Science & Technology; Radiology, Nuclear Medicine & Medical Imaging GA 290HB UT WOS:000085669900008 ER PT J AU Badhwar, GD Cucinotta, FA AF Badhwar, GD Cucinotta, FA TI A comparison of depth dependence of dose and linear energy transfer spectra in aluminum and polyethylene SO RADIATION RESEARCH LA English DT Article ID GALACTIC COSMIC-RAYS; RADIATION AB A set of four tissue-equivalent proportional counters (TEPCs), with their detector heads at the centers of 0 (bare), 3, 7 and 9-inch-diameter aluminum spheres, were flown on Shuttle flight STS-89, Five such detectors at the centers of polyethylene spheres were flown 1 year earlier on STS-81, The results of dose-depth dependence for the two materials convincingly show the merits of using material rich in hydrogen to decrease the radiation exposure to the crew. A comparison of the calculated galactic cosmic radiation (GCR) absorbed dose and dose-equivalent rates using the radiation transport code HZETRN with nuclear fragmentation model NUCFRG2 and the measured GCR absorbed dose rates and dose-equivalent rates shows that they agree within root mean square (rms) error of 12.5 and 8.2%, respectively. However, there are significant depth-dependent differences in the linear energy transfer (LET) spectra. A comparison for trapped protons using the proton transport code BRYNTRN and the AP-8 MIN trapped-proton model shows a systematic bias, with the model underpredicting dose and dose-equivalent rates. These results show the need for improvements in the radiation transport and/or fragmentation models. (C) 2000 by Radiation Research Society. C1 NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Badhwar, GD (reprint author), NASA, Lyndon B Johnson Space Ctr, 2101 NASA Rd 1,Code SN3, Houston, TX 77058 USA. NR 19 TC 28 Z9 29 U1 0 U2 2 PU RADIATION RESEARCH SOC PI OAK BROOK PA 2021 SPRING RD, STE 600, OAK BROOK, IL 60521 USA SN 0033-7587 J9 RADIAT RES JI Radiat. Res. PD JAN PY 2000 VL 153 IS 1 BP 1 EP 8 DI 10.1667/0033-7587(2000)153[0001:ACODDO]2.0.CO;2 PG 8 WC Biology; Biophysics; Radiology, Nuclear Medicine & Medical Imaging SC Life Sciences & Biomedicine - Other Topics; Biophysics; Radiology, Nuclear Medicine & Medical Imaging GA 270WT UT WOS:000084560700001 PM 10630971 ER PT B AU Cucinotta, FA Wilson, JW Goldhagen, P Saganti, P AF Cucinotta, FA Wilson, JW Goldhagen, P Saganti, P BE Moriaty, M Edington, M Mothersill, C Ward, JF Seymour, C Fry, RJM TI Radiation physics for space and high-altitude air travel SO RADIATION RESEARCH, VOL 2, CONGRESS PROCEEDINGS LA English DT Proceedings Paper CT 11th International Congress of Radiation Research CY JUL 18-23, 1999 CL DUBLIN, IRELAND ID CELLS C1 NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Cucinotta, FA (reprint author), NASA, Lyndon B Johnson Space Ctr, SN3, Houston, TX 77058 USA. NR 11 TC 0 Z9 0 U1 0 U2 0 PU ALLEN PRESS INC PI LAWRENCE PA 1041 NEW HAMPSHIRE ST, LAWRENCE, KS 66044 USA BN 1-891276-14-X PY 2000 BP 728 EP 732 PG 5 WC Multidisciplinary Sciences SC Science & Technology - Other Topics GA BR30V UT WOS:000166083700174 ER PT B AU Badhwar, GD AF Badhwar, GD BE Moriaty, M Edington, M Mothersill, C Ward, JF Seymour, C Fry, RJM TI Radiation environment for interplanetary travel SO RADIATION RESEARCH, VOL 2, CONGRESS PROCEEDINGS LA English DT Proceedings Paper CT 11th International Congress of Radiation Research CY JUL 18-23, 1999 CL DUBLIN, IRELAND C1 NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Badhwar, GD (reprint author), NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. NR 3 TC 0 Z9 0 U1 1 U2 1 PU ALLEN PRESS INC PI LAWRENCE PA 1041 NEW HAMPSHIRE ST, LAWRENCE, KS 66044 USA BN 1-891276-14-X PY 2000 BP 737 EP 740 PG 4 WC Multidisciplinary Sciences SC Science & Technology - Other Topics GA BR30V UT WOS:000166083700176 ER PT J AU Treuhaft, RN Siqueira, PR AF Treuhaft, RN Siqueira, PR TI Vertical structure of vegetated land surfaces from interferometric and polarimetric radar SO RADIO SCIENCE LA English DT Article ID SAR INTERFEROMETRY; MODEL AB This paper describes the estimation of parameters characterizing the vertical structure of vegetated land surfaces, from combined interferometric and polarimetric radar data. Physical models expressing radar observations in terms of parameters describing vegetated land surfaces are the foundation for parameter estimation techniques. Defining a general complex cross correlation enables the unified development of models for interferometry and polarimetry, including polarimetric interferometry. Three simple physical models in this paper express this complex cross correlation in terms of vegetation parameters: (1) a randomly oriented volume, (2) a randomly oriented volume with a ground return, and (3) an oriented volume. For the first two models the parameters include vegetation height, extinction coefficient, underlying topography, and another parameter depending on ground electrical properties and roughness. For the oriented volume, additional parameters depend on the refractivity, extinction coefficients, and backscattering characteristics of waves propagating along eigenpolarizations of the vegetation volume. The above models show that the interferometric cross-correlation amplitude and the polarimetric (HHHH/VVVV) ratio both change by about 1% per meter of vegetation height change, for experimental conditions typical of airborne and spaceborne interferometric radars. These vertical-structure sensitivities prompt a parameter estimation demonstration with two-baseline TOPSAR interferometric and zero-baseline polarimetric data from the Boreal Ecosystem-Atmosphere Study (BOREAS) Southern Study Area in Prince Albert National Park, Saskatchewan, Canada. The demonstrations show the feasibility of measuring vegetation height to better than 4.2 m, underlying topography to better than 6.5 m, and the ratio of ground-to-volume power to better than 10%, using interferometry and polarimetry, coupled with parameter-constraining assumptions, concerning the degree of surface roughness. This paper suggests that single-baseline and multibaseline fully polarimetric interferometry have the potential to obviate the need for such assumptions, thereby making parameter estimation more robust, accurate, and realistic. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Treuhaft, RN (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 138-212, Pasadena, CA 91109 USA. EM rnt@radar-sci.jpl.nasa.gov RI Siqueira, Paul/D-9760-2016 OI Siqueira, Paul/0000-0001-5781-8282 NR 33 TC 258 Z9 291 U1 5 U2 14 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0048-6604 J9 RADIO SCI JI Radio Sci. PD JAN-FEB PY 2000 VL 35 IS 1 BP 141 EP 177 DI 10.1029/1999RS900108 PG 37 WC Astronomy & Astrophysics; Geochemistry & Geophysics; Meteorology & Atmospheric Sciences; Remote Sensing; Telecommunications SC Astronomy & Astrophysics; Geochemistry & Geophysics; Meteorology & Atmospheric Sciences; Remote Sensing; Telecommunications GA 281LF UT WOS:000085161000013 ER PT S AU Cohen, EJ Connell, SJ Dodson, KJ Abbott, JL Abusafieh, AA Backovsky, ZF Dyer, JE Escobedo-Torres, J Friedman, Z Hull, AB Small, DW Thorndyke, P Whitmore, SA AF Cohen, EJ Connell, SJ Dodson, KJ Abbott, JL Abusafieh, AA Backovsky, ZF Dyer, JE Escobedo-Torres, J Friedman, Z Hull, AB Small, DW Thorndyke, P Whitmore, SA BE Butcher, HR TI Architecture of the FIRST telescope SO RADIO TELESCOPES SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Radio Telescopes CY MAR 27-30, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE FIRST; telescope; far-infrared; CFRP; composite; mirror; CTE; CME; thermal gradients; stray light AB The Far Infrared and Submillimeter Telescope (FIRST), is an ESA cornerstone mission, that will be used for photometry, imaging and spectroscopy in the 80 to 670 mu m range. NASA, through the Jet Propulsion Laboratory (JPL), will be contributing the telescope and its design to ESA. This paper will discuss the work being done by JPL and Composite Optics, Incorporated (COI), the developer of the primary mirror technology. Optical and mechanical constraints for the telescope have been defined by ESA and evolved from their trade studies. Design drivers are wave front error (10 mu m rms. with a goal of 6 mu m rms.), mass (260 kg), primary mirror diameter (3.5 m) and f number (f/0.5), and the operational temperature (less than 90 K). Zn response to these requirements a low mass, low coefficient of thermal expansion (CTE) telescope has been designed using carbon fiber reinforced polymer (CFRP). This paper will first present background on the JPL/COI CFRP mirror development efforts. After selection of the material, the next two steps, that are being done in parallel, are to demonstrate that a large CFRP mirror could meet the requirements and to detail the optical, thermal and mechanical design of the telescope. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Cohen, EJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 6 TC 1 Z9 1 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3640-2 J9 P SOC PHOTO-OPT INS PY 2000 VL 4015 BP 215 EP 226 DI 10.1117/12.390414 PG 12 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BQ70J UT WOS:000089219700022 ER PT S AU Cohen, EJ Hull, AB Escobedo-Torres, J Barber, DD Johnston, RA Small, DW Prata, A Freniere, ER AF Cohen, EJ Hull, AB Escobedo-Torres, J Barber, DD Johnston, RA Small, DW Prata, A Freniere, ER BE Butcher, HR TI Optical design of the ultra-light-weight FIRST telescope SO RADIO TELESCOPES SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Radio Telescopes CY MAR 27-30, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE FIRST; telescope; far-infrared; primary mirror; secondary mirror; Ritchey-Chretian; Cassegrain; telescope sensitivities; stray light; standing waves AB The FIRST telescope will be made of carbon fiber reinforced plastic. The optics follow a two mirror near-classical Ritchey-Chretian design, but deviates from that in two respects. The secondary mirror defines the pupil of the system, and the primary mirror is uncommonly fast at f/0.5. After presenting the optical design, the sensitivities will be presented. Current work in progress will be described in the following areas; 1 - secondary mirror figure correction 2 - stray light 3 - primary mirror gaps 4 - standing wave impact on the heterodyne instrument for FIRST (HIFI). C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Cohen, EJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3640-2 J9 P SOC PHOTO-OPT INS PY 2000 VL 4015 BP 559 EP 566 DI 10.1117/12.390451 PG 8 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BQ70J UT WOS:000089219700057 ER PT S AU Sterling, T AF Sterling, T BE Dongarra, JJ Kacsuk, P Podhorszki, N TI Symbolic computing with Beowulf-class PC clusters SO RECENT ADVANCES IN PARALLEL VIRTUAL MACHINE AND MESSAGE PASSING INTERFACE, PROCEEDINGS SE LECTURE NOTES IN COMPUTER SCIENCE LA English DT Article; Proceedings Paper CT 7th European PVM/MPI Users Group Meeting CY SEP 10-13, 2000 CL BALATONFURED, HUNGARY C1 CALTECH, Ctr Adv Comp Res, Pasadena, CA 91125 USA. NASA, Jet Prop Lab, High Performance Comp Grp, Washington, DC 20546 USA. RP Sterling, T (reprint author), CALTECH, Ctr Adv Comp Res, Pasadena, CA 91125 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY SN 0302-9743 BN 3-540-41010-4 J9 LECT NOTES COMPUT SC PY 2000 VL 1908 BP 7 EP 8 PG 2 WC Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BT08K UT WOS:000171904500004 ER PT B AU Gates, TS AF Gates, TS BE Cardon, AH Fukuda, H Reifsnider, KL Verchery, G TI Durability assessment of polymeric composites for high speed civil transport SO RECENT DEVELOPMENTS IN DURABILITY ANALYSIS OF COMPOSITE SYSTEMS LA English DT Proceedings Paper CT 4th International Conference on Durability Analysis of Composite Systems (DURACOSYS99) CY JUL 11-14, 1999 CL BRUSSELS, BELGIUM SP Free Univ Brussels, Fdn SCi Res, Flemish Reg, Virginia Polytechn Inst & State Univ, USN, Off Res, USA, European Res Off, Sci Univ Tokyo, Univ Bourgogne ID MODEL AB Technology development for the next generation High Speed Civil Transport (HSCT) required the construction of a large research program directed towards the durability assessment of polymeric based composites. These material systems would be used extensively in the primary and secondary structure of an HSCT and should meet the stringent requirements of a 72,000-hour design lifetime. The NASA Materials Durability Program was initiated to address this requirement and was composed of elements that addressed the development of a material durability database, predictive and accelerated test methods, and durability validation protocols. This paper will describe in broad terms these elements of the Materials Durability program and how the program elements interacted and supported each other. C1 NASA, Langley Res Ctr, Hampton, VA 23665 USA. RP Gates, TS (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. NR 13 TC 2 Z9 2 U1 0 U2 1 PU A A BALKEMA PUBLISHERS PI LEIDEN PA SCHIPHOLWEG 107C, PO BOX 447, 2316 XC LEIDEN, NETHERLANDS BN 90-5809-103-1 PY 2000 BP 387 EP 392 PG 6 WC Materials Science, Composites SC Materials Science GA BP89E UT WOS:000086522100047 ER PT B AU Bowles, KJ AF Bowles, KJ BE Cardon, AH Fukuda, H Reifsnider, KL Verchery, G TI Predicting the durability of PMR-15 composites aged at elevated temperatures SO RECENT DEVELOPMENTS IN DURABILITY ANALYSIS OF COMPOSITE SYSTEMS LA English DT Proceedings Paper CT 4th International Conference on Durability Analysis of Composite Systems (DURACOSYS99) CY JUL 11-14, 1999 CL BRUSSELS, BELGIUM SP Free Univ Brussels, Fdn SCi Res, Flemish Reg, Virginia Polytechn Inst & State Univ, USN, Off Res, USA, European Res Off, Sci Univ Tokyo, Univ Bourgogne AB Earlier work, which reported relationships between the compression properties and elevated temperature aging times and weight losses, (1) also pointed out the apparent influence of a surface layer formation and growth on the retention of compression properties during extended aging times. Since that time, studies have been directed toward evaluating the growth of the surface layer. This layer was found to change in its composition and features as the aging temperature changed. Microcracks and small voids initiated and advanced inward at all temperatures. Visible oxidation at the surface occurred only at the temperatures above 260 degrees C. Relationships between layer thickness and aging time and temperature were evaluated and empirically formulated. Then the compression properties were graphically related to the surface layer thickness with excellent correlation. C1 NASA, Glenn Res Ctr, Polymers Branch, Mat Div, Cleveland, OH 44135 USA. RP Bowles, KJ (reprint author), NASA, Glenn Res Ctr, Polymers Branch, Mat Div, Cleveland, OH 44135 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU A A BALKEMA PUBLISHERS PI LEIDEN PA SCHIPHOLWEG 107C, PO BOX 447, 2316 XC LEIDEN, NETHERLANDS BN 90-5809-103-1 PY 2000 BP 441 EP 446 PG 6 WC Materials Science, Composites SC Materials Science GA BP89E UT WOS:000086522100055 ER PT S AU van Zyl, J Elachi, C Kim, Y AF van Zyl, J Elachi, C Kim, Y GP IEEE IEEE TI Recent advances in radar technology and techniques for affordable planetary remote sensing SO RECORD OF THE IEEE 2000 INTERNATIONAL RADAR CONFERENCE SE Radar Conference LA English DT Proceedings Paper CT 2000 IEEE Radar Conference CY MAY 07-12, 2000 CL ALEXANDRIA, VA SP Natl Capital Area Council, IEEE, Aerosp & Electr Syst Soc, Radar Syst Panel, Inst Elect Engineers, ITT Gilfillan, Lockheed Martin, Northrop Grumman, Raytheon Co, SAIC, Syst & Electr Inc C1 CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP van Zyl, J (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, 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 1097-5764 BN 0-7803-5776-0 J9 RADAR CONF PY 2000 BP 12 EP 16 DI 10.1109/RADAR.2000.851796 PG 5 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BQ62Y UT WOS:000089015800004 ER PT S AU Wheeler, K Hensley, S AF Wheeler, K Hensley, S GP IEEE IEEE TI The GeoSAR airborne mapping system SO RECORD OF THE IEEE 2000 INTERNATIONAL RADAR CONFERENCE SE Radar Conference LA English DT Proceedings Paper CT 2000 IEEE Radar Conference CY MAY 07-12, 2000 CL ALEXANDRIA, VA SP Natl Capital Area Council, IEEE, Aerosp & Electr Syst Soc, Radar Syst Panel, Inst Elect Engineers, ITT Gilfillan, Lockheed Martin, Northrop Grumman, Raytheon Co, SAIC, Syst & Electr Inc C1 JPL, Pasadena, CA USA. RP Wheeler, K (reprint author), JPL, Pasadena, CA USA. NR 3 TC 3 Z9 3 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1097-5764 BN 0-7803-5776-0 J9 RADAR CONF PY 2000 BP 831 EP 835 DI 10.1109/RADAR.2000.851943 PG 5 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BQ62Y UT WOS:000089015800150 ER PT B AU Statman, JI AF Statman, JI BE Miau, JJ Holdaway, R TI Deep Space Network revitalization - Operations for the 21st century SO REDUCING THE COST OF SPACECRAFT GROUND SYSTEMS AND OPERATIONS SE SPACE TECHNOLOGY PROCEEDINGS LA English DT Proceedings Paper CT 3rd International Symposium on Reducing the Cost of Spacecraft Ground Systems and Operations CY MAR 22-24, 1999 CL TAINAN, TAIWAN SP Natl Cheng Kung Univ, Inst Aeronaut & Astronaut DE RF communications; optical communications; navigation; low-cost operations AB The National Aeronautics and Space Administration (NASA) supports unmanned space missions through a Deep Space Network (DSN) that is developed and operated by the Jet Propulsion Laboratory (JPL) and its subcontractors. The DSN capabilities have been incrementally upgraded since its establishment in the late '50s and are delivered from three Deep Space Communications Complexes (DSCC's) near Goldstone, California, Madrid, Spain, and Canberra, Australia. At present each DSCC includes large antennas with diameters from 11 meters to 70 meters, that operate largely in S-band and X-band frequencies. In addition each DSCC includes ail the associated electronics to receive and process the low-level telemetry signals, and radiate the necessary command with high-power transmitters. To accommodate support of the rapidly increasing number of missions by NASA and of her space agencies, and to facilitate maintaining and increasing the level of service in a shrinking budget environment, JPL has initiated a bold road map with three key components: 1. A Network Simplification Project (NSP) to upgrade aging electronics replacing them with modem commercially based components. NSP and related replacement tasks are projected to reduce the cost of operating the DSN by 50% relative to the 1997 levels. 2. Upgrade of all 34-m and 70-m antennas to provision of Ka-Band telemetry downlink capability, complemented by an existing X-band uplink capability This will increase the effective telemetry downlink capacity by a factor of 4, without building any new antennas. 3. Establishment of an optical communications network to support for high-data-rate unmanned missions that cannot be accommodated with radiofrequency (RF) communications, as well as establish a path toward support of manned missions at Mars. In this paper we present the mission loading projected for 1998-2008 and the elements of the JPL road map that will enable supporting it with a reduced budget. Particular emphasis will be on streamlining the architecture and to reduce the DSN cost for operations, maintenance and sustaining engineering while at the same time also simplifying and reducing the operations cost for the flight missions. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Statman, JI (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 0 TC 7 Z9 7 U1 0 U2 1 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS BN 0-7923-6174-1 J9 SPACE TECHNOL PROC PY 2000 VL 3 BP 9 EP 16 PG 8 WC Engineering, Aerospace SC Engineering GA BR12Q UT WOS:000165710600002 ER PT B AU Prior, M Saylor, R Walyus, K AF Prior, M Saylor, R Walyus, K BE Miau, JJ Holdaway, R TI Autonomous command operations of the WIRE spacecraft SO REDUCING THE COST OF SPACECRAFT GROUND SYSTEMS AND OPERATIONS SE SPACE TECHNOLOGY PROCEEDINGS LA English DT Proceedings Paper CT 3rd International Symposium on Reducing the Cost of Spacecraft Ground Systems and Operations CY MAR 22-24, 1999 CL TAINAN, TAIWAN SP Natl Cheng Kung Univ, Inst Aeronaut & Astronaut DE automation; satellite operations; low-cost operations AB This paper presents the end-to-end design architecture for an autonomous commanding capability to be used on the Wide Field Infrared Explorer (WIRE) mission for the uplink of command loads during unattended station contacts. The WIRE mission is the fifth and final mission of NASA's Goddard Space Flight Center Small Explorer (SMEX) series to be launched in March of 1999. Its primary mission is the targeting of deep space fields using an ultra-cooled infrared telescope. Due to its mission design WIRE command loads are large (approximately 40 Kbytes per 24 hours) and must be performed daily. To reduce the cost of mission operations support that would be required in order to uplink command loads, the WIRE Flight Operations Team has implemented an autonomous command loading capability. This capability allows completely unattended operations over a typical two-day weekend period. The key factors driving design and implementation of this capability were: 1) Integration with already existing ground system autonomous capabilities and systems, 2) The desire to evolve autonomous operations capabilities based upon previous SMEX operations experience - specifically the TRACE mission, 3) Integration with ground station operations - both autonomous and man-tended, 4) Low cost and quick implementation, and 5) End-to-end system robustness. A trade-off study was performed to examine these factors in light of the low-cost, higher-risk SMEX mission philosophy. The study concluded that a STOL (Spacecraft Test and Operations Language) based script, highly integrated with ether scripts used to perform autonomous operations, was best suited given the budget and goals of the mission. Each of these factors is discussed in addition to use of the TRACE mission as a testbed for autonomous commanding prior to implementation on WIRE. The capabilities implemented on the WIRE mission are an example of a low-cost, robust, and efficient method for autonomous command loading when implemented with other autonomous features of the ground system. They can be used as a design and implementation template by other missions interested in evolving toward autonomous and lower cost operations. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Prior, M (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS BN 0-7923-6174-1 J9 SPACE TECHNOL PROC PY 2000 VL 3 BP 79 EP 86 PG 8 WC Engineering, Aerospace SC Engineering GA BR12Q UT WOS:000165710600011 ER PT B AU Breed, J Baker, P Chu, KD Starr, C Fox, J Baitinger, M AF Breed, J Baker, P Chu, KD Starr, C Fox, J Baitinger, M BE Miau, JJ Holdaway, R TI The Spacecraft Emergency Response System (SERS) for autonomous mission operations SO REDUCING THE COST OF SPACECRAFT GROUND SYSTEMS AND OPERATIONS SE SPACE TECHNOLOGY PROCEEDINGS LA English DT Proceedings Paper CT 3rd International Symposium on Reducing the Cost of Spacecraft Ground Systems and Operations CY MAR 22-24, 1999 CL TAINAN, TAIWAN SP Natl Cheng Kung Univ, Inst Aeronaut & Astronaut DE emergency notification; autonomous operation; lights-out; Web-based; groupware; 2-way paging; Lotus Notes; Domino server AB Today, most mission operations are geared toward lowering cost through unmanned operations. 7-day/24-hour operations are reduced to either 5-day/8-hour operations or become totally autonomous, especially for deep-space missions. Proper and effective notification during a spacecraft emergency could mean success or failure for an entire mission. The Spacecraft Emergency Response System (SERS) is a tool designed for autonomous mission operations. The SERS automatically contacts on-call personnel as needed when crises occur, either on-board the spacecraft or within the automated ground systems. Plus, the SERS provides a group-ware solution to facilitate the work of the person(s) contacted. The SERS is independent of the spacecraft's automated ground system. It receives and catalogues reports for various ground system components in near real-time. Then, based on easily configurable parameters, the SERS determines whom, if anyone, should be alerted. Alerts may be issued either via Sky-Tel 2-way pager, Telephony, or e-mail. The alerted personnel can then review and respond to the spacecraft anomalies through the Netscape Internet Web Browser, or directly review and respond from the Sky-Tel 2-way pager. To date, nine missions have chosen the SERS for its adaptability to various ground systems and its low-cost commercial off-the-shelf availability. Research efforts continue to add collaboration tools such as white-boarding, video conferencing, and palm-top devices to the SERS system. For details, please visit our NASA Web site at: http://groucho.gsfc.nasa.gov/Code 520/Code 522/Projects/VMOC/vmocers.html". C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Chu, KD (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS BN 0-7923-6174-1 J9 SPACE TECHNOL PROC PY 2000 VL 3 BP 105 EP 112 PG 8 WC Engineering, Aerospace SC Engineering GA BR12Q UT WOS:000165710600014 ER PT B AU Dodd, S Gustavson, R AF Dodd, S Gustavson, R BE Miau, JJ Holdaway, R TI Flying Cassini with virtual operations teams SO REDUCING THE COST OF SPACECRAFT GROUND SYSTEMS AND OPERATIONS SE SPACE TECHNOLOGY PROCEEDINGS LA English DT Proceedings Paper CT 3rd International Symposium on Reducing the Cost of Spacecraft Ground Systems and Operations CY MAR 22-24, 1999 CL TAINAN, TAIWAN SP Natl Cheng Kung Univ, Inst Aeronaut & Astronaut DE virtual team; distributed operations; uplink operations; sequencing; mission planning; empowerment AB The Cassini Program's challenge is to fly a large, complex mission with a reduced operations budget. A consequence of the reduced budget is elimination of the large, centrally located group traditionally used for uplink operations. Instead, responsibility for completing parts of the uplink function is distributed throughout the Program. A critical strategy employed to handle this challenge is the use of Virtual Uplink Operations Teams. A Virtual Team is comprised of a group of people with the necessary mix of engineering and science expertise who come together for the purpose of building a specific uplink product. These people are drawn from throughout the Cassini Program and participate across a large geographical area (from Germany to the West coast of the USA), covering ten time zones. The participants will often split their time between participating in the Virtual Team and accomplishing their core responsibilities, requiring significant planning and time management. When the particular uplink product task is complete, the Virtual Team disbands and the members turn back to their home organization element for future work assignments. This time-sharing of employees is used on Cassini to build mission planning products, via the Mission Planning Virtual Team, and sequencing products and monitoring of the sequence execution, via the Sequence Virtual Team. This challenging, multitasking approach allows efficient use of personnel in a resource constrained environment. C1 CALTECH, Jet Prop Lab, NASA, Pasadena, CA 91109 USA. RP Dodd, S (reprint author), CALTECH, Jet Prop Lab, NASA, 4800 Oak Grove Dr,M-S 230-101, Pasadena, CA 91109 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS BN 0-7923-6174-1 J9 SPACE TECHNOL PROC PY 2000 VL 3 BP 161 EP 167 PG 7 WC Engineering, Aerospace SC Engineering GA BR12Q UT WOS:000165710600021 ER PT B AU Mirchandani, C Nguyen, D AF Mirchandani, C Nguyen, D BE Miau, JJ Holdaway, R TI Low-cost, high-rate data processing SO REDUCING THE COST OF SPACECRAFT GROUND SYSTEMS AND OPERATIONS SE SPACE TECHNOLOGY PROCEEDINGS LA English DT Proceedings Paper CT 3rd International Symposium on Reducing the Cost of Spacecraft Ground Systems and Operations CY MAR 22-24, 1999 CL TAINAN, TAIWAN SP Natl Cheng Kung Univ, Inst Aeronaut & Astronaut AB The next generation telemetry system has been prototyped at GSFC. This High Rate Prototype (HRP) implementation uses a set of commercial and custom subsystem components based on state-of-the-art Very Large Scale Integration (VLSI) elements and advanced digital system technologies. It is the application of these technologies, together with standardized telemetry formats, that make it possible to build a high-performance telemetry processing systems at low cost in a short development cycle. Workstations running standard UNIX O/S, (DEC 4100 with DEC UNIX or better). The system architecture is based on the Peripheral Component Interconnect (PCI) bus and VLSI Application-Specific Integrated Circuits(ASICs). These ASICs perform frame synchronization, bit-transition density decoding, cyclic redundancy code (CRC) error checking, Reed-Solomon error detection/correction, data unit sorting, packet extraction, annotation and other service processing at rates of up to and greater than 150 Mbps sustained. ASICs are also used for (the digital reception of Intermediate Frequency (IF)) telemetry as well as the spacecraft command interface for commands and data simulations. The HRP supports both the conventional CCSDS packet telemetry recommendations, which define telemetry Transfer Frames and source packet formats, and the CCSDS Advanced Orbiting Systems (AOS) recommendations, which define telemetry in the form of Coded Virtual Channel Data Units (CVCDU), AOS service units, and source packet formats. This paper will briefly discuss the growth of the ground satellite communication systems from the traditional architectures. It will describe the technological in-roads made by the Goddard Space Flight Center's (GSFC) Data Systems Technology Division (DSTD) to bring the science data from the satellite directly to the user's desktop, rapidly and at low cost. Essentially, the paper will describe the next generation "desktop" system, it's architecture and processing capabilities, which provide autonomous high-performance telemetry acquisition at the least possible cost. The paper will also provide a glimpse into the future of data processing using FPGAs as flexible level 1 and higher level processing elements within the same system, and the use of these systems by data archiving and distribution entities. It is envisioned that many users of the National Polar Orbiting Environmental Satellites System (NPOESS) would benefit from the HRP development effort. C1 NASA, Goddard Space Flight Ctr, Lockheed Martin Space Mission Syst, Greenbelt, MD 20771 USA. RP Mirchandani, C (reprint author), NASA, Goddard Space Flight Ctr, Lockheed Martin Space Mission Syst, Greenbelt, MD 20771 USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS BN 0-7923-6174-1 J9 SPACE TECHNOL PROC PY 2000 VL 3 BP 247 EP 254 PG 8 WC Engineering, Aerospace SC Engineering GA BR12Q UT WOS:000165710600032 ER PT B AU Hsieh, CS AF Hsieh, CS BE Miau, JJ Holdaway, R TI Hubble space telescope servicing mission database SO REDUCING THE COST OF SPACECRAFT GROUND SYSTEMS AND OPERATIONS SE SPACE TECHNOLOGY PROCEEDINGS LA English DT Proceedings Paper CT 3rd International Symposium on Reducing the Cost of Spacecraft Ground Systems and Operations CY MAR 22-24, 1999 CL TAINAN, TAIWAN SP Natl Cheng Kung Univ, Inst Aeronaut & Astronaut AB The Hubble Space Telescope (HST) is one of the most complex spacecrafts ever built. It has many components and was designed for multiple on-orbit servicing missions over a planned mission lifetime. The HST Project Database (PDB), by design, provides a central collection and control point for managing the HST data. The PDB supports both HST nominal operations and servicing missions (SM). In an HST SM, the PDB is a key element in supporting ground system operations. It provides data for flight and ground system development, tests, and training. It also supports post-flight data analysis and trending. This article explores the operational challenges faced by the PDB in supporting the HST SM-3. Special emphasis is given to the areas that ensure mission success with minimum cost, including PDB organization and generation, servicing elements change-out, special design for SM-3, and methodology for PDB verification/certitication. C1 NASA, Goddard Space Flight Ctr, Lockheed Martin Tech Operat Co, Greenbelt, MD 20771 USA. RP Hsieh, CS (reprint author), NASA, Goddard Space Flight Ctr, Lockheed Martin Tech Operat Co, Code 440-8, Greenbelt, MD 20771 USA. NR 1 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS BN 0-7923-6174-1 J9 SPACE TECHNOL PROC PY 2000 VL 3 BP 255 EP 261 PG 7 WC Engineering, Aerospace SC Engineering GA BR12Q UT WOS:000165710600033 ER PT B AU Wilson, RK AF Wilson, RK BE Miau, JJ Holdaway, R TI JPL's approach to low cost mission operations - An overview SO REDUCING THE COST OF SPACECRAFT GROUND SYSTEMS AND OPERATIONS SE SPACE TECHNOLOGY PROCEEDINGS LA English DT Proceedings Paper CT 3rd International Symposium on Reducing the Cost of Spacecraft Ground Systems and Operations CY MAR 22-24, 1999 CL TAINAN, TAIWAN SP Natl Cheng Kung Univ, Inst Aeronaut & Astronaut AB Since the beginning of the NASA space program, each center has been tasked with the design, development and operations of a set of project resources necessary to accomplish its mission objectives. Those resources during the earlier years of the program could have been described as unbounded in comparison with today's resource restrictions. As NASA's program matured in the 1980's and even more so in the early 1990's, it became evident that with the reductions in project resources significant changes were needed if the Jet Propulsion Laboratory (JPL) were to have any program at all. Therefore, since the mid-1980's JPL has undertaken steps in an effort to remain fiscally responsible while maintaining its role as the "leader in the exploration of the universe". Although many approaches have been considered for reducing the cost of operations at JPL, this paper describes several approaches being used and several being evaluated by the Jet Propulsion Laboratory to reduce the cost of mission operations. The approaches to be presented are: (1) development of a re-usable ground data system, (2) build to existing capabilities, (3) a consolidation of adaptation resources, (4) development of a set of standard TMOD Services, and (5) the development of an integrated flight and ground architecture. Each of these approaches will be discussed along with results experienced to date, where appropriate. Because this paper will discuss some approaches which are at present only a "work in process", only results to dale with future expectations will be presented where available. C1 Jet Prop Lab, FDC, Pasadena, CA 91109 USA. RP Wilson, RK (reprint author), Jet Prop Lab, FDC, Mail Stop 301-205D,4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS BN 0-7923-6174-1 J9 SPACE TECHNOL PROC PY 2000 VL 3 BP 359 EP 366 PG 8 WC Engineering, Aerospace SC Engineering GA BR12Q UT WOS:000165710600046 ER PT B AU Shell, E Lue, Y Chu, MI AF Shell, E Lue, Y Chu, MI BE Miau, JJ Holdaway, R TI Spacecraft onboard software maintenance - An effective approach which reduces costs and increases science return SO REDUCING THE COST OF SPACECRAFT GROUND SYSTEMS AND OPERATIONS SE SPACE TECHNOLOGY PROCEEDINGS LA English DT Proceedings Paper CT 3rd International Symposium on Reducing the Cost of Spacecraft Ground Systems and Operations CY MAR 22-24, 1999 CL TAINAN, TAIWAN SP Natl Cheng Kung Univ, Inst Aeronaut & Astronaut DE flight software; flight software maintenance; operations AB Flight software (FSW) is a mission critical element of spacecraft functionality and performance. When ground operations personnel interface to a spacecraft, they are dealing almost entirely with onboard software. This software, even more than ground/flight communications systems, is expected to perform perfectly at all times during all phases of on-orbit mission life. Due to the fact that FSW can be reconfigured and reprogrammed to accommodate new spacecraft conditions, the on-orbit FSW maintenance team is usually significantly responsible for the long-term success of a science mission. Failure of FSW can result in very expensive operations work-around costs and lost science opportunities. There are three basic approaches to staffing on-orbit software maintenance, namely: (1) using the original developers, (2) using mission operations personnel, or (3) assembling a Center of Excellence for multi-spacecraft on-orbit FSW support. This paper explains a National Aeronautics and Space Administration, Goddard Space Flight Center (NASA/GSFC) experience related to the roles of on-orbit FSW maintenance personnel. It identifies the advantages and disadvantages of each of the three approaches to staffing the FSW roles, and demonstrates how a cost efficient on-orbit FSW Maintenance Center of Excellence can be established and maintained with significant return on the investment. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Shell, E (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 1 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS BN 0-7923-6174-1 J9 SPACE TECHNOL PROC PY 2000 VL 3 BP 375 EP 383 PG 9 WC Engineering, Aerospace SC Engineering GA BR12Q UT WOS:000165710600048 ER PT B AU Sherwood, R Wyatt, J Hotz, H Schlutsmeyer, A Sue, M AF Sherwood, R Wyatt, J Hotz, H Schlutsmeyer, A Sue, M BE Miau, JJ Holdaway, R TI Lessons learned during implementation and early operations of the DS1 beacon monitor experiment SO REDUCING THE COST OF SPACECRAFT GROUND SYSTEMS AND OPERATIONS SE SPACE TECHNOLOGY PROCEEDINGS LA English DT Proceedings Paper CT 3rd International Symposium on Reducing the Cost of Spacecraft Ground Systems and Operations CY MAR 22-24, 1999 CL TAINAN, TAIWAN SP Natl Cheng Kung Univ, Inst Aeronaut & Astronaut DE beacon operations; low-cost operations; data summarization; tone messaging; lessons learned AB A new approach to mission operations will be flight validated on NASA's New Millennium Program Deep Space One (DS1) mission which launched in October 1998. The Beacon Monitor Operations Technology is aimed at decreasing the total volume of downlinked engineering telemetry by reducing the frequency of downlink and the volume of data received per pass. Cost savings are achieved by reducing the amount of routine telemetry processing and analysis performed by ground staff. The technology is required for upcoming NASA missions to Pluto, Europa, and possibly some other missions. With beacon monitoring, the spacecraft will assess its own health and will transmit one of four beacon messages each representing a unique frequency tone to inform the ground how urgent it is to track the spacecraft for telemetry. If all conditions are nominal, the tone provides periodic assurance to ground personnel that the mission is proceeding as planned without having to receive and analyze downlinked telemetry. If there is a problem, the tone will indicate that tracking is required and the resulting telemetry will contain a concise summary of what has occurred since the last telemetry pass. The primary components of the technology are a tone monitoring technology, AI-based software for onboard engineering data summarization, and a ground response system. In addition, there is a ground visualization system for telemetry summaries. This paper includes a description of the Beacon monitor concept, the trade-offs with adapting that concept as a technology experiment, the current state of the resulting implementation on DSI, and our lessons learned during the initial checkout phase of the mission. Applicability to future missions is also included. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Sherwood, R (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 7 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS BN 0-7923-6174-1 J9 SPACE TECHNOL PROC PY 2000 VL 3 BP 385 EP 393 PG 9 WC Engineering, Aerospace SC Engineering GA BR12Q UT WOS:000165710600049 ER PT B AU Cangahuala, LA Drain, TR AF Cangahuala, LA Drain, TR BE Miau, JJ Holdaway, R TI Navigation operations with prototype components of an automated real-time spacecraft navigation system SO REDUCING THE COST OF SPACECRAFT GROUND SYSTEMS AND OPERATIONS SE SPACE TECHNOLOGY PROCEEDINGS LA English DT Proceedings Paper CT 3rd International Symposium on Reducing the Cost of Spacecraft Ground Systems and Operations CY MAR 22-24, 1999 CL TAINAN, TAIWAN SP Natl Cheng Kung Univ, Inst Aeronaut & Astronaut DE automation; deep space navigation; mission operations; orbit determination; radio metric data processing AB At present, ground navigation support for interplanetary spacecraft requires human intervention for data pre-processing, filtering, and post-processing activities; these actions must be repeated each time a new batch of data is collected by the ground data system. ARTSN, the Automated Rear-Time Spacecraft Navigation system, is a prototype of a software system for navigation systems that are in the planning stage. It has established new paradigms for deep space navigation operations by introducing new capabilities to the navigation analyst: (1) automated radio metric data validation and correction, (2) real-time monitoring of spacecraft and tracking station performance through radio metric Doppler and range data, (3) real-time orbit and target updates, and (4) "one step" access to trajectory, observable, filter, and mapping information. These capabilities make it possible to demonstrate the feasibility of removing historical latencies in ground-based radio metric data processing and orbit determination tasks. Several projects have taken advantage of the automated data processing, especially during critical mission scenarios such as maneuvers and aerobraking. In one case of aerobraking operations, which occurred over several months, the need for off-hours staffing for tracking data processing was eliminated. Automated orbit determination has been demonstrated as well; the combination of automated data validation and orbit determination, to be performed in 1999, will enable navigation analysts to monitor more missions simultaneously. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Cangahuala, LA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS BN 0-7923-6174-1 J9 SPACE TECHNOL PROC PY 2000 VL 3 BP 409 EP 416 PG 8 WC Engineering, Aerospace SC Engineering GA BR12Q UT WOS:000165710600052 ER PT S AU Iguchi, T Meneghini, R Awaka, J Kozu, T Okamoto, K AF Iguchi, T Meneghini, R Awaka, J Kozu, T Okamoto, K BE Igarashi, T Nakamura, K Shimoda, H Tanaka, T Burrows, JP Nakajima, T Talagrand, O Naeije, MC TI Rain profiling algorithm for TRMM precipitation radar data SO REMOTE SENSING AND APPLICATIONS: EARTH, ATMOSPHERE AND OCEANS SE ADVANCES IN SPACE RESEARCH-SERIES LA English DT Article; Proceedings Paper CT A0 1, A0 3, A1 2 and A2 1 Symposium of COSPAR Scientific Commission A Held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP IGARSS, Int Soc Photogrammetry & Remote Sensing, IEEE, Comm Space Res, NASA, NOAA, US EPA, RSSJ, Ctr European Rech & Format Avancee Calcul Sci, European Space Agcy, European Org Exploitat Meterol Satellites, Natl Space Dev Agcy Japan, NAOO, World Meterol Org, Ctr Natl Etudes Spatiales AB This paper describes the TRMM standard algorithm 2A25 which estimates the instantaneous vertical profile of rain from Precipitation Radar (PR) data. Major challenges in rain profiling from the TRMM PR lie in the corrections for the effects of rain attenuation and non-uniform beam filling (NUBF) and in the rejection of surface clutter. A combination of the Hitschfeld-Bordan and surface reference methods is used to correct the attenuation effect in radar returns. The NUBF effects are estimated from the spatial variations of the estimated total path integral of attenuation from the top of the rain to the surface in the vicinity of the radar beam concerned. This paper outlines the critical part of the algorithm, and shows some results of comparisons of data taken nearly simultaneously by the TRMM PR and a ground-based radar, (C) 2000 COSPAR. Published by Elsevier Science Ltd. C1 Commun Res Labs, Kashima, Ibaraki 3140012, Japan. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Hokkaido Tokai Univ, Minami Ku, Sapporo, Hokkaido 005, Japan. Commun Res Labs, Tokyo 1848795, Japan. RP Iguchi, T (reprint author), Commun Res Labs, 893-1 Hirai, Kashima, Ibaraki 3140012, Japan. RI PMM, JAXA/K-8537-2016 NR 2 TC 27 Z9 29 U1 1 U2 3 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES-SERIES PY 2000 VL 25 IS 5 BP 973 EP 976 DI 10.1016/S0273-1177(99)00933-3 PG 4 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences; Remote Sensing SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences; Remote Sensing GA BP57U UT WOS:000085558100010 ER PT S AU Choudhury, BJ AF Choudhury, BJ BE Gupta, RK TI Carbon-water-energy relations for selected river basins SO REMOTE SENSING FOR LAND SURFACE CHARACTERISATION SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT A3 1 and A3 2 Symposia of COSPAR Scientific Commission A held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP NASA, Indian Space Res Org, European Space Agcy, NOAA, Natl Space Dev Agcy Japan, Int Geosphere Biosphere Programme, World Meteorol Org, UN Environm Programme, UN Food & Agr Org, Int Soc Photogrammetry & Remote Sensing, Third World Acad Sci, Comm Sci & Technol Dev Countries, Int Biosci Networks, CEU, RSS, NRCT, UN Off Outer Space Affairs, World Climate Res Programme, Comm Space Res ID LAND-SURFACE EVAPORATION; GROWTH; SATELLITE; MODEL; RESPIRATION; DATASET; BUDGET; YIELD; CROPS; SOIL AB Total evaporation couples water and energy balance equations, while transpiration, which is the major component of total evaporation over most of the global land surface, is strongly determined by the rate of carbon assimilation. A model combining the rate of carbon assimilation with water and energy balance equations has been developed, and run using satellite and ancillary data for 48-month period (January 1987 to December 1990) over global land surface. Relations between net carbon accumulation by terrestrial plant communities, evaporation, and net radiation are presented for 15 largest river basins of the world, and evaluated against those derived from field measurements. (C) 2000 COSPAR. Published by Elsevier Science Ltd. C1 NASA, Goddard Space Flight Ctr, Hydrol Sci Branch, Lab Hydrospher Proc, Greenbelt, MD 20771 USA. RP Choudhury, BJ (reprint author), NASA, Goddard Space Flight Ctr, Hydrol Sci Branch, Lab Hydrospher Proc, Greenbelt, MD 20771 USA. NR 25 TC 2 Z9 2 U1 1 U2 2 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2000 VL 26 IS 7 BP 1091 EP 1099 DI 10.1016/S0273-1177(99)01124-2 PG 9 WC Engineering, Aerospace; Remote Sensing SC Engineering; Remote Sensing GA BQ23J UT WOS:000087680700013 ER PT S AU Choudhury, BJ AF Choudhury, BJ BE Gupta, RK TI Carbon use efficiency, and net primary productivity of terrestrial vegetation SO REMOTE SENSING FOR LAND SURFACE CHARACTERISATION SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT A3 1 and A3 2 Symposia of COSPAR Scientific Commission A held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP NASA, Indian Space Res Org, European Space Agcy, NOAA, Natl Space Dev Agcy Japan, Int Geosphere Biosphere Programme, World Meteorol Org, UN Environm Programme, UN Food & Agr Org, Int Soc Photogrammetry & Remote Sensing, Third World Acad Sci, Comm Sci & Technol Dev Countries, Int Biosci Networks, CEU, RSS, NRCT, UN Off Outer Space Affairs, World Climate Res Programme, Comm Space Res ID GROWTH; RESPIRATION; MODEL AB The carbon use efficiency (CUE), defined as the ratio of net carbon gain to gross carbon assimilation during a period, is a highly significant determinant of primary production of terrestrial plant communities. Available data for CUE is summarized. Then, a model for gross assimilation has been run using satellite and ancillary data to calculate annual net carbon gain or net primary productivity for the global land surface during four year period (1987-1990). The results are compared with other estimates. Interannual variability of 30-50% is found in some of the latitude bands. (C) 2000 COSPAR. Published by Elsevier Science Ltd. C1 NASA, Goddard Space Flight Ctr, Hydrol Sci Branch, Lab Hydrospher Proc, Greenbelt, MD 20771 USA. RP Choudhury, BJ (reprint author), NASA, Goddard Space Flight Ctr, Hydrol Sci Branch, Lab Hydrospher Proc, Greenbelt, MD 20771 USA. NR 14 TC 7 Z9 8 U1 2 U2 7 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2000 VL 26 IS 7 BP 1105 EP 1108 DI 10.1016/S0273-1177(99)01126-6 PG 4 WC Engineering, Aerospace; Remote Sensing SC Engineering; Remote Sensing GA BQ23J UT WOS:000087680700015 ER PT S AU Krueger, AJ Schaefer, SJ Krotkov, N Bluth, G Barker, S AF Krueger, AJ Schaefer, SJ Krotkov, N Bluth, G Barker, S BE MouginisMark, PJ Crisp, JA Fink, JH TI Ultraviolet remote sensing of volcanic emissions SO REMOTE SENSING OF ACTIVE VOLCANISM SE GEOPHYSICAL MONOGRAPH SERIES LA English DT Proceedings Paper CT Fall Meeting of the American-Geophysical-Union CY 1997 CL SAN FRANCISCO, CA SP Amer Geophys Union ID OZONE MAPPING SPECTROMETER; SULFUR-DIOXIDE EMISSIONS; ATMOSPHERIC SULFUR; EXPLOSIVE VOLCANISM; ERUPTION CLOUD; ASH CLOUDS; TOMS; RETRIEVALS; RABAUL; AVHRR AB Satellite-based ultraviolet remote sensing of volcanic eruptions has produced quantitative measurements of the mass of sulfur dioxide and ash in volcanic clouds by accounting for ozone absorption and Rayleigh scattering in the atmosphere. These retrieval techniques were developed with data from the total ozone mapping spectrometer (TOMS) instruments on American, Russian, and Japanese satellites. The sulfur dioxide retrievals have been validated against ground-based Brewer and COSPEC measurements. The ash mass retrievals are in agreement with AVHRR two-band infrared ash retrievals. Daily satellite monitoring has detected, tracked, and quantified SO2 emissions from a wide range of eruptive activity, from highly explosive to effusive types, and has produced an unprecedented 20-year record of global volcanism. Primary findings from the TOMS data are (1) observations of "excess sulfur" over that liberated during liquid-phase degassing have indicated the existence of a volatile phase in pre-erupted magma; (2) indirect evidence for co-erupted H2S gas from apparent increase in SO2 mass in drifting clouds; (3) insights into the removal rates Of SO2 from the atmosphere, interactions with co-emitted ash particles, and responses to meteorological conditions; and (4) potential operational application of sulfur dioxide and ash detection for aviation hazard mitigation. C1 NASA, Goddard Space Flight Ctr, Earth Sci Directorate, Greenbelt, MD 20771 USA. RP Krueger, AJ (reprint author), NASA, Goddard Space Flight Ctr, Earth Sci Directorate, Code 916, Greenbelt, MD 20771 USA. RI Krotkov, Nickolay/E-1541-2012 OI Krotkov, Nickolay/0000-0001-6170-6750 NR 60 TC 32 Z9 32 U1 2 U2 11 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0065-8448 BN 0-87590-099-2 J9 GEOPH MONOG SERIES PY 2000 VL 116 BP 25 EP 43 PG 19 WC Geochemistry & Geophysics; Remote Sensing SC Geochemistry & Geophysics; Remote Sensing GA BS62N UT WOS:000170596800003 ER PT S AU Realmuto, VJ AF Realmuto, VJ BE MouginisMark, PJ Crisp, JA Fink, JH TI The potential use of earth observing system data to monitor the passive emission of sulfur dioxide from volcanoes SO REMOTE SENSING OF ACTIVE VOLCANISM SE GEOPHYSICAL MONOGRAPH SERIES LA English DT Proceedings Paper CT Fall Meeting of the American-Geophysical-Union CY 1997 CL SAN FRANCISCO, CA SP Amer Geophys Union ID MOUNT-ST-HELENS; IMAGING SPECTRORADIOMETER MODIS; OZONE MAPPING SPECTROMETER; SATELLITE-OBSERVATIONS; PINATUBO ERUPTION; AUGUSTINE VOLCANO; ASH CLOUDS; PLUMES; ETNA; ASTER AB Long-term monitoring of the passive emission of SO2 is essential if volcanologists are to establish baseline emission rates and correlate changes in emission rates with the behavior of a volcano. The synoptic perspective, rapid mode of data acquisition, and short revisit intervals of satellite-based remote sensing are well-suited for the monitoring Of SO2 emissions. This paper evaluates the potential of detecting passive SO2 emissions from space using the data anticipated from the advanced spaceborne thermal emission and reflection radiometer (ASTER) and moderate resolution imaging spectroradiometer (MODIS). ASTER and MODIS are two of the instruments aboard the first satellite of NASA's Earth Observing System, which is scheduled for a launch in 1999. Image data acquired with NASA's airborne thermal infrared multispectral scanner (TIMS) over Kilauea and Mount Etna volcanoes were used to simulate the ASTER and MODIS data products. These simulations suggest that both ASTER and MODIS will detect Etna-scale plumes, while reliable detection of Kilauea-scale plumes may be limited to ASTER. In addition, both instruments should be able to detect stratospheric SO2 clouds of a size and concentration similar to those created by the August 1992 eruption of Mount Spurr. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Realmuto, VJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 68 TC 14 Z9 14 U1 0 U2 1 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0065-8448 BN 0-87590-099-2 J9 GEOPH MONOG SERIES PY 2000 VL 116 BP 101 EP 115 PG 15 WC Geochemistry & Geophysics; Remote Sensing SC Geochemistry & Geophysics; Remote Sensing GA BS62N UT WOS:000170596800007 ER PT S AU Hofton, MA Minster, JB Ridgway, JR Williams, NP Blair, JB Rabine, DL Bufton, JL AF Hofton, MA Minster, JB Ridgway, JR Williams, NP Blair, JB Rabine, DL Bufton, JL BE MouginisMark, PJ Crisp, JA Fink, JH TI Using airborne laser altimetry to detect topographic change at Long Valley Caldera, California SO REMOTE SENSING OF ACTIVE VOLCANISM SE GEOPHYSICAL MONOGRAPH SERIES LA English DT Proceedings Paper CT Fall Meeting of the American-Geophysical-Union CY 1997 CL SAN FRANCISCO, CA SP Amer Geophys Union ID EASTERN CALIFORNIA; DEFORMATION; INFLATION; GPS AB The topography of the Long Valley caldera, California, was sampled using airborne laser altimetry in 1993, 1995, and 1997 to test the feasibility of using airborne laser altimetry for monitoring deformation of volcanic origin. Results show the laser altimeters are able to resolve subtle topographic features such as a gradual slope and to detect small transient changes in lake elevation. Crossover and repeat pass analyses of laser tracks indicate decimeter-level vertical precision is obtained over flat and low-sloped terrain for altimeter systems performing waveform. digitization. Comparisons with complementary, ground-based GPS data at a site close to Bishop airport indicate that the laser and GPS-derived elevations agree to within the error inherent in the measurement and that horizontal locations agree to within the radius of the laser footprint. A comparison of the data at two sites, one where no change and the other where the maximum amount of vertical uplift is expected, indicates similar to 10 cm of relative uplift occurred 1993-1997, in line with predictions from continuous GPS measurements in the region. Extensive terrain mapping flights during the 1995 and 1997 missions demonstrate some of the unique abilities of laser altimetry; the straightforward creation of high resolution, high accuracy digital elevation models of overflown terrain, and the ability to determine ground topography in the presence of significant ground cover such as dense tree canopies. These capabilities make laser altimetry an attractive technique for quantifying topographic change of volcanic origin, especially in forested regions of the world where other remote sensing instruments have difficulty detecting the underlying topography. C1 NASA, Goddard Space Flight Ctr, Lab Terr Phys, Greenbelt, MD 20771 USA. Univ Calif San Diego, Scripps Inst Oceanog, Cecil H & Ida M Green Inst Geophys & Planetary Ph, La Jolla, CA 92093 USA. RP Hofton, MA (reprint author), Univ Maryland, Dept Geog, College Pk, MD 20742 USA. RI Rabine, David/C-9626-2013; Blair, James/D-3881-2013 NR 32 TC 2 Z9 3 U1 1 U2 1 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0065-8448 BN 0-87590-099-2 J9 GEOPH MONOG SERIES PY 2000 VL 116 BP 249 EP 264 PG 16 WC Geochemistry & Geophysics; Remote Sensing SC Geochemistry & Geophysics; Remote Sensing GA BS62N UT WOS:000170596800014 ER PT J AU Gonzalez-Zugasti, JP Otto, KN Baker, JD AF Gonzalez-Zugasti, JP Otto, KN Baker, JD TI A method for architecting product platforms SO RESEARCH IN ENGINEERING DESIGN-THEORY APPLICATIONS AND CONCURRENT ENGINEERING LA English DT Article DE product families; product platforms; product portfolio architecture AB Consider a group of products sharing common parts and assemblies. The products in question we call a product family, and the common elements, the platform. In this paper, we present a method for designing product platforms and the derived family that takes into consideration both the technical performance requirements as well as the cost of the product family. The design of a platform-based product family is formulated as a general optimization problem in which the advantages of designing a common platform must be balanced against the constraints of the individual product variants and constraints of the family as a whole. This optimization approach forms the basis for a practical implementation as an interactive, team-based negotiation model for designing a family of interplanetary spacecraft based on a common platform. The approach is used to consider and specify different subsystems that could be made common to all the missions. It is also used to evaluate the impact of those platform design decisions on the performance of the product family, and thus be able to select from among feasible platform designs. C1 MIT, Engn Design Res Lab, Cambridge, MA 02139 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Otto, KN (reprint author), MIT, Engn Design Res Lab, 77 Massachusetts Ave,Room 3-449, Cambridge, MA 02139 USA. NR 12 TC 92 Z9 107 U1 0 U2 12 PU SPRINGER-VERLAG LONDON LTD PI GODALMING PA SWEETAPPLE HOUSE CATTESHALL ROAD, GODALMING GU7 3DJ, SURREY, ENGLAND SN 0934-9839 J9 RES ENG DES JI Res. Eng. Design-Theory Appl. Concurrent Eng. PY 2000 VL 12 IS 2 BP 61 EP 72 DI 10.1007/s001630050024 PG 12 WC Engineering, Multidisciplinary; Engineering, Industrial; Engineering, Manufacturing SC Engineering GA 381UX UT WOS:000165782800001 ER PT S AU Madaras, EI Anastasi, RF AF Madaras, EI Anastasi, RF BE Thompson, DO Chimenti, DE TI Pseudo-random modulation of a laser diode for generating ultrasonic longitudinal waves SO REVIEW OF PROGRESS IN QUANTITATIVE NONDESTRUCTIVE EVALUATION, VOLS 19A AND 19B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 26th Annual Review of Progress in Quantitative Nondestructive Evaluation CY JUL 25-30, 1999 CL MONTREAL, CANADA SP Iowa State Univ, Ctr NDE, Ind Mat Inst, Natl Res Council Canada, US DOE, Ames Lab, Amer Soc Nondestruct Testing, NASA, Natl Inst Stand & Technol, Fed Aviat Adm, Natl Sci Fdn Ind, Univ Cooperat Res Ctr C1 USA, Vehicle Technol Ctr, ARL, AMSRL,VT,S,NASA,Langley Res Ctr, Hampton, VA 23681 USA. RP Madaras, EI (reprint author), USA, Vehicle Technol Ctr, ARL, AMSRL,VT,S,NASA,Langley Res Ctr, Mail Stop 231, Hampton, VA 23681 USA. NR 11 TC 5 Z9 5 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-930-0 J9 AIP CONF PROC PY 2000 VL 509 BP 303 EP 309 PG 7 WC Acoustics; Engineering, Electrical & Electronic; Materials Science, Characterization & Testing; Physics, Applied SC Acoustics; Engineering; Materials Science; Physics GA BQ87X UT WOS:000089913700037 ER PT S AU Namkung, M Wincheski, F Nath, S Fulton, JP AF Namkung, M Wincheski, F Nath, S Fulton, JP BE Thompson, DO Chimenti, DE TI Characteristics of electromagnetic pulse propagation in metal SO REVIEW OF PROGRESS IN QUANTITATIVE NONDESTRUCTIVE EVALUATION, VOLS 19A AND 19B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 26th Annual Review of Progress in Quantitative Nondestructive Evaluation CY JUL 25-30, 1999 CL MONTREAL, CANADA SP Iowa State Univ, Ctr NDE, Ind Mat Inst, Natl Res Council Canada, US DOE, Ames Lab, Amer Soc Nondestruct Testing, NASA, Natl Inst Stand & Technol, Fed Aviat Adm, Natl Sci Fdn Ind, Univ Cooperat Res Ctr C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Namkung, M (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. RI Namkung, Min/E-1533-2012 NR 4 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-930-0 J9 AIP CONF PROC PY 2000 VL 509 BP 409 EP 416 PG 8 WC Acoustics; Engineering, Electrical & Electronic; Materials Science, Characterization & Testing; Physics, Applied SC Acoustics; Engineering; Materials Science; Physics GA BQ87X UT WOS:000089913700050 ER PT S AU Wincheski, B Namkung, M AF Wincheski, B Namkung, M BE Thompson, DO Chimenti, DE TI Deep flaw detection with giant magnetoresistive (GMR) based self-nulling probe SO REVIEW OF PROGRESS IN QUANTITATIVE NONDESTRUCTIVE EVALUATION, VOLS 19A AND 19B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 26th Annual Review of Progress in Quantitative Nondestructive Evaluation CY JUL 25-30, 1999 CL MONTREAL, CANADA SP Iowa State Univ, Ctr NDE, Ind Mat Inst, Natl Res Council Canada, US DOE, Ames Lab, Amer Soc Nondestruct Testing, NASA, Natl Inst Stand & Technol, Fed Aviat Adm, Natl Sci Fdn Ind, Univ Cooperat Res Ctr C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Wincheski, B (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. RI Namkung, Min/E-1533-2012 NR 9 TC 16 Z9 16 U1 0 U2 1 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-930-0 J9 AIP CONF PROC PY 2000 VL 509 BP 465 EP 472 PG 8 WC Acoustics; Engineering, Electrical & Electronic; Materials Science, Characterization & Testing; Physics, Applied SC Acoustics; Engineering; Materials Science; Physics GA BQ87X UT WOS:000089913700057 ER PT S AU Plotnikov, YA Winfree, WP AF Plotnikov, YA Winfree, WP BE Thompson, DO Chimenti, DE TI Temporal treatment of a thermal response for defect depth estimation SO REVIEW OF PROGRESS IN QUANTITATIVE NONDESTRUCTIVE EVALUATION, VOLS 19A AND 19B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 26th Annual Review of Progress in Quantitative Nondestructive Evaluation CY JUL 25-30, 1999 CL MONTREAL, CANADA SP Iowa State Univ, Ctr NDE, Ind Mat Inst, Natl Res Council Canada, US DOE, Ames Lab, Amer Soc Nondestruct Testing, NASA, Natl Inst Stand & Technol, Fed Aviat Adm, Natl Sci Fdn Ind, Univ Cooperat Res Ctr ID COMPOSITES C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Plotnikov, YA (reprint author), NASA, Langley Res Ctr, MS 231, Hampton, VA 23681 USA. NR 7 TC 8 Z9 8 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-930-0 J9 AIP CONF PROC PY 2000 VL 509 BP 587 EP 594 PG 8 WC Acoustics; Engineering, Electrical & Electronic; Materials Science, Characterization & Testing; Physics, Applied SC Acoustics; Engineering; Materials Science; Physics GA BQ87X UT WOS:000089913700074 ER PT S AU Winfree, WP Cramer, KE AF Winfree, WP Cramer, KE BE Thompson, DO Chimenti, DE TI Reconstruction of back surface profiles from scanned thermal line source data using neural networks SO REVIEW OF PROGRESS IN QUANTITATIVE NONDESTRUCTIVE EVALUATION, VOLS 19A AND 19B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 26th Annual Review of Progress in Quantitative Nondestructive Evaluation CY JUL 25-30, 1999 CL MONTREAL, CANADA SP Iowa State Univ, Ctr NDE, Ind Mat Inst, Natl Res Council Canada, US DOE, Ames Lab, Amer Soc Nondestruct Testing, NASA, Natl Inst Stand & Technol, Fed Aviat Adm, Natl Sci Fdn Ind, Univ Cooperat Res Ctr ID TRANSIENT THERMOGRAPHY; IMAGES; SHAPE C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Winfree, WP (reprint author), NASA, Langley Res Ctr, MS 231, Hampton, VA 23681 USA. NR 13 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-930-0 J9 AIP CONF PROC PY 2000 VL 509 BP 691 EP 698 PG 8 WC Acoustics; Engineering, Electrical & Electronic; Materials Science, Characterization & Testing; Physics, Applied SC Acoustics; Engineering; Materials Science; Physics GA BQ87X UT WOS:000089913700088 ER PT S AU Johnston, PH Boghosian, JS Hinders, MK AF Johnston, PH Boghosian, JS Hinders, MK BE Thompson, DO Chimenti, DE TI Toward the measurement of angular dependence of in-plane ultrasonic properties of unidirectional carbon fiber reinforced composites SO REVIEW OF PROGRESS IN QUANTITATIVE NONDESTRUCTIVE EVALUATION, VOLS 19A AND 19B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 26th Annual Review of Progress in Quantitative Nondestructive Evaluation CY JUL 25-30, 1999 CL MONTREAL, CANADA SP Iowa State Univ, Ctr NDE, Ind Mat Inst, Natl Res Council Canada, US DOE, Ames Lab, Amer Soc Nondestruct Testing, NASA, Natl Inst Stand & Technol, Fed Aviat Adm, Natl Sci Fdn Ind, Univ Cooperat Res Ctr C1 NASA, Langley Res Ctr, Nondestruct Evaluat Sci Branch, Hampton, VA 23681 USA. RP Johnston, PH (reprint author), NASA, Langley Res Ctr, Nondestruct Evaluat Sci Branch, Hampton, VA 23681 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-930-0 J9 AIP CONF PROC PY 2000 VL 509 BP 1135 EP 1142 PG 8 WC Acoustics; Engineering, Electrical & Electronic; Materials Science, Characterization & Testing; Physics, Applied SC Acoustics; Engineering; Materials Science; Physics GA BQ87X UT WOS:000089913700146 ER PT S AU Seale, MD Madaras, EI AF Seale, MD Madaras, EI BE Thompson, DO Chimenti, DE TI Lamb wave assessment of stiffness degradation in fatigued composites SO REVIEW OF PROGRESS IN QUANTITATIVE NONDESTRUCTIVE EVALUATION, VOLS 19A AND 19B SE AIP Conference Proceedings LA English DT Proceedings Paper CT 26th Annual Review of Progress in Quantitative Nondestructive Evaluation CY JUL 25-30, 1999 CL MONTREAL, CANADA SP Iowa State Univ, Ctr NDE, Ind Mat Inst, Natl Res Council Canada, US DOE, Ames Lab, Amer Soc Nondestruct Testing, NASA, Natl Inst Stand & Technol, Fed Aviat Adm, Natl Sci Fdn Ind, Univ Cooperat Res Ctr C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Seale, MD (reprint author), NASA, Langley Res Ctr, Mail Stop 231, Hampton, VA 23681 USA. EM e.i.madaras@larc.nasa.gov NR 13 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-930-0 J9 AIP CONF PROC PY 2000 VL 509 BP 1223 EP 1230 PG 8 WC Acoustics; Engineering, Electrical & Electronic; Materials Science, Characterization & Testing; Physics, Applied SC Acoustics; Engineering; Materials Science; Physics GA BQ87X UT WOS:000089913700157 ER PT S AU Cantrell, JH Yost, WT AF Cantrell, JH Yost, WT BE Thompson, DO Chimenti, DE TI Nonlinear acoustical assessment of precipitate nucleation and growth in aluminum alloy 2024 SO REVIEW OF PROGRESS IN QUANTITATIVE NONDESTRUCTIVE EVALUATION, VOLS 19A AND 19B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 26th Annual Review of Progress in Quantitative Nondestructive Evaluation CY JUL 25-30, 1999 CL MONTREAL, CANADA SP Iowa State Univ, Ctr NDE, Ind Mat Inst, Natl Res Council Canada, US DOE, Ames Lab, Amer Soc Nondestruct Testing, NASA, Natl Inst Stand & Technol, Fed Aviat Adm, Natl Sci Fdn Ind, Univ Cooperat Res Ctr C1 NASA, Langley Res Ctr, Nondestruct Evaluat Sci Branch, Hampton, VA 23681 USA. RP Cantrell, JH (reprint author), NASA, Langley Res Ctr, Nondestruct Evaluat Sci Branch, Hampton, VA 23681 USA. NR 8 TC 0 Z9 1 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-930-0 J9 AIP CONF PROC PY 2000 VL 509 BP 1375 EP 1380 PG 6 WC Acoustics; Engineering, Electrical & Electronic; Materials Science, Characterization & Testing; Physics, Applied SC Acoustics; Engineering; Materials Science; Physics GA BQ87X UT WOS:000089913700176 ER PT S AU Yost, WT Cantrell, JH AF Yost, WT Cantrell, JH BE Thompson, DO Chimenti, DE TI Fatigue cycle induced variation of the acoustic nonlinearity parameter in aluminum alloy 2024 SO REVIEW OF PROGRESS IN QUANTITATIVE NONDESTRUCTIVE EVALUATION, VOLS 19A AND 19B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 26th Annual Review of Progress in Quantitative Nondestructive Evaluation CY JUL 25-30, 1999 CL MONTREAL, CANADA SP Iowa State Univ, Ctr NDE, Ind Mat Inst, Natl Res Council Canada, US DOE, Ames Lab, Amer Soc Nondestruct Testing, NASA, Natl Inst Stand & Technol, Fed Aviat Adm, Natl Sci Fdn Ind, Univ Cooperat Res Ctr C1 NASA, Langley Res Ctr, Nondestruct Evaluat Sci Branch, Hampton, VA 23681 USA. RP Yost, WT (reprint author), NASA, Langley Res Ctr, Nondestruct Evaluat Sci Branch, Hampton, VA 23681 USA. NR 11 TC 3 Z9 4 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-930-0 J9 AIP CONF PROC PY 2000 VL 509 BP 1381 EP 1386 PG 6 WC Acoustics; Engineering, Electrical & Electronic; Materials Science, Characterization & Testing; Physics, Applied SC Acoustics; Engineering; Materials Science; Physics GA BQ87X UT WOS:000089913700177 ER PT S AU Roth, DJ Kautz, HE Abel, PB Whalen, MF Hendricks, JL Bodis, JR AF Roth, DJ Kautz, HE Abel, PB Whalen, MF Hendricks, JL Bodis, JR BE Thompson, DO Chimenti, DE TI 3-D surface profiling using focused air-coupled ultrasound SO REVIEW OF PROGRESS IN QUANTITATIVE NONDESTRUCTIVE EVALUATION, VOLS 19A AND 19B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 26th Annual Review of Progress in Quantitative Nondestructive Evaluation CY JUL 25-30, 1999 CL MONTREAL, CANADA SP Iowa State Univ, Ctr NDE, Ind Mat Inst, Natl Res Council Canada, US DOE, Ames Lab, Amer Soc Nondestruct Testing, NASA, Natl Inst Stand & Technol, Fed Aviat Adm, Natl Sci Fdn Ind, Univ Cooperat Res Ctr C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Roth, DJ (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 6 TC 1 Z9 1 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-930-0 J9 AIP CONF PROC PY 2000 VL 509 BP 1787 EP 1792 PG 6 WC Acoustics; Engineering, Electrical & Electronic; Materials Science, Characterization & Testing; Physics, Applied SC Acoustics; Engineering; Materials Science; Physics GA BQ87X UT WOS:000089913700229 ER PT S AU Zalameda, JN Winfree, WP AF Zalameda, JN Winfree, WP BE Thompson, DO Chimenti, DE TI Quartz lamp characterization for quantitative thermal nondestructive evaluation SO REVIEW OF PROGRESS IN QUANTITATIVE NONDESTRUCTIVE EVALUATION, VOLS 19A AND 19B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 26th Annual Review of Progress in Quantitative Nondestructive Evaluation CY JUL 25-30, 1999 CL MONTREAL, CANADA SP Iowa State Univ, Ctr NDE, Ind Mat Inst, Natl Res Council Canada, US DOE, Ames Lab, Amer Soc Nondestruct Testing, NASA, Natl Inst Stand & Technol, Fed Aviat Adm, Natl Sci Fdn Ind, Univ Cooperat Res Ctr C1 NASA, Langley Res Ctr MS231, Vehicle Technol Directorate, USA Res Lab, Hampton, VA 23681 USA. RP Zalameda, JN (reprint author), NASA, Langley Res Ctr MS231, Vehicle Technol Directorate, USA Res Lab, Hampton, VA 23681 USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-930-0 J9 AIP CONF PROC PY 2000 VL 509 BP 1889 EP 1896 PG 8 WC Acoustics; Engineering, Electrical & Electronic; Materials Science, Characterization & Testing; Physics, Applied SC Acoustics; Engineering; Materials Science; Physics GA BQ87X UT WOS:000089913700242 ER PT S AU Lopatin, CM Froggatt, M Childers, BA Rogowski, RS AF Lopatin, CM Froggatt, M Childers, BA Rogowski, RS BE Adams, PJ Elsworth, SA Petkauskos, MJ Walton, TC TI Distributed measurement of strain in smart materials using Rayleigh scattering SO REVOLUTIONARY MATERIALS: TECHNOLOGY AND ECONOMICS SE INTERNATIONAL SAMPE TECHNICAL CONFERENCE SERIES LA English DT Proceedings Paper CT 32nd International SAMPE Technical Conference CY NOV 05-09, 2000 CL BOSTON, MA SP Soc Advancement Mat & Process Engn DE smart materials; sensors; composite materials ID OPTICAL-FIBER; SENSORS AB Rayleigh scattering is used to determine distributed strain along a single mode optical fiber. The technique consists of scanning a laser diode source to form an interference pattern between Rayleigh scattered light in the sensing fiber and a reference reflector. This pattern is then Fourier transformed to obtain the spatial distribution of Rayleigh scattering along the fiber. Changes in this distribution during sample loading are then interpreted in terms of strains along the fiber. The technique was demonstrated in several configurations, including beam bending in tension and compression, near a circular hole in a flat tensile specimen, and embedded in a graphite epoxy specimen. Strains up to 500 microstrain were obtained with a spatial resolution of 1 cm. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Lopatin, CM (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. NR 13 TC 0 Z9 0 U1 0 U2 0 PU SOC ADVANCEMENT MATERIAL & PROCESS ENGINEERING PI COVINA PA 1161 PARKVIEW DR,, COVINA, CA 91724-3748 USA SN 0892-2624 BN 0-938994-89-1 J9 INT SAMPE TECH CONF PY 2000 VL 32 BP 231 EP 241 PG 11 WC Engineering, Aerospace; Materials Science, Multidisciplinary; Materials Science, Characterization & Testing; Materials Science, Coatings & Films; Materials Science, Composites SC Engineering; Materials Science GA BR79P UT WOS:000167557000023 ER PT S AU Johnson, AR Chen, TK AF Johnson, AR Chen, TK BE Adams, PJ Elsworth, SA Petkauskos, MJ Walton, TC TI Coupled thermo-mechanical analyses of dynamically loaded rubber cylinders SO REVOLUTIONARY MATERIALS: TECHNOLOGY AND ECONOMICS SE INTERNATIONAL SAMPE TECHNICAL CONFERENCE SERIES LA English DT Proceedings Paper CT 32nd International SAMPE Technical Conference CY NOV 05-09, 2000 CL BOSTON, MA SP Soc Advancement Mat & Process Engn DE viscoelasticity; structural analysis; thermal analysis ID VISCOELASTIC CONSTITUTIVE MODELS AB A procedure that models coupled thermo-mechanical deformations of viscoelastic rubber cylinders by employing the ABAQUS finite element code is described. Computational simulations of hysteretic heating are presented for several tall and short rubber cylinders both with and without a steel disk at their centers. The cylinders are compressed axially and are then cyclically loaded about the compressed state. The non-uniform hysteretic heating of the rubber cylinders containing a steel disk is presented. The analyses performed suggest that the coupling procedure should be considered for further development as a design tool for rubber degradation studies. C1 NASA, Langley Res Ctr, Analyt & Computat Methods Branch, Res Lab, Hampton, VA 23681 USA. RP Johnson, AR (reprint author), NASA, Langley Res Ctr, Analyt & Computat Methods Branch, Res Lab, MS 240, Hampton, VA 23681 USA. NR 13 TC 0 Z9 0 U1 0 U2 0 PU SOC ADVANCEMENT MATERIAL & PROCESS ENGINEERING PI COVINA PA 1161 PARKVIEW DR,, COVINA, CA 91724-3748 USA SN 0892-2624 BN 0-938994-89-1 J9 INT SAMPE TECH CONF PY 2000 VL 32 BP 360 EP 371 PG 4 WC Engineering, Aerospace; Materials Science, Multidisciplinary; Materials Science, Characterization & Testing; Materials Science, Coatings & Films; Materials Science, Composites SC Engineering; Materials Science GA BR79P UT WOS:000167557000035 ER PT S AU Meador, MA AF Meador, MA BE Adams, PJ Elsworth, SA Petkauskos, MJ Walton, TC TI UV curable polymers SO REVOLUTIONARY MATERIALS: TECHNOLOGY AND ECONOMICS SE INTERNATIONAL SAMPE TECHNICAL CONFERENCE SERIES LA English DT Proceedings Paper CT 32nd International SAMPE Technical Conference CY NOV 05-09, 2000 CL BOSTON, MA SP Soc Advancement Mat & Process Engn DE polyimides; polyesters; radiation curing AB A new approach to the preparation of high performance polymers (polyimides and polyesters) has been developed that utilizes ultraviolet light, rather than heat, to effect polymerization. This method is based upon the Diels-Alder trapping of a photochemically generated o-quinodimethane intermediate with bismaleimides (to produce polyimides) or bisacrylates (to produce polyesters). Polyimides prepared by this route have glass transition temperatures as high as 300 degreesC, depending upon the monomers used. Glass transition temperatures for polyesters produced using this chemistry are in the neighborhood of 200 degreesC. Thermal gravimetric analysis of these polyimides and polyesters show that they have modest thermal oxidative stability - Td's for both systems were in excess of 300 degreesC. C1 NASA, Polymers Branch, Div Mat, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Meador, MA (reprint author), NASA, Polymers Branch, Div Mat, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 7 TC 0 Z9 0 U1 0 U2 0 PU SOC ADVANCEMENT MATERIAL & PROCESS ENGINEERING PI COVINA PA 1161 PARKVIEW DR,, COVINA, CA 91724-3748 USA SN 0892-2624 BN 0-938994-89-1 J9 INT SAMPE TECH CONF PY 2000 VL 32 BP 724 EP 732 PG 3 WC Engineering, Aerospace; Materials Science, Multidisciplinary; Materials Science, Characterization & Testing; Materials Science, Coatings & Films; Materials Science, Composites SC Engineering; Materials Science GA BR79P UT WOS:000167557000070 ER PT S AU Bowles, KJ AF Bowles, KJ BE Adams, PJ Elsworth, SA Petkauskos, MJ Walton, TC TI Thermal and mechanical durability of graphite fiber reinforced PMR-15 composites at elevated temperatures SO REVOLUTIONARY MATERIALS: TECHNOLOGY AND ECONOMICS SE INTERNATIONAL SAMPE TECHNICAL CONFERENCE SERIES LA English DT Proceedings Paper CT 32nd International SAMPE Technical Conference CY NOV 05-09, 2000 CL BOSTON, MA SP Soc Advancement Mat & Process Engn DE composites; durability; polymers AB Earlier work, that reported relationships between the compression properties and elevated temperature aging duration and weight losses, also pointed out the apparent influence of a surface layer formation and growth on the retention of compression properties during extended aging times. Since that time, further studies focused toward evaluating the growth of the surface layer. This layer was found to change in its composition and features as the aging temperature changed. Microcracks and small voids initiated and advanced inward at all temperatures. Visible oxidation at the surface occurred only at the temperatures above 260 degreesC. Relationships between layer thickness and aging time and temperature were evaluated and empirically formulated. Then the compression properties were graphically related to the surface layer thickness with excellent correlation. C1 NASA, Glenn Res Ctr, Div Mat, Polymers Branch, Cleveland, OH 44135 USA. RP Bowles, KJ (reprint author), NASA, Glenn Res Ctr, Div Mat, Polymers Branch, Cleveland, OH 44135 USA. NR 10 TC 0 Z9 0 U1 0 U2 0 PU SOC ADVANCEMENT MATERIAL & PROCESS ENGINEERING PI COVINA PA 1161 PARKVIEW DR,, COVINA, CA 91724-3748 USA SN 0892-2624 BN 0-938994-89-1 J9 INT SAMPE TECH CONF PY 2000 VL 32 BP 838 EP 853 PG 4 WC Engineering, Aerospace; Materials Science, Multidisciplinary; Materials Science, Characterization & Testing; Materials Science, Coatings & Films; Materials Science, Composites SC Engineering; Materials Science GA BR79P UT WOS:000167557000080 ER PT S AU Jaworske, DA AF Jaworske, DA BE Adams, PJ Elsworth, SA Petkauskos, MJ Walton, TC TI Brazing of graphite fibers to Inconel (TM) 718 SO REVOLUTIONARY MATERIALS: TECHNOLOGY AND ECONOMICS SE INTERNATIONAL SAMPE TECHNICAL CONFERENCE SERIES LA English DT Proceedings Paper CT 32nd International SAMPE Technical Conference CY NOV 05-09, 2000 CL BOSTON, MA SP Soc Advancement Mat & Process Engn DE graphite fibers; metals/alloys; solar collector AB Pitch-based graphite fibers offer a number of potentially attractive properties, including high thermal conductivity and high solar absorptance. In many conventional applications, these fibers are embedded in an epoxy matrix. However, the epoxy is limited to use at temperatures below 300 degreesC and adds little to the thermal conductivity of the end product. To make use of the high thermal conductivity and high solar absorptance of pitch-based graphite fibers for solar thermal applications, a research effort was initiated to develop a technique to attach graphite fibers directly to a high temperature alloy, Inconel(TM) 718. The goal of the effort was to identify a vacuum brazing technique to attach pitch-based graphite fibers directly to the Inconel(TM) 718, for the purpose of providing a good thermally conductive pathway from the fibers to the Inconel(TM) 718. Several different vacuum brazing materials were evaluated. Incusil(TM) ABA was found to be the brazing material of choice. The technique chosen to braze pitch-based graphite fiber fabric to the Inconel(TM) 718 is discussed. A discussion of future activities is also presented. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Jaworske, DA (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 1 TC 0 Z9 0 U1 0 U2 0 PU SOC ADVANCEMENT MATERIAL & PROCESS ENGINEERING PI COVINA PA 1161 PARKVIEW DR,, COVINA, CA 91724-3748 USA SN 0892-2624 BN 0-938994-89-1 J9 INT SAMPE TECH CONF PY 2000 VL 32 BP 873 EP 878 PG 4 WC Engineering, Aerospace; Materials Science, Multidisciplinary; Materials Science, Characterization & Testing; Materials Science, Coatings & Films; Materials Science, Composites SC Engineering; Materials Science GA BR79P UT WOS:000167557000082 ER PT S AU Ely, TA Bishop, RH Crain, TP AF Ely, TA Bishop, RH Crain, TP BE Junkins, JL Alfriend, KT Howell, KC TI Adaptive interplanetary navigation using genetic algorithms SO RICHARD H BATTIN ASTRODYNAMICS SYMPOSIUM SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT Richard H Battin Astrodynamics Symposium CY MAR 19-21, 2000 CL TEXAX A&M UNIV, COLLEGE STN, TX SP Amer Astronaut Soc, Texas Eng Expt Stn, Aerosp Engn Dept HO TEXAX A&M UNIV AB The problem of tuning trajectory determination models for interplanetary navigation is a complex task requiring an intensive search of multiple dynamical and nondynamical models that yield trajectory solutions with minimal errors. The process that operational teams currently utilize is based as much on previous experience, as it is on a scientific understanding of these underlying models. This study illustrates an automated approach for filter tuning (via model optimization) using a genetic algorithm (GA) coupled with an extended Kalman filter (EKF). In particular, the solar radiation pressure (SRP) model of the Mars Pathfinder (MPF) spacecraft is investigated using a 3 month span of tracking data during the cruise phase of the mission. The results obtained in this study are compared to the best model obtained by the MPF navigation team. Unlike many previous adaptive filtering schemes, the GA based approach does not require gradient information about neighboring model options, hence it is capable of examining filter models of varying structure. The GA operates on a population of individuals that are selected (initially at random) from the design space. in this study, the selected design space includes 1.44E+17 distinct SRP models. Each individual processes the tracking data set using the EKF. The basis for the GA's fitness function is a normalized sample statistic of the output residual sequence. Using the fitness values computed for each individual, the GA selects the parent population via a tournament method. For crossover; several strategies are investigated to determine the best method for quick convergence of the GA to a near optimal solution. The results show that the GA is able to determine an SRP model with a fitness value that is similar to 6% better than the model selected by the MPF navigation team, and produces predicted residuals that are more stable. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Ely, TA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 301-125L, Pasadena, CA 91109 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 0-87703-471-0 J9 ADV ASTRONAUT SCI PY 2000 VL 106 BP 147 EP 160 PG 14 WC Engineering, Aerospace SC Engineering GA BR01H UT WOS:000165335700009 ER PT S AU Hughes, SP Hall, CD AF Hughes, SP Hall, CD BE Junkins, JL Alfriend, KT Howell, KC TI Optimal configurations for rotating spacecraft formations SO RICHARD H BATTIN ASTRODYNAMICS SYMPOSIUM SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT Richard H Battin Astrodynamics Symposium CY MAR 19-21, 2000 CL TEXAX A&M UNIV, COLLEGE STN, TX SP Amer Astronaut Soc, Texas Eng Expt Stn, Aerosp Engn Dept HO TEXAX A&M UNIV AB In this paper we introduce a new class of formations that maintain a constant shape as viewed from the Earth. We develop an algorithm to place n spacecraft in a constant shape formation spaced equally in time using the classical orbital elements. To first order the dimensions of the formation are shown to be simple functions of orbit eccentricity and inclination. The performance of the formation is investigated over a Keplerian orbit using a performance measure based on a weighted average of the angular separations between spacecraft in formation. Analytic approximations are developed that yield optimum configurations for different values of n. The analytic approximations are shown to be in excellent agreement with the exact solutions. C1 NASA, Goddard Space Flight Ctr, Guidance Navigat & Control Ctr, Greenbelt, MD 20771 USA. RP Hughes, SP (reprint author), NASA, Goddard Space Flight Ctr, Guidance Navigat & Control Ctr, Code 661, Greenbelt, MD 20771 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 0-87703-471-0 J9 ADV ASTRONAUT SCI PY 2000 VL 106 BP 163 EP 185 PG 23 WC Engineering, Aerospace SC Engineering GA BR01H UT WOS:000165335700010 ER PT S AU Markley, FL Mortari, D AF Markley, FL Mortari, D BE Junkins, JL Alfriend, KT Howell, KC TI New developments in quaternion estimation from vector observations SO RICHARD H BATTIN ASTRODYNAMICS SYMPOSIUM SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT Richard H Battin Astrodynamics Symposium CY MAR 19-21, 2000 CL TEXAX A&M UNIV, COLLEGE STN, TX SP Amer Astronaut Soc, Texas Eng Expt Stn, Aerosp Engn Dept HO TEXAX A&M UNIV ID ATTITUDE DETERMINATION; ALGORITHM AB This paper contains a critical comparison of estimators minimizing Wahba's loss function. Some new results are presented for the QUaternion ESTimator (QUEST) and EStimators of the Optimal Quatemion (ESOQ and ESOQ2) to avoid the computational burden of sequential rotations in these algorithms. None of these methods is as robust in principle as Davenport's q method or the Singular Value Decomposition (SVD) method, which are significantly slower. Robustness is only an issue for measurements with widely differing accuracies, so the fastest estimators, the modified ESOQ and ESOQ2, are well suited to sensors that track multiple stars with comparable accuracies. More robust forms of ESOQ and ESOQ2 are developed that are intermediate in speed. C1 NASA, Goddard Space Flight Ctr, Guidance Navigat & Control Ctr, Greenbelt, MD 20771 USA. RP Markley, FL (reprint author), NASA, Goddard Space Flight Ctr, Guidance Navigat & Control Ctr, Code 661, Greenbelt, MD 20771 USA. NR 27 TC 7 Z9 7 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-471-0 J9 ADV ASTRONAUT SCI PY 2000 VL 106 BP 373 EP 393 PG 21 WC Engineering, Aerospace SC Engineering GA BR01H UT WOS:000165335700019 ER PT B AU Lehman, DH Rayman, MD Varghese, P Livesay, LL AF Lehman, DH Rayman, MD Varghese, P Livesay, LL BE Stone, WC TI Deep Space 1: Robotic exploration in the New Millennium SO ROBOTICS 2000, PROCEEDINGS LA English DT Proceedings Paper CT 4th International Conference and Exposition/Demonstration on Robotics for Challenging Situations and Environments CY FEB 27-MAR 02, 2000 CL ALBUQUERQUE, NM SP Amer Soc Civil Engineers, Aerosp Div, Amer Astronaut Soc, NASA, Sandia Natl Labs, Natl Space Soc, Int Assoc Automat & Robot Construct, Univ New Mexico, Dept Civil Engn, Space Daily, Spacenews Com AB Deep Space 1 (DS1), launched on October 24, 1998, was the first mission of NASA's New Millennium program. DS1 was chartered to flight validate twelve high-risk, advanced technologies important for future space and Earth science programs. Advanced technologies tested during its primary mission included solar electric propulsion, high-power solar concentrator arrays, three on-board autonomy technologies, two low-mass science instrument packages, and several telecommunications and microelectronics devices. During the primary mission, which was completed in September 1999, the technology payload for the mission was exercised extensively to assess performance so subsequent missions will not have to incur the cost and risk of being the first users of these new capabilities. DS1 was the first deep space mission to use solar electric propulsion as its main source of propulsion. In addition, DSI was the first mission to demonstrate the ability to perform autonomous on-board navigation for a deep space probe. Although DS1 was driven by the requirements of technology validation, it also presented an important opportunity to conduct solar system science, though as a secondary objective to its main technology validation mission goals. As such, the spacecraft flew by asteroid Braille in July of 1999; later encounters during its recently approved extended mission with comets Wilson-Harrington and Borrelly are planned in the year 2001. This paper will describe the technology and mission aspects of Deep Space 1. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91107 USA. RP Lehman, DH (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91107 USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC CIVIL ENGINEERS PI NEW YORK PA UNITED ENGINEERING CENTER, 345 E 47TH ST, NEW YORK, NY 10017-2398 USA BN 0-7844-0476-3 PY 2000 BP 2 EP 8 PG 7 WC Automation & Control Systems; Engineering, Civil SC Automation & Control Systems; Engineering GA BQ36E UT WOS:000088122200001 ER PT B AU Hickey, GS Kennedy, B Ganino, T AF Hickey, GS Kennedy, B Ganino, T BE Stone, WC TI Intelligent mobile systems for assembly, maintenance and operations for Space Solar Power SO ROBOTICS 2000, PROCEEDINGS LA English DT Proceedings Paper CT 4th International Conference and Exposition/Demonstration on Robotics for Challenging Situations and Environments CY FEB 27-MAR 02, 2000 CL ALBUQUERQUE, NM SP Amer Soc Civil Engineers, Aerosp Div, Amer Astronaut Soc, NASA, Sandia Natl Labs, Natl Space Soc, Int Assoc Automat & Robot Construct, Univ New Mexico, Dept Civil Engn, Space Daily, Spacenews Com C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Hickey, GS (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 AMER SOC CIVIL ENGINEERS PI NEW YORK PA UNITED ENGINEERING CENTER, 345 E 47TH ST, NEW YORK, NY 10017-2398 USA BN 0-7844-0476-3 PY 2000 BP 49 EP 55 PG 7 WC Automation & Control Systems; Engineering, Civil SC Automation & Control Systems; Engineering GA BQ36E UT WOS:000088122200006 ER PT B AU Bar-Cohen, Y AF Bar-Cohen, Y BE Stone, WC TI Electroactive polymers as artificial muscles capabilities - Potentials and challenges SO ROBOTICS 2000, PROCEEDINGS LA English DT Proceedings Paper CT 4th International Conference and Exposition/Demonstration on Robotics for Challenging Situations and Environments CY FEB 27-MAR 02, 2000 CL ALBUQUERQUE, NM SP Amer Soc Civil Engineers, Aerosp Div, Amer Astronaut Soc, NASA, Sandia Natl Labs, Natl Space Soc, Int Assoc Automat & Robot Construct, Univ New Mexico, Dept Civil Engn, Space Daily, Spacenews Com AB For many years, electroactive polymers (EAP) received relatively little attention due to the small number of available materials and their Limited actuation capability. The recent emergence of EAP materials with large displacement response changed the paradigm of these materials and their potential capability. The main attractive characteristic of EAP is their operational similarity to biological muscles, particularly their resilience and ability to induce large actuation strains. Unique robotic components and miniature devices are being explored, where EAP serve as actuators to enable new capabilities. In recognition of the need for international cooperation among the developers, users and potential sponsors, an SPIE Conference was organized for the first time on March 1-2, 1999, in Newport Beach, California. The conference was the largest ever on EAP, and it marked an important milestone, turning the spotlight onto these emerging materials and their potential. Following this success, an MRS conference was initiated to address the fundamental issues related to the material science of EAP. The WW-EAP newsletter was initiated to bring the worldwide EAP community even closer. A homepage was also created to link worldwide EAP research and development facilities websites. In this paper, the current capabilities and potentials as well as the challenges of state-of-the art EAP will be reviewed. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Bar-Cohen, Y (reprint author), CALTECH, Jet Prop Lab, MC 82-105,4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 6 TC 5 Z9 5 U1 0 U2 4 PU AMER SOC CIVIL ENGINEERS PI NEW YORK PA UNITED ENGINEERING CENTER, 345 E 47TH ST, NEW YORK, NY 10017-2398 USA BN 0-7844-0476-3 PY 2000 BP 188 EP 196 PG 9 WC Automation & Control Systems; Engineering, Civil SC Automation & Control Systems; Engineering GA BQ36E UT WOS:000088122200024 ER PT B AU Huntsberger, T Rose, J AF Huntsberger, T Rose, J BE Stone, WC TI Behavior-based control for autonomous mobile robots SO ROBOTICS 2000, PROCEEDINGS LA English DT Proceedings Paper CT 4th International Conference and Exposition/Demonstration on Robotics for Challenging Situations and Environments CY FEB 27-MAR 02, 2000 CL ALBUQUERQUE, NM SP Amer Soc Civil Engineers, Aerosp Div, Amer Astronaut Soc, NASA, Sandia Natl Labs, Natl Space Soc, Int Assoc Automat & Robot Construct, Univ New Mexico, Dept Civil Engn, Space Daily, Spacenews Com DE behavior-based control; neural networks; free flow hierarchy ID ROVER CONTROL; SYSTEM AB The harsh nature of planetary surfaces introduces many new constraints into the types of control systems suitable for use in such environments. These include low power requirements, operation within wide temperature extremes, relatively low computing capabilities and onboard memory, and multiple terrain types ranging from featureless flat plains to sheer cliffs. This paper presents the results of ongoing work at JPL and USC in autonomous rover control, which has concentrated on the development of a behavior-based control system called BISMARC. BISMARC includes full sensor and mobility models, geometric constraints, and environmental feedback based on the SRR/FIDO revers at JPL. It is based on a biologically motivated navigation system derived from a study of human path planning in complicated exterior environments. The system has had over 800 simulation runs of a multiple cooperating rover, multiple sample return mission scenario with an overall success rate of 98.9%, and is currently being tested on the SRR rover in the Planetary Robotics Lab at JPL. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Huntsberger, T (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 AMER SOC CIVIL ENGINEERS PI NEW YORK PA UNITED ENGINEERING CENTER, 345 E 47TH ST, NEW YORK, NY 10017-2398 USA BN 0-7844-0476-3 PY 2000 BP 299 EP 305 PG 7 WC Automation & Control Systems; Engineering, Civil SC Automation & Control Systems; Engineering GA BQ36E UT WOS:000088122200039 ER PT B AU Huntsberger, T Rodriguez, G Schenker, PS AF Huntsberger, T Rodriguez, G Schenker, PS BE Stone, WC TI Robotics challenges for robotic and human Mars exploration SO ROBOTICS 2000, PROCEEDINGS LA English DT Proceedings Paper CT 4th International Conference and Exposition/Demonstration on Robotics for Challenging Situations and Environments CY FEB 27-MAR 02, 2000 CL ALBUQUERQUE, NM SP Amer Soc Civil Engineers, Aerosp Div, Amer Astronaut Soc, NASA, Sandia Natl Labs, Natl Space Soc, Int Assoc Automat & Robot Construct, Univ New Mexico, Dept Civil Engn, Space Daily, Spacenews Com DE robot colonies; manned Mars habitat; behavior-based control AB Infrastructure support for robotic colonies, Mars habitat for humans, and/or robotic exploration of planetary surfaces will need to rely on the field deployment of multiple robust robots. This support includes such tasks as the deployment and servicing of power systems and in-situ resource utilization (ISRU) generators, establishing long-life robotic science stations for measurement and communications, construction of beaconed roadways, and the site preparation and deployment of human habitat modules. Precursor robotic missions to Mars that involve teams of multiple cooperating robots to accomplish some of these tasks is a cost effective solution to the possible long timeline necessary for the deployment of a human habitat. Ongoing work at JPL in the area of robot colonies is investigating many of the technology developments necessary for such an ambitious undertaking. Some of the issues that are being addressed include behavior-based control systems for multiple cooperating robots,development of autonomous robotic systems for the repair of disabled robots, and the design and development of robotic platforms for construction tasks such as material transport and surface clearing. This paper presents the results of an examination of requirements for robotic precursor missions to Mars. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Huntsberger, T (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 14 TC 3 Z9 3 U1 1 U2 1 PU AMER SOC CIVIL ENGINEERS PI NEW YORK PA UNITED ENGINEERING CENTER, 345 E 47TH ST, NEW YORK, NY 10017-2398 USA BN 0-7844-0476-3 PY 2000 BP 340 EP 346 PG 7 WC Automation & Control Systems; Engineering, Civil SC Automation & Control Systems; Engineering GA BQ36E UT WOS:000088122200045 ER PT J AU Hergenrother, PM AF Hergenrother, PM TI Development of composites, adhesives and sealants for high-speed commercial airplanes SO SAMPE JOURNAL LA English DT Article ID POLYIMIDES AB The National Aeronautics and Space Administration (NASA) has funded two programs on the development of technology for high-speed commercial airplanes. One began in the late 1960s and the at her one started in the late 1980s. Although a wealth of important technologies was developed in many areas, these programs did not evolve into an industry-funded program to further develop the technologies that would eventually lead to a production program. This article summarizes the work conducted in the technology areas of high-temperature composites, adhesives, titanium alloy surface treatments and sealants. C1 NASA, Langley Res Ctr, Hampton, VA 23665 USA. RP Hergenrother, PM (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. NR 29 TC 37 Z9 39 U1 0 U2 1 PU SAMPE PUBLISHERS PI COVINA PA 1161 PARKVIEW DRIVE, COVINA, CA 91722 USA SN 0091-1062 J9 SAMPE J JI Sampe J. PD JAN-FEB PY 2000 VL 36 IS 1 BP 30 EP 41 PG 12 WC Engineering, Multidisciplinary; Materials Science, Multidisciplinary SC Engineering; Materials Science GA 277GA UT WOS:000084923300007 ER PT S AU Sridhar, KR Finn, JE Kliss, MH AF Sridhar, KR Finn, JE Kliss, MH BE Mukai, T Clark, BC TI In-situ resource utilization technologies for Mars life support systems SO SAMPLE RETURN MISSIONS TO SMALL BODIES SE ADVANCES IN SPACE RESEARCH-SERIES LA English DT Article; Proceedings Paper CT B0 1 and B0 1/B0 4 Symposia of COSPAR Scientific Commission B held at 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Int Astron Union, Inst Space & Astronaut Sci, Comm Space Res AB The atmosphere of Mars has many of the ingredients that can be used to support human exploration missions. It can be "mined" and processed to produce oxygen, buffer gas, and water, resulting in significant savings on mission costs. The use of local materials, called ISRU (for in-situ resource utilization), is clearly an essential strategy for a long-term human presence on Mars from the standpoints of self-sufficiency, safety, and cost. Currently a substantial effort is underway by NASA to develop technologies and designs of chemical plants to make propellants from the Martian atmosphere. Consumables for life support, such as oxygen and water, will probably benefit greatly from this ISRU technology development for propellant production. However, the buffer gas needed to dilute oxygen for breathing is not a product of a propellant production plant. The buffer gas needs on each human Mars mission will probably be in the order of metric tons, primarily due to losses during airlock activity. Buffer gas can be separated, compressed, and purified from the Mars atmosphere. This paper discusses the buffer gas needs for a human mission to Mars and consider architectures for the generation of buffer gas including an option that integrates it to the propellant production plant. (C) 1999 COSPAR. Published by Elsevier Science Ltd. C1 Univ Arizona, Dept Aerosp & Mech Engn, Tucson, AZ 85721 USA. NASA, Ames Res Ctr, Regenerat Life Support Branch, Moffett Field, CA 94035 USA. RP Univ Arizona, Dept Aerosp & Mech Engn, Tucson, AZ 85721 USA. NR 11 TC 8 Z9 8 U1 4 U2 10 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES-SERIES PY 2000 VL 25 IS 2 BP 249 EP 255 DI 10.1016/S0273-1177(99)00955-2 PG 7 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BP51D UT WOS:000085366000003 PM 11542809 ER PT S AU Yano, H Morishige, K Deshpande, SP Maekawa, Y Kibe, S Neish, MJ Taylor, EA AF Yano, H Morishige, K Deshpande, SP Maekawa, Y Kibe, S Neish, MJ Taylor, EA BE Mukai, T Clark, BC TI Origins of micro-craters on the SFU spacecraft derived from elemental and morphological analyses SO SAMPLE RETURN MISSIONS TO SMALL BODIES SE ADVANCES IN SPACE RESEARCH-SERIES LA English DT Article; Proceedings Paper CT B0 1 and B0 1/B0 4 Symposia of COSPAR Scientific Commission B held at 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Int Astron Union, Inst Space & Astronaut Sci, Comm Space Res AB 170 hypervelocity impact signatures on the MLI and SSM surfaces of the SFU spacecraft were studied their three dimensional morphology and elemental analysis to discriminate them by natural origin from those by artificial debris. Ratio of meteoroids against debris, with some "unknown" and "undetermined" origins, is compared to results from previously retrieved spacecraft. those of LDEF, EuReCa and HST. The impact flux on the Sun pointing face is also compared with (C) 1999 COSPAR. Published by Elsevier Science Ltd. C1 NASA, Lyndon B Johnson Space Ctr, Earth Sci & Solar Syst Explorat Div, Houston, TX 77058 USA. ISAS, Planetary Sci Div, Sagamihara, Kanagawa 2298510, Japan. Deutsch Morgan Grenfell Capital Markets, Tokyo Branch, Tokyo 1050001, Japan. Nippon Univ, Fac Prod Engn, Chiba 275, Japan. NAL, Space Project & Res Ctr, Space Environm Preservat Res Grp, Chofu, Tokyo 1828522, Japan. ESA, Estec, Noordwijk, Netherlands. RP NASA, Lyndon B Johnson Space Ctr, Earth Sci & Solar Syst Explorat Div, Mail Code SN2, Houston, TX 77058 USA. NR 11 TC 6 Z9 6 U1 0 U2 0 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES-SERIES PY 2000 VL 25 IS 2 BP 293 EP 298 DI 10.1016/S0273-1177(99)00947-3 PG 6 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BP51D UT WOS:000085366000011 ER PT S AU McDonnell, JAM Burchell, MJ Green, SF Leese, M Wallis, D Zarnecki, JC Catling, DJ Brownlee, DE Tsou, P Colangeli, L Bussoletti, E Drolshagen, G Maag, CR Yano, H AF McDonnell, JAM Burchell, MJ Green, SF Leese, M Wallis, D Zarnecki, JC Catling, DJ Brownlee, DE Tsou, P Colangeli, L Bussoletti, E Drolshagen, G Maag, CR Yano, H BE Mukai, T Clark, BC TI APSIS - Aerogel position-sensitive impact sensor: Capabilities for in-situ collection and sample return SO SAMPLE RETURN MISSIONS TO SMALL BODIES SE ADVANCES IN SPACE RESEARCH-SERIES LA English DT Article; Proceedings Paper CT B0 1 and B0 1/B0 4 Symposia of COSPAR Scientific Commission B held at 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Int Astron Union, Inst Space & Astronaut Sci, Comm Space Res ID SILICA AEROGEL; DUST AB The capabilities of combining Aerogel (A) as a passive target and position-sensitive impact sensing (PSIS) are examined; experimental performance factors are established from tests on Hypervelocity Impact Facilities at the University of Kent and previous space deployment. Results of system requirements analysis favour the deployment of large area detectors. Analysis of the in-flight impact sensor signals yields the position, time and exposure pointing direction of the tracks containing the impactor residues, which are analysed after retrieval. (C) 1999 COSPAR. Published by Elsevier Science Ltd. C1 Univ Kent, Unit Space Sci & Astrophys, Canterbury, Kent, England. Univ Washington, Dept Astron, Seattle, WA 98195 USA. NASA, Jet Prop Lab, Washington, DC USA. Osservatorio Astron Capodimonte, Naples, Italy. Ist Univ Navale, Ist Fis Sperimentale, Naples, Italy. Estec, Space Environm & Effects Anal Sect, Noordwijk, Netherlands. NASA, Lyndon B Johnson Space Ctr, Earth Sci & Solar Syst Explorat Div, Houston, TX 77058 USA. RP Univ Kent, Unit Space Sci & Astrophys, Canterbury, Kent, England. RI Green, Simon/C-7408-2009; OI Burchell, Mark/0000-0002-2680-8943 NR 27 TC 4 Z9 4 U1 0 U2 0 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES-SERIES PY 2000 VL 25 IS 2 BP 315 EP 322 DI 10.1016/S0273-1177(99)00946-1 PG 8 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BP51D UT WOS:000085366000015 ER PT S AU McDonnell, JAM Burchell, MJ Green, SF McBride, N Vaughan, BAM Zarnecki, JC Tsou, P Hanner, MS Tuzzolino, AJ DiDonna, F Brownlee, DE Clark, B AF McDonnell, JAM Burchell, MJ Green, SF McBride, N Vaughan, BAM Zarnecki, JC Tsou, P Hanner, MS Tuzzolino, AJ DiDonna, F Brownlee, DE Clark, B BE Mukai, T Clark, BC TI The stardust dust flux monitor SO SAMPLE RETURN MISSIONS TO SMALL BODIES SE ADVANCES IN SPACE RESEARCH-SERIES LA English DT Article; Proceedings Paper CT B0 1 and B0 1/B0 4 Symposia of COSPAR Scientific Commission B held at 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Int Astron Union, Inst Space & Astronaut Sci, Comm Space Res AB The Stardust mission is a NASA spacecraft to be launched in February 1999. It will flyby comet 81P/Wild-2 in December 2004, exposing aerogel samples capturing small particles as it does so. The aerogel will be returned to Earth in January 2006. The spacecraft is equipped with other sensors including a dust flux monitor. The dust flux monitor is a combination of low and high rate systems, a large area momentum sensor (LAMS) and PVDF sensors respectively, sensitive to different momentum ranges. This paper describes the dust flux monitor, including the laboratory calibration of the LAMS, modelling of the comet's dust emission and predictions of the impact flux on the dust sensors during the comet flyby. The predicted rates are such that a relatively close flyby is feasible without saturating the detectors. (C) 1999 COSPAR. Published by Elsevier Science Ltd. C1 Univ Kent, Sch Phys Sci, Unit Space Sci & Astrophys, Canterbury CT2 7NR, Kent, England. NASA, Jet Prop Lab, Pasadena, CA 91109 USA. Lab Astrophys & Space Res, Chicago, IL 60637 USA. Univ Washington, Dept Astron, Seattle, WA 98195 USA. Lockheed Martin, Denver, CO USA. RP Univ Kent, Sch Phys Sci, Unit Space Sci & Astrophys, Canterbury CT2 7NR, Kent, England. EM J.A.M.McDonnell@ukc.ac.uk RI Green, Simon/C-7408-2009; OI Burchell, Mark/0000-0002-2680-8943 NR 8 TC 2 Z9 3 U1 0 U2 1 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES-SERIES PY 2000 VL 25 IS 2 BP 335 EP 338 DI 10.1016/S0273-1177(99)00940-0 PG 4 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BP51D UT WOS:000085366000018 ER PT J AU Lee, HJ AF Lee, HJ TI Finite element analysis of individual curved and straight thermopiezoelectric bimorph actuators SO SCIENCE AND ENGINEERING OF COMPOSITE MATERIALS LA English DT Article ID SENSORS; PLATES AB The room and high temperature quasi-static response of straight and curved piezoelectric bimorph actuators is analyzed using a mixed field finite element formulation that accounts for the coupled mechanical, electrical, and thermal response of piezoelectric materials. The mixed field laminate theory combines single layer assumptions for the displacements along with layerwise fields for the electric potential and temperature. The formulation is based on the principles of linear thermopiezoelectricity and is implemented into a curvilinear eight-noded shell element. The accuracy of the formulation is verified with previously published room temperature experimental results for straight and curved piezoelectric bimorph actuators, as well as with published high temperature analytical results for a straight bimorph actuator. Numerical studies are also conducted on bimorph actuators to assess the impact of curvature on the room temperature force-displacement response and to determine the effect of high temperature on the deflection of curved bimorph actuators. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Lee, HJ (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 13 TC 2 Z9 2 U1 0 U2 0 PU FREUND PUBLISHING HOUSE LTD PI LONDON PA STE 500, CHESHAM HOUSE, 150 REGENT ST, LONDON W1R 5FA, ENGLAND SN 0334-181X J9 SCI ENG COMPOS MATER JI Sci. Eng. Compos. Mater. PY 2000 VL 9 IS 3 BP 101 EP 110 PG 10 WC Materials Science, Composites SC Materials Science GA 484JP UT WOS:000171686700001 ER PT B AU Nathal, MV AF Nathal, MV BE Turchi, PEA Shull, RD Gonis, A TI Trends in metallic materials research for aerospace propulsion programs SO SCIENCE OF ALLOYS FOR THE 21ST CENTURY: A HUME ROTHERY SYMPOSIUM CELEBRATION LA English DT Meeting Abstract CT Symposium on the Science of Alloys for the 21st Century - A Hume-Rothery Symposium Celebration CY OCT 18-20, 2000 CL ST LOUIS, MO SP TMS, Electr Magnet & Photon Div, TMS, Extract & Processing Div, TMS, Light Met Div, TMS, Mat Processing & MFG Div, TMS, Struct Mat Div C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU MINERALS, METALS & MATERIALS SOC PI WARRENDALE PA 184 THORN HILL RD, WARRENDALE, PA 15086-7514 USA BN 0-87339-445-3 PY 2000 BP 51 EP 51 PG 1 WC Metallurgy & Metallurgical Engineering SC Metallurgy & Metallurgical Engineering GA BR36G UT WOS:000166191900007 ER PT S AU Jones, WV AF Jones, WV BE Riedler, W Torkar, K TI Meeting the challenge to balloon science SO SCIENTIFIC BALLOONING SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT PSB1 Symposium on COSPAR Panel on Technical Problems Related to Scientific Ballooning held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Amer Inst Aeronaut & Astronaut, NASA, NSF, Comm Space Res AB The promise of superpressure ballooning is helping the balloon program evolve toward a cost-effective means for frequent access to near-space. Superpressure balloons fabricated from strong, light-weight composite materials have the potential for increasing flight times of ton-class payloads to 100 days or more at altitudes above 5 mbars at essentially any geographic latitude. Although this new capability is still in an embryonic stage, its potential has already had an impact. Specifically, a new NASA Office of Space Science policy for University-class Explorer missions allows balloon investigations to compete on an equal basis with other low-cost missions requiring expendable launch vehicles. The new challenge for the science community is to design winning payloads that can be built within the cost cap of $13 M, including launch costs, and be developed within two to three years from selection to launch. Defining the international trajectories and getting the overflight agreements for balloon flights that make several circumnavigations of Earth will also be a challenge. (C) 2000 COSPAR. Published by Elsevier Science Ltd. C1 NASA Headquarers, Off Space Sci, Washington, DC 20546 USA. RP Jones, WV (reprint author), NASA Headquarers, Off Space Sci, Code SR, Washington, DC 20546 USA. NR 0 TC 1 Z9 1 U1 0 U2 0 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2000 VL 26 IS 9 BP 1303 EP 1311 PG 9 WC Engineering, Aerospace SC Engineering GA BQ23L UT WOS:000087681300001 ER PT S AU Smith, IS AF Smith, IS BE Riedler, W Torkar, K TI The Ultra Long Duration Balloon Project SO SCIENTIFIC BALLOONING SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT PSB1 Symposium on COSPAR Panel on Technical Problems Related to Scientific Ballooning held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Amer Inst Aeronaut & Astronaut, NASA, NSF, Comm Space Res AB The USA NASA Balloon Program research and development (R&D) efforts have focused on the development of technologies to support increased capability balloon missions. Advances made in analytical structural/performance modeling and lightweight composite materials offered the promise of superpressure balloons capable of extended flight duration. In 1997 a project was approved to develop and demonstrate a new capability to support balloon missions lasting up to 100 days above 33.5 kms. The development project, called the Ultra Long Duration Balloon Project (ULDB), will conclude with a demonstration flight in the year 2000. The ULDB Project consists of four major systems: Vehicle and Recovery, Ballooncraft, Mission and Operations, and the Science Instrument. Major challenges include the balloon material, balloon fabrication, power, cryogenic refrigeration, thermal control, attitude control, telecommunications and data storage, and international overflight. An overview of ULDB Project (Smith, et al, 1998) will be presented. (C) 2000 COSPAR. Published by Elsevier Science Ltd. C1 NASA, Goddard Space Flight Ctr, Wallops Flight Facil, Wallops Island, VA 23337 USA. RP Smith, IS (reprint author), NASA, Goddard Space Flight Ctr, Wallops Flight Facil, Wallops Island, VA 23337 USA. NR 2 TC 1 Z9 1 U1 0 U2 0 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2000 VL 26 IS 9 BP 1339 EP 1343 DI 10.1016/S0273-1177(00)00119-8 PG 5 WC Engineering, Aerospace SC Engineering GA BQ23L UT WOS:000087681300005 ER PT S AU Cathey, HM AF Cathey, HM BE Riedler, W Torkar, K TI Development of the NASA Long Duration Balloon Vehicle SO SCIENTIFIC BALLOONING SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT PSB1 Symposium on COSPAR Panel on Technical Problems Related to Scientific Ballooning held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Amer Inst Aeronaut & Astronaut, NASA, NSF, Comm Space Res AB The development of the NASA Ultra Long Duration Balloon (ULDB) Vehicle is being approached in three parallel paths. The paths are the balloon design, materials development and specification, and balloon fabrication/production technology development. This paper addresses the balloon design with respect to the requirements, approach, design assumptions, and the trade studies performed. The relationships among the various trade variables are presented. A trade space that illustrates the dependencies among the variables is also presented. A candidate balloon design for the ULDB Balloon Vehicle is presented along with potential system enhancements. (C) 2000 COSPAR Published by Elsevier Science Ltd. C1 New Mexico State Univ, NASA, Goddard Space Flight Ctr, Phys Sci Lab,Wallops Flight Facil, Wallops Island, VA 23337 USA. RP Cathey, HM (reprint author), New Mexico State Univ, NASA, Goddard Space Flight Ctr, Phys Sci Lab,Wallops Flight Facil, Wallops Island, VA 23337 USA. NR 4 TC 1 Z9 1 U1 0 U2 0 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2000 VL 26 IS 9 BP 1345 EP 1348 DI 10.1016/S0273-1177(00)00058-2 PG 4 WC Engineering, Aerospace SC Engineering GA BQ23L UT WOS:000087681300006 ER PT S AU Silverberg, RF AF Silverberg, RF CA MSAM TopHat Collaboration BE Riedler, W Torkar, K TI The TopHat Cosmic Microwave Background anisotropy experiment SO SCIENTIFIC BALLOONING SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT PSB1 Symposium on COSPAR Panel on Technical Problems Related to Scientific Ballooning held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Amer Inst Aeronaut & Astronaut, NASA, NSF, Comm Space Res ID MEDIUM-SCALE ANISOTROPY AB We have developed a balloon-borne experiment to measure the Cosmic Microwave Background Radiation anisotropy on angular scales from similar to 50 degrees down to similar to 20'. The instrument observes at frequencies between 150 and 690 GHz and will be flown on an Antarctic circumpolar long duration flight. To greatly improve the experiment performance, the front-end of the experiment is mounted on the top of the balloon. With high sensitivity, broad sky coverage, and well-characterized systematic errors, the results of this experiment can be used to strongly constrain cosmological models and probe the early stages of large-scale structure formation in the Universe. Published by Elsevier Science Ltd. C1 NASA, Goddard Space Flight Ctr, Astron & Solar Phys Lab, Greenbelt, MD 20771 USA. Univ Chicago, Enrico Fermi Inst, Dept Phys, Chicago, IL 60637 USA. Univ Wisconsin, Dept Phys, Madison, WI 53706 USA. Univ Delaware, Bartol Res Inst, Newark, DE 19716 USA. Danish Space Res Inst, DK-2100 Copenhagen, Denmark. RP Silverberg, RF (reprint author), NASA, Goddard Space Flight Ctr, Astron & Solar Phys Lab, Greenbelt, MD 20771 USA. NR 9 TC 1 Z9 1 U1 0 U2 0 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2000 VL 26 IS 9 BP 1401 EP 1406 DI 10.1016/S0273-1177(00)00077-6 PG 6 WC Engineering, Aerospace SC Engineering GA BQ23L UT WOS:000087681300018 ER PT B AU Zebulum, RS Santini, CC Sinohara, HT Pacheco, MAC Vellasco, MMR Szwarcman, MH AF Zebulum, RS Santini, CC Sinohara, HT Pacheco, MAC Vellasco, MMR Szwarcman, MH BE Lohn, J Stoica, A Keymeulen, D Colombano, S TI A reconfigurable platform for the automatic synthesis of analog circuits SO SECOND NASA/DOD WORKSHOP ON EVOLVABLE HARDWARE, PROCEEDINGS LA English DT Proceedings Paper CT 2nd NASA/DoD Workshop on Evolvable Hardware (EH-2000) CY JUL 13-15, 2000 CL PALO ALTO, CA SP NASA Ames, Computat Sci Div, US Dept Def, Def Adv Res Projects Agcy, NASA Ames Informat Sci & Technol Directorate, JPL, Ctr Integrated Space Microsyst, JPL, Ctr Space Microelectr Technol, NASA Ames, Numer Aerosp Simulat Syst Div, NASA Ames, Integrated Prod Team, Res Inst Adv Comp Sci ID ARTIFICIAL EVOLUTION; PROGRAMMABLE ANALOG; ELECTRONICS; HARDWARE; DESIGN AB Reconfigurable chips are integrated circuits whose internal connections can be programmed by the user to attend a specific application. Field Programmable Gate Arrays (FPGAs) and Field Programmable Analog Arrays (FPAAs) constitute the state of the art in the technology of reconfigurable chips, referring to digital and analog devices respectively. These devices will become the building blocks of a forthcoming class of hardware, with the important features of self-adaptation and self-repairing, through automatic reconfiguration. These are essential features for systems that need to perform for a long time in harsh environments such as those employed in space exploration missions. Automatic reconfiguration of field programmable devices may potentially be driven by Evolutionary Computation techniques such as Generic Algorithms. FPAAs have just recently appeared, and most projects are being carried out in universities and research centers. In this article we propose a new model of reconfigurable analog circuit and describe its application in the intrinsic evolution of a simple logic inverter. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Zebulum, RS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 16 TC 15 Z9 17 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 BN 0-7695-0762-X PY 2000 BP 91 EP 98 DI 10.1109/EH.2000.869346 PG 8 WC Engineering, Aerospace; Computer Science, Hardware & Architecture SC Engineering; Computer Science GA BQ76F UT WOS:000089422400010 ER PT B AU Stoica, A Keymeulen, D Zebulum, R Thakoor, A Daud, T Klimeck, G Jin, Y Tawel, R Duong, V AF Stoica, A Keymeulen, D Zebulum, R Thakoor, A Daud, T Klimeck, G Jin, Y Tawel, R Duong, V BE Lohn, J Stoica, A Keymeulen, D Colombano, S TI Evolution of analog circuits on Field Programmable Transistor Arrays SO SECOND NASA/DOD WORKSHOP ON EVOLVABLE HARDWARE, PROCEEDINGS LA English DT Proceedings Paper CT 2nd NASA/DoD Workshop on Evolvable Hardware (EH-2000) CY JUL 13-15, 2000 CL PALO ALTO, CA SP NASA Ames, Computat Sci Div, US Dept Def, Def Adv Res Projects Agcy, NASA Ames Informat Sci & Technol Directorate, JPL, Ctr Integrated Space Microsyst, JPL, Ctr Space Microelectr Technol, NASA Ames, Numer Aerosp Simulat Syst Div, NASA Ames, Integrated Prod Team, Res Inst Adv Comp Sci ID FUZZY AB Evolvable Hardware (EHW) refers to HW design and self-reconfiguration using evolutionary/genetic mechanisms. The paper presents an overview of some key concepts of EHW, describing also a set of selected applications. A fine-grained Field Programmable Transistor Array (FPTA) architecture for reconfigurable hardware is presented as an example of an initial effort toward evolution-oriented devices. Evolutionary experiments in simulations and with a FPTA chip in-the-loop demonstrate automatic synthesis of electronic circuits. Unconventional circuits, for which there are no textbook design guidelines, are particularly appealing to evolvable hardware. To illustrate this situation, one demonstrates here the evolution of circuits implementing parametrical connectives for fuzzy logics. In addition to synthesizing circuits for new functions, evolvable hardware can be used to preserve existing functions and achieve fault-tolerance, determining circuit configurations that circumvent the faults. In addition, we illustrate with an example how evolution can recover functionality lost due to an increase in teimperature. In the particular case of space applications, these characteristics are extremely important for enabling spacecraft to survive harsh environments and to have long life. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Stoica, A (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RI Klimeck, Gerhard/A-1414-2012 OI Klimeck, Gerhard/0000-0001-7128-773X NR 17 TC 48 Z9 50 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 BN 0-7695-0762-X PY 2000 BP 99 EP 108 DI 10.1109/EH.2000.869347 PG 10 WC Engineering, Aerospace; Computer Science, Hardware & Architecture SC Engineering; Computer Science GA BQ76F UT WOS:000089422400011 ER PT B AU Olson, JO Whitlock, C Carlson, A Ritchey, NA Brown, D Chandler, W AF Olson, JO Whitlock, C Carlson, A Ritchey, NA Brown, D Chandler, W GP AMS AMS TI Surface solar energy and meteorological data available for renewable energy use SO SECOND SYMPOSIUM ON ENVIRONMENTAL APPLICATIONS LA English DT Proceedings Paper CT 2nd Symposium on Environmental Applications CY JAN 09-14, 2000 CL LONG BEACH, CA SP Amer Meteorol Soc C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Olson, JO (reprint author), NASA, Langley Res Ctr, 2 S Wright St,Mail Stop 157D, Hampton, VA 23681 USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU AMER METEOROLOGICAL SOCIETY PI BOSTON PA 45 BEACON ST, BOSTON, MA 02108 USA PY 2000 BP 235 EP 238 PG 4 WC Environmental Sciences; Meteorology & Atmospheric Sciences SC Environmental Sciences & Ecology; Meteorology & Atmospheric Sciences GA BS13K UT WOS:000168779300051 ER PT S AU Fischer, B Schumann, J Pressburger, T AF Fischer, B Schumann, J Pressburger, T BE Taha, W TI Generating data analysis programs from statistical models - Position paper SO SEMANTICS, APPLICATIONS AND IMPLEMENTATION OF PROGRAM GENERATION, PROCEEDINGS SE Lecture Notes in Computer Science LA English DT Article; Proceedings Paper CT International Workshop on Semantics, Applications, and Implementation of Program Generation CY SEP 20, 2000 CL MONTREAL, CANADA SP ACM, SIGPLAN AB Extracting information from data, often also called data analysis, is an important scientific task. Statistical approaches, which use methods from probability theory and numerical analysis, axe well-founded but difficult to implement: the development of a statistical data analysis program for any given application is time-consuming and requires knowledge and experience in several areas. In this paper, we describe AUTOBAYES, a high-level generator system for data analysis programs from statistical models. A statistical model specifies the properties for each problem variable (i.e., observation or parameter) and its dependencies in the form of a probability distribution. It is thus a fully declarative problem description, similar in spirit to a set of differential equations. Rom this model, AUTOBAYES generates optimized and fully commented C/C++ code which can be linked dynamically into the Matlab and Octave environments. Code is generated by schema-guided deductive synthesis. A schema consists of a code template and applicability constraints which are checked against the model during synthesis using theorem proving technology. AUTOBAYES augments schema-guided synthesis by symbolic-algebraic computation and can thus derive closed-form solutions for many problems. In this paper, we outline the AUTOBAYES system, its theoretical foundations in Bayesian probability theory, and its application by means of a detailed example. C1 NASA Ames, RIACS, Moffett Field, CA 94035 USA. NASA Ames, QSS, Moffett Field, CA 94035 USA. RP NASA Ames, RIACS, Moffett Field, CA 94035 USA. EM fisch@ptolemy.arc.nasa.gov; schumann@ptolemy.arc.nasa.gov; ttp@ptolemy.arc.nasa.gov NR 25 TC 2 Z9 2 U1 0 U2 0 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY SN 0302-9743 BN 3-540-41054-6 J9 LECT NOTES COMPUT SC PY 2000 VL 1924 BP 212 EP 229 PG 18 WC Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BT09H UT WOS:000171919400015 ER PT S AU Schenker, PS Huntsberger, TL Pirjanian, P Trebi-Ollennu, A Das, H Joshi, S Aghazarian, H Ganino, AJ Kennedy, BA Garrett, MS AF Schenker, PS Huntsberger, TL Pirjanian, P Trebi-Ollennu, A Das, H Joshi, S Aghazarian, H Ganino, AJ Kennedy, BA Garrett, MS BE McKEE, GT Schenker, PS TI Robot work crews for planetary outposts: close cooperation and coordination of multiple mobile robots SO SENSOR FUSION AND DECENTRALIZED CONTROL IN ROBOTIC SYSTEMS III SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Sensor Fusion and Decentralized Control in Robotic Systems III CY NOV 06-08, 2000 CL BOSTON, MA SP SPIE DE mobile robots; cooperating robots; robot control architecture; sensor fusion; intelligent control; Mars exploration; Mars rovers; robot outposts; field robotics; mobile manipulation; robotic navigation; SRR (Sample Return Rover) AB We report on the development of cooperating multiple robots. This work builds from our earlier research on autonomous planetary revers and robot arms. Here, we seek to closely coordinate the mobility and manipulation of multiple robots to perform site construction operations-as an example, the autonomous deployment of a planetary power station-a task viewed as essential to a sustained robotic presence and human habitation on Mars. There are numerous technical challenges; these include the mobile handling of extended objects, as well as cooperative transport/navigation of such objects over natural, unpredictable terrain. We describe an extensible system concept, related simulations, a hardware implementation, and preliminary experimental results. In support of this work we have developed an enabling hybrid control architecture wherein multi-robot mobility and sensor-based controls are derived as group compositions and coordination of more basic behaviors under a task-level multi-agent planner. We summarize this Control Architecture for Multi-robot Planetary Outposts (CAMPOUT), and its application to physical experiments where two revers carry an extended payload over natural terrain. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Schenker, PS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 125-224, Pasadena, CA 91109 USA. NR 18 TC 3 Z9 3 U1 0 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 0-8194-3861-8 J9 P SOC PHOTO-OPT INS PY 2000 VL 4196 BP 210 EP 220 DI 10.1117/12.403720 PG 11 WC Robotics; Imaging Science & Photographic Technology SC Robotics; Imaging Science & Photographic Technology GA BR66K UT WOS:000167105100020 ER PT S AU Pirjanian, P Huntsberger, TL Trebi-Ollennu, A Aghazarian, H Das, H Joshi, SS Schenker, PS AF Pirjanian, P Huntsberger, TL Trebi-Ollennu, A Aghazarian, H Das, H Joshi, SS Schenker, PS BE McKEE, GT Schenker, PS TI CAMPOUT: A control architecture for multi-robot planetary outposts SO SENSOR FUSION AND DECENTRALIZED CONTROL IN ROBOTIC SYSTEMS III SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Sensor Fusion and Decentralized Control in Robotic Systems III CY NOV 06-08, 2000 CL BOSTON, MA SP SPIE DE behavior-based control; multiple mobile robots; robot outposts AB A manned Mars habitat will require a significant amount of infrastructure that can be deployed using robotic precursor missions. This infrastructure deployment will probably include the use of multiple, heterogeneous, mobile robotic platforms. Delays due to the long communication path to Mars limit the amount of teleoperation that is possible. A control architecture called CAMPOUT (Control Architecture for Multirobot Planetary Outposts) is currently under development at the Jet Propulsion Lab in Pasadena, CA. It is a three layer behavior-based system that incorporates the low level control routines currently used on the JPL SRR/FIDO/LEMUR revers. The middle behavior layer uses either the BISMARC (Biologically Inspired System for Map based Autonomous Rover Control) or MOBC (Multi-Objective Behavior Control) action selection mechanisms. CAMPOUT includes the necessary group behaviors and communication mechanisms for coordinated/cooperative control of heterogeneous robotic platforms. We report the results of some ongoing work at the Jet Propulsion Lab in Pasadena, CA on the transport phase of a photovoltaic (PV) tent deployment mission. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Pirjanian, P (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 82-105, Pasadena, CA 91109 USA. NR 15 TC 19 Z9 19 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3861-8 J9 P SOC PHOTO-OPT INS PY 2000 VL 4196 BP 221 EP 230 DI 10.1117/12.403721 PG 10 WC Robotics; Imaging Science & Photographic Technology SC Robotics; Imaging Science & Photographic Technology GA BR66K UT WOS:000167105100021 ER PT S AU Baumgartner, ET Aghazarian, H Trebi-Ollennu, A Huntsberger, TL Garrett, MS AF Baumgartner, ET Aghazarian, H Trebi-Ollennu, A Huntsberger, TL Garrett, MS BE McKEE, GT Schenker, PS TI State estimation and vehicle localization for the FIDO rover SO SENSOR FUSION AND DECENTRALIZED CONTROL IN ROBOTIC SYSTEMS III SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Sensor Fusion and Decentralized Control in Robotic Systems III CY NOV 06-08, 2000 CL BOSTON, MA SP SPIE DE rover localization; state estimation; extended Kalman filter; covariance intersection ID MOBILE AB This paper describes the means for generating rover localization information for NASA/JPL's FIDO rover. This is accomplished using a sensor fusion framework which combines wheel odometry with sun sensor and inertial navigation sensors to provide an integrated state estimate for the vehicle's position and orientation relative to a fixed reference frame. This paper describes two separate state estimation approaches built around the extended Kalman filter formulation and the Covariance Intersection formulation. Experimental results from runs in JPL's MarsYard are presented in order to compare the state estimates generated using each formulation. C1 CALTECH, Jet Prop Lab, Sci & Technol Dev Sect, Pasadena, CA 91109 USA. RP Baumgartner, ET (reprint author), CALTECH, Jet Prop Lab, Sci & Technol Dev Sect, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 11 TC 15 Z9 17 U1 0 U2 2 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3861-8 J9 P SOC PHOTO-OPT INS PY 2000 VL 4196 BP 329 EP 336 DI 10.1117/12.403731 PG 8 WC Robotics; Imaging Science & Photographic Technology SC Robotics; Imaging Science & Photographic Technology GA BR66K UT WOS:000167105100031 ER PT S AU Leger, C AF Leger, C BE McKEE, GT Schenker, PS TI Performance characterization of an automated system for robot configuration synthesis SO SENSOR FUSION AND DECENTRALIZED CONTROL IN ROBOTIC SYSTEMS III SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Sensor Fusion and Decentralized Control in Robotic Systems III CY NOV 06-08, 2000 CL BOSTON, MA SP SPIE DE automated design; evolutionary algorithms; design optimization; robot design ID MANIPULATORS; DESIGN AB We describe the results of several experiments aimed at understanding the performance, behavior, and limitations of Darwin2K, an automated system for robot configuration synthesis and optimization. Two design tasks are addressed: the design of a robot for walking along trusses in zero gravity, and of a manipulator for a coverage task. We explore the impact of several factors on synthesizer performance, including the set of robot components and assemblies available to the synthesizer, the set of metrics used to quantify robot performance, and the scope of the task on which robots are assessed. The meaning and impact of the experimental results is given, and we discuss potential improvements in the method of use of Darwin2K as well as future improvements to the system itself. C1 CALTECH, Jet Prop Lab, Sci & Technol Dev Sect, Pasadena, CA 91125 USA. RP CALTECH, Jet Prop Lab, Sci & Technol Dev Sect, Pasadena, CA 91125 USA. NR 17 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3861-8 J9 PROC SPIE PY 2000 VL 4196 BP 429 EP 440 PG 12 WC Robotics; Imaging Science & Photographic Technology SC Robotics; Imaging Science & Photographic Technology GA BR66K UT WOS:000167105100041 ER PT S AU Schenker, PS Pirjanian, P Balaram, B Ali, KS Trebi-Ollennu, A Huntsberger, TL Aghazarian, H Kennedy, BA Baumgartner, ET Iagnemma, K Rzepniewski, A Dubowsky, S Leger, PC Apostolopoulos, D McKee, GT AF Schenker, PS Pirjanian, P Balaram, B Ali, KS Trebi-Ollennu, A Huntsberger, TL Aghazarian, H Kennedy, BA Baumgartner, ET Iagnemma, K Rzepniewski, A Dubowsky, S Leger, PC Apostolopoulos, D McKee, GT BE McKEE, GT Schenker, PS TI Reconfigurable robots for all terrain exploration SO SENSOR FUSION AND DECENTRALIZED CONTROL IN ROBOTIC SYSTEMS III SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Sensor Fusion and Decentralized Control in Robotic Systems III CY NOV 06-08, 2000 CL BOSTON, MA SP SPIE DE mobile robots; reconfigurable robots; modular robots; Mars rovers; robot architectures; robot control; intelligent control; sensor fusion; fused state estimation; field robotics ID STATE ESTIMATION; ROVER AB While significant recent progress has been made in development of mobile robots for planetary surface exploration, there remain major challenges. These include increased autonomy of operation, traverse of challenging terrain, and fault-tolerance under long, unattended periods of use. We have begun work which addresses some of these issues, with an initial focus on problems of "high risk access," that is, autonomous roving over highly variable, rough terrain. This is a dual problem of sensing those conditions which require rover adaptation, and controlling the rover actions so as to implement this adaptation in a well understood way (relative to metrics of rover stability, traction, power utilization, etc.). Our work progresses along several related technical lines: 1) development a fused state estimator which robustly integrates internal rover state and externally sensed environmental information to provide accurate "configuration" information; 2) kinematic and dynamical stability analysis of such configurations so as to determine "predicts" for a needed change of control regime (e.g., traction control, active c.g. positioning, rover shoulder stance/pose); 3) definition and implementation of a behavior-based control architecture and action-selection strategy which autonomously sequences multi-level rover controls and reconfiguration. We report on these developments, both software simulations and hardware experimentation. Experiments include reconfigurable control of JPL's Sample Return Rover geometry and motion during its autonomous traverse over simulated Mars terrain. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Schenker, PS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 125-224, Pasadena, CA 91109 USA. NR 29 TC 7 Z9 7 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3861-8 J9 P SOC PHOTO-OPT INS PY 2000 VL 4196 BP 454 EP 468 DI 10.1117/12.403744 PG 15 WC Robotics; Imaging Science & Photographic Technology SC Robotics; Imaging Science & Photographic Technology GA BR66K UT WOS:000167105100043 ER PT S AU Jones, TJ Deelman, PW Elliott, ST Grunthaner, PJ Wilson, R Nikzad, S AF Jones, TJ Deelman, PW Elliott, ST Grunthaner, PJ Wilson, R Nikzad, S BE Bloueke, MM Sampat, N William, GM Yeh, T TI Thinned charge coupled devices with flat focal planes for UV imaging SO SENSORS AND CAMERA SYSTEMS FOR SCIENTIFIC, INDUSTRIAL AND DIGITAL PHOTOGRAPHY APPLICATIONS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Sensors and Camera Systems for Scientific, Industrial, and Digital Photography Applications CY JAN 24-26, 2000 CL SAN JOSE, CA SP Soc Imaging Sci & Technol, SPIE ID DELTA-DOPED CCDS AB A versatile post-fabrication process to produce thinned, flat, back-illuminated charge-coupled devices (CCDs) has been developed at Jet Propulsion Laboratory's Microdevices Laboratory. This technique is compatible with many ultraviolet enhancement treatments and has been demonstrated with the delta doping process. The significance of this demonstration is that thinned, robust, and flat CCDs are produced without the use of epoxies or waxes using temperatures and materials that are compatible with standard CCD fabrication and delta doping processes. In our approach, the CCD is attached by thermocompression bonding to a specially-designed silicon substrate using gold-gold diffusion bonding prior to thinning. CCDs with optically flat membranes (10-20 mu m) were produced with excellent yield. These flat CCDs have been successfully delta doped. We will discuss the process of producing thinned flat CCDs, their delta doping, and our results to date. C1 CALTECH, Jet Prop Lab, Ctr Space Microelect Technol, Pasadena, CA 91109 USA. RP Jones, TJ (reprint author), CALTECH, Jet Prop Lab, Ctr Space Microelect Technol, Pasadena, CA 91109 USA. NR 15 TC 5 Z9 5 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3583-X J9 P SOC PHOTO-OPT INS PY 2000 VL 3965 BP 148 EP 156 DI 10.1117/12.385472 PG 9 WC Optics; Imaging Science & Photographic Technology SC Optics; Imaging Science & Photographic Technology GA BQ31W UT WOS:000087919300015 ER PT S AU Deelman, PW Nikzad, S Blouke, MM AF Deelman, PW Nikzad, S Blouke, MM BE Bloueke, MM Sampat, N William, GM Yeh, T TI Delta-doped CCDs with integrated UV coatings SO SENSORS AND CAMERA SYSTEMS FOR SCIENTIFIC, INDUSTRIAL AND DIGITAL PHOTOGRAPHY APPLICATIONS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Sensors and Camera Systems for Scientific, Industrial, and Digital Photography Applications CY JAN 24-26, 2000 CL SAN JOSE, CA SP Soc Imaging Sci & Technol, SPIE DE delta-dope; CCD; UV; detector; AR AB Although they are not intrinsically sensitive to ultraviolet light, CCDs can be treated to have UV-enhanced response. JPL has developed a technology for modifying the backside of thinned, commercial CCDs that uses low-temperature molecular-beam epitaxy (MBE) to produce stable, 100% internal quantum efficiency throughout the full ultraviolet waveband. The delta-doping process is reproducible, the response of delta-doped CCDs is stable over several years, and no hysteresis is exhibited. The delta-doping process is compatible with optical filters and antireflection coatings deposited directly on the CCD back surface, because the delta-layer is localized beneath the back surface. Integrated filters eliminate the need for the additional structural support of an external filter; eliminate the need for the lossy substrates on which external filters are constructed and which would introduce loss and cut off the response at short wavelengths; imply fewer optical surfaces and eliminate the 2-3% minimum loss associated with each; and are more robust than the fragile and bulky external filter technologies. We have established our ability to deposit filters and coatings directly on delta-doped CCDs by constructing a metal/insulator MBE chamber connected via an ultra-high-vacuum transfer line to the silicon MBE chamber, in which delta-doping is performed. We have fabricated preliminary MgF2 AR coatings on delta-doped SITe CCDs. C1 CALTECH, Jet Prop Lab, Ctr Space Microelect Technol, Pasadena, CA 91109 USA. RP Deelman, PW (reprint author), CALTECH, Jet Prop Lab, Ctr Space Microelect Technol, Pasadena, CA 91109 USA. NR 6 TC 3 Z9 3 U1 0 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 0-8194-3583-X J9 P SOC PHOTO-OPT INS PY 2000 VL 3965 BP 462 EP 466 DI 10.1117/12.385471 PG 5 WC Optics; Imaging Science & Photographic Technology SC Optics; Imaging Science & Photographic Technology GA BQ31W UT WOS:000087919300050 ER PT J AU Gunapala, SD Bandara, SV Liu, JK Luong, EM Rafol, SB Mumolo, JM Ting, DZ Bock, JJ Ressler, ME Werner, MW LeVan, PD Chehayeb, R Kukkonen, CA Levy, M LeVan, P Fauci, MA AF Gunapala, SD Bandara, SV Liu, JK Luong, EM Rafol, SB Mumolo, JM Ting, DZ Bock, JJ Ressler, ME Werner, MW LeVan, PD Chehayeb, R Kukkonen, CA Levy, M LeVan, P Fauci, MA TI Quantum well infrared photodetector research and development at jet propulsion laboratory SO SENSORS AND MATERIALS LA English DT Review DE infrared detectors; long-wavelength infrared; multi quantum well; multi-color; focal plane arrays ID FOCAL-PLANE ARRAY; QWIP ARRAY; CAMERA; FABRICATION AB One of the simplest device realizations of the classic particle in-the-box problem of basic quantum mechanics is the quantum well infrared photodetector (QWIP). In this paper we discuss the effect of focal plane array nonuniformity on the performance, optimization of the detector design, material growth and processing that has culminated in the realization of large format, long-wavelength QWIP cameras, holding forth great promise for many applications in the 6-18 micron wavelength range in science, medicine, defense and industry. In addition, we present the recent developments in long-wave-length/very long-wavelength dualband QWIP imaging camera for various applications. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. USAF, Res Lab, Kirtland AFB, NM 87117 USA. Univ So Calif Hosp, Los Angeles, CA 90027 USA. OmniCorder Technol Inc, Stony Brook, NY 11790 USA. NR 29 TC 13 Z9 13 U1 0 U2 1 PU MYU, SCIENTIFIC PUBLISHING DIVISION PI TOKYO PA 1-23-3-303 SENDAGI, TOKYO, 113-0022, JAPAN SN 0914-4935 J9 SENSOR MATER JI Sens. Mater. PY 2000 VL 12 IS 6 BP 327 EP 351 PG 25 WC Instruments & Instrumentation; Materials Science, Multidisciplinary SC Instruments & Instrumentation; Materials Science GA 399TD UT WOS:000166827700001 ER PT S AU Diner, DJ AF Diner, DJ CA MISR Sci Team BE Fujisada, H Lurie, JB Ropertz, A Weber, K TI Imagery and initial results from the Terra Multi-angle Imaging SpectroRadiometer (MISR) SO SENSORS, SYSTEMS, AND NEXT-GENERATION SATELLITES IV SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Sensors, Systems, and Next-Generation Satellites IV CY SEP 25-28, 2000 CL BARCELONA, SPAIN SP European Opt Soc, SPIE, NASA DE Terra; MISR; multi-angle; imaging; remote sensing AB The Multi-angle Imaging SpectroRadiometer (MISR) instrument was launched into polar orbit aboard the Terra spacecraft in December 1999, and collection of Earth imagery began in February 2000. MISR contains nine cameras pointed at fixed along-track directions, and acquires images with view angles at the Earth's surface ranging from 70.5 degrees forward of nadir to 70.5 degrees aft-ward. Each camera contains four CCD line arrays filtered to blue, green, red, and near-infrared wavelengths. Spatial sampling ranging from 275 m to 1.1 km is obtained over a 400-km swath width. Each area observed by MISR is imaged at all nine angles within a seven-minute period. MISR provides a unique approach to characterizing atmospheric aerosols, the surface, and clouds. This paper provides examples of MISR products derived from imagery acquired during the first six months of data collection. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Diner, DJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 4 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 0-8194-3825-1 J9 P SOC PHOTO-OPT INS PY 2000 VL 4169 BP 9 EP 16 PG 8 WC Engineering, Aerospace SC Engineering GA BS13M UT WOS:000168779700002 ER PT S AU Barkstrom, BR Wielicki, BA Smith, GL Lee, RB Priestley, KJ Charlock, TP Kratz, DP AF Barkstrom, BR Wielicki, BA Smith, GL Lee, RB Priestley, KJ Charlock, TP Kratz, DP BE Fujisada, H Lurie, JB Ropertz, A Weber, K TI Validation of CERES/TERRA data SO SENSORS, SYSTEMS, AND NEXT-GENERATION SATELLITES IV SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Sensors, Systems, and Next-Generation Satellites IV CY SEP 25-28, 2000 CL BARCELONA, SPAIN SP European Opt Soc, SPIE, NASA DE CERES; TERRA; radiometry; validation ID ENERGY SYSTEM CERES; SATELLITE DATA; CLOUDS; SENSORS AB There are 2 CERES scanning radiometer instruments aboard the TERRA spacecraft, one for mapping the solar radiation reflected from the Earth and the outgoing longwave radiation and the other for measuring the anisotropy of the radiation. Each CERES instrument has on-board calibration devices, which have demonstrated that from ground to orbit the broadband total and shortwave sensor responses maintained their ties to the International Temperature Scale of 1990 at precisions approaching radiances have been validated in orbit to +/-0.3 % (0.3 W m(-2)sr(-1)). Top of atmosphere fluxes are produced by use of the CERES data alone. By including data from other instruments, surface radiation fluxes and radiant fluxes within the atmosphere and at its top, shortwave and longwave, for both up and down components, are derived. Validation of these data products requires ground and aircraft measurements of fluxes and of cloud properties. C1 Virginia Polytech Inst & State Univ, Langley Res Ctr, Hampton, VA 23681 USA. RP Smith, GL (reprint author), Virginia Polytech Inst & State Univ, Langley Res Ctr, MS 420, Hampton, VA 23681 USA. NR 36 TC 5 Z9 5 U1 0 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 0-8194-3825-1 J9 P SOC PHOTO-OPT INS PY 2000 VL 4169 BP 17 EP 28 PG 12 WC Engineering, Aerospace SC Engineering GA BS13M UT WOS:000168779700003 ER PT S AU Leibee, J AF Leibee, J BE Fujisada, H Lurie, JB Ropertz, A Weber, K TI One size fit all SO SENSORS, SYSTEMS, AND NEXT-GENERATION SATELLITES IV SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Sensors, Systems, and Next-Generation Satellites IV CY SEP 25-28, 2000 CL BARCELONA, SPAIN SP European Opt Soc, SPIE, NASA C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Leibee, J (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3825-1 J9 P SOC PHOTO-OPT INS PY 2000 VL 4169 BP 29 EP 35 PG 7 WC Engineering, Aerospace SC Engineering GA BS13M UT WOS:000168779700004 ER PT S AU Bruegge, CJ Chrien, NCL Chafin, BG Diner, DJ Ando, RR AF Bruegge, CJ Chrien, NCL Chafin, BG Diner, DJ Ando, RR BE Fujisada, H Lurie, JB Ropertz, A Weber, K TI In-flight calibration of the EOS/Multi-angle Imaging SpectroRadiometer (MISR) SO SENSORS, SYSTEMS, AND NEXT-GENERATION SATELLITES IV SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Sensors, Systems, and Next-Generation Satellites IV CY SEP 25-28, 2000 CL BARCELONA, SPAIN SP European Opt Soc, SPIE, NASA DE on-orbit sensors; in-flight calibration ID SENSORS AB The Multi-angle Imaging SpectroRadiometer (MISR) is one of five instruments on the EOS/ Terra spacecraft. MISR consists of nine Earth-viewing cameras which continuously acquire global data sets in view perspectives from nadir to 70 degrees. In order to maintain the radiometric calibration of the cameras, the instrument is equipped with an on-board calibrator. Spectralon panels, deployed at bi-monthly intervals, reflect sunlight into the cameras to be tested. This reflected light is measured by photodiode detectors which define the radiometric scale and allow the sensor calibration to be achieved. There exists six sets of four spectrally filtered photodiodes. For the first of the in-flight experiments the analysis was focused on validating the performance of the on-board calibrator components. As a result of these studies one blue-filtered, light-trapped detector was selected as the primary standard. All other on-board photodiodes have now been adjusted to be in agreement. This procedure has allowed improved band-to-band and camera-to-camera calibrations, in that all camera calibrations are traceable to a single standard. With these procedures in place MISR now plans to calibrate once every two months. New radiometric response coefficients will be delivered to the processing center following each experiment. This paper reports on these validation studies, and the post-launch radiometric response of the MISR cameras as determined during the first six months of on-orbit MISR calibration. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Bruegge, CJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 8 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3825-1 J9 P SOC PHOTO-OPT INS PY 2000 VL 4169 BP 36 EP 46 PG 11 WC Engineering, Aerospace SC Engineering GA BS13M UT WOS:000168779700005 ER PT S AU Pitts, M Hostetler, C Poole, L Holden, C Rault, D AF Pitts, M Hostetler, C Poole, L Holden, C Rault, D BE Fujisada, H Lurie, JB Ropertz, A Weber, K TI An airborne A-band spectrometer for remote sensing of aerosol and cloud optical properties SO SENSORS, SYSTEMS, AND NEXT-GENERATION SATELLITES IV SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Sensors, Systems, and Next-Generation Satellites IV CY SEP 25-28, 2000 CL BARCELONA, SPAIN SP European Opt Soc, SPIE, NASA DE aerosols; clouds; climate; A-band; remote sensing ID MOLECULAR LINE ABSORPTION; SCATTERING ATMOSPHERE; OXYGEN AB Atmospheric remote sensing with the O-2 A-band has a relatively long history, but most of these studies were attempting to estimate surface pressure or cloud-top pressure. Recent conceptual studies have demonstrated the potential of spaceborne high spectral resolution O-2 A-band spectrometers for retrieval of aerosol and cloud optical properties. The physical rationale of this new approach is that information on the scattering properties of the atmosphere is embedded in the detailed line structure of the O-2 A-band reflected radiance spectrum. The key to extracting this information is to measure the radiance spectrum at very high spectral resolution. Instrument performance requirement studies indicate that, in addition to high spectral resolution, the successful retrieval of aerosol and cloud properties from A-band radiance spectra will also require high radiometric accuracy instrument stability, and high signal-to-noise measurements. To experimentally assess the capabilities of this promising new remote sensing application, the NASA Langley Research Center is developing an airborne high spectral resolution A-band spectrometer. The spectrometer uses a plane holographic grating with a folded Littrow geometry to achieve high spectral resolution (0.5 cm(-1)) and low stray light in a compact package. This instrument will be flown in a series of field campaigns beginning in 2001 to evaluate the overall feasibility of this new technique. Results from these campaigns should be particularly valuable for future spaceborne applications of A-band spectrometers for aerosol and cloud retrievals. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Pitts, M (reprint author), NASA, Langley Res Ctr, MS 435, Hampton, VA 23681 USA. NR 12 TC 0 Z9 0 U1 0 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 0-8194-3825-1 J9 P SOC PHOTO-OPT INS PY 2000 VL 4169 BP 123 EP 132 PG 10 WC Engineering, Aerospace SC Engineering GA BS13M UT WOS:000168779700014 ER PT S AU Butler, JJ Wanchoo, L Le, T AF Butler, JJ Wanchoo, L Le, T BE Fujisada, H Lurie, JB Ropertz, A Weber, K TI CEOS database of world-wide calibration facilities and validation test sites SO SENSORS, SYSTEMS, AND NEXT-GENERATION SATELLITES IV SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Sensors, Systems, and Next-Generation Satellites IV CY SEP 25-28, 2000 CL BARCELONA, SPAIN SP European Opt Soc, SPIE, NASA DE calibration; validation; test sites; laboratories; instruments; database; World Wide Web; CEOS AB Since 1995, the CEOS Calibration/Validation (Cal/Val) Database has provided the international Earth remote sensing science community with a) a central repository for information on current and planned Calibration/Validation activities and b) a means to foster collaboration on common Cal/Val issues. The Cal/Val Database uses an ORACLE relation database management system to store the data and is accessed via the World Wide Web (WWW) using PERL scripts to search and query the database. The search queries are structured such that users can define any combination of fields, either through selection of valids, or by directly typing the information. All query results are displayed in the text form. The text displays are interactive allowing the user to point and click to access more detailed information. System functionality provides an online form of all of the three questionnaires for submitting new information and allows a user with the assigned password to edit archived information for their facility. This functionality allows users to update information, as it becomes available. In 2000, the Cal/Val database was updated through a process of additional surveying of existing and planned Cal/Val capabilities to support the NASA's Earth Science Enterprise (ESE) and other international Earth observing missions. A set of three updated questionnaires was prepared: one for calibration laboratories, one for test sites, and one for field instruments. The information requested included: a description of the facility, instruments available, instrument characteristics, types of measurements performed, programs/projects that have used the facility, etc. These questionnaires with cover letter were mailed to over 250 research groups that included CEOS members and facilities within the USA. The information collected from worldwide facilities was used to construct and update this on-line database for use not only by the CEOS members, but also the broader international Earth science community. This project has been funded by NASA Headquarters based on the recommendation from the Committee on Earth Observation Satellites (CEOS) Working Group on Calibration and Validation (WGCV6). NASA is maintaining this database on behalf of CEOS. The database can be accessed at the following URL: http://spso.gsfc.nasa.gov/calval/. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Butler, JJ (reprint author), NASA, Goddard Space Flight Ctr, Code 920 1, Greenbelt, MD 20771 USA. RI Butler, James/D-4188-2013 NR 1 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3825-1 J9 P SOC PHOTO-OPT INS PY 2000 VL 4169 BP 202 EP 208 PG 7 WC Engineering, Aerospace SC Engineering GA BS13M UT WOS:000168779700022 ER PT S AU Park, H McPeters, R Jaross, G Kowalewski, M Janz, S Haring, R AF Park, H McPeters, R Jaross, G Kowalewski, M Janz, S Haring, R BE Fujisada, H Lurie, JB Ropertz, A Weber, K TI Radiometric calibration of total ozone mapping spectrometer - Flight model 5 (TOMS-5) aboard QuikTOMS SO SENSORS, SYSTEMS, AND NEXT-GENERATION SATELLITES IV SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Sensors, Systems, and Next-Generation Satellites IV CY SEP 25-28, 2000 CL BARCELONA, SPAIN SP European Opt Soc, SPIE, NASA DE ozone; ultraviolet; backscatter; spectrometer; TOMS; calibration AB The Total Ozone Mapping Spectrometer - Flight Model 5 (TOMS-5), aboard the QuikTOMS spacecraft, is designed to continue the measurement of the total column amount of ozone in the atmosphere in order to monitor the global trend. Since the predicted total ozone change due to man-made sources is very small, an accurate calibration of the measuring instrument is required. Since in the TOMS-5 experiment the total ozone amount is determined from the ratio of the measurement of the solar backscattered ultraviolet Earth radiance to the incident solar irradiance, the accuracy of the calibration of the instrument sensitivity to this ratio measurement is critical. The prelaunch calibration of TOMS-5 was designed to achieve a ratio calibration accuracy of 1 % in addition to the uncertainties of the standards used. Multiple calibration techniques were employed to ensure the self-consistency of results of different techniques to eliminate any systematic errors. TOMS-5 prelaunch radiometric calibration was performed twice, one in 1996 and the second in 1999 due to the launch delay. The ratio calibration was reproduced within 0.5 % from the tests of 1996 to those of 1999 while the calibration of the individual measurement modes agreed among the various techniques to within 1%. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Park, H (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RI McPeters, Richard/G-4955-2013 OI McPeters, Richard/0000-0002-8926-8462 NR 5 TC 0 Z9 0 U1 0 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 0-8194-3825-1 J9 P SOC PHOTO-OPT INS PY 2000 VL 4169 BP 227 EP 236 PG 10 WC Engineering, Aerospace SC Engineering GA BS13M UT WOS:000168779700025 ER PT S AU Lee, RB Smith, GL Spence, PL Walikainen, DR Szewczyk, ZP Paden, J Priestley, KJ AF Lee, RB Smith, GL Spence, PL Walikainen, DR Szewczyk, ZP Paden, J Priestley, KJ BE Fujisada, H Lurie, JB Ropertz, A Weber, K TI Broadband measurements of lunar radiances using the Tropical Rainfall Measuring Mission (TRMM) Spacecraft/Clouds and the Earth's Radiant Energy System (CERES) sensors SO SENSORS, SYSTEMS, AND NEXT-GENERATION SATELLITES IV SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Sensors, Systems, and Next-Generation Satellites IV CY SEP 25-28, 2000 CL BARCELONA, SPAIN SP European Opt Soc, SPIE, NASA DE climate; lunar; radiometry; thermistor bolometers; CERES; TRMM; Terra; Aqua; total solar irradiance ID CALIBRATION; CLOUDS; ORBIT; MOON; TEMPERATURE; SEAWIFS AB Currently, the moon is being used as a radiometric target to determine on-orbit relative shifts or shifts in the responses of certain spacecraft shortwave sensors. Along these lines, the 1998 Tropical Rainfall Measuring Mission (TRMM) Spacecraft/Clouds and the Earth's Radiant Energy System (CERES) thermistor bolometer sensor observations of lunar radiances were analyzed to evaluate the feasibility using the lunar radiances to calibrate the CERES sensor responses. Over a 5 to 110 degree phase angle range, the CERES sensors were used to measure (1) broadband shortwave [0.3 mum to 5.0 mum] moon-reflected solar filtered radiances; (2) broadband total [0.3 mum to > 100 mum] moon-reflected solar and moon-emitted longwave filtered radiances; and (3) narrowband window [8 mum to 12 mum] moon-emitted longwave filtered radiances. The TRMM/CERES on-orbit radiance measurements are tied to an International Temperature Scale of 1990 (ITS-90) modeled radiometric scale at uncertainty levels approaching 0.2% (0.2 Wm(-2)sr(-1)). Therefore, the TRMM/CERES measurements should be useful in forecasting the precisions of scheduled CERES lunar measurements from the NASA Terra and Aqua Spacecraft platforms near phase angle of 22 and 55 degrees, respectively. The 7-degree phase angle, 1998 CERES shortwave, total, and window measurements yielded lunar filtered radiances of approximately 4.5 +/- 02, 24.4 +/-0.5, and 4.5 +/-0.2 Wm(-2)sr(-1), respectively. These lunar measurements indicate that broadband shortwave radiances can be characterized at the 5% uncertainty range. The 7-degree, shortwave lunar radiances were found to be approximately 1.5 and 3 times brighter greater the corresponding radiances found at the 22-degree and 55-degree phase angles, respectively. Therefore, the Term and Aqua CERES lunar shortwave measurements near 22.5-degree and 55-degree phase angles should yield projected precisions in the 7% and 15% range, respectively. The CERES lunar filtered radiance are presented and discussed. Research efforts are outlined briefly for comparing the total sensor broadband and window narrowband longwave lunar radiances during the January 9, 2001 lunar eclipse. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Lee, RB (reprint author), NASA, Langley Res Ctr, MS 420, Hampton, VA 23681 USA. NR 26 TC 1 Z9 1 U1 2 U2 3 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3825-1 J9 P SOC PHOTO-OPT INS PY 2000 VL 4169 BP 237 EP 247 PG 11 WC Engineering, Aerospace SC Engineering GA BS13M UT WOS:000168779700026 ER PT S AU Marketon, J Abel, P Butler, JJ Smith, GR Cooper, JW AF Marketon, J Abel, P Butler, JJ Smith, GR Cooper, JW BE Fujisada, H Lurie, JB Ropertz, A Weber, K TI A filter radiometer monitoring system for integrating sphere sources SO SENSORS, SYSTEMS, AND NEXT-GENERATION SATELLITES IV SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Sensors, Systems, and Next-Generation Satellites IV CY SEP 25-28, 2000 CL BARCELONA, SPAIN SP European Opt Soc, SPIE, NASA DE source monitor; calibration; integrating sphere AB Two critical requirements of a calibration source are short- and long-term operational stability and repeatability. Monitoring the source is an asset in determining the origin of temporal changes, thus increasing confidence in source performance and quantifying repeatability. Monitor data which fall outside established parameters indicate that the source requires maintenance or re-calibration against the standard. The NASA GSFC Code 920.1 Radiance Calibration Facility (RCF) has developed a Filter Radiometer Monitoring System (FRMS) to continuously monitor the performance of its integrating sphere calibration sources in the 400-2400nm region. Sphere output change mechanisms include lamp aging, coating (BaSO4) deterioration, and water vapor level. FRMS wavelength bands are selected to be sensitive to changes caused by these mechanisms. Several FRMS bands coincide with common remote sensing instrument bands. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Marketon, J (reprint author), NASA, Goddard Space Flight Ctr, Code 920 1, Greenbelt, MD 20771 USA. RI Butler, James/D-4188-2013 NR 7 TC 1 Z9 1 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3825-1 J9 P SOC PHOTO-OPT INS PY 2000 VL 4169 BP 260 EP 267 PG 8 WC Engineering, Aerospace SC Engineering GA BS13M UT WOS:000168779700028 ER PT S AU Pagano, TS Aumann, HH Strow, L AF Pagano, TS Aumann, HH Strow, L BE Fujisada, H Lurie, JB Ropertz, A Weber, K TI Prelaunch performance characteristics of the Atmospheric Infrared Sounder (AIRS) SO SENSORS, SYSTEMS, AND NEXT-GENERATION SATELLITES IV SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Sensors, Systems, and Next-Generation Satellites IV CY SEP 25-28, 2000 CL BARCELONA, SPAIN SP European Opt Soc, SPIE, NASA DE EOS; AIRS; infrared; sounder; calibration; weather forecasting AB The Atmospheric Infrared Sounder represents a quantum leap in spaceborne sounding instruments with 2,378 infrared spectral channels ranging in wavelength from 3.5 to 15.5 microns. AIRS was built by NASA subcontractor Lockheed Martin Sanders (LM Sanders) in Lexington, Massachusetts and is scheduled for launch on the NASA EOS-Aqua spacecraft in December 2000. Characterization of this high spectral resolution infrared spectrometer involved extensive laboratory testing in a thermal vacuum environment at cold optical temperatures. This paper summarizes the results of that testing and gives a detailed report on the spectral, radiometric, and spatial performance of the AIRS. Based on the excellent prelaunch calibration and results of data simulation, AIRS data should significantly improve global weather forecasts and provide an important new tool for climate research. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Pagano, TS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 6 TC 2 Z9 2 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3825-1 J9 P SOC PHOTO-OPT INS PY 2000 VL 4169 BP 268 EP 278 PG 11 WC Engineering, Aerospace SC Engineering GA BS13M UT WOS:000168779700029 ER PT S AU Chapman, JJ AF Chapman, JJ BE Fujisada, H Lurie, JB Ropertz, A Weber, K TI CERES aqua instrument simulator for command and upload validation SO SENSORS, SYSTEMS, AND NEXT-GENERATION SATELLITES IV SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Sensors, Systems, and Next-Generation Satellites IV CY SEP 25-28, 2000 CL BARCELONA, SPAIN SP European Opt Soc, SPIE, NASA DE satellite; simulation; microprocessor; instrument; validation AB Three CERES (Clouds and the Earth's Radiant Energy System) Instruments are currently in orbit, one instrument is on the TRMM (Tropical Rainfall Measuring Mission) spacecraft launched in November, 1997 and two instruments are on the Terra spacecraft launched in December, 1999. The Aqua/CERES is scheduled to loft two additional CERES instruments in December, 2000. Three CERES Instrument Simulation Systems have been built which mimic the microprocessor-controlled operational characteristics of each instrument to a high degree. The original CERES engineering development models developed by NASA and TRW Space and Electronics Group were modified to provide the gimballed azimuth and elevation real-time simulation in synchronization with the embedded control processors. The simulators are used to perform testing and functional validation of custom commands and command sequences prior to the actual uploading to the individual orbiting instruments. The architecture of the benchtop simulation hardware matches that of the individual instruments and each operates in conjunction with the associated unmodified TRW developed flight software to assure a virtual reproduction of the performance of each instrument. Performance results of command sequences for calibration maneuvers and other simulation scenarios are presented. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Chapman, JJ (reprint author), NASA, Langley Res Ctr, 21 Langley Blvd,MS 423, Hampton, VA 23681 USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3825-1 J9 P SOC PHOTO-OPT INS PY 2000 VL 4169 BP 309 EP 316 PG 8 WC Engineering, Aerospace SC Engineering GA BS13M UT WOS:000168779700033 ER PT J AU Mohamadinejad, H Knox, J Smith, J AF Mohamadinejad, H Knox, J Smith, J TI Experimental and numerical investigation of adsorption/desorption in packed sorption beds under ideal and nonideal flows SO SEPARATION SCIENCE AND TECHNOLOGY LA English DT Article ID LAMINAR-FLOW; TUBES AB The importance of the wall effect on packed beds in the adsorption and desorption of carbon dioxide, nitrogen, and water on molecular sieve 5A of 0.127 cm radius is examined experimentally and with one-dimensional computer simulations. Experimental results are presented for a 22.5-cm long by 4.5-cm diameter cylindrical column with concentration measurements taken at various radial locations. The set of partial differential equations is solved using finite differences and Newmans's method. Comparison of test data with the axial-dispersed, nonisothermal, linear driving force model suggests that a two-dimensional model (submitted to Separation Science and Technology) is required for accurate simulation of the average column breakthrough concentration. Additional comparisons of test data with the model provided information on the interactive effects of carrier gas coadsorption with CO2 as well as CO2-H2O interactions. C1 Univ Alabama, Dept Chem Engn, Huntsville, AL 35899 USA. Boeing Aerosp Co, Huntsville, AL USA. NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Univ Alabama, Dept Chem Engn, Huntsville, AL 35899 USA. NR 23 TC 12 Z9 12 U1 2 U2 6 PU TAYLOR & FRANCIS INC PI PHILADELPHIA PA 530 WALNUT STREET, STE 850, PHILADELPHIA, PA 19106 USA SN 0149-6395 EI 1520-5754 J9 SEP SCI TECHNOL JI Sep. Sci. Technol. PY 2000 VL 35 IS 1 BP 1 EP 22 DI 10.1081/SS-100100140 PG 22 WC Chemistry, Multidisciplinary; Engineering, Chemical SC Chemistry; Engineering GA 274GY UT WOS:000084758900001 ER PT B AU Bell, AM Sethares, WA Bucklew, JA AF Bell, AM Sethares, WA Bucklew, JA GP AAAI AAAI TI Coordination failure and congestion in information networks SO SEVENTEENTH NATIONAL CONFERENCE ON ARTIFICIAL INTELLIGENCE (AAAI-2001) / TWELFTH INNOVATIVE APPLICATIONS OF ARTIFICIAL INTELLIGENCE CONFERENCE (IAAI-2000) LA English DT Proceedings Paper CT 17th National Conference on Artificial Intelligence (AAAI-2000)/12th Conference on Innovative Applications of Artificial Intelligence (IAAI-2000) CY JUL 30-AUG 03, 2000 CL AUSTIN, TX SP Amer Assoc Artificial Intelligence AB Coordination failure, or agents' uncertainty about the action of other agents, may be an important source of congestion in large decentralized systems. The El Farol or Santa Fe bar problem provides a simple paradigm for congestion and coordination problems that may arise with over utilization of the Internet. This paper recasts the problem in a stochastic framework and derives a simple adaptive strategy that has intriguing optimization properties; a large collection of decentralized decision makers, each acting in their own best interests and with limited knowledge, converge to a solution that (optimally) solves a complex congestion and social coordination problem. A variation in which agents are allowed access to full information is not nearly as successful. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Bell, AM (reprint author), NASA, Ames Res Ctr, Mail Stop 269-3, Moffett Field, CA 94035 USA. NR 8 TC 0 Z9 0 U1 0 U2 0 PU M I T PRESS PI CAMBRIDGE PA FIVE CAMBRIDGE CENTER, CAMBRIDGE, MA 02142 USA BN 0-262-51112-6 PY 2000 BP 9 EP 14 PG 6 WC Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic; Robotics SC Computer Science; Engineering; Robotics GA BT26B UT WOS:000172441000002 ER PT B AU Tumer, K Wolpert, D AF Tumer, K Wolpert, D GP AAAI AAAI TI Collective intelligence and Braess' paradox SO SEVENTEENTH NATIONAL CONFERENCE ON ARTIFICIAL INTELLIGENCE (AAAI-2001) / TWELFTH INNOVATIVE APPLICATIONS OF ARTIFICIAL INTELLIGENCE CONFERENCE (IAAI-2000) LA English DT Proceedings Paper CT 17th National Conference on Artificial Intelligence (AAAI-2000)/12th Conference on Innovative Applications of Artificial Intelligence (IAAI-2000) CY JUL 30-AUG 03, 2000 CL AUSTIN, TX SP Amer Assoc Artificial Intelligence ID CONGESTION; NETWORKS AB We consider the use of multi-agent systems to control network routing. Conventional approaches to this task are based on Ideal Shortest Path routing Algorithm (ISPA), under which at each moment each agent in the network sends all of its traffic down the path that will incur the lowest cost to that traffic. We demonstrate in computer experiments that due to the side-effects of one agent's actions on another agent's traffic, use of ISPA's can result in large global cost. In particular, in a simulation of Braess' paradox we see that adding new capacity to a network with ISPA agents can decrease overall throughput. The theory of COllective INtelligence (COIN) design concerns precisely the issue of avoiding such side-effects. We use that theory to derive an idealized routing algorithm and show that a practical machine-learning-based version of this algorithm, in which costs are only imprecisely estimated substantially outperforms the ISPA, despite having access to less information than does the ISPA. In particular, this practical COIN algorithm avoids Braess' paradox. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Tumer, K (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 21 TC 0 Z9 0 U1 0 U2 0 PU M I T PRESS PI CAMBRIDGE PA FIVE CAMBRIDGE CENTER, CAMBRIDGE, MA 02142 USA BN 0-262-51112-6 PY 2000 BP 104 EP 109 PG 6 WC Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic; Robotics SC Computer Science; Engineering; Robotics GA BT26B UT WOS:000172441000016 ER PT B AU Kurien, J Nayak, PP AF Kurien, J Nayak, PP GP AAAI AAAI TI Back to the future for consistency-based trajectory tracking SO SEVENTEENTH NATIONAL CONFERENCE ON ARTIFICIAL INTELLIGENCE (AAAI-2001) / TWELFTH INNOVATIVE APPLICATIONS OF ARTIFICIAL INTELLIGENCE CONFERENCE (IAAI-2000) LA English DT Proceedings Paper CT 17th National Conference on Artificial Intelligence (AAAI-2000)/12th Conference on Innovative Applications of Artificial Intelligence (IAAI-2000) CY JUL 30-AUG 03, 2000 CL AUSTIN, TX SP Amer Assoc Artificial Intelligence AB Given a model of a physical process and a sequence of commands and observations received over time, the task of an autonomous controller is to determine the likely states of the process and the actions required to move the process to a desired configuration. We introduce a representation and algorithms for incrementally generating approximate belief states for a restricted but relevant class of partially observable Markov decision processes with very large state spaces. The algorithm incrementally generates, rather than revises, an approximate belief state at any point by abstracting and summarizing segments of the likely trajectories of the process. This enables applications to efficiently maintain a partial belief state when it remains consistent with observations and revisit past assumptions about the process's evolution when the belief state is ruled out. The system presented has been implemented and results on examples from the domain of spacecraft control are presented. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Kurien, J (reprint author), NASA, Ames Res Ctr, MS 269-3, Moffett Field, CA 94035 USA. NR 10 TC 28 Z9 32 U1 0 U2 1 PU M I T PRESS PI CAMBRIDGE PA FIVE CAMBRIDGE CENTER, CAMBRIDGE, MA 02142 USA BN 0-262-51112-6 PY 2000 BP 370 EP 377 PG 8 WC Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic; Robotics SC Computer Science; Engineering; Robotics GA BT26B UT WOS:000172441000057 ER PT B AU Morris, P Muscettola, N AF Morris, P Muscettola, N GP AAAI AAAI TI Execution of temporal plans with uncertainty SO SEVENTEENTH NATIONAL CONFERENCE ON ARTIFICIAL INTELLIGENCE (AAAI-2001) / TWELFTH INNOVATIVE APPLICATIONS OF ARTIFICIAL INTELLIGENCE CONFERENCE (IAAI-2000) LA English DT Proceedings Paper CT 17th National Conference on Artificial Intelligence (AAAI-2000)/12th Conference on Innovative Applications of Artificial Intelligence (IAAI-2000) CY JUL 30-AUG 03, 2000 CL AUSTIN, TX SP Amer Assoc Artificial Intelligence AB Simple Temporal Networks (STNS) have proved useful in applications that involve metric time. However, many applications involve events whose timing is uncertain in the sense that it is not controlled by the execution agent. In this paper we consider execution algorithms for temporal networks that include events of uncertain timing. We present two such algorithms. The first retains maximum flexibility, but requires potentially costly updates during execution. The second surrenders some flexibility in order to obtain a fast execution comparable to that available for ordinary STNS. C1 NASA, Ames Res Ctr, Caelum Res Corp, MS 269 1, Moffett Field, CA 94035 USA. NR 9 TC 6 Z9 6 U1 0 U2 0 PU M I T PRESS PI CAMBRIDGE PA FIVE CAMBRIDGE CENTER, CAMBRIDGE, MA 02142 USA BN 0-262-51112-6 PY 2000 BP 491 EP 496 PG 6 WC Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic; Robotics SC Computer Science; Engineering; Robotics GA BT26B UT WOS:000172441000075 ER PT J AU Fleming, GA Gorton, SA AF Fleming, GA Gorton, SA TI Measurement of rotorcraft blade deformation using Projection Moire Interferometry SO SHOCK AND VIBRATION LA English DT Article; Proceedings Paper CT 3rd International Conference on Vibration Measurements by Laser Techniques - Advances and Applications CY JUN 16-19, 1998 CL ANCONA, ITALY SP Italian Assoc Laser Velocimetry, Univ Studi Ancona, Dipartimento Meccan, AEA SArl, API Raffineria Ancona SpA, DAYCO PTI SpA, Merloni Elettrodomestici, NUOVO PIGNONE SpA, Opto & Laser Europe, TEUCO Guzzini Srl, Amer Concrete Inst Int, AMA, Fachverband Sensorik e V, Acoust Soc Japan, Bulgarreklama, GISI, Gruppo Imprese Strumentazione Italia, Int Assoc Hydraul Res, Int Measurement Confederat, Soc Automot Engineers Japan, Opt Soc Amer, Soc Automot Engineers, Soc Exptl Mech, Soc Instrument & Control Engineers DE Projection Moire Interferometry; PMI; rotorcraft; helicopter; blade; deformation; deflection AB Projection Moire Interferometry (PMI) has been used to obtain near instantaneous, quantitative blade deformation measurements of a generic rotorcraft model at several test conditions. These laser-based measurements provide quantitative, whole field, dynamic blade deformation profiles conditionally sampled as a function of rotor azimuth. The instantaneous nature of the measurements permits computation of the mean and unsteady blade deformation, blade bending, and twist. The PMI method is presented, and the image processing steps required to obtain quantitative deformation profiles from PMI interferograms are described. Experimental results are provided which show blade bending, twist, and unsteady motion. This initial proof-of-concept test has demonstrated the capability of PMI to acquire accurate, full field rotorcraft blade deformation data. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Fleming, GA (reprint author), NASA, Langley Res Ctr, Mail Stop 493, Hampton, VA 23681 USA. NR 19 TC 11 Z9 11 U1 1 U2 2 PU IOS PRESS PI AMSTERDAM PA NIEUWE HEMWEG 6B, 1013 BG AMSTERDAM, NETHERLANDS SN 1070-9622 J9 SHOCK VIB JI Shock Vib. PY 2000 VL 7 IS 3 BP 149 EP 165 PG 17 WC Acoustics; Engineering, Mechanical; Mechanics SC Acoustics; Engineering; Mechanics GA 359BM UT WOS:000089591700003 ER PT S AU Dudley, M Huang, W Vetter, WM Neudeck, P Powell, JA AF Dudley, M Huang, W Vetter, WM Neudeck, P Powell, JA BE Carter, CH Devaty, RP Rohrer, GS TI Synchrotron white beam topography studies of 2H SiC crystals SO SILICON CARBIDE AND RELATED MATERIALS - 1999 PTS, 1 & 2 SE MATERIALS SCIENCE FORUM LA English DT Article; Proceedings Paper CT International Conference on Silicon Carbide and Related Materials CY OCT 10-15, 1999 CL RES TRIANGLE PK, NORTH CAROLINA SP NASA, Glenn Res Ctr, USAF, Res Lab, mat & Mfg Directoirate, USN, Off Res, Def Res & Engn, Cree Inc, Charles & Colvard Inc, ABB Semicond, Sterling Semicond Inc, ATMI Inc, Epigress AB, Aixtron AG, Northrop Grumman, Siemens AG, EMCORE Inc, GE, Corp R & D, Litton Airton, II-VI Inc DE 2H polytype; Eshelby twist; Pendellosung AB Synchrotron White Beam X-ray Topography (SWBXT) has been used to characterize 2H silicon carbide crystals grown at NASA Glenn Research Center by the chemical reduction of methyltrichlorosilane at 1400 degreesC. The crystals studied have the form of tapered needles around 0.5 millimeters long and had hexagonal cross-sections 0.2 millimeters in diameter. Transmission Laue patterns confirmed the wurtzite structure of the 2H crystal. SWBXT images recorded in transmission geometry from two different crystals revealed excellent crystal quality, as evidenced by the presence of Pendellosung fringes, a result of the dynamical diffaction processes occurring inside the crystal. Close examination of these topographs and others recorded with different diffraction vectors revealed no evidence for the presence of the axial screw dislocations reported by Setaka and Ejiri, based on their observations of spiral growth steps, and also observed, for example, in alpha -Al2O3 and AlN whiskers. Nor was any evidence found for the presence of the "Eshelby Twist" associated with the presence of such dislocations. The absence of axial screw dislocations evidently indicates that the growth was not screw dislocation-assisted, and suggests that the stacking sequence was determined by the thermodynamic growth conditions, isolated inclusions, with characteristic contrast, were also observed in both crystals. C1 SUNY Stony Brook, Dept Mat Sci & Engn, Stony Brook, NY 11794 USA. NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Dudley, M (reprint author), SUNY Stony Brook, Dept Mat Sci & Engn, Stony Brook, NY 11794 USA. NR 8 TC 1 Z9 1 U1 0 U2 0 PU TRANS TECH PUBLICATIONS LTD PI ZURICH-UETIKON PA BRANDRAIN 6, CH-8707 ZURICH-UETIKON, SWITZERLAND SN 0255-5476 J9 MATER SCI FORUM PY 2000 VL 338-3 BP 465 EP 468 PG 4 WC Materials Science, Multidisciplinary; Materials Science, Coatings & Films SC Materials Science GA BR27W UT WOS:000165996700112 ER PT S AU Vetter, WM Dudley, M Huang, W Neudeck, P Powell, JA AF Vetter, WM Dudley, M Huang, W Neudeck, P Powell, JA BE Carter, CH Devaty, RP Rohrer, GS TI Synchrotron white beam x-ray topography and atomic force microscopy studies of a 540R-SiC Lely platelet SO SILICON CARBIDE AND RELATED MATERIALS - 1999 PTS, 1 & 2 SE MATERIALS SCIENCE FORUM LA English DT Article; Proceedings Paper CT International Conference on Silicon Carbide and Related Materials CY OCT 10-15, 1999 CL RES TRIANGLE PK, NORTH CAROLINA SP NASA, Glenn Res Ctr, USAF, Res Lab, mat & Mfg Directoirate, USN, Off Res, Def Res & Engn, Cree Inc, Charles & Colvard Inc, ABB Semicond, Sterling Semicond Inc, ATMI Inc, Epigress AB, Aixtron AG, Northrop Grumman, Siemens AG, EMCORE Inc, GE, Corp R & D, Litton Airton, II-VI Inc DE gaseous etching; long-repeat polytype; silicon carbide; x-ray topography AB Optical Microscopy and Atomic Force Microscopy (AFM) of a SiC Lely platelet revealed a macrostep pattern the periodicity of which led to speculation that it possessed a structure with a repeat distance roughly 350 times the SiC bilayer thickness. Transmission Laue patterns recorded from the crystal revealed a 3-fold symmetric pattern, qualitatively similar to that obtained from the 6H structure, but displaying an immense number of closely-spaced reflections. The diffraction spots were resolved with a specimen-film distance of 1.4m. The spacing of the spots in the 10 (1) over barl row indicated that the specimen's polytype was 540R. Synchrotron White Beam X-ray Topography (SWBXT) revealed the presence of growth dislocations emanating towards the platelet's growth facets, deformation-induced basal plane dislocations, and a group of superscrew dislocations close to the crystal's nucleation point. Optical microscopy revealed micropipes, which correlated with the superscrew dislocation images revealed by SWBXT, Preliminary calculations indicate that the total of the Burgers vectors of the observed micropipes was between 100 and 200nm. Trails of basal plane dislocation etch pits were shown by Nomarski microscopy to intersect the etched crystal surface in a roughly periodic fashion. The trails were attributed to enhanced etching of the intersection across a 1 degrees surface tilt of a series of basal plane dislocations distributed along the crystallographic c-axis with a periodicity related to that of the crystal surface's stepped ledges, This was confirmed using AFM, which revealed a faster etch rate at the intersections of basal plane dislocations at the ledges. C1 SUNY Stony Brook, Dept Mat Sci & Engn, Stony Brook, NY 11794 USA. NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Vetter, WM (reprint author), SUNY Stony Brook, Dept Mat Sci & Engn, Stony Brook, NY 11794 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU TRANS TECH PUBLICATIONS LTD PI ZURICH-UETIKON PA BRANDRAIN 6, CH-8707 ZURICH-UETIKON, SWITZERLAND SN 0255-5476 J9 MATER SCI FORUM PY 2000 VL 338-3 BP 469 EP 472 PG 4 WC Materials Science, Multidisciplinary; Materials Science, Coatings & Films SC Materials Science GA BR27W UT WOS:000165996700113 ER PT S AU Schnabel, CM Tabib-Azar, M Neudeck, PG Bailey, SG Su, HB Dudley, M Raffaelle, RP AF Schnabel, CM Tabib-Azar, M Neudeck, PG Bailey, SG Su, HB Dudley, M Raffaelle, RP BE Carter, CH Devaty, RP Rohrer, GS TI Correlation of EBIC and SWBXT imaged defects and epilayer growth pits in 6H-SiC Schottky diodes SO SILICON CARBIDE AND RELATED MATERIALS - 1999 PTS, 1 & 2 SE MATERIALS SCIENCE FORUM LA English DT Article; Proceedings Paper CT International Conference on Silicon Carbide and Related Materials CY OCT 10-15, 1999 CL RES TRIANGLE PK, NORTH CAROLINA SP NASA, Glenn Res Ctr, USAF, Res Lab, mat & Mfg Directoirate, USN, Off Res, Def Res & Engn, Cree Inc, Charles & Colvard Inc, ABB Semicond, Sterling Semicond Inc, ATMI Inc, Epigress AB, Aixtron AG, Northrop Grumman, Siemens AG, EMCORE Inc, GE, Corp R & D, Litton Airton, II-VI Inc DE defects; diffusion length; electron beam induced current (EBIC); epilayer growth pits; recombination centers; screw dislocation; synchrotron white-beam x-ray topography (SWBXT) AB We show the first direct experimental correlation between the presence of closed core screw dislocations in 6H-SiC epilayers with recombination centers, as well as with some of the small growth pits on the epilayer surface in lightly-doped 6H-SiC Schottky diodes. At every SWBXT-identified closed core screw dislocation, an EBIC image showed a dark spot indicating a recombination center, and Nomarski optical microscope and Atomic Force Microscope (AFM) images showed a corresponding small growth pit with a sharp apex on the surface of the epilayer. C1 Case Western Reserve Univ, Cleveland, OH 44106 USA. NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. SUNY Stony Brook, Stony Brook, NY 11794 USA. Rochester Inst Technol, Rochester, NY 14623 USA. RP Neudeck, PG (reprint author), Case Western Reserve Univ, Glennan 517,10900 Euclid Ave, Cleveland, OH 44106 USA. RI Su, Haibin/A-9434-2008 OI Su, Haibin/0000-0001-9760-6567 NR 6 TC 20 Z9 20 U1 0 U2 0 PU TRANS TECH PUBLICATIONS LTD PI ZURICH-UETIKON PA BRANDRAIN 6, CH-8707 ZURICH-UETIKON, SWITZERLAND SN 0255-5476 J9 MATER SCI FORUM PY 2000 VL 338-3 BP 489 EP 492 PG 4 WC Materials Science, Multidisciplinary; Materials Science, Coatings & Films SC Materials Science GA BR27W UT WOS:000165996700118 ER PT S AU Williams, EK Ila, D Poker, DB Hensley, DK Larkin, DJ AF Williams, EK Ila, D Poker, DB Hensley, DK Larkin, DJ BE Carter, CH Devaty, RP Rohrer, GS TI Ion beam induced change in the linear optical properties of SiC SO SILICON CARBIDE AND RELATED MATERIALS - 1999 PTS, 1 & 2 SE MATERIALS SCIENCE FORUM LA English DT Article; Proceedings Paper CT International Conference on Silicon Carbide and Related Materials CY OCT 10-15, 1999 CL RES TRIANGLE PK, NORTH CAROLINA SP NASA, Glenn Res Ctr, USAF, Res Lab, mat & Mfg Directoirate, USN, Off Res, Def Res & Engn, Cree Inc, Charles & Colvard Inc, ABB Semicond, Sterling Semicond Inc, ATMI Inc, Epigress AB, Aixtron AG, Northrop Grumman, Siemens AG, EMCORE Inc, GE, Corp R & D, Litton Airton, II-VI Inc DE colloids; ion implantation; nanoclusters ID SILICA; NANOCLUSTERS; IMPLANTATION AB We present the results of our investigation of producing nanoclusters of gold and tin in 6H-SiC and changes in the linear optical properties induced by Au, Sn and Si implantation, This is accomplished by implanting 1.0 MeV Au, 160 keV Sn and 5.0 MeV Si into the Si face of SiC at room or elevated temperature followed by annealing at various temperatures. Using optical absorption spectrophotometry, we determined the location of the absorption band for each metal nanocluster in SiC. Elevated temperature implantation reduces optical absorption due to ion implantation induced defects. Using the Mie theory, we determined the index of refraction in the implanted volume and estimated the size of the Au nanoclusters. C1 Alabama A&M Univ, Ctr Irradiat Mat, Normal, AL 35762 USA. Oak Ridge Natl Lab, Div Solid State, Oak Ridge, TN 37831 USA. NASA, Lewis Res Ctr, Cleveland, OH 44135 USA. RP Williams, EK (reprint author), Alabama A&M Univ, Ctr Irradiat Mat, Normal, AL 35762 USA. RI Hensley, Dale/A-6282-2016 OI Hensley, Dale/0000-0001-8763-7765 NR 10 TC 1 Z9 1 U1 0 U2 0 PU TRANS TECH PUBLICATIONS LTD PI ZURICH-UETIKON PA BRANDRAIN 6, CH-8707 ZURICH-UETIKON, SWITZERLAND SN 0255-5476 J9 MATER SCI FORUM PY 2000 VL 338-3 BP 667 EP 670 PG 4 WC Materials Science, Multidisciplinary; Materials Science, Coatings & Films SC Materials Science GA BR27W UT WOS:000165996700162 ER PT S AU Neudeck, PG AF Neudeck, PG BE Carter, CH Devaty, RP Rohrer, GS TI Electrical impact of SiC structural crystal defects on high electric field devices SO SILICON CARBIDE AND RELATED MATERIALS - 1999 PTS, 1 & 2 SE MATERIALS SCIENCE FORUM LA English DT Article; Proceedings Paper CT International Conference on Silicon Carbide and Related Materials CY OCT 10-15, 1999 CL RES TRIANGLE PK, NORTH CAROLINA SP NASA, Glenn Res Ctr, USAF, Res Lab, mat & Mfg Directoirate, USN, Off Res, Def Res & Engn, Cree Inc, Charles & Colvard Inc, ABB Semicond, Sterling Semicond Inc, ATMI Inc, Epigress AB, Aixtron AG, Northrop Grumman, Siemens AG, EMCORE Inc, GE, Corp R & D, Litton Airton, II-VI Inc DE avalanche breakdown; crystal defect; diode; epilayer growth pits; micropipe; microplasmas; pn junction; rectifiers; reliability; safe operating area; Schottky diodes; screw dislocation ID SILICON-CARBIDE; AVALANCHE BREAKDOWN; DENSITY AB Commercial epilayers are known to contain a variety of crystallographic imperfections, including micropipes, closed core screw dislocations, low-angle boundaries, basal plane dislocations, heteropolytypic inclusions, and non-ideal surface features like step bunching and pits. This paper reviews the limited present understanding of the operational impact of various crystal defects on SiC electrical devices. Aside from micropipes and triangular inclusions whose densities have been shrinking towards manageably small values in recent years, many of these defects appear to have little adverse operational and/or yield impact on SiC-based sensors, high-frequency RF, and signal conditioning electronics. However high-power switching devices used in power management and distribution circuits have historically (in silicon experience) demanded the highest material quality for prolonged safe operation, and are thus more susceptible to operational reliability problems that arise from electrical property nonuniformities likely to occur at extended crystal defects. A particular emphasis is placed on the impact of closed-core screw dislocations on high-power switching devices, because these difficult to observe defects are present in densities of thousands per cm(2) in commercial SiC epilayers, and their reduction to acceptable levels seems the most problematic at the present time. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Neudeck, PG (reprint author), NASA, Glenn Res Ctr, MS 77-1,21000 Brookpk Rd, Cleveland, OH 44135 USA. NR 22 TC 74 Z9 75 U1 0 U2 5 PU TRANS TECH PUBLICATIONS LTD PI ZURICH-UETIKON PA BRANDRAIN 6, CH-8707 ZURICH-UETIKON, SWITZERLAND SN 0255-5476 J9 MATER SCI FORUM PY 2000 VL 338-3 BP 1161 EP 1166 PG 6 WC Materials Science, Multidisciplinary; Materials Science, Coatings & Films SC Materials Science GA BR27W UT WOS:000165996700282 ER PT S AU Keskar, N Shenai, K Neudeck, PG AF Keskar, N Shenai, K Neudeck, PG BE Carter, CH Devaty, RP Rohrer, GS TI Transient characterization of SiCP-N diode SO SILICON CARBIDE AND RELATED MATERIALS - 1999 PTS, 1 & 2 SE MATERIALS SCIENCE FORUM LA English DT Article; Proceedings Paper CT International Conference on Silicon Carbide and Related Materials CY OCT 10-15, 1999 CL RES TRIANGLE PK, NORTH CAROLINA SP NASA, Glenn Res Ctr, USAF, Res Lab, mat & Mfg Directoirate, USN, Off Res, Def Res & Engn, Cree Inc, Charles & Colvard Inc, ABB Semicond, Sterling Semicond Inc, ATMI Inc, Epigress AB, Aixtron AG, Northrop Grumman, Siemens AG, EMCORE Inc, GE, Corp R & D, Litton Airton, II-VI Inc DE buck-converter; hard switching; p-n diodes; reliability; ZVS switching ID JUNCTION AB Silicon carbide is emerging as a superior material for semiconductor devices for applications that require high power operation at high temperature, radiation and chemically harsh environments. Besides the material properties of wide band-gap, high breakdown electric field, good thermal conductivity and carrier saturation velocity, SiC devices have been observed to display other useful properties that make them suitable for high current applications. This is especially true for bipolar devices where SIC can be used at high frequencies prohibited for silicon devices by large carrier storage and the consequent switching losses. SiC p-n diodes display a much reduced reverse recovery charge than silicon p-n diodes. Only a slight variation with forward current and temperature further improve their advantages. From this standpoint, the performance of the SiC diodes in applications that subject them to transient stresses must be studied. C1 Univ Illinois, Dept Elect Engn & Comp Sci, Chicago, IL 60607 USA. NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Keskar, N (reprint author), Univ Illinois, Dept Elect Engn & Comp Sci, 851 S Morgan St,1135 SEO, Chicago, IL 60607 USA. NR 7 TC 0 Z9 0 U1 0 U2 1 PU TRANS TECH PUBLICATIONS LTD PI ZURICH-UETIKON PA BRANDRAIN 6, CH-8707 ZURICH-UETIKON, SWITZERLAND SN 0255-5476 J9 MATER SCI FORUM PY 2000 VL 338-3 BP 1343 EP 1346 PG 4 WC Materials Science, Multidisciplinary; Materials Science, Coatings & Films SC Materials Science GA BR27W UT WOS:000165996700327 ER PT S AU Keskar, N Shenai, K Neudeck, P AF Keskar, N Shenai, K Neudeck, P BE Carter, CH Devaty, RP Rohrer, GS TI Defect modeling and simulation of 4-H SiCP-N diode SO SILICON CARBIDE AND RELATED MATERIALS - 1999 PTS, 1 & 2 SE MATERIALS SCIENCE FORUM LA English DT Article; Proceedings Paper CT International Conference on Silicon Carbide and Related Materials CY OCT 10-15, 1999 CL RES TRIANGLE PK, NORTH CAROLINA SP NASA, Glenn Res Ctr, USAF, Res Lab, mat & Mfg Directoirate, USN, Off Res, Def Res & Engn, Cree Inc, Charles & Colvard Inc, ABB Semicond, Sterling Semicond Inc, ATMI Inc, Epigress AB, Aixtron AG, Northrop Grumman, Siemens AG, EMCORE Inc, GE, Corp R & D, Litton Airton, II-VI Inc DE 2-D simulations; "defect" diode; forward I-V characteristics; modeling; p-n diodes ID DISLOCATIONS; DEVICES AB Silicon carbide is seen as a potent material for high power, high temperature and harsh environment applications. However the commercial use of SiC devices is greatly restricted by the immature process technology and wafer quality deficiencies. While the most degrading micropipe defects have been significantly reduced in number, other defect types like the closed core screw dislocations continue to contaminate SiC devices in large quantities. The effects of these defects on the quality and performance of SiC devices is under study. This paper models the presence of embedded structural defects in SiC PN junction diodes. The defects are presented as parallel diodes to the "ideal" ones with areas correspondingly reduced. "Defect" diodes are shown to turn on earlier to the "ideal" ones giving an anomalous bump in the initial part of forward I-V curves. C1 Univ Illinois, Dept Elect Engn & Comp Sci, Chicago, IL 60607 USA. NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Keskar, N (reprint author), Univ Illinois, Dept Elect Engn & Comp Sci, 851 S Morgan St,1135 SEO, Chicago, IL 60607 USA. NR 8 TC 6 Z9 6 U1 0 U2 1 PU TRANS TECH PUBLICATIONS LTD PI ZURICH-UETIKON PA BRANDRAIN 6, CH-8707 ZURICH-UETIKON, SWITZERLAND SN 0255-5476 J9 MATER SCI FORUM PY 2000 VL 338-3 BP 1351 EP 1354 PG 4 WC Materials Science, Multidisciplinary; Materials Science, Coatings & Films SC Materials Science GA BR27W UT WOS:000165996700329 ER PT S AU Hunter, GW Neudeck, PG Gray, M Androjna, D Chen, LY Hoffman, RW Liu, CC Wu, QH AF Hunter, GW Neudeck, PG Gray, M Androjna, D Chen, LY Hoffman, RW Liu, CC Wu, QH BE Carter, CH Devaty, RP Rohrer, GS TI SiC-based gas sensor development SO SILICON CARBIDE AND RELATED MATERIALS - 1999 PTS, 1 & 2 SE MATERIALS SCIENCE FORUM LA English DT Article; Proceedings Paper CT International Conference on Silicon Carbide and Related Materials CY OCT 10-15, 1999 CL RES TRIANGLE PK, NORTH CAROLINA SP NASA, Glenn Res Ctr, USAF, Res Lab, mat & Mfg Directoirate, USN, Off Res, Def Res & Engn, Cree Inc, Charles & Colvard Inc, ABB Semicond, Sterling Semicond Inc, ATMI Inc, Epigress AB, Aixtron AG, Northrop Grumman, Siemens AG, EMCORE Inc, GE, Corp R & D, Litton Airton, II-VI Inc DE electronic nose; emission; gas; high temperature; hydrocarbon; packaging; sensor AB Silicon carbide based Schottky diode gas sensors are being developed for applications such as emission measurements and leak detection. The effects of the geometry of the tin oxide film in a Pd/SnO2/SiC structure will be discussed as well as improvements in packaging SiC-based sensors. It is concluded that there is considerable versatility in the formation of SiC-based Schottky diode gas sensing structures which will potentially allow the fabrication of a SiC-based gas sensor array for a variety of gases and temperatures. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. Corez, Cleveland, OH 44135 USA. Ayt Corp, NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. Ohio Aerosp Inst, Cleveland, OH 44142 USA. Case Western Reserve Univ, Ctr Elect Design, Cleveland, OH 44106 USA. RP Hunter, GW (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 3 TC 43 Z9 44 U1 0 U2 1 PU TRANS TECH PUBLICATIONS LTD PI ZURICH-UETIKON PA BRANDRAIN 6, CH-8707 ZURICH-UETIKON, SWITZERLAND SN 0255-5476 J9 MATER SCI FORUM PY 2000 VL 338-3 BP 1439 EP 1442 PG 4 WC Materials Science, Multidisciplinary; Materials Science, Coatings & Films SC Materials Science GA BR27W UT WOS:000165996700351 ER PT S AU Muntele, CI Ila, D Williams, EK Poker, DB Hensley, DK Larkin, DJ Muntele, I AF Muntele, CI Ila, D Williams, EK Poker, DB Hensley, DK Larkin, DJ Muntele, I BE Carter, CH Devaty, RP Rohrer, GS TI Fabrication of SiC hydrogen sensor by Pd-implantation SO SILICON CARBIDE AND RELATED MATERIALS - 1999 PTS, 1 & 2 SE MATERIALS SCIENCE FORUM LA English DT Article; Proceedings Paper CT International Conference on Silicon Carbide and Related Materials CY OCT 10-15, 1999 CL RES TRIANGLE PK, NORTH CAROLINA SP NASA, Glenn Res Ctr, USAF, Res Lab, mat & Mfg Directoirate, USN, Off Res, Def Res & Engn, Cree Inc, Charles & Colvard Inc, ABB Semicond, Sterling Semicond Inc, ATMI Inc, Epigress AB, Aixtron AG, Northrop Grumman, Siemens AG, EMCORE Inc, GE, Corp R & D, Litton Airton, II-VI Inc DE hydrogen sensors; ion implantation AB Silicon carbide, a semiconductor, is used to fabricate an efficient high temperature hydrogen sensor. When a palladium coating is applied on the exposed surface of silicon carbide, the chemical reaction between palladium and hydrogen produces a detectable change in the surface chemical potential. Rather than applying an external palladium film we have implanted palladium ions into the silicon face of 6H, n-type SiC samples at the ion energies of 130 keV and 70 keV and various fluences at 500 degreesC. Then each sample was exposed to low levels of hydrogen and its response measured by monitoring the current through the sample, with respect to time. The results obtained are presented in this paper. C1 Alabama A&M Univ, Ctr Irradiat Mat, Normal, AL 35762 USA. Oak Ridge Natl Lab, Div Solid State, Oak Ridge, TN 37831 USA. NASA, Lewis Res Ctr, Cleveland, OH 44135 USA. RP Muntele, CI (reprint author), Alabama A&M Univ, Ctr Irradiat Mat, Normal, AL 35762 USA. RI Hensley, Dale/A-6282-2016 OI Hensley, Dale/0000-0001-8763-7765 NR 6 TC 7 Z9 7 U1 0 U2 1 PU TRANS TECH PUBLICATIONS LTD PI ZURICH-UETIKON PA BRANDRAIN 6, CH-8707 ZURICH-UETIKON, SWITZERLAND SN 0255-5476 J9 MATER SCI FORUM PY 2000 VL 338-3 BP 1443 EP 1446 PG 4 WC Materials Science, Multidisciplinary; Materials Science, Coatings & Films SC Materials Science GA BR27W UT WOS:000165996700352 ER PT B AU Rouff, C Rash, J Hinchey, MG AF Rouff, C Rash, J Hinchey, MG GP IEEE COMPUTER SOCIETY IEEE COMPUTER SOCIETY TI Experience using formal methods for specifying a multi-agent system SO SIXTH IEEE INTERNATIONAL CONFERENCE ON ENGINEERING OF COMPLEX COMPUTER SYSTEMS, PROCEEDINGS SE IEEE International Conference on Engineering Complex Computer Systems-ICECCS LA English DT Proceedings Paper CT 6th IEEE International Conference on Engineering of Complex Computer Systems CY SEP 11-14, 2000 CL TOKYO, JAPAN SP IEEE Comp Soc, IEEE Tech Comm Complex Comp, Informat Processing Soc Japan, Inst Electr Informat & Commun Engineers Japan, Japan Soc Software Sci & Technol AB The process and results of using formal methods to specify the Lights Out Ground Operations System (LOGOS) are presented in this paper. LOGOS is a prototype multi-agent system developed to demonstrate the feasibility of providing autonomy to satellite ground operations functions at NASA Goddard Space Flight Center (GSFC). Following the initial implementation of LOGOS, the development team decided to use formal methods to check for race conditions, deadlocks and omissions. The specification exercise revealed several omissions as well as race conditions. After completing the specification the team concluded that certain tools would have made the specification process easier. This paper gives a sample specification of two of the agents in the LOGOS system and examples of omissions and race conditions found. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Rouff, C (reprint author), NASA, Goddard Space Flight Ctr, Code 588-0, Greenbelt, MD 20771 USA. EM chris.rouff@gsfc.nasa.gov; james.rash@gsfc.nasa.gov; mhinchey@unomaha.edu NR 5 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 BN 0-7695-0583-X J9 IEEE INT C ENG COMP PY 2000 BP 72 EP 80 DI 10.1109/ICECCS.2000.873929 PG 9 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BQ92M UT WOS:000090093700007 ER PT S AU Bilbro, JW Walker, JG AF Bilbro, JW Walker, JG BE SanchezMondragon, JJ TI Optics education for K-12 SO SIXTH INTERNATIONAL CONFERENCE ON EDUCATION AND TRAINING IN OPTICS AND PHOTONICS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT 6th International Conference on Education and Training in Optics and Photonics CY JUL 28-30, 1999 CL CANCUN, MEXICO SP Int Commiss Opt, Opt Soc Amer, SPIE, Univ Autonoma Estado Morelos, Mexico, Univ Guanajuato, Mexico, Acad Mexicana Optica, Secretaria Educ Publica, Consejo Nacl Cienca & Technol, Univ Amer Puebla, Inst Natl Astrofisica, Optica Electronica, Centro Investigaciones Opticas, CICESE, Univ Nacl Autonoma Medixo, Natl Sci Fdn AB The SPIE Education Committee has developed an outreach program aimed at enhancing the dissemination of information about optics to children in kindergarten through the 12(th) grade (K-12). The main impetus behind the program was that more practicing optical scientists and engineers would be willing to give lectures and demonstrations aimed at inspiring the next generation about optics if material could be made easily available. Consequently, three instructional "outreach kits" were assembled for use in teaching optics to kids in exciting and fun ways. These kits were beta-tested over the last two years at six different U.S. regional sites: Huntsville, Alabama; San Diego, California; Stem, Connecticut; Orlando, Florida; and Terre Haute, Indiana. Each "outreach kit" contained: 1) a workbook on Optical Demonstrations on the Overhead Projector; 2) a Science and Math Experience Manual: Light, Color and Their Uses; 3) The Optics Discovery, Classroom Kif; 4) a slide show; and 5) a video on careers in optics. The beta tests were aimed at evaluating the practical ways of utilizing the kits, developing easy-to-follow instructions for guiding others in their use and providing suggestions on modifications, additions, and deletions to the kits. This paper discusses this outreach program and provides details relative to the kit's composition and future plans. C1 NASA, George C Marshall Space Flight Ctr, SPIE Educ Comm & Special Assistant Opt, Huntsville, AL 35812 USA. RP Bilbro, JW (reprint author), NASA, George C Marshall Space Flight Ctr, SPIE Educ Comm & Special Assistant Opt, MS DA01, Huntsville, AL 35812 USA. NR 0 TC 0 Z9 0 U1 0 U2 2 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3322-5 J9 P SOC PHOTO-OPT INS PY 2000 VL 3831 BP 92 EP 97 DI 10.1117/12.388721 PG 2 WC Engineering, Electrical & Electronic; Optics SC Engineering; Optics GA BQ51B UT WOS:000088548900012 ER PT B AU Shaya, E Peebles, PJE Phelps, S Tully, RB AF Shaya, E Peebles, PJE Phelps, S Tully, RB BE Valtonen, MJ Flynn, C TI Mass-to-light ratio measurements of galaxies, groups, and clusters using the numerical action method SO SMALL GALAXY GROUPS SE ASTRONOMICAL SOCIETY OF THE PACIFIC CONFERENCE SERIES LA English DT Proceedings Paper CT 174th IAU Colloquium on Small Galaxy Groups CY JUN 13-18, 1999 CL TURKU, FINLAND SP IAU, Univ Turku, Acad Finland ID LEAST ACTION PRINCIPLE; LOCAL GROUP; NEARBY GALAXIES; ORBITS AB The numerical action variational method (NAM) is an elegant, non-chaotic technique for calculating the trajectories of gravitating systems in a cosmological context. It has been used extensively for establishing orbits of Local Group galaxies in a series of papers (Peebles 1989, 1990, 1994, 1995) and for the Local Supercluster (Shaya, Peebles, & Tully 1995). Our repertoir of tools include code that holds present distances constant and predicts possible redshifts, one that holds present redshifts constant and predicts possible distances, and one that varies masses of each mass tracer and simultaneously satisfies both distance and redshift. Our results indicate a Omega(0) = 0.2, a mass-to-light ratio of field galaxies in the range of 100 M./L. in blue light (t(0) = 11 Gyr with no cosmological constant), but for the Virgo Cluster, the value is 6 or 7 times higher. The higher values of Omega(0) determined from using the IRAS galaxy distributions may be a result of under weighting this important mass component of the universe plus a poor correlation between cluster and field galaxy distributions. C1 NASA, RITSS, Washington, DC 20546 USA. RP Shaya, E (reprint author), NASA, RITSS, Washington, DC 20546 USA. NR 12 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 1-58381-040-4 J9 ASTR SOC P PY 2000 VL 209 BP 445 EP 452 PG 8 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BQ80T UT WOS:000089621300077 ER PT S AU Leon, J Cutlip, WE Hametz, ME AF Leon, J Cutlip, WE Hametz, ME BE Horais, BJ Twiggs, RJ TI Access To Space interactive mission design web site SO SMALL PAYLOADS IN SPACE SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Small Payloads in Space CY AUG 03-04, 2000 CL SAN DIEGO, CA SP SPIE AB The Access To Space (ATS) Group at NASA's Goddard Space Flight Center (GSFC) supports the science and technology community by facilitating frequent and affordable opportunities for access to space. The ATS Group has developed an interactive Mission Design web site that provides both the information and the tools necessary to assist mission planners in selecting and planning their ride to space. The ATS web site was developed through core partnerships with other government agencies seeking similar tools for their mission planners. Key design features of the site include a searchable mission database and launch vehicle toolboxes. The mission database contains a listing of missions ranging from proposed missions to manifested missions allowing users to interactively search for potential partnering opportunities. Missions can be added to the database by the user community through data input tools. The launch vehicle toolbox section provides the user with a full range of information on vehicle classes and individual configurations. This section has been enhanced to include additional access modes such as RLVs, ultra long duration balloons, sub-orbital rockets, Space Shuttle carriers, and spacecraft buses. Use of the ATS web site has climbed 400% in the last six months indicating widespread usage across the mission planning community. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Leon, J (reprint author), NASA, Goddard Space Flight Ctr, MS 740-2, Greenbelt, MD 20771 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3781-6 J9 P SOC PHOTO-OPT INS PY 2000 VL 4136 BP 8 EP 16 DI 10.1117/12.406657 PG 9 WC Engineering, Aerospace SC Engineering GA BR62D UT WOS:000166963700002 ER PT S AU Allison, SG Fox, RL Froggatt, ME Childers, BA AF Allison, SG Fox, RL Froggatt, ME Childers, BA BE Jacobs, JH TI THUNDER piezoelectric actuators as a method of stretch-tuning an optical fiber grating SO SMART STRUCTURES AND MATERIAL 2000: INDUSTRIAL AND COMMERCIAL APPLICATIONS OF SMART STRUCTURES TECHNOLOGIES SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2000 Conference CY MAR 05-09, 2000 CL NEWPORT BEACH, CA SP SPIE, Soc Exptl Mech, Amer Soc Mech Engn, BFGoodrich, Def Adv Res Projects Agcy, USA Res Off, USAF Res Lab, Ceram Soc Japan, Intelligent Mat Forum, Japan DE tuning; optical; fiber Bragg grating; piezoelectric; actuator ID DISTRIBUTED MEASUREMENT; MODULATION; STRAIN AB A method of stretching optical fiber holds interest for measuring strain in smart structures where the physical displacement may be used to tune optical fiber lasers. A small, light weight, low power tunable fiber laser is ideal for demodulating strain in optical fiber Bragg gratings attached to smart structures such as the reusable launch vehicle that is being developed by NASA. A method is presented for stretching optical fibers using the THUNDER piezoelectric actuators invented at NASA Langley Research Center. THUNDER actuators use a piezoelectric layer bonded to a metal backing to enable the actuators to produce displacements larger than the unbonded piezoelectric material. The shift in reflected optical wavelength resulting from stretching the fiber Bragg grating is presented. Means of adapting THUNDER actuators for stretching optical fibers is discussed, including ferrules, ferrule clamp blocks, and plastic hinges made with stereo lithography. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Allison, SG (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. NR 14 TC 2 Z9 2 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 0-8194-3609-7 J9 P SOC PHOTO-OPT INS PY 2000 VL 3991 BP 74 EP 83 DI 10.1117/12.388148 PG 10 WC Engineering, Aerospace; Engineering, Industrial; Engineering, Mechanical; Materials Science, Multidisciplinary; Optics SC Engineering; Materials Science; Optics GA BQ59X UT WOS:000088917900009 ER PT S AU Bryant, RG Evans, SA Long, ER Fox, RL AF Bryant, RG Evans, SA Long, ER Fox, RL BE Jacobs, JH TI Thermal and mechanical characterization of NASA high displacement actuators for satellite instrumentation SO SMART STRUCTURES AND MATERIAL 2000: INDUSTRIAL AND COMMERCIAL APPLICATIONS OF SMART STRUCTURES TECHNOLOGIES SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2000 Conference CY MAR 05-09, 2000 CL NEWPORT BEACH, CA SP SPIE, Soc Exptl Mech, Amer Soc Mech Engn, BFGoodrich, Def Adv Res Projects Agcy, USA Res Off, USAF Res Lab, Ceram Soc Japan, Intelligent Mat Forum, Japan DE high displacement actuators; THUNDER; NASDRIV; piezoelectric devices; HDA AB NASA's High Displacement Actuators (HDAs) are being examined for several potential aerospace applications. In order to determine if these HDAs are suitable for these applications, the strain must be determined as a function of applied voltage and stress over the range of temperatures required for the environment of space. Additionally, the variability between HDAs of the same design must be determined to establish their performance average and standard deviation. Towards this end, a matched set of rectangular HDAs were fabricated and characterized to determine their on-center displacement. These actuators were run at a 1 Hz (sine) frequency using peak-to-peak voltages from 100 to 800 volts with a maximum negative voltage of -150 volts. The test temperatures ranged from -101 to 66 degrees C (+/-150 degrees F) at 28 degrees C (50 degrees F) intervals. Loads ranging from 50g to 1450g were line loaded on center to observe the effects of strain on displacement. After preliminary characterization, these HDAs were incorporated into a prototype linear motor drive system for satellite instrumentation. This paper describes the fabrication, test methodology and the resulting performance of these HDAs as well as the linear piezo motor. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Bryant, RG (reprint author), NASA, Langley Res Ctr, MS 226, Hampton, VA 23681 USA. NR 7 TC 1 Z9 1 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3609-7 J9 P SOC PHOTO-OPT INS PY 2000 VL 3991 BP 195 EP 201 DI 10.1117/12.388161 PG 7 WC Engineering, Aerospace; Engineering, Industrial; Engineering, Mechanical; Materials Science, Multidisciplinary; Optics SC Engineering; Materials Science; Optics GA BQ59X UT WOS:000088917900021 ER PT S AU Scott, RC AF Scott, RC BE Jacobs, JH TI Active control of wind-tunnel model aeroelastic response using neural networks SO SMART STRUCTURES AND MATERIAL 2000: INDUSTRIAL AND COMMERCIAL APPLICATIONS OF SMART STRUCTURES TECHNOLOGIES SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2000 Conference CY MAR 05-09, 2000 CL NEWPORT BEACH, CA SP SPIE, Soc Exptl Mech, Amer Soc Mech Engn, BFGoodrich, Def Adv Res Projects Agcy, USA Res Off, USAF Res Lab, Ceram Soc Japan, Intelligent Mat Forum, Japan DE neural network; adaptive control; aeroelasticity; flutter suppression AB Under a joint research and development effort conducted by the National Aeronautics and Space Administration and The Boeing Company (formerly McDonnell Douglas) three neural-network based control systems were developed and tested. The control systems were experimentally evaluated using a transonic wind-tunnel model in the Langley Transonic Dynamics Tunnel. One system used a neural network to schedule flutter suppression control laws, another employed a neural network in a predictive control scheme, and the third employed a neural network in an inverse model control scheme. All three of these control schemes successfully suppressed flutter do or near the limits of the testing apparatus, and represent the first experimental applications of neural networks to flutter suppression. This paper will summarize the findings of this project. C1 NASA, Langley Res Ctr, Aeroelast Branch, Hampton, VA 23681 USA. RP Scott, RC (reprint author), NASA, Langley Res Ctr, Aeroelast Branch, Hampton, VA 23681 USA. NR 22 TC 1 Z9 1 U1 0 U2 4 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3609-7 J9 P SOC PHOTO-OPT INS PY 2000 VL 3991 BP 232 EP 243 DI 10.1117/12.388166 PG 12 WC Engineering, Aerospace; Engineering, Industrial; Engineering, Mechanical; Materials Science, Multidisciplinary; Optics SC Engineering; Materials Science; Optics GA BQ59X UT WOS:000088917900025 ER PT S AU Wilkie, WK Bryant, RG High, JW Fox, RL Hellbaum, RF Jalink, A Little, BD Mirick, PH AF Wilkie, WK Bryant, RG High, JW Fox, RL Hellbaum, RF Jalink, A Little, BD Mirick, PH BE Jacobs, JH TI Low-cost piezocomposite actuator for structural control applications SO SMART STRUCTURES AND MATERIAL 2000: INDUSTRIAL AND COMMERCIAL APPLICATIONS OF SMART STRUCTURES TECHNOLOGIES SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2000 Conference CY MAR 05-09, 2000 CL NEWPORT BEACH, CA SP SPIE, Soc Exptl Mech, Amer Soc Mech Engn, BFGoodrich, Def Adv Res Projects Agcy, USA Res Off, USAF Res Lab, Ceram Soc Japan, Intelligent Mat Forum, Japan DE piezoceramic actuators; interdigitated electrodes; piezoceramic fibers; piezoelectric composites AB The design, manufacture, and testing of a low-cost, flexible, planar composite piezoceramic actuator device will be presented. The actuator uses interdigitated electrodes for poling and subsequent actuation of an internal layer of machined piezoceramic fibers. The fiber sheets are formed from monolithic piezoceramic wafers and conventional computer controlled wafer-dicing methods. The fabrication and use of fiber sheets allows precise handling and alignment of piezoceramic fibers during subsequent phases of actuator assembly. Tests show that the actuator is capable of producing large, directional in-plane strains; on order of 2000 parts-per-million under a 4000 V peak-to-peak applied voltage cycle. Preliminary endurance testing indicates that the device is relatively durable, with no reductions in free-strain performance up to 90 million electrical cycles. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Wilkie, WK (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. NR 11 TC 154 Z9 155 U1 2 U2 13 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3609-7 J9 P SOC PHOTO-OPT INS PY 2000 VL 3991 BP 323 EP 334 DI 10.1117/12.388175 PG 12 WC Engineering, Aerospace; Engineering, Industrial; Engineering, Mechanical; Materials Science, Multidisciplinary; Optics SC Engineering; Materials Science; Optics GA BQ59X UT WOS:000088917900034 ER PT S AU Turner, TL AF Turner, TL BE Jacobs, JH TI Dynamic response tuning of composite beams by embedded shape memory alloy actuators SO SMART STRUCTURES AND MATERIAL 2000: INDUSTRIAL AND COMMERCIAL APPLICATIONS OF SMART STRUCTURES TECHNOLOGIES SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2000 Conference CY MAR 05-09, 2000 CL NEWPORT BEACH, CA SP SPIE, Soc Exptl Mech, Amer Soc Mech Engn, BFGoodrich, Def Adv Res Projects Agcy, USA Res Off, USAF Res Lab, Ceram Soc Japan, Intelligent Mat Forum, Japan DE shape memory alloys; nitinol; hybrid composites; thermoelasticity; constitutive modeling; finite element analysis; material nonlinearity; thermal suckling; thermal post-buckling; random response ID NITINOL-REINFORCED PLATES; ACTIVE VIBRATION; LAMINATED PLATES; FIBERS; MODEL AB The thermomechanical performance of a shape memory alloy hybrid composite beam specimen is demonstrated and used in a preliminary validation study of a recently developed constitutive model and finite element formulation for analysis of such structures. A brief description of the thermoelastic formulation is given. A material system consisting of a glass/epoxy matrix with embedded Nitinol actuators was chosen for this study. Results from Nitinol material characterization testing, beam specimen fabrication processes, and base acceleration testing for measuring the dynamic response performance is presented. Selected results from the dynamic tests are shown, interpreted, and compared with predictions from the FE model. Elimination of a thermal post-buckling deflection by the activated SMA was observed. The fundamental natural frequency is shown to increase by a factor of 5.3 and the RMS displacement response is attenuated by a factor 6.4. Preliminary comparisons between predicted and measured performance is good. Discrepancies are attributable to insufficient knowledge of the matrix material properties at elevated temperature. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Turner, TL (reprint author), NASA, Langley Res Ctr, MS 463, Hampton, VA 23681 USA. NR 31 TC 7 Z9 7 U1 0 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 0-8194-3609-7 J9 P SOC PHOTO-OPT INS PY 2000 VL 3991 BP 377 EP 388 DI 10.1117/12.388180 PG 12 WC Engineering, Aerospace; Engineering, Industrial; Engineering, Mechanical; Materials Science, Multidisciplinary; Optics SC Engineering; Materials Science; Optics GA BQ59X UT WOS:000088917900039 ER PT S AU Dekens, FG Neat, G AF Dekens, FG Neat, G BE Werely, NM TI Micro-precision interferometer: Pointing system solutions for on-orbit disturbance environment. SO SMART STRUCTURES AND MATERIAL 2000: SMART STRUCTURES AND INTEGRATED SYSTEMS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2000 Conference CY MAR 05-09, 2000 CL NEWPORT BEACH, CA SP SPIE, Soc Exptl Mech, Amer Soc Mech Engn, BFGoodrich, Def Adv Res Projects Agcy, USA Res Off, USAF Res Lab, Ceram Soc Japan, Intelligent Mat Forum, Japan DE space interferometry; isolation system; interferometry testbed AB The Space Interferometer Mission (SIM) is required to point each arm of its science interferometer to better than 30 milli-arcseconds (mas) RMS residual jitter using a 0.01 Hz bandwidth optical sensor on the star. We address the residual pointing error due to the spinning spacecraft reaction wheel assemblies which emit disturbances from 2 Hz to 1 kHz. The vibration attenuation strategy for this "blind" pointing problem is to isolate each reaction wheel assembly with a vibration isolation system and to possibly augment the low bandwidth closed loop system with an internal high bandwidth sensor. Central to estimating the high frequency pointing error is the Micro-Precision Interferometer (MPI) testbed which is a softly suspended hardware model of a spaceborne optical interferometer and is dimensionally representative of SIM. Using the testbed and a transfer function-based performance prediction algorithm, we show that the 30 mas requirement is missed by a factor of six when only employing a six-axis active vibration isolator made by TRW. In preparation for augmenting the vibration attenuation strategy, we also show that the primary contributor to the tip-tilt jitter error is the first optic in the interferometer's optical train. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Dekens, FG (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3603-8 J9 P SOC PHOTO-OPT INS PY 2000 VL 3985 BP 386 EP 393 DI 10.1117/12.388841 PG 8 WC Automation & Control Systems; Engineering, Electrical & Electronic; Materials Science, Ceramics SC Automation & Control Systems; Engineering; Materials Science GA BQ59C UT WOS:000088899900035 ER PT S AU Bar-Cohen, Y Sherrit, S Dolgin, B Pal, D Peterson, T Kroh, J Krahe, R AF Bar-Cohen, Y Sherrit, S Dolgin, B Pal, D Peterson, T Kroh, J Krahe, R BE Lynch, CS TI Ultrasonic/sonic drilling/coring (USDC) for in-situ planetary applications SO SMART STRUCTURES AND MATERIALS 2000 - ACTIVE MATERIALS: BEHAVIOR AND MECHANICS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2000 Conference CY MAR 05-09, 2000 CL NEWPORT BEACH, CA SP SPIE, Soc Exptl Mech, Amer Soc Mech Engn, BFGoodrich, Def Adv Res Projects Agcy, USA Res Off, USAF Res Lab, Ceram Soc Japan, Intelligent Mat Forum, Japan DE piezoelectric; drilling; ultrasonic; sonic; USDC; stack; horn; strain amplification; light rovers; planetary exploration AB A novel ultrasonic drilling and coring device (USDC) was demonstrated to drill a wide variety of rocks: from ice and chalk to granite and basalt. The USDC addresses the key shortcomings of the conventional drills. The device requires low preload (<10 N) and power (down to an average of 5W). The drill bits are not sharpened and, therefore there is no concern to loss of performance due to warring out. The device is not subject to drill walk during core initiation, and, does nor apply larger lateral forces on its platform. The USDC has produced round and square cores and 14-cm deep holes and has opened new possibilities to the designers of future NASA planetary exploration missions. USDC can be mounted on a Sojourner class rover, a robotic arm or an Aerobot. USDC itself can perform in very diverse environments and it is an ideal tool for down-the-well delivery of in-situ instruments. Since the drill bit does not rotate, many interface problems are simplified. The ultrasonic vibration was observed to transport the drilling debris out of the well. The USDC itself can be used as a sensor for screening drilled objects and the ultrasonic waves produced by the USDC can be used for in-situ characterization of rock properties and as a source for sonar. This article describes preliminary modeling of the USDC actuator that predicted various resonance frequencies of the device with a relatively good accuracy. Efforts to develop a comprehensive model that accounts for the properties of the drilled objects are underway. This model should allow optimization of the USDC performance. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Bar-Cohen, Y (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 82-105, Pasadena, CA 91109 USA. NR 6 TC 1 Z9 2 U1 0 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 0-8194-3610-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 3992 BP 661 EP 668 DI 10.1117/12.388189 PG 8 WC Materials Science, Ceramics; Mechanics; Materials Science, Composites; Physics, Applied SC Materials Science; Mechanics; Physics GA BQ59Y UT WOS:000088918100064 ER PT S AU Bar-Cohen, Y Chang, ZS AF Bar-Cohen, Y Chang, ZS BE Lynch, CS TI Piezoelectrically actuated miniature peristaltic pump SO SMART STRUCTURES AND MATERIALS 2000 - ACTIVE MATERIALS: BEHAVIOR AND MECHANICS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2000 Conference CY MAR 05-09, 2000 CL NEWPORT BEACH, CA SP SPIE, Soc Exptl Mech, Amer Soc Mech Engn, BFGoodrich, Def Adv Res Projects Agcy, USA Res Off, USAF Res Lab, Ceram Soc Japan, Intelligent Mat Forum, Japan DE pumps; piezoelectric actuation; piezopump; peristaltic pump; actuators AB Increasingly NASA experiments, instruments and applications are requiring pumps that are miniature and consume low power. To address this need, a piezoelectrically actuated pump is being developed. This pump employs a novel volume displacing mechanism using flexural traveling waves that act peristaltically eliminating the need for valves or physically moving parts. Finite element model was developed using ANSYS to predict the resonance frequency of the vibrating mode for the piezopump driving stator. The model also allows determining simultaneously the mode shapes that are associated with the various resonance frequencies. This capability is essential for designing the pump size and geometry. To predict and optimize the pump efficiency, which is determined by the volume of pumping chambers, the model was modified to perform harmonic analysis. Current capability allows the determination of the effect of such design parameters as pump geometry, construction materials and operating modes on the volume of the chambers that is available between the peaks and valleys of the waves. Experiments were conducted using a breadboard of the piezopump and showed water-pumping rate of about 3.0 cc/min. The performance of pump is continuing to be modified to enhance the performance and efficiency. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Bar-Cohen, Y (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 82-105, Pasadena, CA 91109 USA. NR 9 TC 7 Z9 7 U1 0 U2 2 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3610-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 3992 BP 669 EP 676 DI 10.1117/12.388190 PG 8 WC Materials Science, Ceramics; Mechanics; Materials Science, Composites; Physics, Applied SC Materials Science; Mechanics; Physics GA BQ59Y UT WOS:000088918100065 ER PT S AU Bao, XQ Bar-Cohen, Y AF Bao, XQ Bar-Cohen, Y BE Lynch, CS TI Complete modeling of rotary ultrasonic motors actuated by traveling flexural waves SO SMART STRUCTURES AND MATERIALS 2000 - ACTIVE MATERIALS: BEHAVIOR AND MECHANICS SE Proceedings of SPIE LA English DT Proceedings Paper CT Smart Structures and Materials 2000 Conference CY MAR 05-09, 2000 CL NEWPORT BEACH, CA SP SPIE, Soc Exptl Mech, Amer Soc Mech Engn, BFGoodrich, Def Adv Res Projects Agcy, USA Res Off, USAF Res Lab, Ceram Soc Japan, Intelligent Mat Forum, Japan DE piezoelectric motors; ultrasonic motors (USMs); stators and rotors; modal analysis; actuators; active materials AB Ultrasonic rotary motors have the potential to meet this NASA need and they are developed as actuators for miniature telerobotic applications. These motors are being adapted for operation at the harsh space environments that include cryogenic temperatures and vacuum and analytical tools for the design of efficient motors are being developed. A hybrid analytical model was developed to address a complete ultrasonic motor as a system. Included in this model is the influence of the rotor dynamics, which was determined experimentally to be important to the motor performance. The analysis employs a 3D finite element model to express the dynamic characteristics of the stator with piezoelectric elements and the rotor. The details of the stator including the teeth, piezoelectric ceramic, geometry, bonding layer, etc. are included to support practical USM designs. A brush model is used for the interface layer and Coulomb's law for the friction between the stator and the rotor. The theoretical predictions were corroborated experimentally for the motor. In parallel, efforts have been made to determine the thermal and vacuum performance of these motors. To explore telerobotic applications for USMs a robotic arm was constructed with such motors. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM yosi@jpl.nasa.gov NR 13 TC 2 Z9 4 U1 3 U2 11 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3610-0 J9 PROC SPIE PY 2000 VL 3992 BP 677 EP 689 DI 10.1117/12.388191 PG 13 WC Materials Science, Ceramics; Mechanics; Materials Science, Composites; Physics, Applied SC Materials Science; Mechanics; Physics GA BQ59Y UT WOS:000088918100066 ER PT S AU Bar-Cohen, Y Leary, S AF Bar-Cohen, Y Leary, S BE BarCohen, Y TI Electroactive polymers (EAP) characterization methods SO SMART STRUCTURES AND MATERIALS 2000: ELECTROACTIVE POLYMER ACTUATORS AND DEVICES (EAPAD) SE Proceedings of SPIE LA English DT Proceedings Paper CT Smart Structures and Materials 2000 Conference CY MAR 05-09, 2000 CL NEWPORT BEACH, CA SP SPIE, Soc Exptl Mech, Amer Soc Mech Engn, BFGoodrich, Def Adv Res Projects Agcy, USA Res Off, USAF Res Lab, Ceram Soc Japan, Intelligent Mat Forum, Japan AB Electroactive polymers (EAP) are emerging as a new class of actuation materials bring considered in a wide range of applications. Their large electrically induced strains (bending or extensional), low density,ease of processing, and mechanical flexibility offer advantages over traditional electroactive materials. However, before these materials can be properly exploited, their electrical and mechanical properties must be properly quantified. Two general types of EAP can be identified including wet (hydrated) and dry materials. The first type requires relatively low voltages (<10V) to achieve large bending deflections (more than 90 degrees). This class usually needs to be hydrated and electrochemical reactions may occur. The second type of EAP involves electrostrictive and/or Maxwell stresses. These types of materials require large electric fields (>100MV/m) to achieve large extensional deformation (>4%). Some of the difficulties that are involved with the characterization of the properties of EAP include nonlinearity, large compliance (large mismatch with metal electrodes), non-homogeneity formed during processing, etc. In order for this technology to fully mature, the authors are developing characterization techniques to quantify their electroactive responses and material properties. This paper focuses on a new testing procedure for bending EAP. Results for ion exchange Flemion membranes are presented. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 82-105, Pasadena, CA 91109 USA. EM yosi@jpl.nasa.gov NR 9 TC 8 Z9 8 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3605-4 J9 PROC SPIE PY 2000 VL 3987 BP 12 EP 16 DI 10.1117/12.387788 PG 5 WC Engineering, Electrical & Electronic; Materials Science, Multidisciplinary; Physics, Applied; Polymer Science SC Engineering; Materials Science; Physics; Polymer Science GA BQ59T UT WOS:000088914900002 ER PT S AU Su, J Ounaies, Z Harrison, JS Bar-Cohen, Y Leary, S AF Su, J Ounaies, Z Harrison, JS Bar-Cohen, Y Leary, S BE BarCohen, Y TI Electromechanically active polymer blends for actuation SO SMART STRUCTURES AND MATERIALS 2000: ELECTROACTIVE POLYMER ACTUATORS AND DEVICES (EAPAD) SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2000 Conference CY MAR 05-09, 2000 CL NEWPORT BEACH, CA SP SPIE, Soc Exptl Mech, Amer Soc Mech Engn, BFGoodrich, Def Adv Res Projects Agcy, USA Res Off, USAF Res Lab, Ceram Soc Japan, Intelligent Mat Forum, Japan DE piezoelectric; electrostrictive; graft-elastomer; copolymer; blend; and actuators ID VINYLIDENE AB Actuator mechanisms that are lightweight, durable, and efficient are needed to support telerobotic requirements for future NASA missions. In this work, we present a series of electromechanically active polymer blends that can potentially be used as actuators for a variety of applications. This polymer blend combines an electrostrictive graft-elastomer with a ferroelectric poly (vinylidene fluoride-trifluoroethylene) polymer. Mechanical and piezoelectric properties of the blends as a function of temperature, frequency and relative composition of the two constituents in the blends have been studied. Electric field induced strain response of the blend films has also been studied as a function of the relative composition. A bending actuator device was developed incorporating the use of the polymer blend materials. The results and the possible effects of the combination of piezoelectricity and electrostriction in a material system are presented and discussed. This type of analysis may enable the design of blend compositions with optimal strain, mechanical, and dielectric properties for specific actuator applications. C1 NASA, Langley Res Ctr, ICASE, Hampton, VA 23681 USA. RP Su, J (reprint author), NASA, Langley Res Ctr, ICASE, Hampton, VA 23681 USA. NR 6 TC 5 Z9 5 U1 1 U2 6 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3605-4 J9 P SOC PHOTO-OPT INS PY 2000 VL 3987 BP 65 EP 72 DI 10.1117/12.387764 PG 8 WC Engineering, Electrical & Electronic; Materials Science, Multidisciplinary; Physics, Applied; Polymer Science SC Engineering; Materials Science; Physics; Polymer Science GA BQ59T UT WOS:000088914900007 ER PT S AU Bar-Cohen, Y Leary, S Yavrouian, A Oguro, K Tadokoro, S Harrison, J Smith, J Su, J AF Bar-Cohen, Y Leary, S Yavrouian, A Oguro, K Tadokoro, S Harrison, J Smith, J Su, J BE BarCohen, Y TI Challenges to the application of IPMC as actuators of planetary mechanisms SO SMART STRUCTURES AND MATERIALS 2000: ELECTROACTIVE POLYMER ACTUATORS AND DEVICES (EAPAD) SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2000 Conference CY MAR 05-09, 2000 CL NEWPORT BEACH, CA SP SPIE, Soc Exptl Mech, Amer Soc Mech Engn, BFGoodrich, Def Adv Res Projects Agcy, USA Res Off, USAF Res Lab, Ceram Soc Japan, Intelligent Mat Forum, Japan ID MEMBRANES; SYSTEMS AB Ion-exchange polymer membrane metallic composites (IPMC) are one of the electroactive polymers (EAP) that were shown to have potential application as actuators. The recent introduction of perfluorocarboxylate-gold composite with tetra-n-butylammonium and lithium cations instead of sodium made the most significant improvement of the material's electroactivity. Under less than 3 volts, such IPMC materials were shown to induce bending beyond a complete loop. The bending characteristic of IPMC offered an attractive actuation capability for a dust wiper in planetary applications and it was explored for the Nanorover's infrared camera window of the MUSES-CN mission. This joint NASA and the Japanese space agency mission, is scheduled to be launched from Kagoshima, Japan, in January 2002, to explore the surface of a small near-Earth asteroid. The application of EAP at space conditions posed a great challenge due to the harsh operating conditions that are expected and the critical need for robustness and durability. Several issues that are critical to the application of IPMC were addressed including operation in vacuum and low temperatures, as well as the effect of the electromechanical characteristics of the IPMC on its actuation capability. Highly efficient IPMC materials, mechanical modeling, unique elements and protective coatings were introduced to enhance the applicability of this EAP material. However, critical issues were identified that hamper the transition of IPMC from being considered for practical applications at this stage. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Bar-Cohen, Y (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 82-105, Pasadena, CA 91109 USA. NR 13 TC 38 Z9 38 U1 1 U2 6 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3605-4 J9 P SOC PHOTO-OPT INS PY 2000 VL 3987 BP 140 EP 146 DI 10.1117/12.387772 PG 7 WC Engineering, Electrical & Electronic; Materials Science, Multidisciplinary; Physics, Applied; Polymer Science SC Engineering; Materials Science; Physics; Polymer Science GA BQ59T UT WOS:000088914900015 ER PT J AU Rosenzweig, C Hillel, D AF Rosenzweig, C Hillel, D TI Soils and global climate change: Challenges and opportunities SO SOIL SCIENCE LA English DT Article DE soil organic matter; soil-climate interactions; greenhouse gas emissions; carbon sequestration; climate change ID ORGANIC-MATTER; CARBON; GRASSLANDS; DYNAMICS; EROSION AB In the interplay of the soil and the atmosphere, the soil can be both a contributor to and a recipient of the impacts of climate change. In the past, land management has generally resulted in considerable depletion of soil organic matter and the release into the atmosphere of such radiatively active gases as carbon dioxide, methane, and nitrous oxide. Global climate change, to the extent that it occurs, will strongly impact all soil processes. At this time, the task of soil management should be to restore soil organic carbon in order to enhance soil structure and fertility and to help counter the atmospheric greenhouse effect, Widely varying estimates of the soil's organic carbon content and of the potential for soil carbon sequestration point to the need to conduct a comprehensive inventory of this important property. C1 Columbia Univ, NASA, Goddard Inst Space Studies, New York, NY 10025 USA. RP Hillel, D (reprint author), Columbia Univ, NASA, Goddard Inst Space Studies, 2880 Broadway, New York, NY 10025 USA. NR 30 TC 39 Z9 57 U1 2 U2 24 PU LIPPINCOTT WILLIAMS & WILKINS PI PHILADELPHIA PA 530 WALNUT ST, PHILADELPHIA, PA 19106-3621 USA SN 0038-075X J9 SOIL SCI JI Soil Sci. PD JAN PY 2000 VL 165 IS 1 BP 47 EP 56 DI 10.1097/00010694-200001000-00007 PG 10 WC Soil Science SC Agriculture GA 281TC UT WOS:000085176000007 ER PT J AU Hymer, DC Moran, MS Keefer, TO AF Hymer, DC Moran, MS Keefer, TO TI Soil water evaluation using a hydrologic model and calibrated sensor network SO SOIL SCIENCE SOCIETY OF AMERICA JOURNAL LA English DT Article AB Studies show that it may be possible to combine satellite-derived soil water maps with soil-vegetation-atmosphere transfer (SVAT) models to obtain spatially distributed, temporally continuous information on vadose zone water contents. However, before this method can be instituted, it is essential to determine the ability of a SVAT model to simulate vadose zone soil water contents. A study was designed to evaluate the simultaneous heat and water (SHAW) model by comparing its soil water predictions with measured soil water contents collected by electrical resistance sensors (ERS) during the Monsoon '90 multidisciplinary field experiment. ERS collected hourly soil water measurements at 5-, 15-, and 30-cm depths in a shrub-dominated site [Larrea tridentada (Sesse & Moc, ex DC.) Coville] with large bare interspace areas. Data collected by the ERS were calibrated to time domain reflectometer (TDR) sensor measurements placed adjacent to the ERS using an in situ calibration technique. Results indicated that the SHAW model overestimated soil water at each depth by 0.02 m(3) m(-3) under bare soil and underestimated soil water at each depth under shrub cover by 0.02 m3 m-3. The ability of the model to simulate ERS water content values gives it the potential to be periodically updated with remotely sensed data to predict vadose zone soil water content over large areas at high temporal resolutions. C1 NASA, Goddard Space Flight Ctr, Hydrol Sci Branch, Greenbelt, MD 20771 USA. USDA, SWRC, Tucson, AZ 85719 USA. RP Hymer, DC (reprint author), NASA, Goddard Space Flight Ctr, Hydrol Sci Branch, Code 974, Greenbelt, MD 20771 USA. NR 24 TC 40 Z9 43 U1 0 U2 4 PU SOIL SCI SOC AMER PI MADISON PA 677 SOUTH SEGOE ROAD, MADISON, WI 53711 USA SN 0361-5995 J9 SOIL SCI SOC AM J JI Soil Sci. Soc. Am. J. PD JAN-FEB PY 2000 VL 64 IS 1 BP 319 EP 326 PG 8 WC Soil Science SC Agriculture GA 356MA UT WOS:000089446000043 ER PT S AU Jones, SM AF Jones, SM BE Dunn, BS Pope, EJA Schmidt, HK Yamane, M TI Gradient composition sol-gel materials SO SOL-GEL OPTICS V SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT 5th Sol-Gel Optics Conference CY JAN 26-28, 2000 CL SAN JOSE, CA SP SPIE DE sol-gel; gradient composition; aerogel; xerogel ID SILICA AEROGEL FILMS; AMBIENT-PRESSURE; FORMALDEHYDE; RESORCINOL AB The STARDUST Mission, which launched in February of 1999, plans to fly through the coma of Comet 81P/Wild2, capture some of the material ejected by the comet, and return the samples to Earth in 2006. The capture media for the encounter is silica aerogel. In the course of the capture media development the aerogel evolved from single density, to discontiuous (layered) density changes, to a continuous (gradient) density change. Since various physical properties such as the index of refraction, the porosity, the dielectric constant, etc., are directly related to the density of these materials, they too vary in a gradient manner. Employing the method developed for the production of the STARDUST media, samples have been produced which exhibit order of magnitude density changes and refractive index gradients of up to 0.1. Other samples have been made which include compositional gradients such as varying dopant(s) concentration and oxide composition. The method has been used to form samples that display linear, planar, and cylindrical gradients. Sol-gel materials have been produced of not only gradient aerogel, but also gradient xerogel, as well as, gradient hybrid aerogel/xerogel materials. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Jones, SM (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 24 TC 3 Z9 3 U1 1 U2 4 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3560-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 3943 BP 260 EP 269 DI 10.1117/12.384345 PG 10 WC Optics SC Optics GA BQ31T UT WOS:000087917400031 ER PT S AU Abbaschian, R de Groh, H Leonardi, E Timchenko, V Davis, GD AF Abbaschian, R de Groh, H Leonardi, E Timchenko, V Davis, GD BE Roosz, A Rettenmayr, M Watring, D TI Directional solidification of Bi-Sn on USMP-4 SO SOLIDIFICATION AND GRAVITY 2000 SE MATERIALS SCIENCE FORUM LA English DT Article; Proceedings Paper CT 3rd International Conference on Solidification and Gravity (SG 99) CY APR 25-29, 1999 CL MISKOLC LILLAFURED, HUNGARY SP Univ Miskolc, Fac Met, Phys Met Dept, Darmstadt Univ Technol, Mat Sci Inst, NASA Marshall Space Flight Ctr, Hungarian Acad Sci, Miskolc Comm, Hungarian Astronaut Soc, Hungarian Space Off, ASM Hungarian Chapter DE morphological instability; directional solidification; Seebeck signal; solid-liquid interface ID LIQUID GA INTERFACES; GROWTH-KINETICS AB The experiments used MEPHISTO hardware to study the solidification and melting behavior of bismuth alloyed with 1 at% tin. Three samples, each approximately 900 mm long and 6mm in diameter, were used. A portion of each sample also included a Z mm diameter growth capillary, to assist in the formation of a single grain. One sample provided the Seebeck voltage generated during melting and freezing processes. Another provided temperature data and Peltier pulsed demarcation of the interface shape for post flight analysis. The third sample provided resistance and growth velocity measurements, as well as additional thermal data. The third sample was also quenched at the end of the mission to preserve the composition of the liquid near the interface for post flight determination. A total of 450mm of directionally solidified samples were preserved for post mission structural and compositional characterization. Substantial differences were observed in the Set beck signal between the ground-based experiments and the space-based experiments. The temperature gradient in the liquid for the groundbased experiments was significantly lower than the temperature gradient in the liquid fur the space-based experiments. C1 Univ Florida, Gainesville, FL 32611 USA. NASA, Lewis Res Ctr, Cleveland, OH 44135 USA. Univ New S Wales, Sydney, NSW 2052, Australia. RP Abbaschian, R (reprint author), Univ Florida, Gainesville, FL 32611 USA. NR 20 TC 4 Z9 4 U1 0 U2 2 PU TRANS TECH PUBLICATIONS LTD PI ZURICH-UETIKON PA BRANDRAIN 6, CH-8707 ZURICH-UETIKON, SWITZERLAND SN 0255-5476 BN 0-87849-852-4 J9 MATER SCI FORUM PY 2000 VL 329-3 BP 235 EP 245 PG 11 WC Materials Science, Multidisciplinary; Metallurgy & Metallurgical Engineering SC Materials Science; Metallurgy & Metallurgical Engineering GA BQ57Z UT WOS:000088851000035 ER PT J AU Pappa, RS Doebling, SW Kholwad, TD AF Pappa, RS Doebling, SW Kholwad, TD TI On-line database of vibration-based damage detection experiments SO SOUND AND VIBRATION LA English DT Article AB This article describes a new, on-line bibliographic database of vibration-based damage detection experiments. Publications in the database discuss experiments conducted on actual structures as well as those conducted with simulated data. The database can be searched and sorted in many ways, and it provides photographs of test structures when available. It currently contains 100 publications, which is estimated to be about 5%-10% of the number of papers written to date on this subject. Additional entries are forthcoming. This database is available for public use on the Internet at the following address: http://sdbpappa-mac.larc.nasa.gov. Click on the link named "dd_experiments.fp3" and then type 'guest' as the password. No user name is required. C1 NASA, Langley Res Ctr, Hampton, VA 23665 USA. Univ Calif Los Alamos Natl Lab, Los Alamos, NM USA. Univ New Mexico, Albuquerque, NM 87131 USA. RP Pappa, RS (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. NR 7 TC 1 Z9 1 U1 0 U2 0 PU ACOUSTICAL PUBL INC PI BAY VILLAGE PA 27101 E OVIATT RD PO BOX 40416, BAY VILLAGE, OH 44140 USA SN 0038-1810 J9 SOUND VIB JI Sound Vib. PD JAN PY 2000 VL 34 IS 1 BP 28 EP 33 PG 6 WC Acoustics; Engineering, Mechanical; Mechanics SC Acoustics; Engineering; Mechanics GA 282JR UT WOS:000085215300006 ER PT B AU Launius, RD AF Launius, RD BE Johnson, SW Chua, KM Galloway, R Richter, P TI Project Apollo in American memory and myth SO SPACE 2000, PROCEEDINGS LA English DT Proceedings Paper CT 7th International Conference and Exposition on Engineering, Construction, Operations, and Business in Space CY FEB 27-MAR 02, 2000 CL ALBUQUERQUE, NM SP Amer Soc Civil Engineers, Aerosp Div, Amer Astronaut Soc, NASA, SandiA Natl Labs, Natl Space Soc, Int Assoc Automat & Robot Construct, Univ New Mexico, Dept Civil Engn, Space Daily, Spacenews Com, Bechtel Grp, Fluor Global Serv AB This paper presents an historical perspective on the importance of Project Apollo from the perspective of the end of the twentieth century and the millennium. After thirty years, it is only now becoming possible to assess the significance of the lunar landings, accomplished between 1969 and 1972, with any degree of historical perspective. This essay discusses the key elements of the American public's memory about Apollo and why it was important, and is suggestive of the myths that have emerged since the landings and how they have affected the course of American society. C1 NASA, Washington, DC 20546 USA. RP Launius, RD (reprint author), NASA, Code ZH,Headquaters, Washington, DC 20546 USA. NR 54 TC 2 Z9 2 U1 0 U2 1 PU AMER SOC CIVIL ENGINEERS PI NEW YORK PA UNITED ENGINEERING CENTER, 345 E 47TH ST, NEW YORK, NY 10017-2398 USA BN 0-7844-0479-8 PY 2000 BP 1 EP 13 PG 13 WC Engineering, Aerospace; Engineering, Civil SC Engineering GA BQ36D UT WOS:000088122100001 ER PT B AU Dickerson, PW Muehlberger, WR Bauer, PW AF Dickerson, PW Muehlberger, WR Bauer, PW BE Johnson, SW Chua, KM Galloway, R Richter, P TI Astronaut training in field geophysical methods SO SPACE 2000, PROCEEDINGS LA English DT Proceedings Paper CT 7th International Conference and Exposition on Engineering, Construction, Operations, and Business in Space CY FEB 27-MAR 02, 2000 CL ALBUQUERQUE, NM SP Amer Soc Civil Engineers, Aerosp Div, Amer Astronaut Soc, NASA, SandiA Natl Labs, Natl Space Soc, Int Assoc Automat & Robot Construct, Univ New Mexico, Dept Civil Engn, Space Daily, Spacenews Com, Bechtel Grp, Fluor Global Serv AB Astronaut teams acquired roughly 16 km of gravity data in the course of a planetary exploration simulation conducted in the vicinity of Taos, New Mexico. The gravimetric survey was the first phase of a geophysical assessment of the ground-water resources around Taos, an area of rapid population growth, and it was executed to help delineate buried structures that significantly influence ground-water flow and accumulation in the valley. Participants in the investigation learned a technique with direct relevance for lunar and planetary exploration and took a substantive step toward building an exploration culture within and beyond NASA. C1 NASA, Lyndon B Johnson Space Ctr, Lockheed Martin, Houston, TX 77058 USA. RP Dickerson, PW (reprint author), NASA, Lyndon B Johnson Space Ctr, Lockheed Martin, Houston, TX 77058 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC CIVIL ENGINEERS PI NEW YORK PA UNITED ENGINEERING CENTER, 345 E 47TH ST, NEW YORK, NY 10017-2398 USA BN 0-7844-0479-8 PY 2000 BP 115 EP 121 PG 7 WC Engineering, Aerospace; Engineering, Civil SC Engineering GA BQ36D UT WOS:000088122100011 ER PT B AU Ticker, RL McLennan, D AF Ticker, RL McLennan, D BE Johnson, SW Chua, KM Galloway, R Richter, P TI The New Millennium Program space technology 5 (ST5) SO SPACE 2000, PROCEEDINGS LA English DT Proceedings Paper CT 7th International Conference and Exposition on Engineering, Construction, Operations, and Business in Space CY FEB 27-MAR 02, 2000 CL ALBUQUERQUE, NM SP Amer Soc Civil Engineers, Aerosp Div, Amer Astronaut Soc, NASA, SandiA Natl Labs, Natl Space Soc, Int Assoc Automat & Robot Construct, Univ New Mexico, Dept Civil Engn, Space Daily, Spacenews Com, Bechtel Grp, Fluor Global Serv AB In August 1999, NASA selected Nanosat Constellation Trailblazer (NCT) as the New Millennium Program's ST5 project. NCT will validate technologies needed for future NASA science missions, particularly enabling the constellation class missions envisioned for the Sun-Earth Connection (SEC) science theme. Three 20-kg class spacecraft will be developed and operated for a total project cost of $29M. These spacecraft will demonstrate eight component technologies and interact with each other to create an instrument greater than the sum of its parts. This paper will describe the NCT project and technologies, and assess ST5's impact on future NASA science missions. C1 NASA, Goddard Space Flight Ctr, New Millennium Program, Greenbelt, MD 20771 USA. RP Ticker, RL (reprint author), NASA, Goddard Space Flight Ctr, New Millennium Program, Mail Code 730, Greenbelt, MD 20771 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC CIVIL ENGINEERS PI NEW YORK PA UNITED ENGINEERING CENTER, 345 E 47TH ST, NEW YORK, NY 10017-2398 USA BN 0-7844-0479-8 PY 2000 BP 469 EP 475 PG 7 WC Engineering, Aerospace; Engineering, Civil SC Engineering GA BQ36D UT WOS:000088122100058 ER PT B AU Chen, PC Oliversen, RJ Kondo, Y AF Chen, PC Oliversen, RJ Kondo, Y BE Johnson, SW Chua, KM Galloway, R Richter, P TI A first generation lunar UV observatory SO SPACE 2000, PROCEEDINGS LA English DT Proceedings Paper CT 7th International Conference and Exposition on Engineering, Construction, Operations, and Business in Space CY FEB 27-MAR 02, 2000 CL ALBUQUERQUE, NM SP Amer Soc Civil Engineers, Aerosp Div, Amer Astronaut Soc, NASA, SandiA Natl Labs, Natl Space Soc, Int Assoc Automat & Robot Construct, Univ New Mexico, Dept Civil Engn, Space Daily, Spacenews Com, Bechtel Grp, Fluor Global Serv AB We present a new concept for a first generation unmanned, minimal cosr robotic telescope based on the Moon in the near future. The telescope is designed to carry out cutting edge astrophysical research; it can also facilitate future lunar exploration and settlement. The key is to develop and use versatile new technologies that can dramatically lower the mission cost. Major elements are: ultra lightweight telescope mirrors; high temperature superconductor telescope drives; smart, radiation tolerant sensors and electronics, the use of SMEX (Small Explorer) classes rockets such as the Taurus or the Med-Lite; innovative fuel saving trajectories; inexpensive miniature landers, novel power system for night time operation; and world wide amateur participation in data reception and analysis. Most of the elements are in advanced development; some have already been proven in use. By means of these new technologies, we suggest that it is possible to baseline a meter class robotic UV telescope on the Moon for the cost of a SMEX class mission. A followup MIDEX class project can deploy an optical interferometer pair consisting of two diffraction-limited meter class telescopes with a baseline of 50-1000 meters. Angular resolution of better than 0.001 arcsecond can be achieved in visible light. The observatory can be expanded to very large aperture UV/VIS/IR telescopes and interferometer arrays. C1 NASA, Goddard Space Flight Ctr, Composite Mirror Applicat Inc, Greenbelt, MD 20771 USA. RP Chen, PC (reprint author), NASA, Goddard Space Flight Ctr, Composite Mirror Applicat Inc, Code 681, Greenbelt, MD 20771 USA. NR 12 TC 0 Z9 0 U1 0 U2 1 PU AMER SOC CIVIL ENGINEERS PI NEW YORK PA UNITED ENGINEERING CENTER, 345 E 47TH ST, NEW YORK, NY 10017-2398 USA BN 0-7844-0479-8 PY 2000 BP 712 EP 718 PG 7 WC Engineering, Aerospace; Engineering, Civil SC Engineering GA BQ36D UT WOS:000088122100086 ER PT B AU Watson, JK Blaisdell, GL AF Watson, JK Blaisdell, GL BE Johnson, SW Chua, KM Galloway, R Richter, P TI Salient characteristics for terrestrial analog engineering test sites SO SPACE 2000, PROCEEDINGS LA English DT Proceedings Paper CT 7th International Conference and Exposition on Engineering, Construction, Operations, and Business in Space CY FEB 27-MAR 02, 2000 CL ALBUQUERQUE, NM SP Amer Soc Civil Engineers, Aerosp Div, Amer Astronaut Soc, NASA, SandiA Natl Labs, Natl Space Soc, Int Assoc Automat & Robot Construct, Univ New Mexico, Dept Civil Engn, Space Daily, Spacenews Com, Bechtel Grp, Fluor Global Serv ID MARS; DISTRIBUTIONS; SIZE AB The use of terrestrial analog sites is an essential component of the development process for systems that are planned for lunar and planetary surfaces. These sites can also be valuable for training personnel who are expected to operate those systems. The fact that the site is an integral element, capable of influencing data and impacting test results, must not be overlooked. For tests performed in analog environments to be truly valid it is essential that the relevant characteristics of the employed sites be thoroughly understood. It is also critical that a comparative evaluation be made to assess the similarity of the analog sites to target planetary sites. C1 NASA, Lyndon B Johnson Space Ctr, Explorat Off, Houston, TX 77058 USA. RP Watson, JK (reprint author), NASA, Lyndon B Johnson Space Ctr, Explorat Off, EX13, Houston, TX 77058 USA. NR 13 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC CIVIL ENGINEERS PI NEW YORK PA UNITED ENGINEERING CENTER, 345 E 47TH ST, NEW YORK, NY 10017-2398 USA BN 0-7844-0479-8 PY 2000 BP 748 EP 759 PG 12 WC Engineering, Aerospace; Engineering, Civil SC Engineering GA BQ36D UT WOS:000088122100090 ER PT B AU Gruener, JE Ming, DW AF Gruener, JE Ming, DW BE Johnson, SW Chua, KM Galloway, R Richter, P TI Zeoponic plant growth substrate development at the Johnson Space Center and possible use at a Martian outpost SO SPACE 2000, PROCEEDINGS LA English DT Proceedings Paper CT 7th International Conference and Exposition on Engineering, Construction, Operations, and Business in Space CY FEB 27-MAR 02, 2000 CL ALBUQUERQUE, NM SP Amer Soc Civil Engineers, Aerosp Div, Amer Astronaut Soc, NASA, SandiA Natl Labs, Natl Space Soc, Int Assoc Automat & Robot Construct, Univ New Mexico, Dept Civil Engn, Space Daily, Spacenews Com, Bechtel Grp, Fluor Global Serv ID PHOSPHATE ROCK; CHEMICAL-COMPOSITION; CLINOPTILOLITE; PHOSPHORUS; MIXTURES; RELEASE; SYSTEMS; SOILS AB The National Aeronautics and Space Administration (NASA) Johnson Space Center (JSC) is developing a substrate, termed zeoponics, that will slowly release all of the essential nutrients into solution for plant growth experiments in advanced life support system testbeds. This substrate is also potentially useful in the near future on the Space Shuttle and International Space Station and could eventually be used at an outpost on Mars. Chemical analyses of the martain soil by the Viking and Mars Pathfinder missions have indicated that several of the elements required for plant growth are available in the soil. It may be possible to use the martian soil as the bulk substrate for growing food crops, while using smaller amounts of zeoponic substrate as an amendment to rectify any nutrient deficiencies. C1 Hernandez Engn Inc, Houston, TX 77058 USA. NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Gruener, JE (reprint author), Hernandez Engn Inc, Houston, TX 77058 USA. NR 21 TC 0 Z9 0 U1 0 U2 1 PU AMER SOC CIVIL ENGINEERS PI NEW YORK PA UNITED ENGINEERING CENTER, 345 E 47TH ST, NEW YORK, NY 10017-2398 USA BN 0-7844-0479-8 PY 2000 BP 876 EP 882 PG 7 WC Engineering, Aerospace; Engineering, Civil SC Engineering GA BQ36D UT WOS:000088122100106 ER PT J AU Mac Rae, AU Pelton, JN De Paula, R AF Mac Rae, AU Pelton, JN De Paula, R TI Global satellite communications technology and systems SO SPACE COMMUNICATIONS LA English DT Editorial Material AB This special issue of Space Communications contains nine papers derived from a study, 'Global satellite communications technology and systems', sponsored by NASA and the NSF. The purpose of this study was to compare the position of the US in commercial satellite communications technology, research, development and markets with that of the rest of the world. It included visits to over 65 satellite manufacturers, service providers and R&D Institutes located in North and South America, Europe, Asia and Africa. These papers include overviews and country by country material on R&D activities, technology status, markets and trends from this study. The conclusions of this panel indicate that the US continues to have a strong presence in this large and rapidly growing global industry but that European and Asian entities are making significant investments in their manufacturing and R&D activities and are becoming major participants in this satellite communications industry. The migration of US aerospace corporations from being primarily manufacturers of spacecraft to being primarily satellite service providers could serve to undercut necessary longer term R&D to develop new technologies. C1 Mac Rae Technol, Berkeley Hts, NJ 07922 USA. George Washington Univ, Inst Appl Space Res, Washington, DC 20052 USA. NASA Headquarters, Off Space Sci, Washington, DC 20546 USA. RP Mac Rae, AU (reprint author), Mac Rae Technol, 72 Sherbrook Dr, Berkeley Hts, NJ 07922 USA. NR 2 TC 3 Z9 3 U1 0 U2 0 PU IOS PRESS PI AMSTERDAM PA NIEUWE HEMWEG 6B, 1013 BG AMSTERDAM, NETHERLANDS SN 0924-8625 J9 SPACE COMMUN JI Space Commun. PY 2000 VL 16 IS 2-3 BP 51 EP 54 PG 4 WC Engineering, Aerospace; Telecommunications SC Engineering; Telecommunications GA 319ZR UT WOS:000087376800001 ER PT J AU Bostian, CW Brandon, WT Mac Rae, AU Mahle, CE Townes, SA AF Bostian, CW Brandon, WT Mac Rae, AU Mahle, CE Townes, SA TI Key technology trends - Satellite systems SO SPACE COMMUNICATIONS LA English DT Article DE satellite communications; communications satellites; satellite technology overview AB This paper is based on material extracted from the WTEC Panel Report Global Satellite Communications Technology and Systems, December 1998. It presents an overview of key technology trends in communications satellites in the last few years. After the introduction which deals with such issues as the transformation of the one-at-a-time approach for building satellites to a production-oriented one, there follows a discussion of critical technologies for large geosynchronous earth orbit (GEO) satellites with power systems growing to 20 kW and more. Satellite antenna technology, one of the most critical areas in measuring progress, is next reviewed, including large reflector antennas, phased arrays and optical beam formers. This is followed by a discussion of onboard processing (analog and digital), progress in satellite traveling wave tubes, solid state power amplifiers and optical satellite technologies including intersatellite links (ISLs). Last some pertinent satellite bus issues (electric propulsion, thermal control and attitude control) are reviewed. Small and mini-satellites are discussed, but not treated in great detail as much of their technology is derived from that of GEO satellites. C1 Virginia Tech, Ctr Wireless Telecommun, Blacksburg, VA 24061 USA. Mitre Corp, Bedford, MA 01730 USA. Telecommun & Satellite Technol, Berkeley Hts, NJ 07922 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Bostian, CW (reprint author), Virginia Tech, Ctr Wireless Telecommun, Blacksburg, VA 24061 USA. NR 8 TC 9 Z9 11 U1 2 U2 3 PU IOS PRESS PI AMSTERDAM PA NIEUWE HEMWEG 6B, 1013 BG AMSTERDAM, NETHERLANDS SN 0924-8625 J9 SPACE COMMUN JI Space Commun. PY 2000 VL 16 IS 2-3 BP 97 EP 124 PG 28 WC Engineering, Aerospace; Telecommunications SC Engineering; Telecommunications GA 319ZR UT WOS:000087376800005 ER PT J AU Pelton, JN Bhasin, K AF Pelton, JN Bhasin, K TI Key policy, regulatory and standards issues in global satellite communications SO SPACE COMMUNICATIONS LA English DT Article DE ITU; INTELSAT; Inmarsat; World Trade Organization (WTO); ETSI; TIA; SIA; IEEE; ATM Forum; ITU-R and ITU-T; WIPO; satellite standards and protocols; open systems interconnection; IMT 2000; FPLMTS; technology transfer; international cooperation; frequency allocation; paper satellites; intellectual property rights AB The field of satellite communications is becoming at least as constrained and shaped by policy, regulatory and standards issues as it is by technology. Satellite communications is currently facing a host of challenging issues, including national economic competition, open trade issues, standards and protocols, spectrum and frequency allocation, definition of essential space services requiring public funding, institutional reform, international industrial patterns of change and consolidation, technology transfer, and the proper role of government in future space communications development. This article seeks to identify possible areas for reform with regard to 'paper satellites', multi-purpose frequency allocations, longer range spectrum planning, new standards-making approaches to seamless satellite-fiber interconnectivity, and reforms to more open international trade and licensing of satellite systems. Specific issues addressed include: - Global trade and access to national markets in the new 'open markets' trading environment. - Interoperability standards and protocols. Issues of compatibility among the satellite systems of the world. - Access to needed frequency allocations for satellite services amid growing global demand for broad band multi-media services and the need to revise ITU planning processes. - The difference in policy perspective and objectives between developed and developing countries in the field of satellite communications and its applications. - The on-going problem of 'paper satellites' and the fact that 'due diligence' has not solved this problem. - Needed regulatory reforms to encourage new types of interactive broadband, multi-media satellites. - Institutional reforms of key entities (the ITU, INTELSAT, Inmarsat, etc.) in the coming decade. - Technology transfer issues, especially those that involve sensitive or strategic issues as well as streamlined methods to protect international property rights. - New patterns of industrial cooperation, merger and as the new global market emerges. - The proper role of governmental R&D support in developing new technology, applications and markets. C1 George Washington Univ, Inst Appl Space Res, Washington, DC 20052 USA. NASA, John Glenn Res Ctr, Cleveland, OH 44135 USA. RP Pelton, JN (reprint author), George Washington Univ, Inst Appl Space Res, 2033 K St NW,Suite 340, Washington, DC 20052 USA. NR 8 TC 4 Z9 4 U1 0 U2 1 PU IOS PRESS PI AMSTERDAM PA NIEUWE HEMWEG 6B, 1013 BG AMSTERDAM, NETHERLANDS SN 0924-8625 J9 SPACE COMMUN JI Space Commun. PY 2000 VL 16 IS 2-3 BP 167 EP 179 PG 13 WC Engineering, Aerospace; Telecommunications SC Engineering; Telecommunications GA 319ZR UT WOS:000087376800009 ER PT S AU Ootsubo, T Onaka, T Yamamura, I Tanabe, T Roellig, TL Chan, KW Matsumoto, T AF Ootsubo, T Onaka, T Yamamura, I Tanabe, T Roellig, TL Chan, KW Matsumoto, T BE DeGraauw, T Matsumoto, T TI IRTS observations of the mid-infrared spectrum of the zodiacal emission SO SPACE INFRARED TELESCOPES AND RELATED SCIENCE SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT E1 4 Symposium of COSPAR Scientific Commission E Which was held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Comm Space Res ID TELESCOPE IN-SPACE; MIDINFRARED SPECTROMETER; LIGHT; MISSION; DUST; IRAS AB We present the spectrum of the zodiacal emission from 3 to 12 mu m obtained by the Infrared Telescope in Space (IRTS). The spectrum is fitted by models based on the IRAS data. The models consist of spatial distributions of the dust volumetric emissivity and temperature. The entire spectrum of 3-12 mu m cannot be fitted by one gray body emissivity model. This suggests that either the dust emissivity is not constant for 3-12 mu m or there are very hot dust grains. The present analysis suggests a dominant population of submicron size particles in the solar system. (C) 2000 COSPAR. Published by Elsevier Science Ltd. C1 Univ Tokyo, Sch Sci, Dept Astron, Tokyo 1130033, Japan. Univ Amsterdam, Astron Inst Anton Pannekoek, NL-1098 SJ Amsterdam, Netherlands. Univ Tokyo, Sch Sci, Inst Astron, Tokyo 1818588, Japan. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. Inst Space & Astronaut Sci, Sagamihara, Kanagawa 2298510, Japan. RP Ootsubo, T (reprint author), Univ Tokyo, Sch Sci, Dept Astron, Tokyo 1130033, Japan. NR 19 TC 12 Z9 12 U1 0 U2 0 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2000 VL 25 IS 11 BP 2163 EP 2166 DI 10.1016/S0273-1177(99)01148-5 PG 4 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BP70Z UT WOS:000085937400003 ER PT S AU Greenfield, MA AF Greenfield, MA BE Reid, MS Flury, W TI Risk management - The future role for the product assurance community SO SPACE SAFETY AND RESCUE 1998 SE SCIENCE AND TECHNOLOGY SERIES LA English DT Proceedings Paper CT Symposium of the International-Academy-of-Astronautics on Safety, Rescue, and Quality Held in Conjunction with the 49th International-Astronautical-Federation Congress CY SEP 28-OCT 02, 1998 CL MELBOURNE, AUSTRALIA SP Int Acad Astronaut, Comm Safety Rescue & Qual, Int Astronaut Federat, Int Acad Astronaut, Subcomm Space Debris AB Today's environment provides NASA with a myriad of financial, technical, and programmatic challenges. There is less money for development and little money to recover from contingencies or mishaps. NASA is moving away from operations and focusing on scientific research and development of cutting edge technologies. The Agency is incorporating performance-based and fixed-price contracts with industry and employing more partnerships with the international community. In this environment, effective risk management is critical to success. The implementation of a thorough, disciplined risk management approach is now required of all NASA programs and projects. By advising in the development of risk management plans, analyzing the many aspects of risk management tradeoffs, and providing risk management consultation throughout the program/project life cycle, product assurance personnel can play a critical role in mission success. C1 NASA, Washington, DC 20546 USA. RP Greenfield, MA (reprint author), NASA, 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 0278-4017 BN 0-87703-463-X J9 SCI TECH PY 2000 VL 99 BP 77 EP 85 PG 9 WC Engineering, Aerospace SC Engineering GA BP90H UT WOS:000086547900008 ER PT S AU Johnson, NL AF Johnson, NL BE Reid, MS Flury, W TI The complexities and challenges of space traffic modeling SO SPACE SAFETY AND RESCUE 1998 SE SCIENCE AND TECHNOLOGY SERIES LA English DT Proceedings Paper CT Symposium of the International-Academy-of-Astronautics on Safety, Rescue, and Quality Held in Conjunction with the 49th International-Astronautical-Federation Congress CY SEP 28-OCT 02, 1998 CL MELBOURNE, AUSTRALIA SP Int Acad Astronaut, Comm Safety Rescue & Qual, Int Astronaut Federat, Int Acad Astronaut, Subcomm Space Debris AB Mid-term and long-term projections of the Earth's satellite population rely, in part, on the ability to predict the nature and magnitude of space launch activities. Historically, the success of space traffic modeling has been a function of the degree of fidelity employed, political and economic factors, and the effects of emerging technologies. This paper describes the results of space traffic modeling performed at the National Aeronautics and Space Administration Lyndon B. Johnson Space Center in 1998 using the author's 1986 and 1993 space traffic modeling efforts as a foundation. Despite the significant decline in worldwide space missions in the 1990's, the growth of on-orbit mass has remained essentially unchanged. The sharp decline in low Earth orbit missions by the Russian Federation has had relatively little impact on the environment since these flights were primarily inserted into orbits with short orbital lifetimes. However, the advent of new commercial communications networks should reverse the launch decline, as evidenced by the world launch rate in 1997. At higher altitudes, the use of multiple payload launch vehicles and the reduction in use of upper stages as a result of more spacecraft with integrated propulsion systems have also changed the calculus of earlier space traffic models. The adoption of guidelines to limit low Earth orbit spacecraft and upper stages to less than 25 years after mission completion may have a demonstrable effect on space traffic modeling since some upper stages are being deorbited immediately after payload deployment. Finally, the potential development of new, reusable space transportation may have off-setting benefits for satellite population growth, while the emergence of new conventional launch vehicles by additional entrants in space transportation activities may be important. C1 NASA, Lyndon B Johnson Space Ctr, Orbital Debris Program Off, Houston, TX 77058 USA. RP Johnson, NL (reprint author), NASA, Lyndon B Johnson Space Ctr, Orbital Debris Program Off, Houston, TX 77058 USA. NR 12 TC 1 Z9 1 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 0278-4017 BN 0-87703-463-X J9 SCI TECH PY 2000 VL 99 BP 175 EP 187 PG 13 WC Engineering, Aerospace SC Engineering GA BP90H UT WOS:000086547900016 ER PT S AU Stansbery, EG Settecerri, TJ AF Stansbery, EG Settecerri, TJ BE Reid, MS Flury, W TI A comparison of statistical measurements of the orbital debris environment using radars SO SPACE SAFETY AND RESCUE 1998 SE SCIENCE AND TECHNOLOGY SERIES LA English DT Proceedings Paper CT Symposium of the International-Academy-of-Astronautics on Safety, Rescue, and Quality Held in Conjunction with the 49th International-Astronautical-Federation Congress CY SEP 28-OCT 02, 1998 CL MELBOURNE, AUSTRALIA SP Int Acad Astronaut, Comm Safety Rescue & Qual, Int Astronaut Federat, Int Acad Astronaut, Subcomm Space Debris AB The U.S. Space Command maintains a deterministic catalog of orbiting satellites and debris, which dates back to the beginning of the Space Age. However, the sensors and techniques used to create and maintain the catalog limit the size of the tracked objects to sizes larger than about 10-30 cm diameter. In order to understand the orbital debris environment for sizes smaller than this, statistical sampling has been used. NASA has been using the Haystack radar to statistically monitor the orbital debris environment since 1990. The Haystack measurements have been NASA's primary source of data in the important 0.4-20 cm diameter size range. Although the Haystack data comprise the largest database of observations, other radars have also been used to statistically sample the debris environment. The Haystack Auxiliary (HAX) radar, co-located with Haystack, began collecting debris data in 1994. By sharing location, real-time data collection hardware and software, and post-mission data analysis, any differences in results should be attributable to wavelength effects. The Goldstone radar is slightly more sensitive than Haystack and actually began sampling the debris environment in 1989, although for only a few hours each year. In 1996, a radar measurement campaign coordinated by the inter-Agency Space Debris Coordination Committee (IADC) was conducted using Haystack, the FGAN/TIRA radar operated in a bi-static mode with the Effelsbeg radio telescope, and the TRADEX radars. During this campaign each radar collected approximately 24 hours of statistical debris data. Limited data are also available from the ALTAIR, MU, and Arecibo radars collected prior to 1990. This paper will compare the results of these different measurements and attempt to reconcile any observed differences. C1 NASA, Lyndon B Johnson Space Ctr, Orbital Debris Program Off, Houston, TX 77058 USA. RP Stansbery, EG (reprint author), NASA, Lyndon B Johnson Space Ctr, Orbital Debris Program Off, Houston, TX 77058 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 0278-4017 BN 0-87703-463-X J9 SCI TECH PY 2000 VL 99 BP 201 EP 220 PG 20 WC Engineering, Aerospace SC Engineering GA BP90H UT WOS:000086547900018 ER PT S AU Loftus, JP AF Loftus, JP BE Reid, MS Flury, W TI The management of the geostationary environment SO SPACE SAFETY AND RESCUE 1998 SE SCIENCE AND TECHNOLOGY SERIES LA English DT Proceedings Paper CT Symposium of the International-Academy-of-Astronautics on Safety, Rescue, and Quality Held in Conjunction with the 49th International-Astronautical-Federation Congress CY SEP 28-OCT 02, 1998 CL MELBOURNE, AUSTRALIA SP Int Acad Astronaut, Comm Safety Rescue & Qual, Int Astronaut Federat, Int Acad Astronaut, Subcomm Space Debris AB The population in the geostationary orbit is increasing at the rate of about 25 spacecraft a year and operating lifetimes are increasing. The size of the spacecraft is increasing, as is the power level. The only way to protect the operational are is to reboost spacecraft at end of life to a burial orbit. While most operators do some reboost maneuver at end of mission there has been no agreed upon criterion for the maneuver. The ITU-R S.1003(1) recommends reboost of not less than 300 km with the apogee as high as possible. The Interagency Debris Coordination Working Group (IADC) has recently achieved a consensus on a recommendation that the minimum maneuver be 235 km + Cr 1000 A/M. The concept is that this accommodates the +/-3 7.5 km variance in normal radial positioning and a 167.5 km corridor above the are for repositioning or supersynchronous delivery and establishes a criterion by which the dispositioned spacecraft will never enter that zone after its completion of the maneuver. It also deals with the fact the area mass ratio of spacecraft has been evolving to higher values. Earlier spacecraft had characteristic values of 0.03 but the average now is closer to 0.05 and there are some as great as 0.10. Disposition of the upper stage should be the same as the spacecraft if it is delivered to GSO. It is preferable to have the stage deliver the spacecraft supersynchronous and then have the spacecraft maneuver down to the GSO. C1 NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Loftus, JP (reprint author), NASA, Lyndon B Johnson Space Ctr, 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 0278-4017 BN 0-87703-463-X J9 SCI TECH PY 2000 VL 99 BP 283 EP 287 PG 5 WC Engineering, Aerospace SC Engineering GA BP90H UT WOS:000086547900024 ER PT J AU Adams, FC Laughlin, G AF Adams, FC Laughlin, G TI Protostellar disk formation and early evolution SO SPACE SCIENCE REVIEWS LA English DT Review DE self gravitating disks; spiral modes; nonlinear Interactions ID SELF-GRAVITATING DISKS; MOLECULAR CLOUD CORES; STAR-FORMATION; MASSIVE STARS; YOUNG STARS; COLLAPSE; INSTABILITIES; ACCRETION; PROTOSTARS; DYNAMICS AB This contribution describes the formation of circumstellar disks and their earliest evolutionary phases when self-gravity in the disk plays a crucial role in eliciting the transport of mass and angular momentum. We first discuss the formation of protostellar disks within the context of analytic infall-collapse solutions. We then discuss our efforts to understand the behavior of the newly formed disks. Our specific approach consists of performing a detailed analysis of a simplified model disk which is susceptible to the growth of a spiral instability. Using a combination of numerical simulation and semi-analytic analysis, we show how the dramatic early phase of mass and angular momentum transport in the disk can be explained by a second-order nonlinear process involving self-interaction of a dominant two-armed spiral mode. C1 NASA, Ames Res Ctr, Moffett Field, CA 94720 USA. Univ Michigan, Dept Phys, Ann Arbor, MI 48109 USA. RP NASA, Ames Res Ctr, Moffett Field, CA 94720 USA. EM adams@pablo.physics.lsa.umich.edu; gpl@sun.berkeley.edu NR 46 TC 3 Z9 3 U1 0 U2 0 PU SPRINGER PI DORDRECHT PA VAN GODEWIJCKSTRAAT 30, 3311 GZ DORDRECHT, NETHERLANDS SN 0038-6308 EI 1572-9672 J9 SPACE SCI REV JI Space Sci. Rev. PY 2000 VL 92 IS 1-2 BP 23 EP 38 DI 10.1023/A:1005241115899 PG 16 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 357HP UT WOS:000089492700004 ER PT J AU Gibson, WC Burch, JL Scherrer, JR Tapley, MB Killough, RL Volpe, FA Davis, WD Vaccarello, DC Grismore, G Sakkas, D Housten, SJ AF Gibson, WC Burch, JL Scherrer, JR Tapley, MB Killough, RL Volpe, FA Davis, WD Vaccarello, DC Grismore, G Sakkas, D Housten, SJ TI The IMAGE observatory SO SPACE SCIENCE REVIEWS LA English DT Review AB The Imager for Magnetopause-to-Aurora Global Exploration (IMAGE) mission will be the first of the new Medium-class Explorer (MIDEX) missions to fly. IMAGE will utilize a combination of ultraviolet and neutral atom imaging instruments plus an RF sounder to map and image the temporal and spatial features of the magnetosphere. The eight science sensors are mounted to a single deckplate. The deckplate is enveloped in an eight-sided spacecraft bus, 225 cm across the flats, developed by Lockheed Martin Missiles and Space Corporation. Constructed of laminated aluminum honeycomb panels, covered extensively by Gallium Arsenide solar cells, the spacecraft structure is designed to withstand the launch loads of a Delta 7326-9.5 ELV. Attitude control is via a single magnetic torque rod and passive nutation damper with aspect information provided by a star camera, sun sensor, and three-axis magnetometer. A single S-band transponder provides telemetry and command functionality. Interfaces between the self-contained payload and the spacecraft are limited to MIL-STD-1553 and power. This paper lists the requirements that drove the design of the IMAGE Observatory and the implementation that met the requirements. C1 SW Res Inst, San Antonio, TX 78228 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Lockheed Martin Missiles & Space, Sunnyvale, CA USA. RP Gibson, WC (reprint author), SW Res Inst, 6220 Culebra Rd, San Antonio, TX 78228 USA. NR 0 TC 15 Z9 15 U1 0 U2 0 PU KLUWER ACADEMIC PUBL PI DORDRECHT PA SPUIBOULEVARD 50, PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS SN 0038-6308 J9 SPACE SCI REV JI Space Sci. Rev. PD JAN PY 2000 VL 91 IS 1-2 BP 15 EP 50 DI 10.1023/A:1005203207186 PG 36 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 296LB UT WOS:000086024900003 ER PT J AU Pollock, CJ Asamura, K Baldonado, J Balkey, MM Barker, P Burch, JL Korpela, EJ Cravens, J Dirks, G Fok, MC Funsten, HO Grande, M Gruntman, M Hanley, J Jahn, JM Jenkins, M Lampton, M Marckwordt, M McComas, DJ Mukai, T Penegor, G Pope, S Ritzau, S Schattenburg, ML Scime, E Skoug, R Spurgeon, W Stecklein, T Storms, S Urdiales, C Valek, P van Beek, JTM Weidner, SE Wuest, M Young, MK Zinsmeyer, C AF Pollock, CJ Asamura, K Baldonado, J Balkey, MM Barker, P Burch, JL Korpela, EJ Cravens, J Dirks, G Fok, MC Funsten, HO Grande, M Gruntman, M Hanley, J Jahn, JM Jenkins, M Lampton, M Marckwordt, M McComas, DJ Mukai, T Penegor, G Pope, S Ritzau, S Schattenburg, ML Scime, E Skoug, R Spurgeon, W Stecklein, T Storms, S Urdiales, C Valek, P van Beek, JTM Weidner, SE Wuest, M Young, MK Zinsmeyer, C TI Medium Energy Neutral Atom (MENA) imager for the IMAGE mission SO SPACE SCIENCE REVIEWS LA English DT Review ID FREESTANDING TRANSMISSION GRATINGS; ULTRAVIOLET AB The Medium Energy Neutral Atom (MENA) imager was developed in response to the Imaging from the Magnetopause to the Aurora for Global Exploration (IMAGE) requirement to produce images of energetic neutral atoms (ENAs) in the energy range from 1 to 30 keV. These images will be used to infer characteristics of magnetospheric ion distributions. The MENA imager is a slit camera that images incident ENAs in the polar angle (based on a conventional spherical coordinate system defined by the spacecraft spin axis) and utilizes the spacecraft spin to image in azimuth. The speed of incident ENAs is determined by measuring the time-of-flight (TOF) from the entrance aperture to the detector. A carbon foil in the entrance aperture yields secondary electrons, which are imaged using a position-sensitive Start detector segment. This provides both the one-dimensional (1D) position at which the ENA passed through the aperture and a Start time for the TOF system. Impact of the incident ENA on the 1D position-sensitive Stop detector segment provides both a Stop-timing signal and the location that the ENA impacts the detector. The ENA incident polar angle is derived from the measured Stop and Start positions. Species identification (H vs. O) is based on variation in secondary electron yield with mass for a fixed ENA speed. The MENA imager is designed to produce images with 8 degrees x4 degrees angular resolution over a field of view 140 degrees x360 degrees, over an energy range from 1 keV to 30 keV. Thus, the MENA imager is well suited to conduct measurements relevant to the Earth's ring current, plasma sheet, and (at times) magnetosheath and cusp. C1 SW Res Inst, San Antonio, TX 78238 USA. Inst Space & Astronaut Sci, Kanagawa 2298510, Japan. Univ Calif Los Alamos Natl Lab, Los Alamos, NM 87545 USA. W Virginia Univ, Dept Phys, Morgantown, WV 26506 USA. NASA, Univ Space Res Assoc, GSFC, Greenbelt, MD 20771 USA. Rutherford Appleton Lab, Didcot OX11 0QX, Oxon, England. Univ So Calif, Dept Aerosp Engn, Los Angeles, CA 90089 USA. Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. MIT, Ctr Space Res, Cambridge, MA 02139 USA. Auburn Univ, Dept Phys, Allison Lab 206, Auburn, AL 36849 USA. Philips Res Labs, NL-5656 AA Eindhoven, Netherlands. RP Pollock, CJ (reprint author), SW Res Inst, 6220 Culebra Rd, San Antonio, TX 78238 USA. RI Fok, Mei-Ching/D-1626-2012; Funsten, Herbert/A-5702-2015; Gruntman, Mike/A-5426-2008; Grande, Manuel/C-2242-2013; OI Funsten, Herbert/0000-0002-6817-1039; Gruntman, Mike/0000-0002-0830-010X; Grande, Manuel/0000-0002-2233-2618; Valek, Philip/0000-0002-2318-8750; Korpela, Eric/0000-0001-8078-9395 NR 24 TC 71 Z9 73 U1 2 U2 5 PU KLUWER ACADEMIC PUBL PI DORDRECHT PA SPUIBOULEVARD 50, PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS SN 0038-6308 J9 SPACE SCI REV JI Space Sci. Rev. PD JAN PY 2000 VL 91 IS 1-2 BP 113 EP 154 DI 10.1023/A:1005259324933 PG 42 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 296LB UT WOS:000086024900006 ER PT J AU Moore, TE Chornay, DJ Collier, MR Herrero, FA Johnson, J Johnson, MA Keller, JW Laudadio, JF Lobell, JF Ogilvie, KW Rozmarynowski, P Fuselier, SA Ghielmetti, AG Hertzberg, E Hamilton, DC Lundgren, R Wilson, P Walpole, P Stephen, TM Peko, BL Van Zyl, B Wurz, P Quinn, JM Wilson, GR AF Moore, TE Chornay, DJ Collier, MR Herrero, FA Johnson, J Johnson, MA Keller, JW Laudadio, JF Lobell, JF Ogilvie, KW Rozmarynowski, P Fuselier, SA Ghielmetti, AG Hertzberg, E Hamilton, DC Lundgren, R Wilson, P Walpole, P Stephen, TM Peko, BL Van Zyl, B Wurz, P Quinn, JM Wilson, GR TI The low-energy neutral atom imager for IMAGE SO SPACE SCIENCE REVIEWS LA English DT Review ID MASS SPECTROGRAPH; POLAR-CAP; SCATTERING; IONS; HYDROGEN; SURFACE; AG(111); FIELD AB The 'Imager for Magnetosphere-to-Aurora Global Exploration' (IMAGE) will be launched early in the year 2000. It will be the first mission dedicated to imaging, with the capability to determine how the magnetosphere changes globally in response to solar storm effects in the solar wind, on time scales as short as a few minutes. The low energy neutral atom (LENA) imager uses a new atom-to-negative ion surface conversion technology to image the neutral atom flux and measure its composition (H and O) and energy distribution (10 to 750 eV). LENA uses electrostatic optics techniques for energy (per charge) discrimination and carbon foil time-of-flight techniques for mass discrimination. It has a 90 degrees x8 degrees field-of-view in 12 pixels, each nominally 8 degrees x8 degrees. Spacecraft spin provides a total field-of-view of 90 degrees x360 degrees, comprised of 12x45 pixels. LENA is designed to image fast neutral atom fluxes in its energy range, emitted by auroral ionospheres or the sun, or penetrating from the interstellar medium. It will thereby determine how superthermal plasma heating is distributed in space, how and why it varies on short time scales, and how this heating is driven by solar activity as reflected in solar wind conditions. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Lockheed Martin Adv Technol Ctr, Palo Alto, CA 94304 USA. Univ Maryland, College Pk, MD 20742 USA. Univ Denver, Denver, CO 80208 USA. Univ Bern, CH-301 Bern, Switzerland. Univ New Hampshire, Durham, NH 03824 USA. Mission Res Corp, Nashua, NH 03062 USA. RP Moore, TE (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RI Moore, Thomas/D-4675-2012; Keller, John/I-5097-2013; Collier, Michael/I-4864-2013; OI Moore, Thomas/0000-0002-3150-1137; Collier, Michael/0000-0001-9658-6605; Hamilton, Douglas/0000-0001-6103-8019 NR 32 TC 98 Z9 99 U1 2 U2 10 PU KLUWER ACADEMIC PUBL PI DORDRECHT PA SPUIBOULEVARD 50, PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS SN 0038-6308 J9 SPACE SCI REV JI Space Sci. Rev. PD JAN PY 2000 VL 91 IS 1-2 BP 155 EP 195 DI 10.1023/A:1005211509003 PG 41 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 296LB UT WOS:000086024900007 ER PT J AU Sandel, BR Broadfoot, AL Curtis, CC King, RA Stone, TC Hill, RH Chen, J Siegmund, OHW Raffanti, R Allred, DD Turley, RS Gallagher, DL AF Sandel, BR Broadfoot, AL Curtis, CC King, RA Stone, TC Hill, RH Chen, J Siegmund, OHW Raffanti, R Allred, DD Turley, RS Gallagher, DL TI The extreme ultraviolet imager investigation for the IMAGE mission SO SPACE SCIENCE REVIEWS LA English DT Review ID X-RAY; MICROCHANNEL PLATES; HELIUM; SATELLITE; DETECTORS AB The Extreme Ultraviolet Imager (EUV) of the IMAGE Mission will study the distribution of He+ in Earth's plasmasphere by detecting its resonantly-scattered emission at 30.4 nm. It will record the structure and dynamics of the cold plasma in Earth's plasmasphere on a global scale. The 30.4-nm feature is relatively easy to measure because it is the brightest ion emission from the plasmasphere, it is spectrally isolated, and the background at that wavelength is negligible. Measurements are easy to interpret because the plasmaspheric He+ emission is optically thin, so its brightness is directly proportional to the He+ column abundance. Effective imaging of the plasmaspheric He+ requires global 'snapshots' in which the high apogee and the wide field of view of EUV provide in a single exposure a map of the entire plasmasphere. EUV consists of three identical sensor heads, each having a field of view 30 degrees in diameter. These sensors are tilted relative to one another to cover a fan-shaped field of 84 degrees x30 degrees, which is swept across the plasmasphere by the spin of the satellite. EUV's spatial resolution is 0.6 degrees or similar to 0.1 R-E in the equatorial plane seen from apogee. The sensitivity is 1.9 count s(-1) Rayleigh(-1), sufficient to map the position of the plasmapause with a time resolution of 10 min. C1 Univ Arizona, Lunar & Planetary Lab, Tucson, AZ 85721 USA. Baja Technol LLC, Tucson, AZ 85721 USA. Siegmund Sci, Walnut Creek, CA 94595 USA. Brigham Young Univ, Dept Phys & Astron, Provo, UT 84602 USA. NASA, Dept Space Sci, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Sandel, BR (reprint author), Univ Arizona, Lunar & Planetary Lab, Tucson, AZ 85721 USA. OI Allred, David/0000-0001-6163-518X NR 34 TC 154 Z9 168 U1 2 U2 13 PU KLUWER ACADEMIC PUBL PI DORDRECHT PA SPUIBOULEVARD 50, PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS SN 0038-6308 J9 SPACE SCI REV JI Space Sci. Rev. PD JAN PY 2000 VL 91 IS 1-2 BP 197 EP 242 DI 10.1023/A:1005263510820 PG 46 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 296LB UT WOS:000086024900008 ER PT J AU Mende, SB Heetderks, H Frey, HU Lampton, M Geller, SP Habraken, S Renotte, E Jamar, C Rochus, P Spann, J Fuselier, SA Gerard, JC Gladstone, R Murphree, S Cogger, L AF Mende, SB Heetderks, H Frey, HU Lampton, M Geller, SP Habraken, S Renotte, E Jamar, C Rochus, P Spann, J Fuselier, SA Gerard, JC Gladstone, R Murphree, S Cogger, L TI Far ultraviolet imaging from the IMAGE spacecraft. 1. System design SO SPACE SCIENCE REVIEWS LA English DT Review ID ENERGETIC NEUTRAL ATOMS; RING CURRENT; ATMOSPHERE AB Direct imaging of the magnetosphere by the IMAGE spacecraft will be supplemented by observation of the global aurora, the footprint of magnetospheric regions. To assure the simultaneity of these observations and the measurement of the magnetospheric background neutral gas density, the IMAGE satellite instrument complement includes three Far Ultraviolet (FUV) instruments. In the wavelength region 120-190 nm, a downward-viewing auroral imager is only minimally contaminated by sunlight, scattered from clouds and ground, and radiance of the aurora observed in a nadir viewing geometry can be observed in the presence of the high-latitude dayglow. The Wideband Imaging Camera (WIC) will provide broad band ultraviolet images of the aurora for maximum spatial and temporal resolution by imaging the LBH N-2 bands of the aurora. The Spectrographic Imager (SI), a monochromatic imager, will image different types of aurora, filtered by wavelength. By measuring the Doppler-shifted Ly-alpha, the proton-induced component of the aurora will be imaged separately. Finally, the GEO instrument will observe the distribution of the geocoronal emission, which is a measure of the neutral background density source for charge exchange in the magnetosphere. The FUV instrument complement looks radially outward from the rotating IMAGE satellite and, therefore, it spends only a short time observing the aurora and the Earth during each spin. Detailed descriptions of the WIC, SI, GEO, and their individual performance validations are discussed in companion papers. This paper summarizes the system requirements and system design approach taken to satisfy the science requirements. One primary requirement is to maximize photon collection efficiency and use efficiently the short time available for exposures. The FUV auroral imagers WIC and SI both have wide fields of view and take data continuously as the auroral region proceeds through the field of view. To minimize data volume, multiple images are taken and electronically co-added by suitably shifting each image to compensate for the spacecraft rotation. In order to minimize resolution loss, the images have to be distortion-corrected in real time for both WIC and SI prior to co-adding. The distortion correction is accomplished using high speed look up tables that are pre-generated by least square fitting to polynomial functions by the on-orbit processor. The instruments were calibrated individually while on stationery platforms, mostly in vacuum chambers as described in the companion papers. Extensive ground-based testing was performed with visible and near UV simulators mounted on a rotating platform to estimate their on-orbit performance. The predicted instrument system performance is summarized and some of the preliminary data formats are shown. C1 Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. Ctr Spatiale Liege, B-4031 Liege, Belgium. NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. Lockheed Martin Adv Technol Ctr, Palo Alto, CA 94304 USA. Univ Liege, B-4000 Liege, Belgium. SW Res Inst, San Antonio, TX 78228 USA. Univ Calgary, Calgary, AB T2N 1N4, Canada. RP Mende, SB (reprint author), Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. OI Frey, Harald/0000-0001-8955-3282; GERARD, Jean-Claude/0000-0002-8565-8746 NR 31 TC 172 Z9 176 U1 2 U2 12 PU KLUWER ACADEMIC PUBL PI DORDRECHT PA SPUIBOULEVARD 50, PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS SN 0038-6308 J9 SPACE SCI REV JI Space Sci. Rev. PD JAN PY 2000 VL 91 IS 1-2 BP 243 EP 270 DI 10.1023/A:1005271728567 PG 28 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 296LB UT WOS:000086024900009 ER PT J AU Mende, SB Heetderks, H Frey, HU Lampton, M Geller, SP Abiad, R Siegmund, OHW Tremsin, AS Spann, J Dougani, H Fuselier, SA Magoncelli, AL Bumala, MB Murphree, S Trondsen, T AF Mende, SB Heetderks, H Frey, HU Lampton, M Geller, SP Abiad, R Siegmund, OHW Tremsin, AS Spann, J Dougani, H Fuselier, SA Magoncelli, AL Bumala, MB Murphree, S Trondsen, T TI Far ultraviolet imaging from the IMAGE spacecraft. 2. Wideband FUV imaging SO SPACE SCIENCE REVIEWS LA English DT Review AB The Far Ultraviolet Wideband Imaging Camera (WIC) complements the magnetospheric images taken by the IMAGE satellite instruments with simultaneous global maps of the terrestrial aurora. Thus, a primary requirement of WIC is to image the total intensity of the aurora in wavelength regions most representative of the auroral source and least contaminated by dayglow, have sufficient field of view to cover the entire polar region from spacecraft apogee and have resolution that is sufficient to resolve auroras on a scale of 1 to 2 latitude degrees. The instrument is sensitive in the spectral region from 140-190 nm. The WIC is mounted on the rotating IMAGE spacecraft viewing radially outward and has a field of view of 17 degrees in the direction parallel to the spacecraft spin axis. Its field of view is 30 degrees in the direction perpendicular to the spin axis, although only a 17 degrees x17 degrees image of the Earth is recorded. The optics was an all-reflective, inverted Cassegrain Burch camera using concentric optics with a small convex primary and a large concave secondary mirror. The mirrors were coated by a special multi-layer coating, which has low reflectivity in the visible and near UV region. The detector consists of a MCP-intensified CCD. The MCP is curved to accommodate the focal surface of the concentric optics. The phosphor of the image intensifier is deposited on a concave fiberoptic window, which is then coupled to the CCD with a fiberoptic taper. The camera head operates in a fast frame transfer mode with the CCD being read approximately 30 full frames (512x256 pixel) per second with an exposure time of 0.033 s. The image motion due to the satellite spin is minimal during such a short exposure. Each image is electronically distortion corrected using the look up table scheme. An offset is added to each memory address that is proportional to the image shift due to satellite rotation, and the charge signal is digitally summed in memory. On orbit, approximately 300 frames will be added to produce one WIC image in memory. The advantage of the electronic motion compensation and distortion correction is that it is extremely flexible, permitting several kinds of corrections including motions parallel and perpendicular to the predicted axis of rotation. The instrument was calibrated by applying ultraviolet light through a vacuum monochromator and measuring the absolute responsivity of the instrument. To obtain the data for the distortion look up table, the camera was turned through various angles and the input angles corresponding to a pixel matrix were recorded. It was found that the spectral response peaked at 150 nm and fell off in either direction. The equivalent aperture of the camera, including mirror reflectivities and effective photocathode quantum efficiency, is about 0.04 cm(2). Thus, a 100 Rayleigh aurora is expected to produce 23 equivalent counts per pixel per 10 s exposure at the peak of instrument response. C1 Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. Tala Adv Applicat Inc, Madison, AL 35758 USA. Lockheed Martin Adv Technol Ctr, Palo Alto, CA 94304 USA. Univ Calgary, Calgary, AB T2N 1N4, Canada. RP Mende, SB (reprint author), Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. RI Trondsen, Trond/F-5751-2016; OI Trondsen, Trond/0000-0002-9538-1832; Frey, Harald/0000-0001-8955-3282 NR 6 TC 138 Z9 142 U1 2 U2 19 PU KLUWER ACADEMIC PUBL PI DORDRECHT PA SPUIBOULEVARD 50, PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS SN 0038-6308 J9 SPACE SCI REV JI Space Sci. Rev. PD JAN PY 2000 VL 91 IS 1-2 BP 271 EP 285 DI 10.1023/A:1005227915363 PG 15 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 296LB UT WOS:000086024900010 ER PT J AU Reinisch, BW Haines, DM Bibl, K Cheney, G Galkin, IA Huang, X Myers, SH Sales, GS Benson, RF Fung, SF Green, JL Boardsen, S Taylor, WWL Bougeret, JL Manning, R Meyer-Vernet, N Moncuquet, M Carpenter, DL Gallagher, DL Reiff, P AF Reinisch, BW Haines, DM Bibl, K Cheney, G Galkin, IA Huang, X Myers, SH Sales, GS Benson, RF Fung, SF Green, JL Boardsen, S Taylor, WWL Bougeret, JL Manning, R Meyer-Vernet, N Moncuquet, M Carpenter, DL Gallagher, DL Reiff, P TI The radio plasma imager investigation on the IMAGE spacecraft SO SPACE SCIENCE REVIEWS LA English DT Review ID DIGITAL IONOSONDE; THERMAL NOISE; WAVES; TORUS AB Radio plasma imaging uses total reflection of electromagnetic waves from plasmas whose plasma frequencies equal the radio sounding frequency and whose electron density gradients are parallel to the wave normals. The Radio Plasma Imager (RPI) has two orthogonal 500-m long dipole antennas in the spin plane for near omni-directional transmission. The third antenna is a 20-m dipole along the spin axis. Echoes from the magnetopause, plasmasphere and cusp will be received with the three orthogonal antennas, allowing the determination of their angle-of-arrival. Thus it will be possible to create image fragments of the reflecting density structures. The instrument can execute a large variety of programmable measuring options at frequencies between 3 kHz and 3 MHz. Tuning of the transmit antennas provides optimum power transfer from the 10 W transmitter to the antennas. The instrument can operate in three active sounding modes: (1) remote sounding to probe magnetospheric boundaries, (2) local (relaxation) sounding to probe the local plasma frequency and scalar magnetic field, and (3) whistler stimulation sounding. In addition, there is a passive mode to record natural emissions, and to determine the local electron density, the scalar magnetic field, and temperature by using a thermal noise spectroscopy technique. C1 Univ Massachusetts, Ctr Atmospher Res, Lowell, MA 01854 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Raytheon ITSS, Goddard Space Flight Ctr, Greenbelt, MD USA. Observ Paris, Meudon, France. Stanford Univ, Stanford, CA 94305 USA. NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. Rice Univ, Houston, TX 77251 USA. RP Reinisch, BW (reprint author), Univ Massachusetts, Ctr Atmospher Res, Lowell, MA 01854 USA. RI Fung, Shing/F-5647-2012; Reiff, Patricia/D-2564-2014 OI Reiff, Patricia/0000-0002-8043-5682 NR 34 TC 110 Z9 112 U1 0 U2 1 PU KLUWER ACADEMIC PUBL PI DORDRECHT PA SPUIBOULEVARD 50, PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS SN 0038-6308 J9 SPACE SCI REV JI Space Sci. Rev. PD JAN PY 2000 VL 91 IS 1-2 BP 319 EP 359 DI 10.1023/A:1005252602159 PG 41 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 296LB UT WOS:000086024900012 ER PT J AU Green, JL Benson, RF Fung, SF Taylor, WWL Boardsen, SA Reinisch, BW Haines, DM Bibl, K Cheney, G Galkin, IA Huang, X Myers, SH Sales, GS Bougeret, JL Manning, R Meyer-Vernet, N Moncuquet, M Carpenter, DL Gallagher, DL Reiff, PH AF Green, JL Benson, RF Fung, SF Taylor, WWL Boardsen, SA Reinisch, BW Haines, DM Bibl, K Cheney, G Galkin, IA Huang, X Myers, SH Sales, GS Bougeret, JL Manning, R Meyer-Vernet, N Moncuquet, M Carpenter, DL Gallagher, DL Reiff, PH TI Radio Plasma Imager simulations and measurements SO SPACE SCIENCE REVIEWS LA English DT Review ID ELECTRON-DENSITY IRREGULARITIES; AURORAL KILOMETRIC RADIATION; CYCLOTRON HARMONIC-WAVES; SUBAURORAL ION DRIFTS; RELAXATION SOUNDER; OUTER PLASMASPHERE; WHISTLER EVIDENCE; DUSKSIDE BULGE; THERMAL NOISE; MAGNETOSPHERE AB The Radio Plasma Imager (RPI) will be the first-of-its kind instrument designed to use radio wave sounding techniques to perform repetitive remote sensing measurements of electron number density (N-e) structures and the dynamics of the magnetosphere and plasmasphere. RPI will fly on the Imager for Magnetopause-to-Aurora Global Exploration (IMAGE) mission to be launched early in the year 2000. The design of the RPI is based on recent advances in radio transmitter and receiver design and modern digital processing techniques perfected for ground-based ionospheric sounding over the last two decades. Free-space electromagnetic waves transmitted by the RPI located in the low-density magnetospheric cavity will be reflected at distant plasma cutoffs. The location and characteristics of the plasma at those remote reflection points can then be derived from measurements of the echo amplitude, phase, delay time, frequency, polarization, Doppler shift, and echo direction. The 500 m tip-to-tip X and Y (spin plane) antennas and 20 m Z axis antenna on RPI will be used to measures echoes coming from distances of several R-E. RPI will operate at frequencies between 3 kHz to 3 MHz and will provide quantitative N-e values from 10(-1) to 10(5) cm(-3). Ray tracing calculations, combined with specific radio imager instrument characteristics, enables simulations of RPI measurements. These simulations have been performed throughout an IMAGE orbit and under different model magnetospheric conditions. They dramatically show that radio sounding can be used quite successfully to measure a wealth of magnetospheric phenomena such as magnetopause boundary motions and plasmapause dynamics. The radio imaging technique will provide a truly exciting opportunity to study global magnetospheric dynamics in a way that was never before possible. C1 NASA, Raytheon Corp, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Univ Massachusetts, Ctr Atmospher Res, Lowell, MA USA. Observ Paris, Meudon, France. Stanford Univ, Stanford, CA 94305 USA. NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. Rice Univ, Houston, TX 77251 USA. RP NASA, Raytheon Corp, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RI Fung, Shing/F-5647-2012; Reiff, Patricia/D-2564-2014 OI Reiff, Patricia/0000-0002-8043-5682 NR 97 TC 13 Z9 13 U1 0 U2 0 PU SPRINGER PI DORDRECHT PA VAN GODEWIJCKSTRAAT 30, 3311 GZ DORDRECHT, NETHERLANDS SN 0038-6308 EI 1572-9672 J9 SPACE SCI REV JI Space Sci. Rev. PD JAN PY 2000 VL 91 IS 1-2 BP 361 EP 389 DI 10.1023/A:1005256703977 PG 29 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 296LB UT WOS:000086024900013 ER PT J AU Fung, SF Benson, RF Carpenter, DL Reinisch, BW Gallagher, DL AF Fung, SF Benson, RF Carpenter, DL Reinisch, BW Gallagher, DL TI Investigations of irregularities in remote plasma regions by radio sounding: applications of the radio plasma imager on image SO SPACE SCIENCE REVIEWS LA English DT Review ID LATITUDE IONOSPHERIC IRREGULARITIES; FLUX-TRANSFER EVENTS; SOLAR-WIND CONTROL; BOUNDARY-LAYER; MAGNETOPAUSE SHAPE; MAGNETOSPHERE; DENSITY; WAVES; SURFACE; FEASIBILITY AB The Radio Plasma Imager (RPI) on the IMAGE mission operates like a radar by transmitting and receiving coherent electromagnetic pulses. The RPI is designed to receive mirror-like (specular) reflections and coherent scatter returns. Long-range echoes of electromagnetic sounder waves are reflected at remote plasma cutoffs. Thus, analyses of RPI observations will yield the plasma parameters and distances to the remote reflection points. The RPI will employ pulse compression and spectral integration techniques, perfected in ground-based ionospheric digital sounders, in order to enhance the signal-to-noise ratio in long-range magnetospheric sounding. When plasma irregularities exist in the remote magnetospheric plasmas being probed by the sounder waves, echo signatures may become complicated. Experience in ionospheric sounding under such conditions indicates that sounding echo strengths can actually be enhanced by the presence of irregularities, and ground-based sounding indicates that coherent detection techniques can still be employed. In this paper we investigate the conditions that will allow coherent signals to be detected by the RPI and the signatures of scattering to be expected in the presence of multi-scale irregularities. Sounding of irregular plasma structures in the plasmasphere, plasmapause and magnetopause are also discussed. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Stanford Univ, Palo Alto, CA 94304 USA. Univ Massachusetts, Lowell, MA USA. NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Fung, SF (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RI Fung, Shing/F-5647-2012 NR 72 TC 15 Z9 15 U1 1 U2 1 PU KLUWER ACADEMIC PUBL PI DORDRECHT PA SPUIBOULEVARD 50, PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS SN 0038-6308 J9 SPACE SCI REV JI Space Sci. Rev. PD JAN PY 2000 VL 91 IS 1-2 BP 391 EP 419 DI 10.1023/A:1005264906702 PG 29 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 296LB UT WOS:000086024900014 ER PT J AU Perez, JD Fok, MC Moore, TE AF Perez, JD Fok, MC Moore, TE TI Deconvolution of energetic neutral atom images of the Earth's magnetosphere SO SPACE SCIENCE REVIEWS LA English DT Review ID SHEET AB A method for deconvolving equatorial pitch angle distributions of energetic neutral atoms from images from the ENA instruments on the IMAGE satellite is described and illustrated using simulated data obtained from calculated models of ring current flux. The unknown flux is expanded in terms of cubic B-splines and Legendre polynomials. The expansion coefficients are obtained from the solution of a linear set of equations that select the smoothest solution that fits the data. In this way, all the information that is contained in the data is extracted but no more. C1 Auburn Univ, Dept Phys, Auburn, AL 36849 USA. NASA, Univ Space Res Assoc, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NASA, Extraterr Phys Lab, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Perez, JD (reprint author), Auburn Univ, Dept Phys, Auburn, AL 36849 USA. RI Moore, Thomas/D-4675-2012; Fok, Mei-Ching/D-1626-2012 OI Moore, Thomas/0000-0002-3150-1137; NR 11 TC 26 Z9 26 U1 0 U2 1 PU KLUWER ACADEMIC PUBL PI DORDRECHT PA SPUIBOULEVARD 50, PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS SN 0038-6308 J9 SPACE SCI REV JI Space Sci. Rev. PD JAN PY 2000 VL 91 IS 1-2 BP 421 EP 436 DI 10.1023/A:1005277307611 PG 16 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 296LB UT WOS:000086024900015 ER PT J AU Burley, RJ Green, JL Coyle, SE AF Burley, RJ Green, JL Coyle, SE TI The IMAGE science and mission operations center SO SPACE SCIENCE REVIEWS LA English DT Review AB The Imager for Magnetopause-to-Aurora Global Exploration (IMAGE) will produce forefront science by quantifying the response of the magnetosphere to the time variable solar wind. It will acquire, for the first time, a variety of three-dimensional images of magnetospheric boundaries and plasma distributions extending from the magnetopause to the inner plasmasphere. The images will be produced on time scales needed to answer important questions about the interactions of the solar wind and the magnetosphere. The IMAGE team will provide open access to all IMAGE data. Thus there will be no proprietary rights or periods. All IMAGE data products will be archived and available to the scientific research community. The IMAGE mission will operate with a near 100% duty cycle with all instruments in their baseline operational modes. A Science and Mission Operations Control Center or SMOC has been developed at the NASA Goddard Space Flight Center (GSFC) to be the main data and command processing system for IMAGE. The IMAGE Level-0 data will be processed into Level 0.5 and Level-1 data and browse products within 24 hours after their receipt of raw data in the SMOC. These data products will be transferred to the NSSDC, for long-term archiving, and posted immediately on the world-wide-web for use by the international scientific community and the public. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Burley, RJ (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 3 TC 1 Z9 1 U1 0 U2 1 PU KLUWER ACADEMIC PUBL PI DORDRECHT PA SPUIBOULEVARD 50, PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS SN 0038-6308 J9 SPACE SCI REV JI Space Sci. Rev. PD JAN PY 2000 VL 91 IS 1-2 BP 483 EP 496 DI 10.1023/A:1005289628084 PG 14 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 296LB UT WOS:000086024900018 ER PT J AU Odenwald, SF Taylor, WWL Reiff, PH AF Odenwald, SF Taylor, WWL Reiff, PH TI The IMAGE/POETRY Education and Public Outreach program SO SPACE SCIENCE REVIEWS LA English DT Review AB Education and public outreach are viewed by NASA as significant undertakings for all of its space missions. The IMAGE satellite is one of the first missions to explicitly include 'E&PO' in its original proposal to NASA in 1996. We will discuss what IMAGE has accomplished in this area to date, and what new activities it will conduct following a successful launch. C1 NASA, Raytheon ITSS, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Rice Univ, Houston, TX 77251 USA. RP Odenwald, SF (reprint author), NASA, Raytheon ITSS, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RI Reiff, Patricia/D-2564-2014 OI Reiff, Patricia/0000-0002-8043-5682 NR 10 TC 0 Z9 0 U1 0 U2 0 PU KLUWER ACADEMIC PUBL PI DORDRECHT PA SPUIBOULEVARD 50, PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS SN 0038-6308 J9 SPACE SCI REV JI Space Sci. Rev. PD JAN PY 2000 VL 91 IS 1-2 BP 497 EP 506 DI 10.1023/A:1005249929901 PG 10 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 296LB UT WOS:000086024900019 ER PT S AU Bartoe, JDF AF Bartoe, JDF BE ElGenk, MS TI Research plans for the International Space Station - Research begins this year! SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB Research onboard the International Space Station begins this year, 2000, shortly after the launch and assembly of the U.S. Laboratory "Destiny." The International Space Station will house a broad range of research disciplines; more than any space or ground laboratory in history. Planning for this diverse research activity begins with a strategic plan looking forward over the next five years. The strategic plan is then refined into a flight-by-flight outfitting plan: identifying which research racks and attached payloads are carried to orbit on each flight. The placement of payloads is then developed for the nearly 40 rack sites and 40 attached payload sites, taking into account the differing resource requirements of each payload and the differing resource capabilities of each site. Finally, chosen investigators and investigations are assigned to specific time periods. This paper provides the explanation and results of each step in the planning process, culminating in a list of the chosen investigators. C1 NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Bartoe, JDF (reprint author), NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 3 EP 20 PG 18 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500001 ER PT S AU Sledd, AM AF Sledd, AM BE ElGenk, MS TI The ISS EXPRESS Rack: An innovative approach for rapid integration SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB The Expedite the Processing of Experiments to Space Station or EXPRESS Rack System, was developed to provide Space Station accommodations for small, subrack payloads. The EXPRESS Rack accepts Space Shuttle middeck locker type payloads and International Subrack Interface Standard (ISIS) Drawer payloads, allowing previously flown payloads an opportunity to transition to the International Space Station. The EXPRESS Rack provides power, data command and control, video. water cooling, air cooling, vacuum exhaust, and Nitrogen supply to payloads. The EXPRESS Rack system also includes transportation racks to transport payloads to and from the Space Station, Suitcase Simulators to allow a payload developer to verify data interfaces at the development site, Functional Checkout Units to allow payload checkout at KSC prior to launch, and trainer racks for the astronauts to learn how to operate the EXPRESS Racks prior to flight. Standard hardware and software interfaces provided by the EXPRESS Rack simplify the analytical and physical integration processes, and facilitates simpler ISS payload development. The EXPRESS Rack has also formed the basis for the U.S. Life Sciences payload racks and the Window Observational Research Facility on Space Station. C1 NASA, George C Marshall Space Flight Ctr, EXPRESS Rack Dev, Project Lead, Huntsville, AL 35812 USA. RP Sledd, AM (reprint author), NASA, George C Marshall Space Flight Ctr, EXPRESS Rack Dev, Project Lead, FD 31, Huntsville, AL 35812 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 21 EP 26 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500002 ER PT S AU Smith, ME AF Smith, ME BE ElGenk, MS TI Launch site processing of payloads for the ISS SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB For over 30 years, Kennedy Space Center has processed payloads for numerous NASA Programs. This paper provides an overview of KSC and its role in processing payloads for the International Space Station. Best practices and lessons learned from Station's predecessor, the Spacelab Program, have been adopted for the processing of ISS payloads at the launch/landing site, and some of these are highlighted in this paper. C1 NASA, John F Kennedy Space Ctr, Space Stn & Shuttle Payloads Directorate, NNL,Utilizat Div, Kennedy Space Ctr, FL 32899 USA. RP Smith, ME (reprint author), NASA, John F Kennedy Space Ctr, Space Stn & Shuttle Payloads Directorate, NNL,Utilizat Div, Kennedy Space Ctr, FL 32899 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 27 EP 30 PG 4 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500003 ER PT S AU Cissom, RD Cobb, BJ Ramage, KS AF Cissom, RD Cobb, BJ Ramage, KS BE ElGenk, MS TI Payload operations and telescience on ISS SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB The objective of this paper is to provide future International Space Station (ISS) scientists and/or engineers with an overview of the ISS payload operations and integration process. This process begins with the payload being manifested on the ISS and continued through the integration and operations process. Emphasis is placed on the interfaces and tools that the payload will utilize when going through the process. For each of the Data Sets, the Payload Operations and Integration Center (POIC) provides a Data Set Manager to work with the PD's. C1 NASA, George C Marshall Space Flight Ctr, FPD, Huntsville, AL 35812 USA. RP Cissom, RD (reprint author), NASA, George C Marshall Space Flight Ctr, FPD, Huntsville, AL 35812 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 31 EP 36 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500004 ER PT S AU Jackson, RW Savage, P AF Jackson, RW Savage, P BE ElGenk, MS TI The Telescience Support Center at NASA Ames Research Center SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB NASA is developing a Telescience Support Center (TSC) at the Ames Research Center. The TSC will be part of the infrastructure needed to conduct Research in the Space Station and has been tailored to satisfy the requirements of Non-Human Life Sciences. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Jackson, RW (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 57 EP 62 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500008 ER PT S AU Adeni, K Picinich, L AF Adeni, K Picinich, L BE ElGenk, MS TI Ames Research Center Telescience Support Center capabilities SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB The Ames Research Center (ARC) Telescience Support Center (TSC) provides the necessary ground operations capability and infrastructure for achieving the mission objectives of the Space Station Biological Research Project (SSBRP). One of the primary operations objectives is to provide the Principal Investigator (PI) access to archived or real-time telemetry, image, video, and voice data. The remote PI is provided access to the Ames TSC capabilities utilizing Internet technologies. To control experiments in the SSBRP payloads, the PI will be able to originate commands either from a console Graphical User Interface (GUI) at ARC TSC or remotely request commands from his/her institution The ARC TSC also provides the capability for other ground operations functions such as console operator training, mission simulation, payload planning, payload logistics, and ground specimen controls. This paper discusses the implementation strategy of the ARC TSC to achieve SSBRP science objectives. C1 NASA, Ames Res Ctr, Space Stn Biol Res Project, Moffett Field, CA 94035 USA. RP Adeni, K (reprint author), NASA, Ames Res Ctr, Space Stn Biol Res Project, Moffett Field, CA 94035 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 63 EP 68 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500009 ER PT S AU Mixson, CD AF Mixson, CD BE ElGenk, MS TI Operational methodology for the International Space Station (ISS) High Rate Communications Outage Recorder (HCOR) SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB The HCOR will be used onboard the ISS to record digital data during Ku-band Loss of Signal (LOS) periods. This recorded data will be played back to the ground during Ku-band Acquisition of Signal (AOS) periods. The Data Management (DM) Team at the Payload Operations Integration Center (POIC) is the primary operator of this complex recorder. The record and playback capabilities - along with the memory management functions - are presented in this paper. To illustrate how the DM Team plans to manage the record, playback, and memory management tasks of operating the HCOR, an operational scenario for a ninety minute orbit is presented. C1 NASA, George C Marshall Space Flight Ctr, Flight Projects Directorate FD33, POIC Data Management Team, Huntsville, AL 35812 USA. RP Mixson, CD (reprint author), NASA, George C Marshall Space Flight Ctr, Flight Projects Directorate FD33, POIC Data Management Team, Huntsville, AL 35812 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 69 EP 76 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500010 ER PT S AU Jones, WV AF Jones, WV BE ElGenk, MS TI NASA Office of Space Science plans for selecting and funding ISS payloads SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB The NASA Office of Space Science expects to solicit International Space Station (ISS) payloads as Missions of Opportunity in Explorer Program Announcements of Opportunity. This policy allows ISS investigations to compete on an equal basis with other missions requiring expendable launch vehicles, secondary-payload launches, etc. Each of three Explorer announcements are released approximately every two years, so there should be an opportunity to propose for ISS research at least once per year. On the other hand, these solicitations must be matched with the limited availability of ISS sites allocated for space science research, so some of them may not include ISS research opportunities. The ISS investigations are expected to have the traditional three-year maximum time limit for Explorer payload development, but some flexibility may be required to match the ISS site availability. C1 NASA Headquarters, Off Space Sci, Washington, DC 20546 USA. RP Jones, WV (reprint author), NASA Headquarters, Off Space Sci, Code SR, Washington, DC 20546 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 83 EP 88 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500012 ER PT S AU Park, B Voels, SA Eppler, DB AF Park, B Voels, SA Eppler, DB BE ElGenk, MS TI Accommodations for external payloads on the International Space Station SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Meeting Abstract CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Park, B (reprint author), NASA, Goddard Space Flight Ctr, Code 740-2, Greenbelt, MD 20771 USA. NR 3 TC 1 Z9 1 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 89 EP 90 PG 2 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500013 ER PT S AU Archer, JL AF Archer, JL BE ElGenk, MS TI ISS payload launch site capabilities and processing flow SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB This paper describes the capabilities at the launch site for preparing ISS payloads for flight. On-line Utilization Operations, including payload off-line activities, payload turnover to KSC, physical integration of rack and attached payloads, payload-to-ISS final functional checkout, payload closeouts. and passive stowage are discussed in detail. Examples of payload processing in action are given. Throughout the discussion, specific challenges in developing and implementing new operational processes are examined, such as; meeting flight element need dates while maintaining payload arrival at KSC as close to launch as possible. C1 NASA, John F Kennedy Space Ctr, Space Stn & Shuttle Payloads Directorate, NN L1,Operat & Integrat Branch,Utilizat Div, Kennedy Space Ctr, FL 32899 USA. RP Archer, JL (reprint author), NASA, John F Kennedy Space Ctr, Space Stn & Shuttle Payloads Directorate, NN L1,Operat & Integrat Branch,Utilizat Div, Kennedy Space Ctr, FL 32899 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 117 EP 123 PG 7 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500018 ER PT S AU Mathis, JG Traylor, HJ AF Mathis, JG Traylor, HJ BE ElGenk, MS TI ISS ground processing late and early access capabilities SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB This paper contains a general description of the late and early access capabilities provided for the international Space Station (ISS) when a Multi-Purpose Logistics Module (MPLM) is manifested. This includes the accommodations provided in both the MPLM and the Space Shuttle middeck area. The paper describes the timeframes available for installation and removal of stowage, size and mass limitations. as well as power and thermal control availability. The purpose is to provide potential Payload Developers (PDs) with an overview of the capability to deliver time-critical payloads to orbit and to retrieve those payloads upon return to earth. C1 NASA, John F Kennedy Space Ctr, Space Stn & Shuttle Payloads Directorate, Utilizat Div,NN L2,Mech & Fluids Branch, Kennedy Space Ctr, FL 32899 USA. RP Mathis, JG (reprint author), NASA, John F Kennedy Space Ctr, Space Stn & Shuttle Payloads Directorate, Utilizat Div,NN L2,Mech & Fluids Branch, Kennedy Space Ctr, FL 32899 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 124 EP 129 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500019 ER PT S AU Jacobson, C Yaskovic, R Johnson, J AF Jacobson, C Yaskovic, R Johnson, J BE ElGenk, MS TI Advancing payload processing into the 21st century SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB Launching payloads into space has become a weekly occurrence around the world. Although it is becoming commonplace. it has not become a low-cost or low-risk, quick or simple process. An effort is being worked at NASA's Kennedy Space Center (KSC) to create a process with a generic set of tools and hardware that will advance payload processing into the 21(st) Century by making it more efficient and less complicated. This new process would be more cost effective. have a shorter cycle time, and expend fen-er resources than in the past KSC is NASA's Center of Excellence for Payload Processing and has over thirty years of experience in processing all types of payloads (shuttle and expendable). KSC is currently developing and operating a high fidelity checkout system that will be used to perform a final functional checkout of flight interfaces between the international Space Station (ISS) and its science experiments. These interfaces include high-, medium-, and low-rate data communications, video, command and data handling, power. fluids and gases. This checkout system also contains an ISS Program equivalent ground station that receives, processes and distributes payload telemetry to the appropriate user or operator. KSC is also working with the ISS Program distributed verification tool used by payload developers to verify their experiments meet ISS Program specifications prior to being sent to KSC for final checkout and launch. C1 NASA, Ground Syst Engn Div, Test & Checkout Syst Branch, Kennedy Space Ctr, FL 32899 USA. RP Jacobson, C (reprint author), NASA, Ground Syst Engn Div, Test & Checkout Syst Branch, Mail COde NN-J2, Kennedy Space Ctr, FL 32899 USA. NR 0 TC 1 Z9 1 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 136 EP 141 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500021 ER PT S AU Baumann, DK AF Baumann, DK BE ElGenk, MS TI International hardware and experiment development for human life science research on the International Space Station SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Meeting Abstract CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium C1 NASA, Johnson Space Ctr, Flight Res Management Branch SF4, Houston, TX 77006 USA. RP Baumann, DK (reprint author), NASA, Johnson Space Ctr, Flight Res Management Branch SF4, Houston, TX 77006 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 172 EP 174 PG 3 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500027 ER PT S AU Bauer, L AF Bauer, L BE ElGenk, MS TI Hardware development process for Human Research Facility applications SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Meeting Abstract CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium C1 NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Bauer, L (reprint author), NASA, Lyndon B Johnson Space Ctr, 2101 NASA Rd 1,Mail Stop EA5, Houston, TX 77058 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 224 EP 225 PG 2 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500036 ER PT S AU Singh, BS Alexander, JID AF Singh, BS Alexander, JID BE ElGenk, MS TI Microgravity fluid physics and transport phenomena experiments planned aboard the International Space Station SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB The International Space Station (ISS) with its first two elements already launched in 1998, provides the microgravity research community with a tremendous opportunity to conduct long-duration microgravity experiments which can he controlled and operated from their own laboratory. Frequent planned shuttle flights to the Station will provide opportunities to conduct many mon experiments than were previously possible. NASA Glenn Research Center is in the process of designing a Fluids and Combustion Facility (FCF) to be located in the Laboratory Module of the ISS. The FCF will accommodate multiple users and allow a wide range of experiments to be conducted so that best use is made of available resources. This paper provides an overview of the plan for utilizing the international Space Station to conduct fluids and transport experiments that are vital to NASA's mission. The current plan includes 15 microgravity fluid physics and transport phenomena experiments representing a broad cross-section of the fluid physics and transport phenomena including multiphase flow and phase change; physics of colloids, flow of granular materials: mechanics of foams; stability; and interfacial phenomena. A brief description of each planned experiment and its significance is provided. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Singh, BS (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 17 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 232 EP 239 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500038 ER PT S AU Hill, ME Saavedra, SM AF Hill, ME Saavedra, SM BE ElGenk, MS TI A summary of capabilities and operations for the fluids and combustion facility fluids integrated rack - First four experiments SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB Long-term microgravity experiments will continue on-board the International Space Station (ISS). Glenn Research Center (GRC) is the implimenting center for microgravity research in the areas of combustion science, fluid physics and acceleration measurement disciplines. This paper focuses on the initial ISS facilities and capabilities envisioned for the first four fluids physics experiments. GRC is developing the Fluids Integrated Rack (FIR) to accommodate this first wave of experiments in the 2004 timeframe. Many capabilities are provided by FIR such as: cameras and illumination systems; command and data management systems; environmental control systems; electrical power subsystems; active rack isolation systems; and optics bench accommodations of investigator hardware. The first four experiments, in addition, require microscopy capability; and as well as other sophisticated optical diagnostics (e.g., light scattering). A multi-user apparatus was thus conceived that has developed into the Light Microscopy Module (LMM). The LMM experiments discussed include: ''Constrained Vapor Bubble (CVB)" (Prof. P. Wayner, RPI); "Physics of Hard Spheres Experiment" (PHaSE-2) (Prof. P. Chaikin, Princeton University); "Physics of Colloids in Space" (PCS-2) (Prof. D. Weitz, Harvard University); and the "Colloidal Assembly in Binary Particle Suspensions" (Prof. A. Yodh, University of Pennsylvania). C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Hill, ME (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 253 EP 260 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500041 ER PT S AU Lant, CT Resnick, A AF Lant, CT Resnick, A BE ElGenk, MS TI Multi-function light microscopy module for the International Space Station SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB NASA Glenn Research Center (Cleveland, Ohio) and Dynacs Engineering Co.. Inc. ate developing a multifunctional, remotely operated light microscope for telescience fluids physics research on the International Space Station (ISS). The module is designed for the Fluids and Combustion Facility in the U.S. Laboratory, and is manifested for flight in June. 2003. The design includes the following features: bright field, dark field, phase contrast, differential interference contrast (DIC), confocal microscopy, oil immersion, dynamic light scattering, full-field static light scattering, fluorescence microscopy, spectrophotometry, optical tweezers. and micro-theology. C1 NASA, Glenn Res Ctr, Dynacs Engn Co Inc, Cleveland, OH 44135 USA. RP Lant, CT (reprint author), NASA, Glenn Res Ctr, Dynacs Engn Co Inc, Cleveland, OH 44135 USA. NR 3 TC 1 Z9 1 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 324 EP 329 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500051 ER PT S AU Fletcher, LE Sarver, GL Jahns, G AF Fletcher, LE Sarver, GL Jahns, G BE ElGenk, MS TI Integrated payload resource requirements for NASA's gravitational biology research laboratory on the International Space Station SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Meeting Abstract CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Fletcher, LE (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 1 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 366 EP 367 PG 2 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500059 ER PT S AU Weiland, KJ AF Weiland, KJ BE ElGenk, MS TI Progress on the combustion integrated rack component of the Fluids and Combustion Facility SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium ID MICROGRAVITY; DIFFUSION AB The Fluids and Combustion Facility (FCF) is a facility-class payload planned for the International Space Station. It is designed to accommodate a wide variety of investigations encompassing most of the range of microgravity fluid physics and combustion science. The Combustion Integrated Rack component of the FCF is currently scheduled to be launched in 2003 and will operate independently until additional racks of the FCF are launched. The FCF is intended to complete between five and fifteen combustion experiments per year over its planned ten-year lifetime. Combustion areas that may be studied include laminar flames, reaction kinetics, droplet and spray combustion, flame spread, fire and fire suppressants, condensed phase organic fuel combustion, turbulent combustion, soot and polycyclic aromatic hydrocarbons, and flame-synthesized materials. Three different chamber inserts, one each for investigations of droplet, solid fuel, and gaseous fuel combustion, that can accommodate multiple experiments will be used initially so as to maximize the reuse of hardware. The current flight and flight-definition investigations are briefly described. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Weiland, KJ (reprint author), NASA, Glenn Res Ctr, 21000 Brookpk Rd,MS 110-3, Cleveland, OH 44135 USA. NR 18 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 389 EP 397 PG 9 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500064 ER PT S AU Chapek, R Neville, D Wu, MS Hehemann, D Sheredy, W Pearlman, H AF Chapek, R Neville, D Wu, MS Hehemann, D Sheredy, W Pearlman, H BE ElGenk, MS TI The role of natural convection on cool flames and autoignition SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium ID SURFACES AB Slow reaction, cool flames and autoignition are discussed in the context of unstirred, static reactors st terrestrial (1G) and microgravity (mu g) environments. At 1g, conductive heat transport is important when the Rayleigh number (Ra) is less than 600, conduction and convection are important when the Ra ranges from 600 to approximately 10(4) and convection governs when Ra exceeds 104. Except for highly-diluted, weakly exothermic reactions. the Ra for all laboratory-scale, Ig experiments ranges from 10(3)-10(5). Hence, convection and conduction arp important at Ig. Existing models, however, neglect convection, in lieu of conduction, to simplify mathematical formulation. While this assumption is not valid for most Ig cool flames and autoignitions, it is valid at mu g where Ra numbers on the order of 10-100 are easily attained in drop towers and aircraft. Aboard the Space Shuttle and Station, typical Ra's are order 1/10-1. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Chapek, R (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 17 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 408 EP 415 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500067 ER PT S AU Christian, HJ Blakeslee, RJ Goodman, SJ AF Christian, HJ Blakeslee, RJ Goodman, SJ BE ElGenk, MS TI Lightning Imaging Sensor (LIS) for the International Space Station SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB A Lightning Imaging Sensor (LIS) is proposed for flight on the International Space Station (ISS) platform to conduct scientific research in support of the Earth Science Enterprise (ESE). The LIS, identical to one being flown on the Tropical Rainfall Measuring Mission (TRMM), optically detects lightning flashes that occur within its field-of-view during both day and night conditions with storm scale resolution and a high, uniform detection efficiency. The ISS, with an orbital inclination of 51.6 degrees, will extend the measurements from TRMM into the important mid-latitudinal regions of the Earth. The lightning measurements from LIS support important ESE science objectives including increased knowledge of the amount, distribution, and variability of deep convection and natural sources and sinks of key trace gases (e.g., NOX) on a global scale. A space-qualified LIS instrument built as a spare for the TRMM mission is available for integration onto the external truss of the ISS keeping the overall mission costs low. The LIS, which is divided into a sensor assembly and the electronics unit, weighs approximately 20 kg, consumes less than 30 W of power, and generates a telemetry data rate of only 8 kb/s. C1 NASA, George C Marshall Space Flight Ctr, Global Hydrol & Climate Ctr, Huntsville, AL 35812 USA. RP Christian, HJ (reprint author), NASA, George C Marshall Space Flight Ctr, Global Hydrol & Climate Ctr, Huntsville, AL 35812 USA. NR 14 TC 1 Z9 1 U1 1 U2 2 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 423 EP 428 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500069 ER PT S AU Antol, J Jorgensen, CA AF Antol, J Jorgensen, CA BE ElGenk, MS TI The International Space Station Evolution Data Book: An overview and status SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB The evolution and enhancement of the International Space Station (ISS) is currently being planned inwith the on-orbit construction of the "baseline". configuration. Three principal areas have been identified that will contribute to the evolution of ISS: Pre-Planned Program improvement ((PI)-I-3), Utilization &. Commercialization, and Human Exploration and Development of Space (HEDS) missions. The ISS Evolution Strategy, under development by the Spacecraft and Sensors Branch of NASA Langley Research Center, seeks to coordinate the (PI)-I-3 technology development with Commercialization Utilization activities and HEDS advanced mission accommodation to provide synergistic technology developments for all three areas. The focal point of this proposed strategy is the ISS Evolution Data Book (EDB), a tool for aiding the evolution and enhancement of ISS beyond Assembly Complete. This paper will discuss the strategy and provide an overview of the EDB, describing the contents of each section. It will also discuss potential applications of the EDB and present an example Design Reference Mission (DRM). The latest status of the EDB and the plans for completing and enhancing the book will also be summarized. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Antol, J (reprint author), NASA, Langley Res Ctr, Mail Stop 328, Hampton, VA 23681 USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 436 EP 441 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500072 ER PT S AU Landis, GA Sexton, A Abramczyk, R Francz, J Johnson, DB Yang, L Minjares, D Myers, J AF Landis, GA Sexton, A Abramczyk, R Francz, J Johnson, DB Yang, L Minjares, D Myers, J BE ElGenk, MS TI The Photovoltaic Engineering Testbed: Design options and trade-offs SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB The Photovoltaic Engineering Testbed (PET) is a space-exposure test facility to fly on the international Space Station to calibrate, test, and qualify advanced solar cell types in the space environment. The purpose is to reduce the cost of validating neu technologies and bringing them to spaceflight readiness by measuring them in the in-space environment. This paper reviews engineering options considered for flying PET on the international Space Station, and presents the current status of development. C1 NASA, Glenn Res Ctr, Ohio Aerosp Inst, Cleveland, OH 44135 USA. RP Landis, GA (reprint author), NASA, Glenn Res Ctr, Ohio Aerosp Inst, Mailstop 302-1, Cleveland, OH 44135 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 442 EP 447 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500073 ER PT S AU Roithmayr, CM AF Roithmayr, CM BE ElGenk, MS TI International Space Station attitude motion associated with flywheel energy storage SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB Flywheels can exert torque that alters the Station's attitude motion, either intentionally or unintentionally. A design is presented for a once planned experiment to contribute torque for Station attitude control, while storing or discharging energy. Two contingencies are studied: the abrupt stop of one rotor while another rotor continues to spin at high speed, and energy storage performed with one rotor instead of a counter rotating pair. Finally, the possible advantages to attitude control offered by a system of ninety-six flywheels are discussed. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Roithmayr, CM (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 454 EP 459 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500075 ER PT S AU Daelemans, GJ Goldsmith, TC AF Daelemans, GJ Goldsmith, TC BE ElGenk, MS TI Hitchhiker JEM-EF carrier system SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB The NASA/GSFC Shuttle Small Payloads Projects Office (SSPPO) has been studying the feasibility of migrating Hitchhiker customers past present and future to the international Space Station via a "Hitchhiker like" carrier system. SSPPO has been tasked to make the most use of existing hardware and software systems and infrastructure in its study of an ISS based carrier system. This paper summarizes the results of the SSPPO Hitchhiker on International Space Station (ISS) study. Included are a number of "Hitchhiker like" carrier system concepts that take advantage of the various ISS attached payload accommodation sites. Emphasis will be given to a HH concept that attaches to the Japanese Experiment Module - Exposed Facility (JEM-EF). C1 NASA, Goddard Space Flight Ctr, Shuttle Small Payloads Project Off, Greenbelt, MD 20771 USA. RP Daelemans, GJ (reprint author), NASA, Goddard Space Flight Ctr, Shuttle Small Payloads Project Off, Greenbelt, MD 20771 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 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 460 EP 464 PG 5 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500076 ER PT S AU Crouch, MR Carswell, WE Farmer, J Rose, F Tidwell, PH AF Crouch, MR Carswell, WE Farmer, J Rose, F Tidwell, PH BE ElGenk, MS TI Quench Module Insert (QMI) and the Diffusion Module Insert (DMI) furnace development SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium ID SOLIDIFICATION AB The Quench Module Insert (QMI) and the Diffusion Module Insert (DMI) are microgravity furnaces under development at Marshall Space Flight Center. The furnaces are being developed for the first Materials Science Research Rack (MSRR-1) of the Materials Science Research Facility (MSRF), one of the first International Space Station (ISS) scientific payloads. QMI is a Bridgman furnace with quench capability for studying interface behavior during directional solidification of metallic and alloy materials. DMI will be a Bridgman-Stockbarger furnace to study diffusion processes in semiconductors. The design for each insert, both QMI and DMI, is driven by specific science, operations and safety requirements, as well as by constraints arising from resource limitations, such as volume, mass and power. Preliminary QMI analysis and testing indicates that the design meets these requirements. C1 NASA, George C Marshall Space Flight Ctr, Micrograv Sci Applicat Dept, Syst Engn Grp, Huntsville, AL 35812 USA. RP Crouch, MR (reprint author), NASA, George C Marshall Space Flight Ctr, Micrograv Sci Applicat Dept, Syst Engn Grp, Huntsville, AL 35812 USA. NR 9 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 493 EP 498 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500082 ER PT S AU Foster, WM Sutliff, TJ AF Foster, WM Sutliff, TJ BE ElGenk, MS TI An embedded acceleration measurement capability for EXPRESS Rack payloads SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB The International Space Station provides a microgravity environment allowing long duration studies to be made on phenomena masked by the presence of earth's gravitational effects. Studies are also enabled in areas requiring a substantial decrease in steady-state and vibratory acceleration environments. In anticipation microgravity science experiments being targeted for EXPRESS (EXpedite the PRocessing of Experiments to Space Station) Racks, a capability has been provided to simplify and conduct a consistent measurement of the microgravity environment for payloads. The Space Acceleration Measurement System-II (SAMS-II) project has collaborated with the EXPRESS Rack Project to embed an electronics unit within the four EXPRESS Racks equipped with Active Rack Isolation Systems (ARIS). Each SAMS-II unit provides a standardized means for payload acceleration measurements to be acquired. Access to this capability is via front panel connections similar to those of power, data and water cooling provided for EXPRESS payloads. Furthermore, an International Subrack Interface Standard (ISIS) drawer configuration has been developed to provide measurement capability to the non-ARIS equipped EXPRESS Racks, as well as to other ISIS-configured racks, for non-isolated experimental measurement needs. This paper describes the SAMS-II acceleration measurement capabilities provided to ISS users and, in particular, to the EXPRESS Rack community. C1 NASA, John H Glenn Res Ctr Lewis Field, Cleveland, OH 44135 USA. RP Foster, WM (reprint author), NASA, John H Glenn Res Ctr Lewis Field, Cleveland, OH 44135 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 593 EP 598 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500099 ER PT S AU Whorton, MS AF Whorton, MS BE ElGenk, MS TI Microgravity vibration isolation for the International Space Station SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB The International Space Station (ISS) is being envisioned as a laboratory for experiments in numerous microgravity (mu g) science disciplines. Predictions of the ISS acceleration environment indicate that the ambient acceleration levels will exceed levels that can be tolerated by the science experiments. Hence, microgravity vibration isolation systems are being developed to attenuate the accelerations to acceptable levels. While passive isolation systems are beneficial in certain applications, active isolation systems are required to provide attenuation at low frequencies and to mitigate directly induced payload disturbances. To date, three active isolation systems have been successfully tested in the orbital environment. A fourth system called g-LIMIT is currently being developed for the Microgravity Science Glovebox and is manifested for launch on the UF-1 mission. This paper presents an overview of microgravity vibration isolation technology and the g-LIMIT system in particular. C1 NASA, George C Marshall Space Flight Ctr, TD55 Vehicle Control Syst, Huntsville, AL 35812 USA. RP Whorton, MS (reprint author), NASA, George C Marshall Space Flight Ctr, TD55 Vehicle Control Syst, Huntsville, AL 35812 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 605 EP 610 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500101 ER PT S AU DeLombard, R AF DeLombard, R BE ElGenk, MS TI Disturbance of the microgravity environment by experiments SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB The NASA Headquarters Microgravity Research Division sponsors the Microgravity Research Program with science disciplines of biotechnology, combustion science, fluid physics. fundamental physics, and materials science. Two supporting disciplines are multi-discipline science experiments conducted in a glovebox and microgravity; acceleration measurement. Microgravity science experiments are conducted in a variety of ground based and flight facilities, such as, drop towers, parabolic flight aircraft sounding rockets, the space shuttle, and, in the ver) near future. the Interntional Space Station. The microgravity acceleration measurement activities allow the scientist to know the low-gravity conditions under which an experiment was conducted. For most microgravity science experiments, the ideal microgravity environment is comprised of zero acceleration; this "weightless" condition is difficult if not impossible to achieve with real facilities. An experiment is subject to accelerations from (for example equipment, atmospheric, crew members, and vehicle motions. Each experiment or type of experiment has a unique set of susceptibilities to acceleration depending on the experiment design and sample materials. Some of the acceleration disturbances experienced during operation of microgravity science experiments has been caused by other experiments. This paper will describe several instances where microgravity science experiments experienced deleterious accelerations caused by other microgravity science experiments. The paper will also describe the microgravity; acceleration requirements within the international Space Station Program which are imposed on the payloads as well as the vehicle itself. C1 NASA, Glenn Res Ctr, Micrograv Sci Div, Cleveland, OH 44135 USA. RP DeLombard, R (reprint author), NASA, Glenn Res Ctr, Micrograv Sci Div, Cleveland, OH 44135 USA. NR 5 TC 1 Z9 1 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 614 EP 618 PG 5 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500103 ER PT S AU Wald, L Kacpura, T Kershner, D AF Wald, L Kacpura, T Kershner, D BE ElGenk, MS TI An advanced Ka band phased array communication system at commercial frequencies SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB The Glenn Research Center (GRC) Direct Data Distribution (D-3) project will demonstrate an advanced, high-performance communication system that transmits information from a technology payload carried by the Space Shuttle in low-Earth orbit (LEO) to a small receiving terminal on the Earth. The Shuttle-based communications package will utilize a solid-state, Ka-band phased array antenna that electronically steers the 19.05 Ghz RF signal toward a low-cost, tracking ground terminal, thereby providing agile, vibration-free, electronic steering at reduced size and weight with increased reliability. The project will also demonstrate new digital modulation and processing technology that will allow transmission of user/platform data at rates up to 1200 Mbits per second. This capability will enable the management of the substantially increased amounts of data to be collected from the International Space Station (ISS) or other LEO platforms directly to NASA field centers, principal investigators, or into the commercial terrestrial communications network. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Wald, L (reprint author), NASA, Glenn Res Ctr, 2100 Brookpk Rd, Cleveland, OH 44135 USA. NR 2 TC 0 Z9 0 U1 0 U2 1 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 643 EP 648 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500109 ER PT S AU Thompson, RJ Klipstein, WM Seidel, DJ Kohel, J Maleki, L AF Thompson, RJ Klipstein, WM Seidel, DJ Kohel, J Maleki, L BE ElGenk, MS TI The Laser Cooling and Atomic Physics (LCAP) program at JPL SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB In this paper we will present an overview of the present and future of the Laser Cooling and Atomic Physics (LCAP) program in support of NASA's Micro-gravity Fundamental Physics program. We will address the role played by the Jet Propulsion Laboratory in developing the con technologies to support the wide variety of science that we envision will be explored by this program. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Thompson, RJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 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 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 655 EP 657 PG 3 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500111 ER PT S AU Adriaans, MJ Liu, FC Israelsson, UE AF Adriaans, MJ Liu, FC Israelsson, UE BE ElGenk, MS TI Low temperature research on the International Space Station SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium ID HEAT-CAPACITY; LAMBDA-POINT; HELIUM AB The Low Temperature Microgravity Physics Facility (LTMPF) is a state of the art facility for conducting fundamental research in a microgravity environment at low temperatures. LTMPF is a self-contained, reusable, cryogenic facility that will be attached to the Exposed Facility of the Japanese Experiment Module, named Kibo, on the International Space Station (ISS). The first launch of LTMPF is scheduled in June, 2004 and win carry one or more low temperature experiments. Currently, there are six candidate experiments competing for several flight opportunities from the fields of Low Temperature and Condensed Matter Physics, and Gravitational and Relativistic Physics. Science community input has been solicited in the design and development of LTMPF. In order to create a facility that is useful to current and future experimenters, requirements generated by the current flight definition experiments were taken into consideration early in the design phase of LTMPF In addition, inputs from previous, existing and potential future science investigators, as well as industrial partners, were sought in order to design a facility that is modular, adaptable and upgradeable to meet the long-term needs of the science community. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Adriaans, MJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 79-24, Pasadena, CA 91109 USA. NR 2 TC 1 Z9 1 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 658 EP 661 PG 4 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500112 ER PT S AU Jaworske, DA Skowronski, TJ AF Jaworske, DA Skowronski, TJ BE ElGenk, MS TI Portable infrared reflectometer for evaluating emittance SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB Optical methods are frequently used to evaluate the emittance of candidate spacecraft thermal control materials. One new optical method utilizes a portable infrared reflectometer capable of obtaining spectral reflectance of an opaque surface in the range of 2 to 25 microns using a Michelson-Type FTIR interferometer. This miniature interferometer collects many infrared spectra over a short period of time. It also allows the size of the instrument to be small such that spectra can be collected in the laboratory or in the field. Infrared spectra are averaged and integrated with respect to the room temperature black body spectrum to yield emittance at 300 Ii. Integrating with respect to other black body spectra yields emittance values at other temperatures. Absorption bands in the spectra may also be used for chemical species identification. The emittance of several samples was evaluated using this portable infrared reflectometer. an old infrared reflectometer equipped with dual rotating black body cavities, and a bench top thermal vacuum chamber. Samples for evaluation were purposely selected such that a range of emittance values and thermal control material types would be represented, including polished aluminum, Kapton(R), silvered Teflon(R), and the inorganic paint Z-93-P. Results indicate an excellent linear relationship between the room temperature emittance calculated from infrared spectral data and the emittance obtained from the dual rotating black body cavities and thermal vacuum chamber. The prospect of using the infrared spectral data for chemical species identification will also be discussed. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Jaworske, DA (reprint author), NASA, Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. NR 3 TC 5 Z9 5 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 791 EP 796 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500134 ER PT S AU Liewer, PC Mewaldt, RA Ayon, JA Wallace, RA AF Liewer, PC Mewaldt, RA Ayon, JA Wallace, RA BE ElGenk, MS TI NASA's Interstellar Probe Mission SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB NASA's Interstellar Probe will be the first spacecraft designed to explore the nearby interstellar medium and its interaction with our solar system. As envisioned by NASA's Interstellar Probe Science and Technology Definition Team, the spacecraft will be propelled by a solar sail to reach >200 AU in 15 years. Interstellar Probe will investigate how the Sun interacts with its environment and will directly measure the properties and composition of the dust, neutrals and plasma of the local interstellar material which surrounds the solar system. In the mission concept developed in the spring of 1999, a 400-m diameter solar sail accelerates the spacecraft to similar to 15 AU/year, roughly 5 times the speed of Voyager 1&2. The sail is used to first bring the spacecraft in to similar to 0.25 AU to increase the radiation pressure before heading out in the interstellar upwind direction. After jettisoning the sail at similar to 5 AU, the spacecraft coasts to 200-400 AU, exploring the Kuiper Belt, the boundaries of the heliosphere, and the nearby interstellar medium. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Liewer, PC (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 5 TC 16 Z9 16 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 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 911 EP 916 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500152 ER PT S AU Bakes, E AF Bakes, E BE ElGenk, MS TI The science case for in-situ sampling of Kuiper Belt objects SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB This mission may be thought of as merely a first step in an overall initiative to push humanity's exploration beyond the Solar System and into interstellar space. By initiating a mission to the Kuiper Belt, we are poised to extend human space exploration beyond the Sun's family of planets. However, the ultimate goal of the mission is to better understand the formation and transformation of matter originating in the primordial interstellar medium (ISM) and how it relates in chemical composition and evolution to both the solar nebula and the cometary material which bombarded early Earth with prebiotic volatiles. We are planning an initial single in situ sampling mission of a range of classes of organic molecules and dust particles on two Kuiper Belt Objects (KBO) at around 40 AU, a flyby of an appropriate Centaur object (thought to be the evolutionary step between a KBO and a comet), plus we will perform accompanying cruise science to sample free flying interplanetary dust and impinging interstellar dust on the way to the Kuiper Belt. The cruise science will elucidate the broad physical properties of the dust grain population such as the variation of elemental and isotopic composition, size distribution and the variation in their energetic processing with radius from the Sun. In addition, we aim to quantitatively analyse the color variation of the KBO population. The mission will help establish a virtual presence throughout the Solar System and probe deeper into the mysteries of life on Earth and beyond. It also addresses the necessity to develop and utilize revolutionary enabling technologies for missions impossible in prior decades. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Bakes, E (reprint author), NASA, Ames Res Ctr, MS 245-3, Moffett Field, CA 94035 USA. NR 19 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 925 EP 934 PG 10 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500154 ER PT S AU Wallace, RA Ayon, JA AF Wallace, RA Ayon, JA BE ElGenk, MS TI The quest for interstellar exploration SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB NASA strategic planning includes the objective for a set of missions that would begin exploration beyond our solar system. These missions would determine the nature of the interface between our solar system and the local interstellar medium, as well as directly sample the properties of the interstellar medium as an initial step in exploring the nearby Galaxy. Preliminary planning envisions four missions making up this initial quest for exploration. Each of the mission concepts is described in terms of science objectives, mission characteristics, and technology needs. The four missions are: 1) Interstellar Probe (reaching 200 AU in < 15 years via solar sail to explore the heliospheric boundaries and the interstellar medium); 2) Heliosphere Imager & Galactic Gas Sampler (delivery to a low inclination, 1 by 4 AU ecliptic orbit to establish the 3-D structure of the heliosphere and boundaries and sample Galactic material injected into the heliosphere); 3) Outer Heliosphere Radio Imager (16 subsatellites with mother spacecraft delivered to 20 to 30 AU via solar sail to radio-image the boundaries of the heliosphere); and 4) Interstellar Trailblazer (reach 2000 AU in similar to 30 years via advanced solar sail to explore the local interstellar cloud). Technology needs for these missions include solar sail propulsion, advanced instrumentation, autonomous spacecraft operations, advanced power, advanced telecommunication, and long life systems. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Wallace, RA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 6 TC 1 Z9 1 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 935 EP 940 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500155 ER PT S AU Garner, CE Layman, W Gavit, SA Knowles, T AF Garner, CE Layman, W Gavit, SA Knowles, T BE ElGenk, MS TI A solar sail design for a mission to the near-interstellar medium SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB Mission concepts to several hundred AU are under study at NASA Marshall Space Flight Center (MSFC) and NASA Set Propulsion Laboratory (JPL). In order to send a scientific probe beyond the heliopause in a reasonable length of time-no more than 15 yr and preferably 10 yr-the Delta V requirements are approximately 70 km/s. The preliminary results of these mission studies indicate that a solar sail can provide a cumulative Delta V of over 70 km/s to send a probe to a distance of 200 AU from the Sun in under 15 years. This is done by using photon pressure on the sail to shape the trajectory in the inner solar system so that a perihelion of 0.25 AU is achieved. This paper presents the results of a design study for a solar sail to achieve the performance requirements identified in an interstellar probe (ISP) mission study to the near-interstellar medium. The baseline solar sail design for this ISP mission assumes an areal density of 1g/m(2) (including film and structure), and a diameter of similar to 410 m with an 11-m-wide central opening. The sail will be used from 0.25 to 5 AU, where it will be jettisoned. The total spacecraft module mass propelled by the sail is similar to 191 kg. The gores of the sail are folded together and wrapped around a small cylinder. Centripetal force is used for sail deployment. The spacecraft is moved off-center with booms for sail attitude control and thrust vector pointing. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Garner, CE (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 19 TC 4 Z9 4 U1 0 U2 2 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 947 EP 961 PG 15 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500157 ER PT S AU Landis, GA AF Landis, GA BE ElGenk, MS TI Dielectric films for solar and laser-pushed lightsails SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB This project analyzed the potential use of dielectric thin films for solar and laser sails. Such light-pushed sails allow the possibility of fuel-free propulsion in space. This makes possible missions of extremely high delta-V, potentially as high as 30,000 km/sec (0.1c), which is required for a fly-by mission to a nearby star. C1 NASA, Glenn Res Ctr, Ohio Aerosp Inst, Cleveland, OH 44135 USA. RP Landis, GA (reprint author), NASA, Glenn Res Ctr, Ohio Aerosp Inst, Mailstop 302-1, Cleveland, OH 44135 USA. NR 5 TC 2 Z9 2 U1 2 U2 2 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 989 EP 992 PG 4 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500162 ER PT S AU Robertson, GA AF Robertson, GA BE ElGenk, MS TI Search for a correlation between Josephson junctions and gravity SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium ID SUPERCONDUCTORS; FIELD AB Woodward's transient mass shift (TMS) formula has commonality with Modanese's anomalous coupling theory (ACT) and Woodward's capacitor experiment has commonality with Podkletnov's layered superconductor disk experiment. The TMS formula derives a mass fluctuation from a time-varying energy density. The ACT suggests that the essential ingredient for the gravity phenomenon is the presence of strong variations or fluctuations of the Cooper pair density (a time-varying energy density), Woodward's experiment used a small array of capacitors whose energy density was varied by an applied 11 kHz signal. Podkletnov's superconductor disk contained many Josephson junctions (small capacitive like interfaces), which were radiated with a 3-4 MHz signal. This paper formulates a TMS for superconductor Josephson junctions. The equation was compared to the 2% mass change claimed by Podkletnov in his gravity shielding experiments. The TMS is calculated to be 2% for a 2-kg superconductor with an induced total power to the multiple Josephson junctions of about 3.3-watts. A percent mass change equation is then formulated based on the Cavendish balance equation where the superconductor TMS is used for the delta change in mass, An experiment using a Cavendish balance is then discussed. C1 NASA, George C Marshall Space Flight Ctr, Propuls Res Ctr, Space Transportat Directorate, Huntsville, AL 35812 USA. RP Robertson, GA (reprint author), NASA, George C Marshall Space Flight Ctr, Propuls Res Ctr, Space Transportat Directorate, Huntsville, AL 35812 USA. NR 15 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 1026 EP 1031 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500167 ER PT S AU Mondt, JF Nesmith, BJ AF Mondt, JF Nesmith, BJ BE ElGenk, MS TI Future planetary missions potentially requiring radioisotope power systems SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB This paper summarizes the potential Radioisotope Power System, (RPS), technology requirements for future missions being planned for NASA's Solar System Exploration (SSE) theme. Many missions to the outer planets (Jupiter and beyond) require completion of the work on advanced radioisotope power systems (ARPS) now underway in NASA's Deep Space Systems Technology Program. The power levels for the ARPS can be divided into four classes. Forty to one hundred milliwatt-class provides both thermal and electric power for small in situ science laboratories on the surface of bodies in the solar system. One to two watt class for surface and aerobot science laboratories. Ten to twenty-watt class for micro satellites in orbit, surface science stations and aerobots. One hundred to two hundred watt class for orbiter science spacecraft, for drilling core samples, for powering subsurface hydrobots and cryobots on accessible bodies and for data handling and communicating data from small orbiters, surface laboratories, aerobots and hydrobots back to Earth. Using the most optimistic solar-based power system instead of advanced RPSs pushes the launch masses of these missions beyond the capability of affordable launch vehicles. Advanced RPS is also favored over solar power for obtaining comet samples on extended-duration missions. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Mondt, JF (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 2 TC 1 Z9 1 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 1169 EP 1174 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500189 ER PT S AU Houts, M Bonometti, J Morton, J Hrbud, I Bitteker, L Van Dyke, M Godfroy, T Pedersen, K Dobson, C Patton, B Martin, J Chakrabarti, S AF Houts, M Bonometti, J Morton, J Hrbud, I Bitteker, L Van Dyke, M Godfroy, T Pedersen, K Dobson, C Patton, B Martin, J Chakrabarti, S BE ElGenk, MS TI Utilizing fission technology to enable rapid and affordable access to any point in the solar system SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB Fission technology can enable rapid, affordable access to any point in the solar system. potential fission-based transportation options include bimodal nuclear thermal rockets, high specific energy propulsion systems, and pulsed fission propulsion systems. In-space propellant re-supply enhances the effective performance of all systems, but requires significant infrastructure development. Safe, timely, affordable utilization of first-generation space fission propulsion systems will enable the development of more advanced systems. First generation space systems will build on over 45 years of US and international space fission system technology development to minimize cost. C1 NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Houts, M (reprint author), NASA, George C Marshall Space Flight Ctr, TD40, Huntsville, AL 35812 USA. NR 9 TC 3 Z9 3 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 1182 EP 1187 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500191 ER PT S AU Godfroy, T Van Dyke, M Dickens, R Pedersen, K Lenard, R Houts, M AF Godfroy, T Van Dyke, M Dickens, R Pedersen, K Lenard, R Houts, M BE ElGenk, MS TI Realistic development and testing of fission systems at a non-nuclear testing facility SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB The use of resistance heaters to simulate heat from fission allows extensive development of fission systems to he performed in non-nuclear test facilities, saving time and money. Resistance heated tests on a module has been performed at the Marshall Space Flight Center in the Propellant Energy Source Testbed(PEST). This paper discusses the experimental facilities and equipment used for performing resistance heated tests. Recommendations are made for improving non-nuclear test facilities and equipment for simulated testing of nuclear systems. C1 NASA, George C Marshall Space Flight Ctr, Prop Res Ctr, Huntsville, AL 35812 USA. RP Godfroy, T (reprint author), NASA, George C Marshall Space Flight Ctr, Prop Res Ctr, TD 40, Huntsville, AL 35812 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 1208 EP 1210 PG 3 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500195 ER PT S AU Van Dyke, M Godfroy, T Houts, M Dickens, R Dobson, C Pederson, K Reid, B Sena, JT AF Van Dyke, M Godfroy, T Houts, M Dickens, R Dobson, C Pederson, K Reid, B Sena, JT BE ElGenk, MS TI Results of a first generation least expensive approach to fission module tests: Non-nuclear testing of a fission system SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB The use of resistance heaters to simulate heat from fission allows extensive development of fission systems to be performed in non-nuclear test facilities, saving time and money. Resistance heated tests on the Module Unfueled Thermal-hydraulic Test (MUTT) article has been performed at the Marshall Space Flight Center. This paper discusses the results of these experiments to date, and describes the additional testing that will be performed. Recommendations related to the design of testable space fission power and propulsion systems are made. C1 NASA, George C Marshall Space Flight Ctr, Prop Res Ctr, Huntsville, AL 35812 USA. RP Van Dyke, M (reprint author), NASA, George C Marshall Space Flight Ctr, Prop Res Ctr, TD 40, Huntsville, AL 35812 USA. NR 6 TC 5 Z9 5 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 1211 EP 1217 PG 7 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500196 ER PT S AU Bonometti, JA Morton, PJ Schmidt, GR AF Bonometti, JA Morton, PJ Schmidt, GR BE ElGenk, MS TI External pulsed plasma propulsion and its potential for the near future SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB This paper examines External Pulsed Plasma Propulsion (EPPP), a propulsion concept that derives its thrust from plasma waves generated from a series of small, supercritical fission/fusion pulses behind an object in space. For spacecraft applications, a momentum transfer mechanism translates the intense plasma nave energy into a vehicle acceleration that is tolerable to the rest of the spacecraft and its crew. This propulsion concept offers extremely high performance in terms of both specific impulse (Isp) and thrust-to-weight ratio. something that other concepts based on available technology cannot do. The political concerns that suspended work on this type of system (i.e. termination of Project ORION) may non not be as insurmountable as they were in 1965. The appeal of EPPP stems from its relatively low cost and reusability, fast interplanetary transit times, safety and reliability, and independence from major technological breakthroughs. In fact a first generation EPPP system based on modern-day; technology (i.e., GABRIEL - an evolutionary framework of EPPP concepts) may very well be the only form of propulsion that could realistically be developed to perform ambitious human exploration beyond Mars in the 21st century. It could also provide the most effective approach for deterrence against collision between earth and small planetary objects - a growing concern over recent years. C1 NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Bonometti, JA (reprint author), NASA, George C Marshall Space Flight Ctr, TD40, Huntsville, AL 35812 USA. NR 8 TC 0 Z9 0 U1 0 U2 1 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 1236 EP 1241 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500200 ER PT S AU Thieme, LG Qiu, SG White, MA AF Thieme, LG Qiu, SG White, MA BE ElGenk, MS TI Technology development for a stirling radioisotope power system SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB NASA Glenn Research Center and the Department of Energy are developing a Stirling convertor for an advanced radioisotope power system to provide spacecraft on-board electric Fewer for NASA deep space missions. NASA Glenn is addressing key technology issues through the use of two NASA Phase II SBIRs with Stirling Technology Company (STC) of Kennewick, WA. Under the first SBIR, STC demonstrated a synchronous connection of two thermodynamically independent free-piston Stirling convertors and a 40 to 50 fold reduction in vibrations compared to an unbalanced convertor. The second SBIR is for the development of an Adaptive Vibration Reduction System (AVRS) that will essentially eliminate vibrations over the mission lifetime, even in the unlikely event of a failed convertor. This paper presents the status and results for these two SBIR projects and also discusses a new NASA Glenn in-house project to provide supporting technology for the overall Stirling radioisotope power system development. Tasks for this new effort include convertor performance verification, controls development, heater head structural life assessment, magnet characterization and thermal aging tests, FEA anal)sis for a lightweight alternator concept, and demonstration of convertor operation under launch and orbit transfer load conditions. C1 NASA, John H Glenn Res Ctr, Cleveland, OH 44135 USA. RP Thieme, LG (reprint author), NASA, John H Glenn Res Ctr, Lewis Field,MS 301-2,21000 Brookpk Rd, Cleveland, OH 44135 USA. NR 10 TC 3 Z9 3 U1 0 U2 1 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 1260 EP 1265 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500203 ER PT S AU Mason, LS AF Mason, LS BE ElGenk, MS TI Solar Stirling for deep space applications SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB A study was performed to quantify the performance of solar thermal power systems for deep space planetary missions. The study incorporated projected advances in solar concentrator and energy conversion technologies. These technologies included inflatable structures, lightweight primary concentrators, high efficiency secondary concentrators, and high efficiency Stirling convertors. Analyses were performed to determine the mass and deployed area of multi-hundred watt solar thermal power systems for missions out to 40 astronomical units. Emphasis was given to system optimization, parametric sensitivity analyses, and concentrator configuration comparisons. The results indicated that solar thermal power systems are a competitive alternative to radioisotope systems out to 10 astronomical units without the cost or safety implications associated with nuclear sources. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Mason, LS (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 7 TC 1 Z9 1 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 1272 EP 1277 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500205 ER PT S AU Schreiber, JG AF Schreiber, JG BE ElGenk, MS TI A deep space power system option based on synergistic power conversion technologies SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB Deep space science missions have typically used radioisotope thermaoelectric generator (RTG) power systems. The RTG power system has proven itself to be a rugged and highly reliable power system over many missions, however the thermal-to-electric conversion technology used was approximately 5% efficient. While the relatively low efficiency has some benefits in terms of system integration, there are compelling reasons why a more efficient conversion system should be pursued. The cost savings alone that are available as a result of the reduced isotope inventory are significant. The Advanced Radioisotope Power System (ARPS) project was established to fulfill this goal. Although it was not part of the ARPS project, Stirling conversion technology was being demonstrated with a low level of funding by both NASA and DOE. A power system with Stirling convertors, although intended for use with an isotope heat source, can be combined with other advanced technologies to provide a novel power system for deep space missions. An inflatable primary concentrator would be used in combination with a refractive secondary concentrator (RSC) as the heat source to power the system. The inflatable technology as a structure has made great progress for a variety of potential applications such as communications reflectors, radiators and solar arrays. The RSC has been pursued for use in solar thermal propulsion applications, and it's unique properties allow some advantageous system trades to be made. The power system proposed would completely eliminate the isotope heat source and could potentially provide power for science missions to planets as distant as Uranus. This paper will present the background and developmental status of the technologies and wilt then describe the power system being proposed. C1 NASA, John H Glenn Res Ctr Lewis Field, Cleveland, OH 44135 USA. RP Schreiber, JG (reprint author), NASA, John H Glenn Res Ctr Lewis Field, MS 301-2,21000 Brookpk Rd, Cleveland, OH 44135 USA. NR 11 TC 0 Z9 0 U1 1 U2 2 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 1335 EP 1340 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500214 ER PT S AU Gavert, RB AF Gavert, RB BE ElGenk, MS TI Five major NASA health and safety issues SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB The goal has been set to establish NASA as number one in safety in the nation. This includes Systems and Mission Safety as well as Occupational Safety for all NASA employees and contractors on and off the job. There are five major health and safety issues important in the pursuit of being number one and they are: (1) Radiation (2) Hearing (3) Habitability/Toxicology (4) Extravehicular Activity (EVA) (5) Stress. The issues have features of accumulated injury since NASA's future missions involve long time human presence in space i.e., International Space Station operations and Mars missions. The objective of this paper is to discuss these five issues in terms of controlling risks and enhancing health and safety. Safety metrics are discussed in terms of the overall goal of NASA to be number one in safety. C1 NASA Headquarters, Off Hth Affairs, Washington, DC USA. RP Gavert, RB (reprint author), NASA Headquarters, Off Hth Affairs, 300 E St SW, Washington, DC USA. NR 8 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 1341 EP 1346 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500215 ER PT S AU Ryan, MA Shields, VB Cortez, RH Lara, L Homer, ML Williams, RM AF Ryan, MA Shields, VB Cortez, RH Lara, L Homer, ML Williams, RM BE ElGenk, MS TI Lifetimes of AMTEC electrodes: Molybdenum, rhodium-tungsten, and titanium nitride SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium ID TRANSPORT; ALUMINA AB The lifetime of three types of AMTEC electrodes is predicted from the rats of grain growth in the electrode. Grain size is related to electrode performance, allowing performance to be correlated with grain growth rate. The rate of growth depends on physical characteristics of each material, including the rates of surface self-diffusion and molecule mobility along grain boundaries. Grain growth rates for molybdenum, rhodium-tungsten and titanium nitride electrodes have been determined experimentally and fit to models in order to predict operating lifetimes of AMTEC electrodes. For lifetimes of 10 years or more, RhXW electrodes may be used at any operating temperature supportable by the electrolyte TIN electrodes may be used in AMTEC cells only at operating temperatures under 1150 K: and Mo may be used only below 1100 K. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Ryan, MA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 13 TC 8 Z9 8 U1 0 U2 2 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 1377 EP 1382 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500220 ER PT S AU Williams, RM Homer, ML Kulleck, J Lara, L Kisor, AK Cortez, RH Shields, VB Ryan, MA AF Williams, RM Homer, ML Kulleck, J Lara, L Kisor, AK Cortez, RH Shields, VB Ryan, MA BE ElGenk, MS TI Thermal stability of beta"-alumina solid electrolyte under AMTEC operating conditions SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium ID INTERFACIAL IMPEDANCE; KINETICS; SODIUM; DEPENDENCE; TRANSPORT AB A critical component of alkali metal thermal-to electric converter (AMTEC) devices for long duration space missions is the sodium beta"-alumina solid electrolyte ceramic (BASE), for which there exists no substitute. The major phase in this ceramic. sodium beta"- alumina shows no evidence of thermal decomposition in AMTEC environments including clean liquid sodium and low pressure sodium gas, at temperatures below 1173K, or in vacuum below 1273K. This paper presents additional results of ionic conductivity and exchange current studies in sodium exposure test cells (SETCs) to characterize the changes occurring in BASE below 1273K in low pressure sodium vapor. Also presented an additional annealing studies to characterize the kinetics of processes occurring in in the BASE ceramic in the AMTEC operating regime. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Williams, RM (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 16 TC 1 Z9 1 U1 0 U2 1 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 1408 EP 1411 PG 4 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500224 ER PT S AU Emrich, WJ Kammash, T AF Emrich, WJ Kammash, T BE ElGenk, MS TI Performance optimization of the Gasdynamic Mirror propulsion system SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB Nuclear fusion appears to be a most promising concept for producing extremely high specific impulse rocket engines. Engines such as these would effectively open up the solar system to human exploration and would virtually eliminate launch window restrictions. A preliminary vehicle sizing and mission study was performed based on the conceptual design of a Gasdynamic Mirror (GDM) fusion propulsion system. This study indicated that the potential specific impulse for this engine is approximately 142,000 sec; with about 22,100 N of thrust using a deuterium-tritium fuel cycle. The engine weight inclusive of the power conversion system was optimized around an allowable engine mass of 1500 Mg assuming advanced superconducting magnets and a Field Reversed Configuration (FRC) end plug at the mirrors. The vehicle habitat, lander, and structural weights are based on a NASA Mars mission study which assumes the use of nuclear thermal propulsion(1) Several manned missions to various planets were analyzed to determine fuel requirements and launch windows. For all fusion propulsion cases studied, the fuel weight remained a minor component of the total system weight regardless of when the missions commenced. In other words, the use of fusion propulsion virtually eliminates all mission window constraints and effectively allows unlimited manned exploration of the entire solar system. It also mitigates the need to have a targe space infrastructure which would be required to support the transfer of massive amounts of fuel and supplies to lower a performing spacecraft. C1 NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Emrich, WJ (reprint author), NASA, George C Marshall Space Flight Ctr, Bldg 4666,Room 370, Huntsville, AL 35812 USA. NR 3 TC 1 Z9 1 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 1420 EP 1424 PG 5 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500226 ER PT S AU Fleurial, JP Snyder, GJ Patel, J Herman, JA Caillat, T Nesmith, B Kolawa, EA AF Fleurial, JP Snyder, GJ Patel, J Herman, JA Caillat, T Nesmith, B Kolawa, EA BE ElGenk, MS TI Miniaturized radioisotope solid state power sources SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB Electrical power requirements for the next generation of deep space missions cover a wide range from the kilowatt to the milliwatt. Several of these missions call for the development of compact, low weight, long life, rugged power sources capable of delivering a few milliwatts up to a couple of watts while operating in harsh environments. Advanced solid state thermoelectric microdevices combined with radioisotope heat sources and energy storage devices such as capacitors are ideally suited far these applications. By making use of macroscopic film technology, microgenerators operating across relatively small temperature differences can he conceptualized for a variety of high heat flux or low heat flux heat source configurations. Moreover, by shrinking the size of the thermoelements and increasing their number to several thousands in a single structure, these devices can generate high voltages even at low power outputs that are more compatible with electronic components. Because the miniaturization of state-of-the-art thermoelectric module technology based on Bi2Te3 alloys is limited due to mechanical and manufacturing constraints, we are developing novel microdevices using integrated-circuit type fabrication processes, electrochemical deposition techniques and high thermal conductivity substrate materials. One power source concept is based on several thermoelectric microgenerator modules that are tightly integrated with a 1.1W Radioisotope Heater Unit. Such a system could deliver up to 50mW of electrical power in a small lightweight package of approximately 50 to 60g and 30cm(3). An even higher degree of miniaturization and high specific power values (mW/mm(3)) can he obtained when considering the potential use of radioisotope materials for an alpha-voltaic or a hybrid thermoelectric/alpha-voltaic power source. Some of the technical challenges associated with these concepts are discussed in this paper. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Fleurial, JP (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 277-207, Pasadena, CA 91109 USA. RI Snyder, G. Jeffrey/E-4453-2011; Snyder, G/I-2263-2015 OI Snyder, G. Jeffrey/0000-0003-1414-8682; NR 19 TC 3 Z9 3 U1 0 U2 2 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 1500 EP 1507 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500238 ER PT S AU Caillat, T Borshchevsky, A Snyder, J Fleurial, JP AF Caillat, T Borshchevsky, A Snyder, J Fleurial, JP BE ElGenk, MS TI High efficiency segmented thermoelectric unicouples SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB A new version of a segmented thermoelectric unicouple incorporating advanced thermoelectric materials with superior thermoelectric figures of merit has been recently proposed and is currently being developed at the Jet Propulsion Laboratory. The advanced segmented unicouple currently being developed would operate over a 300 to 975K temperature difference and the predicted efficiency is about 15%. There has been recently a growing interest for thermoelectric power generation using various waste heat sources such as the combustion of solid waste, geothermal energy, power plants, automobile, and other industrial heat-generating processes. Hot-side temperatures ranging from 370 to 1000K have been reported in the literature for some of these potential applications. Although the segmented unicouple currently being developed is expected to operate at a hot-side temperature of 975K, the segmentation can be adjusted to accommodate various hot-side temperatures depending on the specific application. This paper illustrates various segmentation options corresponding to hot-side temperatures ranging from 675 to 975K. The predicted efficiency and characteristics of the corresponding unicouples are described. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Caillat, T (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RI Snyder, G. Jeffrey/E-4453-2011 OI Snyder, G. Jeffrey/0000-0003-1414-8682 NR 6 TC 25 Z9 25 U1 0 U2 4 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 1508 EP 1512 PG 5 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500239 ER PT S AU Lenard, RX Lipinski, RJ AF Lenard, RX Lipinski, RJ BE ElGenk, MS TI Interstellar rendezvous missions employing fission propulsion systems SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB There has been a conventionally held nostrum that fission system specific power and energy content is insufficient to provide the requisite high accelerations and velocities to enable interstellar rendezvous missions within a reasonable fraction of a human lifetime. As a consequence, an forms of alternative mechanisms that are not yet, and may never be technologically feasible, have been proposed, including laser light sails, fusion and antimatter propulsion systems. In previous efforts [Lenard and Lipinski, 1999] the authors developed an architecture that employs fission power to propel two different concepts: one. an unmanned probe. the other a crewed vehicle to Alpha Centauri within mission times of 47 to 60 years. The first portion of this paper discusses employing a variant of the "Forward Resupply Runway" utilizing fission systems to enable both high accelerations and high final velocities necessary for this type of travel. The authors argue that such an architecture, while expensive, is considerably less expensive and technologically risky than other technologically advanced concepts, and, further, provides the ability to explore near-Earth stellar systems out to distances of 8 light years or so. This enables the ability to establish independent human societies which can later expand the domain of human exploration in roughly eight light-year increments even presuming that no further ph,sics or technology breakthroughs or advances occur. In the second portion of the paper, a technology requirement assessment is performed. The authors argue that reasonable to extensive extensions to known technology could enable this revolutionary capability. C1 George C Marshall Space Flight Ctr, Adv Prop Technol Directorate, Huntsville, AL 35812 USA. RP Lenard, RX (reprint author), George C Marshall Space Flight Ctr, Adv Prop Technol Directorate, TD-40, Huntsville, AL 35812 USA. NR 6 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 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 1544 EP 1555 PG 12 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500245 ER PT S AU Polk, J Tikhonov, V Semenikhin, S Kim, V AF Polk, J Tikhonov, V Semenikhin, S Kim, V BE ElGenk, MS TI Cathode temperature reduction by addition of barium in high power lithium plasma thrusters SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium AB Lithium Lorentz Force Accelerators (LFA's) are capable of processing very high power levels and are therefore applicable to a wide range of challenging missions. The cathode in these coaxial discharge devices operates at a very high temperature to supply the required current and appears to be the primary life-limiting component. One potential method for lowering the cathode temperature is to add a small amount of barium to the lithium propellant. An analytical model of the surface kinetics of this system shows that a relatively small partial pressure of barium can dramatically reduce the cathode operating temperature. Preliminary experiments with a lithium-fuelled thruster demonstrated temperature reductions of 350-400 K with barium addition. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Polk, J (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 10 TC 2 Z9 2 U1 1 U2 2 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 1556 EP 1563 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500246 ER PT S AU Best, F AF Best, F BE ElGenk, MS TI Texas A&M vortex type phase separator SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM, PTS 1 AND 2 SE AIP CONFERENCE PROCEEDINGS LA English DT Meeting Abstract CT Space Technology and Applications International Forum (STAIF-2000) CY JAN 30-FEB 03, 2000 CL ALBUQUERQUE, NM SP Boeing Co, Lockheed Martin Corp, NASA, US DOE, Sandia Natl Lab, Los Almos Natl Lab, Amer Astronaut Soc, Amer Inst Chem Engineers, Div Heat Transfer & Energy Convers, Amer Inst Aeronaut & Astronaut, Natl Sect, Amer inst Aeronaut & Astronaut, Local Sect, Amer Nucl Soc, Trinity Sect, Amer Soc Mech Engineers, Div Nucl Engn, Amer Soc Mech Engineers, Div Heat Transfer, Inst Elect & Electr Engineers Inc, Nucl & Plasma Sci Soc, Int Astronaut Federat, NASA, Natl Space Grant Coll & Fellowship Program, New Mexico Space grant Consortium C1 Texas A&M Univ, Dept Nucl Engn, NASA, Commercial Ctr Space Power, College Stn, TX 77843 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-919-X J9 AIP CONF PROC PY 2000 VL 504 BP 1587 EP 1587 PG 1 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BP88C UT WOS:000086475500253 ER PT S AU Lanzerotti, LJ Sayres, DS Medford, LV Maclennan, CG Lepping, RP Szabo, A AF Lanzerotti, LJ Sayres, DS Medford, LV Maclennan, CG Lepping, RP Szabo, A BE Rostoker, G TI Response of large-scale geoelectric fields to identified interplanetary disturbances and the equatorial ring current SO SPACE WEATHER: PHYSICS AND APPLICATIONS SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT D0 5 Symposium of COSPAR Scientific Commission D Held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Comm Space Res, Sci Comm Solar Terr Phys, Int Union Geodesy & Geophys, Int Assoc Geomagnetism & Aeron ID OCEANIC DISTANCES; SPACE WEATHER; GEOPOTENTIALS; SYSTEMS; STORMS AB The changes in the geoelectric field G (mV/km) between Hawaii and Guam are examined during four small geomagnetic disturbances in 1995 and 1996 when interplanetary magnetic field and plasma data are available to provide the interplanetary integrated Poynting flux epsilon input to the magnetosphere. In agreement with a previous study of the geoelectric field at the time of the encounter of an interplanetary magnetic cloud event with the magnetosphere, we conclude that the maximum geoelectric field across this near-equatorial route can be estimated to better than about 50% if the interplanetary conditions are known by using the expression G = 2.3 x 10(-11) epsilon(W). (C) 2000 COSPAR. Published by Elsevier Science Ltd. C1 Bell Labs, Lucent Technol, Murray Hill, NJ 07974 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Lanzerotti, LJ (reprint author), Bell Labs, Lucent Technol, 600 Mt Ave, Murray Hill, NJ 07974 USA. NR 21 TC 3 Z9 3 U1 0 U2 0 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2000 VL 26 IS 1 BP 21 EP 26 DI 10.1016/S0273-1177(99)01021-2 PG 6 WC Astronomy & Astrophysics; Meteorology & Atmospheric Sciences SC Astronomy & Astrophysics; Meteorology & Atmospheric Sciences GA BP89M UT WOS:000086534000003 ER PT S AU Friedel, RHW Reeves, G Belian, D Cayton, T Mouikis, C Korth, A Blake, B Fennell, J Selesnick, R Baker, D Onsager, T Kanekal, S AF Friedel, RHW Reeves, G Belian, D Cayton, T Mouikis, C Korth, A Blake, B Fennell, J Selesnick, R Baker, D Onsager, T Kanekal, S BE Rostoker, G TI A multi-spacecraft synthesis of relativistic electrons in the inner magnetosphere using LANL, GOES, GPS, SAMPEX, HEO and polar SO SPACE WEATHER: PHYSICS AND APPLICATIONS SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT D0 5 Symposium of COSPAR Scientific Commission D Held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Comm Space Res, Sci Comm Solar Terr Phys, Int Union Geodesy & Geophys, Int Assoc Geomagnetism & Aeron ID RADIATION BELT; PARTICLE; SOLAR AB One of the Brussels Radiation Belt Workshop recommendations was the establishment of a near-real-time data driven model of the inner magnetospheric energetic particle population (L < 8). Although the "ideal" missions and data sets for such a model do not exist at present, more spacecraft than ever before are currently sampling the inner magnetosphere. We attempt here in a case study of the January 10, 1997 magnetic cloud event to construct such a model with the energetic electron data available from 5 geosynchronous and 5 elliptically orbiting satellites. We examine the constraints and difficulties of putting together a large number of datasets which are measured near-simultaneously at very different locations in the inner magnetosphere. First results indicate that we can achieve a time resolution of about 3 hours for a given "snapshot" of the inner magnetosphere, and that large azimuthal asymmetries of the energetic electron population can be observed during large storms. (C) 2000 COSPAR. Published by Elsevier Science Ltd. C1 Univ Calif Los Alamos Natl Lab, Los Alamos, NM 87545 USA. Max Planck Inst Aeron, Katlenburg Lindau, Germany. Aerospace Corp, El Segundo, CA 90245 USA. LASP, Boulder, CO USA. NOAA, SEC, Boulder, CO USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Friedel, RHW (reprint author), Univ Calif Los Alamos Natl Lab, POB 1663, Los Alamos, NM 87545 USA. RI Friedel, Reiner/D-1410-2012; Reeves, Geoffrey/E-8101-2011 OI Friedel, Reiner/0000-0002-5228-0281; Reeves, Geoffrey/0000-0002-7985-8098 NR 12 TC 10 Z9 12 U1 0 U2 1 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2000 VL 26 IS 1 BP 93 EP 98 DI 10.1016/S0273-1177(99)01031-5 PG 6 WC Astronomy & Astrophysics; Meteorology & Atmospheric Sciences SC Astronomy & Astrophysics; Meteorology & Atmospheric Sciences GA BP89M UT WOS:000086534000013 ER PT S AU Owens, JK Niehuss, KO Vaughan, WW Shea, MA AF Owens, JK Niehuss, KO Vaughan, WW Shea, MA BE Rostoker, G TI NASA Marshall engineering thermosphere model - 1999 version (MET-99) and implications for satellite lifetime predictions SO SPACE WEATHER: PHYSICS AND APPLICATIONS SE ADVANCES IN SPACE RESEARCH-SERIES LA English DT Review CT D0 5 Symposium of COSPAR Scientific Commission D Held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Comm Space Res, Sci Comm Solar Terr Phys, Int Union Geodesy & Geophys, Int Assoc Geomagnetism & Aeron AB The use of thermospheric density models in the prediction of atmospheric drag (the major perturbation for orbiting spacecraft) is of great importance. Issues associated with these predictions include lifetime estimates, orbit determination and tracking, attitude dynamics, and re-entry prediction. Logistics planning through attitude control requirements and re-boost planning are also influenced by future orbital altitude density estimates. The MET-99 model and its predecessors were developed to provide the inputs needed to address these issues. The sensitivity of the future estimation of solar activity, and thus thermospheric density and the prediction of a satellite's lifetime, to the selection of Solar Cycle 23 minimum other than the conventionally identified mathematical minimum is shown. This can produce about 25 percent error in predicted satellite lifetime for a typical low Earth orbit example. (C) 2000 COSPAR. Published by Elsevier Science Ltd. C1 NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. Univ Alabama, Huntsville, AL 35899 USA. USAF, Res Lab, Bedford, MA 01731 USA. RP Owens, JK (reprint author), NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. NR 10 TC 6 Z9 6 U1 0 U2 0 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES-SERIES PY 2000 VL 26 IS 1 BP 157 EP 162 DI 10.1016/S0273-1177(99)01042-X PG 6 WC Astronomy & Astrophysics; Meteorology & Atmospheric Sciences SC Astronomy & Astrophysics; Meteorology & Atmospheric Sciences GA BP89M UT WOS:000086534000024 ER PT S AU Vassiliadis, D Klimas, AJ Valdivia, JA Baker, DN AF Vassiliadis, D Klimas, AJ Valdivia, JA Baker, DN BE Rostoker, G TI The nonlinear dynamics of space weather SO SPACE WEATHER: PHYSICS AND APPLICATIONS SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT D0 5 Symposium of COSPAR Scientific Commission D Held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Comm Space Res, Sci Comm Solar Terr Phys, Int Union Geodesy & Geophys, Int Assoc Geomagnetism & Aeron ID DATA-DERIVED ANALOGS; MAGNETOSPHERIC DYNAMICS; GEOMAGNETIC-ACTIVITY; TIME-SERIES; PREDICTION; STORMS; DST; INDEXES; MODELS; CHAOS AB Studies of the nonlinear magnetospheric dynamics have led to several directions useful in understanding space physics processes, in particular those related to magnetospheric currents, and making space weather forecasts possible. Four such directions are identified: (a) empirical time series prediction with nonlinear autoregressive moving-average (ARMA) models, for which an example is given in terms of a geosynchronous electron flux index model. (b) Measurement of physical properties of the currents from the coefficients of the ARMA models, such as characteristic time scales and coupling strengths. Using a D-st index model we measure the ring current decay time as a function of storm phase and activity, and identify new oscillation time scales correlating with the substorm injection activity. (c) Spatiotemporal nonlinear modeling predicts the amplitude and location of the disturbance as a function of space, as well as its time evolution. An example is given in terms of predicting the longitudinal and temporal profile of midlatitude geomagnetic disturbances. (d) Nonlinear dynamical models can be coupled to other physical or empirical approaches to build comprehensive space weather models. SWIFT, an ionospheric space weather model, is discussed as an example. Other applications of nonlinear dynamics are briefly discussed. (C) 2000 COSPAR. Published by Elsevier Science Ltd. C1 NASA, Goddard Space Flight Ctr, Univ Space Res Assoc, Greenbelt, MD 20771 USA. NASA, Goddard Space Flight Ctr, Extraterr Phys Lab, Greenbelt, MD 20771 USA. NASA, Goddard Space Flight Ctr, Natl Res Council, Greenbelt, MD 20771 USA. Univ Colorado, Atmospher & Space Phys Lab, Boulder, CO 80309 USA. RP Vassiliadis, D (reprint author), NASA, Goddard Space Flight Ctr, Univ Space Res Assoc, Code 692, Greenbelt, MD 20771 USA. RI Valdivia, Juan/A-3631-2008 OI Valdivia, Juan/0000-0003-3381-9904 NR 25 TC 16 Z9 16 U1 0 U2 2 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2000 VL 26 IS 1 BP 197 EP 207 DI 10.1016/S0273-1177(99)01050-9 PG 11 WC Astronomy & Astrophysics; Meteorology & Atmospheric Sciences SC Astronomy & Astrophysics; Meteorology & Atmospheric Sciences GA BP89M UT WOS:000086534000032 ER PT S AU Newman, LK Noonan, PJ Gramling, CJ AF Newman, LK Noonan, PJ Gramling, CJ BE Kluever, CA Neta, B Hall, CD Hanson, JM TI Ground system support of an onboard navigation system: Implementation and operations experiences SO SPACEFLIGHT MECHANICS 2000, VOL 105, PTS I AND II SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 10th Space Flight Mechanics Meeting CY JAN 23-26, 2000 CL CLEARWATER, FL SP Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut AB NASA's Earth Observing System Terra spacecraft utilizes an onboard orbit determination system called the Tracking and Data Relay Satellite System (TDRSS) Onboard Navigation System (TONS). TONS uses 1-way forward S-Band Doppler data measured from the TDRSS communications signal to determine the spacecraft trajectory in real time. This state vector is then used for a variety of purposes, both onboard and on the ground. On the ground, the vector is used by Flight Dynamics to model the future state of the spacecraft and to provide upload tables and science planning aids. The state is also propagated onboard and used in the attitude determination and control software to acquire the communications signal and to point the high gain antenna. This paper discusses issues which have arisen during the implementation of TONS on Terra and the solutions put in place to address them. Implementation differences between the onboard flight software and the ground software, automation of the ground support system, and accomodation of input data from external sources introduce challenges into many aspects of each of the TONS implementation processes. Lessons learned from the Terra TONS implementation indicate the need for a ground system to analyze the performance of any onboard navigation system, aid other mission planners in anticipating impacts on the ground system imposed by any onboard navigation system implementation, and provide some suggestions for methods of addressing those issues. C1 NASA, Goddard Space Flight Ctr, Flight Dynam Anal Branch, Greenbelt, MD 20771 USA. RP Newman, LK (reprint author), NASA, Goddard Space Flight Ctr, Flight Dynam Anal Branch, Code 572, 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 0-87703-470-2 J9 ADV ASTRONAUT SCI PY 2000 VL 105 BP 337 EP 350 PN 1&2 PG 14 WC Engineering, Aerospace SC Engineering GA BQ99H UT WOS:000165304900021 ER PT S AU Cox, EL AF Cox, EL BE Kluever, CA Neta, B Hall, CD Hanson, JM TI Landsat-7 ascent planning SO SPACEFLIGHT MECHANICS 2000, VOL 105, PTS I AND II SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 10th Space Flight Mechanics Meeting CY JAN 23-26, 2000 CL CLEARWATER, FL SP Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut AB The Landsat-7 spacecraft is in a Sun-synchronous, frozen polar orbit maintaining a daylight equator crossing and longitudinal drift pattern conducive for Earth imaging. The paper discusses several aspects of the Landsat-7 mission requirements with an emphasis on launch window definition, launch vehicle insertion dispersions, and mission constraint definition. The approach utilized to construct the mission ascent plan will discuss maneuver size and execution required for eventual rendezvous with the Landsat-5 spacecraft. Trajectory design will emphasize maneuver targeting analysis necessary for achieving the final Landsat-7 frozen orbit and groundtrack drift pattern. Final mission orbit results indicate frozen orbit stability and longitudinal drift activity. A discussion follows outlining the routine orbit maintenance required for ongoing mission support. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Cox, EL (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 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 0-87703-470-2 J9 ADV ASTRONAUT SCI PY 2000 VL 105 BP 951 EP 965 PN 1&2 PG 15 WC Engineering, Aerospace SC Engineering GA BQ99H UT WOS:000165304900058 ER PT S AU Mazanek, DD Kumar, RR Seywald, H Qu, M AF Mazanek, DD Kumar, RR Seywald, H Qu, M BE Kluever, CA Neta, B Hall, CD Hanson, JM TI Grace mission design: Impact of uncertainties in disturbance environment and satellite force models SO SPACEFLIGHT MECHANICS 2000, VOL 105, PTS I AND II SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 10th Space Flight Mechanics Meeting CY JAN 23-26, 2000 CL CLEARWATER, FL SP Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut ID AEROSTABILIZATION AB The Gravity Recovery and Climate Experiment (GRACE) primary mission will be performed by making measurements of the inter-satellite range change between two coplanar, low altitude, near-polar orbiting satellites. Understanding the uncertainties in the disturbance environment, particularly the aerodynamic drag and torques, is critical in several mission areas. These include an accurate estimate of the spacecraft orbital lifetime, evaluation of spacecraft attitude control requirements, and estimation of the orbital maintenance maneuver frequency necessitated by differences in the drag forces acting on both satellites. The FREEMOL simulation software has been developed and utilized to analyze and suggest design modifications to the GRACE spacecraft. Aerodynamic accommodation bounding analyses were performed and worst-case envelopes were obtained for the aerodynamic torques and the differential ballistic coefficients between the leading and trailing GRACE spacecraft. These analyses demonstrate how spacecraft aerodynamic design and analysis can benefit from a better understanding of spacecraft surface accommodation properties, and the implications for mission design constraints such as formation spacing control. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Mazanek, DD (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. NR 11 TC 1 Z9 1 U1 0 U2 1 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-470-2 J9 ADV ASTRONAUT SCI PY 2000 VL 105 BP 967 EP 986 PN 1&2 PG 20 WC Engineering, Aerospace SC Engineering GA BQ99H UT WOS:000165304900059 ER PT S AU Bordi, JJ Antreasian, PG Miller, JK Williams, BG AF Bordi, JJ Antreasian, PG Miller, JK Williams, BG BE Kluever, CA Neta, B Hall, CD Hanson, JM TI Altimeter range processing analysis for spacecraft navigation about small bodies SO SPACEFLIGHT MECHANICS 2000, VOL 105, PTS I AND II SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 10th Space Flight Mechanics Meeting CY JAN 23-26, 2000 CL CLEARWATER, FL SP Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut AB The impact of using altimeter range measurements as an observation type for navigation of spacecraft about small bodies is evaluated. The altimeter range measurements can supplement or replace the standard optical landmark and Deep Space Network (DSN) radiometric tracking. Navigation of spacecraft orbiting small bodies, like asteroids, can be challenging since the a priori physical characteristics of the central body can have larger than normal uncertainties. The addition of the altimeter range data into the orbit determination problem can be used to alleviate the increased uncertainty in the dynamics of the spacecraft, due to uncertainties in the gravity model of the body. An advantage of the altimeter data is that the measurements can be taken continuously, without the sunlight restrictions of optical landmark tracking, or the station visibility restrictions of DSN tracking. Simulations of various mission scenarios are used as test cases, to quantify the usefulness of the altimeter range data as a navigation tool. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Bordi, JJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 4 TC 0 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 0-87703-470-2 J9 ADV ASTRONAUT SCI PY 2000 VL 105 BP 1001 EP 1015 PN 1&2 PG 15 WC Engineering, Aerospace SC Engineering GA BQ99H UT WOS:000165304900061 ER PT S AU Goodson, TD Gray, DL Hahn, Y Peralta, F AF Goodson, TD Gray, DL Hahn, Y Peralta, F BE Kluever, CA Neta, B Hall, CD Hanson, JM TI Cassini maneuver experience: Finishing inner cruise SO SPACEFLIGHT MECHANICS 2000, VOL 105, PTS I AND II SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 10th Space Flight Mechanics Meeting CY JAN 23-26, 2000 CL CLEARWATER, FL SP Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut AB The Cassini-Huygens spacecraft was launched in 1997. It is an international effort to study the Saturnian system. Cassini's interplanetary cruise, which will deliver the spacecraft to Saturn in 2004, is making use of multiple propulsive maneuvers, both statistical and deterministic. The maneuvers of inner cruise have been completed. The system has performed better than pre-launch expectations and requirements. Improvements to the system have been made and more accurate maneuver execution error models have been determined, based on this in-flight data. This new model will provide more realism to predictions of the fuel required to navigate the tour of the Saturnian system. C1 CALTECH, Jet Prop Lab, Navigat & Mission Design Sect, Pasadena, CA 91109 USA. RP Goodson, TD (reprint author), CALTECH, Jet Prop Lab, Navigat & Mission Design Sect, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 13 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 0-87703-470-2 J9 ADV ASTRONAUT SCI PY 2000 VL 105 BP 1031 EP 1051 PN 1&2 PG 21 WC Engineering, Aerospace SC Engineering GA BQ99H UT WOS:000165304900063 ER PT S AU Guman, MD Roth, DC Ionasescu, R Goodson, TD Taylor, AH Jones, JB AF Guman, MD Roth, DC Ionasescu, R Goodson, TD Taylor, AH Jones, JB BE Kluever, CA Neta, B Hall, CD Hanson, JM TI Cassini orbit determination from first Venus flyby to Earth flyby SO SPACEFLIGHT MECHANICS 2000, VOL 105, PTS I AND II SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 10th Space Flight Mechanics Meeting CY JAN 23-26, 2000 CL CLEARWATER, FL SP Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut AB This paper describes Cassini orbit determination results from the first Venus flyby through the Earth flyby. Emphasis is placed cn orbit determination modeling and the resulting orbit solutions. Key solutions supporting maneuver designs are compared against reconstructed trajectory results. Reconstructed maneuver and planetary flyby events are provided. C1 CALTECH, Jet Prop Lab, Navigat & Mission Design Sect, Pasadena, CA 91109 USA. RP Guman, MD (reprint author), CALTECH, Jet Prop Lab, Navigat & Mission Design Sect, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 10 TC 7 Z9 7 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-470-2 J9 ADV ASTRONAUT SCI PY 2000 VL 105 BP 1053 EP 1072 PN 1&2 PG 20 WC Engineering, Aerospace SC Engineering GA BQ99H UT WOS:000165304900064 ER PT S AU Munk, MM Powell, RW AF Munk, MM Powell, RW BE Kluever, CA Neta, B Hall, CD Hanson, JM TI Aeroassist technology planning for exploration SO SPACEFLIGHT MECHANICS 2000, VOL 105, PTS I AND II SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 10th Space Flight Mechanics Meeting CY JAN 23-26, 2000 CL CLEARWATER, FL SP Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut AB Now that the International Space Station is undergoing assembly, NASA is strategizing about the next logical exploration strategy for robotic missions and the next destination for humans. NASA's current efforts are in developing technologies that will both aid the robotic exploration strategy and make human flight to other celestial bodies both safe and affordable. One of these enabling technologies for future robotic and human exploration missions is aeroassist. This paper will (1) define aeroassist, (2) explain the benefits and uses of aeroassist, and (3) describe a method, currently used by the NASA Aeroassist Working Group, by which widely geographically distributed teams can assemble, present, use, and archive technology information. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Munk, MM (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. NR 4 TC 3 Z9 3 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-470-2 J9 ADV ASTRONAUT SCI PY 2000 VL 105 BP 1073 EP 1083 PN 1&2 PG 11 WC Engineering, Aerospace SC Engineering GA BQ99H UT WOS:000165304900065 ER PT S AU McRonald, AD AF McRonald, AD BE Kluever, CA Neta, B Hall, CD Hanson, JM TI A light-weight hypersonic inflatable drag device for a neptune orbiter SO SPACEFLIGHT MECHANICS 2000, VOL 105, PTS I AND II SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 10th Space Flight Mechanics Meeting CY JAN 23-26, 2000 CL CLEARWATER, FL SP Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut AB The author has analyzed the use of a light-weight inflatable hypersonic drag device, called a ballute, for flight in planetary atmospheres, for entry, aerocapture and aerobraking. Studies to date include Mars, Venus, Earth, Saturn, Titan, Neptune and Pluto, and data on a Neptune orbiter will be presented to illustrate the concept at a large entry speed. For a Neptune orbiter a conventional rigid lifting entry body requires about 40% of the entry mass to be in the thermal shield and structure to take the pressure and thermal loads, and analysis indicates that the ballute mass for the same task may be about half this value. The main advantage of using a ballute is that aero deceleration and heating in atmospheric entry occur at much smaller atmospheric density with a ballute than without it. For example, if a ballute has a diameter 10 times as large as the spacecraft, for unchanged total mass, entry speed and entry angle, the atmospheric density at peak convective heating is reduced by a factor of 100, reducing the peak heating by a factor of 10 for the spacecraft, and a factor of about 30 for the ballute. Consequently, the entry payload (descent probe, orbiter, etc) is subject to much less heating, requires a much reduced thermal protection system (possibly only an MLI blanket), and the spacecraft design is therefore relatively unchanged from its vacuum counterpart. By making the ballute large enough one can make the heat flux on the ballute small enough to be radiated at temperatures below 800 K or so. Also, the heating may be reduced further because the ballute enters at a more shallow angle than a solid vehicle, even allowing for the increased delivery angle error that one expects at shallow entry, for a given error in the target plane. Added advantages are less mass ratio of entry system to total entry mass, and freedom from the low-density instability problem that conventional rigid bodies suffer, since the vehicle attitude is determined by the ballute, which is usually released at continuum conditions. The ballute derives an entry corridor for aerocapture by entering on a path that would lead to entry, and releasing the ballute adaptively, responding to measured deceleration, to achieve the desired orbiter exit conditions. The author will discuss presently available ballute materials and a development program of aerodynamic tests and materials that would be required for ballutes to achieve their full potential. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP McRonald, AD (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 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 0-87703-470-2 J9 ADV ASTRONAUT SCI PY 2000 VL 105 BP 1085 EP 1099 PN 1&2 PG 15 WC Engineering, Aerospace SC Engineering GA BQ99H UT WOS:000165304900066 ER PT S AU Neelon, J Spath, S Sidney, W AF Neelon, J Spath, S Sidney, W BE Kluever, CA Neta, B Hall, CD Hanson, JM TI Mars Global Surveyor azimuth gimbal anomaly: The analysis of the problem and solution, and the implementation SO SPACEFLIGHT MECHANICS 2000, VOL 105, PTS I AND II SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 10th Space Flight Mechanics Meeting CY JAN 23-26, 2000 CL CLEARWATER, FL SP Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut AB The Mars Global Surveyor (MGS) spacecraft experienced an operational anomaly in the High Gain Antenna (L-IGA) azimuth gimbal early in its mapping phase. The initial remedy to this anomaly, Fixed HGA (FHGA) Operations, would not provide adequate data return during the second year of the MGS mapping phase. Alternate methods of operation that mitigate the data loss from FL-IGA Operations were investigated. The sole viable alternative, Beta Supplement Operations, does not satisfy all the science requirements for the second half of the MGS mission, but its shortcomings are complemented by limited use of FHGA Operations. A compromise was achieved by alternating between these operational modes to gain the benefits of each. A description of the implementation of Beta Supplement is provided in this paper. Beta Supplement operations will begin on 5 February 2000. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Neelon, J (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 UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-470-2 J9 ADV ASTRONAUT SCI PY 2000 VL 105 BP 1491 EP 1509 PN 1&2 PG 19 WC Engineering, Aerospace SC Engineering GA BQ99H UT WOS:000165304900088 ER PT S AU Lyons, DT AF Lyons, DT BE Kluever, CA Neta, B Hall, CD Hanson, JM TI Aerobraking trajectory options for the first Mars micro-mission telecom orbiter SO SPACEFLIGHT MECHANICS 2000, VOL 105, PTS I AND II SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 10th Space Flight Mechanics Meeting CY JAN 23-26, 2000 CL CLEARWATER, FL SP Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut ID GLOBAL SURVEYOR AB A small, interplanetary spacecraft is being developed for launch as a piggyback payload on the Ariane V. The spacecraft will be released during the intermediate Geosynchronous Transfer Orbit for the primary payload. The Micro-Mission spacecraft must carry sufficient propellant to leave Earth orbit and perform the remainder of the mission. Although missions to several target bodies have been discussed, the first mission will be to place a telecommunications satellite in orbit around Mars to act as a relay for other spacecraft at Mars. This first Mars Micro-Mission is scheduled to be launched in early 2003 and arrive at Mars on December 26, 2003. Approximately 1400 m/s and several flybys of the Earth and Moon will be required to inject the spacecraft on a trajectory to Mars. Another 900 mis will be required to capture the spacecraft into a highly elliptical orbit around Mars. Since nearly two thirds of the spacecraft mass must be propellant to provide enough DeltaV just to reach Mars, aerobraking will be used to remove another 1190 m/s from a 72 hour capture orbit in order to shrink the apoapsis altitude to 800 km, which is the altitude for a nearly circular orbit required by the telecom system. This paper will discuss some of the tradeoffs associated with the aerobraking phase of the first Mars Micro-Mission. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Lyons, DT (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 264-380, 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 0-87703-470-2 J9 ADV ASTRONAUT SCI PY 2000 VL 105 BP 1511 EP 1530 PN 1&2 PG 20 WC Engineering, Aerospace SC Engineering GA BQ99H UT WOS:000165304900089 ER PT S AU Havelund, K AF Havelund, K BE Havelund, K Penix, J Visser, W TI Using runtime analysis to guide model checking of Java programs SO SPIN MODEL CHECKING AND SOFTWARE VERIFICATON SE LECTURE NOTES IN COMPUTER SCIENCE LA English DT Article; Proceedings Paper CT 7th International SPIN Workshop CY AUG 30-SEP 01, 2000 CL STANFORD, CALIFORNIA SP Automated Software Engn Grp, Res Inst Adv Comp Sci DE concurrent programs; runtime analysis; race conditions; deadlocks; program verification; guided model checking; Java AB This paper describes how two runtime analysis algorithms, an existing data race detection algorithm and a new deadlock detection algorithm, have been implemented to analyze Java programs. Runtime analysis is based on the idea of executing the program once, and observing the generated run to extract various kinds of information. This information can then be used to predict whether other different runs may violate some properties of interest, in addition of course to demonstrate whether the generated run itself violates such properties. These runtime analyses can be performed stand-alone to generate a set of warnings. It is furthermore demonstrated how these warnings can be used to guide a model checker, thereby reducing the search space. The described techniques have been implemented in the home grown Java model checker called Java PathFinder. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Havelund, K (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 28 TC 34 Z9 34 U1 0 U2 1 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY SN 0302-9743 BN 3-540-41030-9 J9 LECT NOTES COMPUT SC PY 2000 VL 1885 BP 245 EP 264 PG 20 WC Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BT08D UT WOS:000171882200015 ER PT J AU Smyth, P AF Smyth, P TI Model selection for probabilistic clustering using cross-validated likelihood SO STATISTICS AND COMPUTING LA English DT Article ID FLOW REGIMES; MIXTURE AB Cross-validated likelihood is investigated as a tool for automatically determining the appropriate number of components (given the data) in finite mixture modeling, particularly in the context of model-based probabilistic clustering. The conceptual framework for the cross-validation approach to model selection is straightforward in the sense that models are judged directly on their estimated out-of-sample predictive performance. The cross-validation approach, as well as penalized likelihood and McLachlan's bootstrap method, are applied to two data sets and the results from all three methods are in close agreement. The second data set involves a well-known clustering problem from the atmospheric science literature using historical records of upper atmosphere geopotential height in the Northern hemisphere. Cross-validated likelihood provides an interpretable and objective solution to the atmospheric clustering problem. The clusters found are in agreement with prior analyses of the same data based on non-probabilistic clustering techniques. C1 Univ Calif Irvine, Irvine, CA 92697 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. NR 39 TC 129 Z9 130 U1 1 U2 11 PU KLUWER ACADEMIC PUBL PI DORDRECHT PA SPUIBOULEVARD 50, PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS SN 0960-3174 J9 STAT COMPUT JI Stat. Comput. PD JAN PY 2000 VL 10 IS 1 BP 63 EP 72 DI 10.1023/A:1008940618127 PG 10 WC Computer Science, Theory & Methods; Statistics & Probability SC Computer Science; Mathematics GA 273KN UT WOS:000084706600007 ER PT S AU McCandless, JW Ellis, SR AF McCandless, JW Ellis, SR BE Merritt, JO Benton, SA Woods, AJ Bolas, MT TI The effect of eye position on the projected stimulus distance in a binocular head-mounted display SO STEREOSCOPIC DISPLAYS AND VIRTUAL REALITY SYSTEMS VII SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Stereoscopic Displays and Virtual Reality Systems VII CY JAN 24-27, 2000 CL SAN JOSE, CA SP Soc Imaging Sci & Technol, SPIE DE vergence; distance; binocular; ocular; projected; head-mounted display ID PERCEPTION; LOCATIONS; DEPTH AB During vergence eye movements, the effective separation between the two eyes varies because the nodal point of each eye is offset from the center of rotation. As a result, the projected distance of a binocularly presented virtual object changes as the observer converges and diverges. A model of eye and stimulus position illustrates that if an observer converges toward a binocular virtual stimulus that is fixed on the display, the projected stimulus will shift outward away fi om the observer. Conversely, if the observer diverges toward a binocular virtual stimulus that is fixed on the display, the projected stimulus will shift inward. For example, if an observer diverges from 25 cm to 300 cm, a binocular virtual stimulus projected at 300 cm will shift inward to 241 cm. Accurate depiction of a fixed stimulus distance in a binocular display requires that the stimulus position on the display surface should be adjusted in real-time to compensate for the observer's eye movements. C1 San Jose State Univ Fdn, San Jose, CA 95172 USA. RP NASA, Ames Res Ctr, MS 262-2, Moffett Field, CA 94035 USA. EM jmccandless@mail.arc.nasa.gov NR 36 TC 0 Z9 0 U1 0 U2 2 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3575-9 J9 PROC SPIE PY 2000 VL 3957 BP 41 EP 48 DI 10.1117/12.384478 PG 8 WC Computer Science, Software Engineering; Engineering, Electrical & Electronic; Optics; Imaging Science & Photographic Technology SC Computer Science; Engineering; Optics; Imaging Science & Photographic Technology GA BQ35Z UT WOS:000088119500006 ER PT B AU Turner, TL AF Turner, TL BE Ferguson, NS Wolfe, HF Ferman, MA Rizzi, SA TI SMA hybrid composites for dynamic response abatement applications SO STRUCTURAL DYNAMICS: RECENT ADVANCES, VOLS 1 & 2, PROCEEDINGS LA English DT Proceedings Paper CT 7th International Conference on Recent Advances in Structural Dynamics CY JUL 24-27, 2000 CL UNIV SOUTHAMPTON, INST SOUND & VIBRAT RES, SOUTHAMPTON, ENGLAND SP USAF, European Off Aerosp Res & Dev, UASF, Res Lab, Wright Patterson AFB, Parks Coll,Engn & Aviat, St Louis Univ, NASA, Langley Res Ctr, Struct Acoust Branch HO UNIV SOUTHAMPTON, INST SOUND & VIBRAT RES ID SHAPE-MEMORY ALLOY; NITINOL-REINFORCED PLATES; ACTIVE VIBRATION; LAMINATED PLATES; FIBERS; MODEL AB A recently developed constitutive model and a finite element formulation for predicting the thermomechanical response of SMA hybrid composite (SMAHC) structures is briefly described. Attention is focused on constrained recovery behavior in this study, but the constitutive formulation is also capable of modeling restrained or free recovery. Numerical results are shown for glass/epoxy panel specimens with embedded Nitinol actuators subjected to thermal and acoustic loads. Control of thermal buckling, random response, sonic fatigue, and transmission loss are demonstrated and compared to conventional approaches including addition of conventional composite layers and a constrained layer damping treatment. Embedded SMA actuators are shown to be significantly more effective in dynamic response abatement applications than the conventional approaches and are attractive for combination with other passive and/or active approaches. C1 NASA, Langley Res Ctr, Struct Acoust Branch, Hampton, VA 23681 USA. RP Turner, TL (reprint author), NASA, Langley Res Ctr, Struct Acoust Branch, MS 463, Hampton, VA 23681 USA. NR 30 TC 0 Z9 0 U1 0 U2 0 PU INST SOUND VIBRATION RESEARCH PI SOUTHAMPTON PA THE UNIVERSITY, SOUTHAMPTON S09 5NH, ENGLAND BN 0-85432-721-5 PY 2000 BP 453 EP 465 PG 13 WC Engineering, Mechanical; Mechanics SC Engineering; Mechanics GA BR55R UT WOS:000166796300033 ER PT B AU Rizzi, SA Muravyov, AA AF Rizzi, SA Muravyov, AA BE Ferguson, NS Wolfe, HF Ferman, MA Rizzi, SA TI Comparison of non-linear random response using equivalent linearization and numerical simulation SO STRUCTURAL DYNAMICS: RECENT ADVANCES, VOLS 1 & 2, PROCEEDINGS LA English DT Proceedings Paper CT 7th International Conference on Recent Advances in Structural Dynamics CY JUL 24-27, 2000 CL UNIV SOUTHAMPTON, INST SOUND & VIBRAT RES, SOUTHAMPTON, ENGLAND SP USAF, European Off Aerosp Res & Dev, UASF, Res Lab, Wright Patterson AFB, Parks Coll,Engn & Aviat, St Louis Univ, NASA, Langley Res Ctr, Struct Acoust Branch HO UNIV SOUTHAMPTON, INST SOUND & VIBRAT RES AB A recently developed finite-element-based equivalent linearization approach for the analysis of random vibrations of geometrically nonlinear multiple degree-of-freedom structures is validated. The validation is based on comparisons with results from a finite element based numerical simulation analysis using a numerical integration technique in physical coordinates. In particular, results for the case of a clamped-clamped beam are considered for an extensive load range to establish the limits of validity of the equivalent linearization approach. C1 NASA, Langley Res Ctr, Struct Acoust Branch, Hampton, VA 23681 USA. RP Rizzi, SA (reprint author), NASA, Langley Res Ctr, Struct Acoust Branch, Hampton, VA 23681 USA. NR 14 TC 1 Z9 1 U1 0 U2 0 PU INST SOUND VIBRATION RESEARCH PI SOUTHAMPTON PA THE UNIVERSITY, SOUTHAMPTON S09 5NH, ENGLAND BN 0-85432-721-5 PY 2000 BP 833 EP 846 PG 14 WC Engineering, Mechanical; Mechanics SC Engineering; Mechanics GA BR55R UT WOS:000166796300062 ER PT B AU Gabb, TP Backman, DG Wei, DY Mourer, DP Furrer, D Garg, A Ellis, DL AF Gabb, TP Backman, DG Wei, DY Mourer, DP Furrer, D Garg, A Ellis, DL BE Pollock, TM Kissinger, RD Bowman, RR Green, KA McLean, M Olson, SL Schirra, JJ TI gamma ' formation in a nickel-base disk superalloy SO SUPERALLOYS 2000 LA English DT Proceedings Paper CT 9th International Symposium on Superalloys CY SEP 17-21, 2000 CL CHAMPION, PA SP TMS Seven Springs Int Symp Comm, TMS High Temp Alloys Comm, ASM Int ID AT-PERCENT AL; DIFFUSIONAL NUCLEATION; KINETICS; GROWTH; ALLOYS AB A streamlined,physics-based kinetic model was formulated, calibrated, and validated on a nickel-base superalloy. It was designed to be simplified and streamlined, to speed up calculations and facilitate linkage to finite element modeling thermal codes. The model describes and predicts the formation of gamma' precipitates during the heat treatment process. Standardized experimental methods were employed to calibrate and initially validate the microstructure model. The model was then validated on an oil-quenched generic disk. Predictions of primary cooling gamma' size and area fraction agreed well with experimental measurements over a large range of values and cooling rates. C1 NASA, Glenn Res Ctr, Washington, DC 20546 USA. RP Gabb, TP (reprint author), NASA, Glenn Res Ctr, Washington, DC 20546 USA. NR 25 TC 12 Z9 12 U1 0 U2 2 PU MINERALS, METALS & MATERIALS SOC PI WARRENDALE PA 184 THORN HILL RD, WARRENDALE, PA 15086-7514 USA BN 0-87339-477-1 PY 2000 BP 405 EP 414 PG 10 WC Metallurgy & Metallurgical Engineering SC Metallurgy & Metallurgical Engineering GA BR29P UT WOS:000166051500044 ER PT B AU Takada, PW Westbrook, J AF Takada, PW Westbrook, J GP ASEM ASEM TI Gender-based differences in learning and satisfaction levels in graduate engineering management education SO TECHNICAL MANAGEMENT: KEY TO ENTERPRISE SUCCESS IN THE 21ST CENTURY LA English DT Proceedings Paper CT 21st National Conference of the American-Society-for-Engineering-Management CY OCT 04-07, 2000 CL GEORGE WASHINGTON UNIV, WASHINGTON, D.C. SP Amer Soc Engn Management HO GEORGE WASHINGTON UNIV AB Researchers have noticed that men and women do not use identical processes in learning. This research seeks to determine if the purported differences are evident in graduate Engineering Management academic programs. If in deed there are differences, such differences would tend to be more evident when comparing learning from qualitative vs. quantitative courses. In an effort to more closely examine these differences, two studies on the same survey population were undertaken. The first study examines whether gender-based differences exist in qualitative graduate engineering management courses and mathematical statistics courses. The second study examines the same population in an effort to determine whether differences exist in satisfaction levels regardless of grade received. Grade-based differences were found when examining equally capable males and females in both statistically quantitative based and engineering management courses. Differences were also found when examining the satisfaction levels of both males and females. For the same undergraduate grade point average (GPA), females will have significantly higher Engineering Management course grades than their male counterparts. The results also indicate that males have significantly higher Statistics course grades for those possessing an undergraduate GPA ranging from 2.0 on a 4.0 scale to 2.8 on a 4.0 scale. From the second study, it was determined that male engineers prefer mathematical, equation based courses whereas female engineers prefer behavioral theory, case based courses. Male engineers also feet greater mastery over those mathematical courses than their female engineering counterparts with the same undergraduate GPA's. C1 NASA, George C Marshall Space Flight Ctr, Syst Management Off VS10, Huntsville, AL 35812 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC ENGINEERING MANAGEMT PI ROLLA PA 310 HARRIS HALL, UMR, ROLLA, MO 65401 USA PY 2000 BP 478 EP 487 PG 10 WC Engineering, Multidisciplinary; Management SC Engineering; Business & Economics GA BY20J UT WOS:000188242100063 ER PT J AU Hunley, JD AF Hunley, JD TI Spaceflight revolution: NASA langley research center from sputnik to apollo. SO TECHNOLOGY AND CULTURE LA English DT Book Review C1 NASA, Dryden Flight Res Ctr, Washington, DC 20546 USA. RP Hunley, JD (reprint author), NASA, Dryden Flight Res Ctr, Washington, DC 20546 USA. NR 1 TC 0 Z9 0 U1 0 U2 0 PU JOHNS HOPKINS UNIV PRESS PI BALTIMORE PA JOURNALS PUBLISHING DIVISION, 2715 NORTH CHARLES ST, BALTIMORE, MD 21218-4319 USA SN 0040-165X J9 TECHNOL CULT JI Technol. Cult. PD JAN PY 2000 VL 41 IS 1 BP 166 EP 168 PG 3 WC History & Philosophy Of Science SC History & Philosophy of Science GA 280ZC UT WOS:000085132800034 ER PT S AU Rakoczy, JM Montgomery, EE Lindner, JL AF Rakoczy, JM Montgomery, EE Lindner, JL BE Sebring, TA Andersen, T TI Recent enhancements of the Phased Array Mirror Extendible Large Aperture (PAMELA) telescope testbed at MSFC SO TELESCOPE STRUCTURES, ENCLOSURES, CONTROLS, ASSEMBLY/INTEGRATION/VALIDATION, AND COMMISSIONING SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Telescope Structures, Enclosures, Controls, Assembly/Integration/Validation, and Commissioning CY MAR 27-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE PAMELA; segmented mirrors; wavefront sensing; wavefront control; segmented mirror phasing AB Recent incremental upgrades to the Phased Array Mirror Extendible Large Aperture (PAMELA) telescope testbed have enabled the demonstration of phasing (with a monochromatic source) of clusters of primary mirror segments down to the diffraction limit. PAMELA upgrades include an improved Shack-Hartmann wavefront sensor, passive viscoelastic damping treatments for the voice-coil actuators, and mechanical improvement of mirror surface figures. This report summarizes the recent PAMELA upgrades and presents a status of this unique testbed for wavefront sensing and control. The Marshall Space Flight Center acquired the Phased Array Mirror Extendible Large Aperture (PAMELA) telescope in 1993 after Kaman Aerospace was unable to complete integration and testing under the limited SDIO and DARPA funding. The PAMELA is a 36-segment, half-meter aperture, adaptive telescope which utilizes a Shack-Hartmann wavefront sensor, inductive coil edge sensors, voice coil acutautors, imaging CCD cameras and interferometry for figure alignment, wavefront sensing and control. MSFC originally obtained the PAMELA to supplement its research in the interactions of control systems with flexible structures. In August 1994, complete tip, tilt and piston control was successfully demonstrated using the Shack-Hartmann wavefront sensor and the inductive edge sensors. C1 NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Rakoczy, JM (reprint author), NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. NR 3 TC 5 Z9 5 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3629-1 J9 P SOC PHOTO-OPT INS PY 2000 VL 4004 BP 352 EP 362 DI 10.1117/12.393940 PG 11 WC Astronomy & Astrophysics; Optics SC Astronomy & Astrophysics; Optics GA BQ70A UT WOS:000089218200035 ER PT B AU Cornford, SL Feather, MS Kelly, JC Larson, TW Sigal, B Kiper, JD AF Cornford, SL Feather, MS Kelly, JC Larson, TW Sigal, B Kiper, JD GP IEEE COMPUTER SOCIETY IEEE COMPUTER SOCIETY IEEE COMPUTER SOCIETY TI Design and development assessment SO TENTH INTERNATIONAL WORKSHOP ON SOFTWARE SPECIFICATION AND DESIGN LA English DT Proceedings Paper CT 10th International Workshop on Software Specification and Design CY NOV 05-07, 2000 CL SAN DIEGO, CA SP IEEE, Comp Soc, Tech Council Software Engn DE assessment; requirements elicitation; risk management; software processes; quality assurance; capability maturity model; tradeoffs AB An assessment methodology is described and illustrated. This methodology separates assessment into the following phases (I) Elicitation of requirements; (2) Elicitation of failure modes and their impact (risk of loss of requirements); (3) Elicitation of failure mode mitigations and their effectiveness (degree of reduction of failure modes); (4) Calculation of outstanding risk taking the mitigations into account This methodology, with accompanying tool support, has been applied to assist in planning the engineering development of advanced technologies Design assessment featured prominently in these applications. The overall approach is also applicable to development assessment (of the development process to be followed to implement the design). Both design and development assessments are demonstrated on hypothetical scenarios based on the,workshop's TRMCS case study. TRMCS information has been entered into the assessment support tool, and serves as illustration throughout. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Cornford, SL (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 COMPUTER SOC PI LOS ALAMITOS PA 10662 LOS VAQUEROS CIRCLE, PO BOX 3014, LOS ALAMITOS, CA 90720-1264 USA BN 0-7695-0884-7 PY 2000 BP 105 EP 114 DI 10.1109/IWSSD.2000.891131 PG 10 WC Computer Science, Software Engineering; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BR14F UT WOS:000165732300011 ER PT B AU Zolensky, M AF Zolensky, M BE Detre, CH TI Discovering the sources of cosmic spherules: Bulk compositions of meteorite ablation materials SO TERRESTRIAL AND COSMIC SPHERULES, PROCEEDINGS LA English DT Proceedings Paper CT Annual Meeting on Terrestrial and Cosmic Spherules (TECOS) CY SEP 28-30, 1998 CL BUDAPEST, HUNGARY ID OXYGEN ISOTOPES AB There are significant compositional differences between the major element composition of fusion crust and a bulk meteorite, which suggests that one cannot relate fusion crust to a specific meteorite. Similarly, it is not possible to distinguish between different petrologic types for ordinary chondrites (i.e. 3,4,5,6). It is also not possible to distinguish the fusion crust of ordinary chondrites (H, L, LL) from each other. It may be possible to distinguish fusion crust of ordinary chondrites from that of carbonaceous chondrites (CM and CV), as the latter have higher Al, Ti, Fe, Ni and lower K than ordinary chondrite fusion crust. I suggest that these same relations (and non-relations) should exist for ablation spherules. C1 NASA, Lyndon B Johnson Space Ctr, SN2, Houston, TX 77058 USA. RP Zolensky, M (reprint author), NASA, Lyndon B Johnson Space Ctr, SN2, Houston, TX 77058 USA. NR 12 TC 0 Z9 0 U1 0 U2 1 PU AKADEMIAI KIADO PI BUDAPEST PA PO BOX 245, H-1519 BUDAPEST, HUNGARY BN 963-05-7693-7 PY 2000 BP 175 EP 182 PG 8 WC Astronomy & Astrophysics; Meteorology & Atmospheric Sciences SC Astronomy & Astrophysics; Meteorology & Atmospheric Sciences GA BT45G UT WOS:000173046700016 ER PT S AU Carreno, V Munoz, C AF Carreno, V Munoz, C BE Aagaard, M Harrison, J TI Aircraft trajectory modeling and alerting algorithm verification SO THEOREM PROVING IN HIGHER ORDER LOGICS, PROCEEDINGS SE Lecture Notes in Computer Science LA English DT Article; Proceedings Paper CT 13th International Conference on Theorem Proving in Higher Order Logics CY AUG 14-18, 2000 CL PORTLAND, OR SP Intel Corp, OGI, Oregon Grad Inst, Compaq, IBM, Intel, Levetate, Synopsys AB The Airborne Information for Lateral Spacing (AILS) program at NASA Langley Research Center aims at giving pilots the information necessary to make independent approaches to parallel runways with spacing down to 2500 feet in Instrument Meteorological Conditions. The AILS concept consists of accurate traffic information visible on the navigation display and an alerting algorithm which warns the crew when one of the aircraft involved in a parallel landing is diverting from its intended flight path. In this paper we present a model of aircraft approaches to parallel runways. Based on this model, we analyze the alerting algorithm with the objective of verifying its correctness. The formalization is conducted in the general verification system PVS. C1 NASA, Langley Res Ctr, Assessment Technol Branch, Hampton, VA 23681 USA. NASA, Langley Res Ctr, ICASE, Hampton, VA 23681 USA. RP Carreno, V (reprint author), NASA, Langley Res Ctr, Assessment Technol Branch, Mail Stop 130, Hampton, VA 23681 USA. EM v.a.carreno@larc.nasa.gov; munoz@icase.edu NR 16 TC 1 Z9 1 U1 0 U2 0 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY SN 0302-9743 BN 3-540-67863-8 J9 LECT NOTES COMPUT SC PY 2000 VL 1869 BP 90 EP 105 PG 16 WC Computer Science, Theory & Methods SC Computer Science GA BT05X UT WOS:000171796500006 ER PT B AU Wooden, DH Harker, DE Woodward, CE AF Wooden, DH Harker, DE Woodward, CE BE Sitko, ML Sprague, AL Lynch, DK TI Crystalline silicates, comets, and protoplanetary disk evolution SO THERMAL EMISSION SPECTROSCOPY AND ANALYSIS OF DUST, DISKS, AND REGOLITHS SE Astronomical Society of the Pacific Conference Series LA English DT Proceedings Paper CT Meeting on Thermal Emission Spectroscopy and Analysis of Dust, Disks, and Regoliths CY APR 28-30, 1999 CL LUNAR & PLANETARY INST, HOUSTON, TX SP Lunar & Planetary Inst, Natl Sci Fdn HO LUNAR & PLANETARY INST ID HERBIG AE/BE STARS; INTERPLANETARY DUST; CIRCUMSTELLAR DISKS; GRAINS; MINERALOGY; HIPPARCOS; SPECTRUM; PYROXENE; OLIVINE; NEBULA AB The analysis of the silicate mineralogy of comets, pre-main sequence T Tauri stars and Herbig Ae/Be stars, and main sequence beta-Pic systems probes chemical and physical conditions in potentially planet-forming environments, condensation of dust from the gas-disk, accretion and annealing of interstellar amorphous silicates, and aggregation and accretion of these solids into planetesimals and comets. Ground-based and space-borne ISO spectroscopy of the 10 mu m and 20 mu m silicate resonances at medium to high resolution (R similar or equal to 200-1000) combined with analytical modeling efforts permits the testing of a current (Waelkens et al. 1999; Nuth 1999) yet unproved (van den Ancker et al. 1999) hypothesis that the degree of silicate crystallinity increases with age and disk evolutionary state. Correlating silicate mineralogy (including Mg-content and degree of crystallinity versus amorphousness) with age, disk properties, and circumstellar environment, develops the relationship between grain properties and protoplanetary disk evolution. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Wooden, DH (reprint author), NASA, Ames Res Ctr, MS 254-3, Moffett Field, CA 94035 USA. EM wooden@delphinus.arc.nasa.gov NR 45 TC 7 Z9 7 U1 0 U2 0 PU ASTRONOMICAL SOC PACIFIC PI SAN FRANCISCO PA 390 ASHTON AVE, SAN FRANCISCO, CA 94112 USA BN 1-58381-023-4 J9 ASTR SOC P PY 2000 VL 196 BP 99 EP 108 PG 10 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BQ13Y UT WOS:000087282200012 ER PT B AU Witteborn, FC Roush, TL Cohen, M AF Witteborn, FC Roush, TL Cohen, M BE Sitko, ML Sprague, AL Lynch, DK TI Thermal emission spectroscopy of 1 Ceres: Evidence for olivine SO THERMAL EMISSION SPECTROSCOPY AND ANALYSIS OF DUST, DISKS, AND REGOLITHS SE ASTRONOMICAL SOCIETY OF THE PACIFIC CONFERENCE SERIES LA English DT Proceedings Paper CT Meeting on Thermal Emission Spectroscopy and Analysis of Dust, Disks, and Regoliths CY APR 28-30, 1999 CL LUNAR & PLANETARY INST, HOUSTON, TX SP Lunar & Planetary Inst, Natl Sci Fdn HO LUNAR & PLANETARY INST ID SPECTRAL IRRADIANCE CALIBRATION; REFLECTANCE SPECTRA; MAIN BELT; ASTEROIDS; PARTICLES; SURFACES; MINERALS AB Thermal emission spectra of the largest asteroid, I Ceres, obtained from the Kuiper Airborne Observatory display features that may provide information about its surface mineralogy. The emissivity, obtained by dividing the spectra by a standard thermal model, is compared with emissivity spectra of olivines and phyllosilicates deduced via Kirchoff's law from reflectivity measurements. The spectra provide a fairly good match to fine grained olivines (0 to 5 mu m size range). The smoothness of the spectrum beyond 18 mu m is an indication of particles smaller than 50 mu m. While the abrupt rise in emissivity near 8 mu m matches many silicates, the distinct emissivity minimum centered near 12.8 mu m is consistant with iron-poor olivines, but not with phyllosilicates. It suggests the presence of opaques and does not exclude a mixture with organics and fine-grained phyllosilicates. C1 NASA, Ames Res Ctr, SETI Inst, Moffett Field, CA 94035 USA. RP Witteborn, FC (reprint author), NASA, Ames Res Ctr, SETI Inst, MS 245-6, Moffett Field, CA 94035 USA. NR 24 TC 3 Z9 3 U1 0 U2 0 PU ASTRONOMICAL SOC PACIFIC PI SAN FRANCISCO PA 390 ASHTON AVE, SAN FRANCISCO, CA 94112 USA BN 1-58381-023-4 J9 ASTR SOC P PY 2000 VL 196 BP 197 EP 203 PG 7 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BQ13Y UT WOS:000087282200018 ER PT B AU Nuth, JA Rietmeijer, FJM Hallenbeck, SL Withey, PA Ferguson, F AF Nuth, JA Rietmeijer, FJM Hallenbeck, SL Withey, PA Ferguson, F BE Sitko, ML Sprague, AL Lynch, DK TI Nucleation, growth, annealing and coagulation of refractory oxides and metals: Recent experimental progress and applications to astrophysical systems SO THERMAL EMISSION SPECTROSCOPY AND ANALYSIS OF DUST, DISKS, AND REGOLITHS SE Astronomical Society of the Pacific Conference Series LA English DT Proceedings Paper CT Meeting on Thermal Emission Spectroscopy and Analysis of Dust, Disks, and Regoliths CY APR 28-30, 1999 CL LUNAR & PLANETARY INST, HOUSTON, TX SP Lunar & Planetary Inst, Natl Sci Fdn HO LUNAR & PLANETARY INST ID MAGNETICALLY ENHANCED COAGULATION; VAPOR-PHASE NUCLEATION; SMALL IRON GRAINS; SOLAR NEBULA; CIRCUMSTELLAR DISKS; SILICATE MINERALOGY; CONDENSATION; DUST; CHONDRULES; GRAPHITE AB Starting with cooling, refractory vapors diluted in significant quantities of hydrogen and helium there are four processes that most natural systems will undergo: nucleation, growth, annealing and coagulation. Although the nucleation of refractory grains remains something of an enigma, there has been considerable progress in our understanding of grain growth, annealing and coagulation over the past few years. Grain growth has been shown to produce amorphous solids of predictable composition. The rate and activation energy for the annealing of at least one type of amorphous condensate has been measured and has been applied to model the conditions leading to the observation of crystalline magnesium silicate grains by ISO. Finally, there is experimental evidence that magnetically induced grain coagulation could be an important and very widespread process in protostellar systems that might have a number of observable signatures both in meteoritic materials and via astronomical observations. We are far from quantitative understandings of any of the above processes, but are poised for considerable progress in the near future given a continuation and extension of the recent trend of successful laboratory experiments described herein. C1 NASA, Goddard Space Flight Ctr, Astrochem Branch, Greenbelt, MD 20771 USA. RP Nuth, JA (reprint author), NASA, Goddard Space Flight Ctr, Astrochem Branch, Code 691, Greenbelt, MD 20771 USA. EM joseph.nuth@gsfc.nasa.gov RI Ferguson, Frank/C-9493-2012; Nuth, Joseph/E-7085-2012 NR 73 TC 15 Z9 15 U1 0 U2 0 PU ASTRONOMICAL SOC PACIFIC PI SAN FRANCISCO PA 390 ASHTON AVE, SAN FRANCISCO, CA 94112 USA BN 1-58381-023-4 J9 ASTR SOC P PY 2000 VL 196 BP 313 EP 332 PG 20 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BQ13Y UT WOS:000087282200029 ER PT B AU Serabyn, E Colavita, MM Beichman, CA AF Serabyn, E Colavita, MM Beichman, CA BE Sitko, ML Sprague, AL Lynch, DK TI Exozodiacal disk detection potential with the Keck interferometer SO THERMAL EMISSION SPECTROSCOPY AND ANALYSIS OF DUST, DISKS, AND REGOLITHS SE ASTRONOMICAL SOCIETY OF THE PACIFIC CONFERENCE SERIES LA English DT Proceedings Paper CT Meeting on Thermal Emission Spectroscopy and Analysis of Dust, Disks, and Regoliths CY APR 28-30, 1999 CL LUNAR & PLANETARY INST, HOUSTON, TX SP Lunar & Planetary Inst, Natl Sci Fdn HO LUNAR & PLANETARY INST AB If the dust content of nearby solar systems is comparable to or larger than that of our own zodiacal disk, the thermal emission from such "exozodiacal" dust disks will significantly outshine planetary companions to nearby stars. As such, the characterization of flux levels from exozodiacal disks is a vital first step on the road to direct planet detection. To this end, a nulling interferometry mode is being implemented on the forthcoming Keck Interferometer. By interferometrically nulling out the mid-infrared radiation from the central star, attendant thermal emission from exozodiacal dust will be rendered more readily detectable. In the following, we estimate the sensitivity of the Keck interferometer to such exozodiacal dust emission. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Serabyn, E (reprint author), CALTECH, Jet Prop Lab, 171-113,4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 11 TC 6 Z9 6 U1 0 U2 0 PU ASTRONOMICAL SOC PACIFIC PI SAN FRANCISCO PA 390 ASHTON AVE, SAN FRANCISCO, CA 94112 USA BN 1-58381-023-4 J9 ASTR SOC P PY 2000 VL 196 BP 357 EP 365 PG 9 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BQ13Y UT WOS:000087282200032 ER PT S AU Halford, GR Lerch, BA Arya, VK AF Halford, GR Lerch, BA Arya, VK BE Sehitoglu, H Maier, HJ TI Thermal strain fatigue modeling of a matrix alloy for a metal matrix composite SO THERMO-MECHANICAL FATIGUE BEHAVIOR OF MATERIALS, 3RD VOL SE AMERICAN SOCIETY FOR TESTING AND MATERIALS SPECIAL TECHNICAL PUBLICATION LA English DT Proceedings Paper CT 3rd Symposium on Thermo-Mechanical Fatigue Behavior of Materials CY NOV 04-05, 1998 CL NORFOLK, VA SP Amer Soc Testing & Mat, Comm E8 Fatigue & Fracture DE metal matrix composites; fatigue (metal); thermal fatigue; thermomechanical fatigue; bithermal fatigue; low cycle fatigue; high temperature fatigue; creep fatigue; life prediction; strainrange partitioning; crack initiation; thermal expansion ID THERMOMECHANICAL FATIGUE; LIFE PREDICTION; OXIDATION; CREEP AB The Total Strain Version of the method of Strainrange Partitioning was used as the basis for modeling the thermomechanical fatigue resistance of the matrix material of the metal matrix composite, SCS-6/Ti-15-3. As prescribed by the model, the resistance was assessed through the use of bithermal creep-fatigue experiments. Bithermal temperatures of 205 and 427 degrees C were imposed. A minimal number of strain limit-controlled, in-phase PP (pure fatigue, no creep) and CP (tensile creep) as well as out-of-phase PP (pure fatigue, no creep) and PC (compressive creep) experiments were conducted on conventional, axially-loaded, cylindrical-bar specimens. Inelastic strain range versus cyclic life curves for each of the Strainrange Partitioning bithermal cycles were evaluated and found to be nominally coincident. Cyclic elastic strain range versus inelastic strain range curves as well as elastic strain range versus life curves were documented for pure-fatigue and creep-fatigue conditions. The time-dependencies of these relationships were calibrated with the available data. These results enable the construction of total strain range versus fatigue life curves for thermomechanical fatigue for in- and out-of-phasing and for any arbitrary creep-time per cycle. Results are applicable to the cyclic life prediction of metal matrix composites using the Ti-15-3 matrix material. C1 NASA, Lewis Res Ctr, Cleveland, OH 44135 USA. RP Halford, GR (reprint author), NASA, Lewis Res Ctr, Cleveland, OH 44135 USA. NR 23 TC 3 Z9 3 U1 0 U2 1 PU AMERICAN SOCIETY TESTING AND MATERIALS PI W CONSHOHOCKEN PA 100 BARR HARBOR DRIVE, W CONSHOHOCKEN, PA 19428-2959 USA SN 1040-1695 BN 0-8031-2853-3 J9 AM SOC TEST MATER PY 2000 VL 1371 BP 186 EP 203 DI 10.1520/STP15261S PG 18 WC Materials Science, Multidisciplinary; Mechanics SC Materials Science; Mechanics GA BP81F UT WOS:000086275500012 ER PT S AU Winfree, WP Cramer, KE AF Winfree, WP Cramer, KE BE Dinwiddie, RB LeMieux, DH TI Reduction of thermal data using neural networks SO THERMOSENSE XXII SE Proceedings of SPIE LA English DT Proceedings Paper CT Thermosense XXII Conference CY APR 25-27, 2000 CL ORLANDO, FL SP SPIE DE thermography; NDE; neural networks; corrosion detection ID TRANSIENT THERMOGRAPHY; SHAPE AB A scanned thermal line source is a rapid and efficient technique for detection of corrosion in aircraft components. Reconstruction of the back surface profile from the data obtained with this technique requires a nonlinear mapping. Neural networks are an effective method for performing nonlinear mappings of one parameter space to another. This paper discusses the application of neural networks to the reconstruction of back surface profiles from the data obtained from a thermal line scan. The neural network is found to be a very effective method of reconstructing arbitrary surface profiles. The network is trained on simulations of the thermal line scan technique. The trained network is then applied to both simulated and experimentally obtained data. The reconstructed profiles are in good agreement with independent characterizations of the profiles. Limitations of the reconstruction technique are illustrated by presenting results for several different configurations. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP NASA, Langley Res Ctr, MS 231, Hampton, VA 23681 USA. NR 13 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3646-1 J9 PROC SPIE PY 2000 VL 4020 BP 128 EP 136 DI 10.1117/12.381542 PG 9 WC Optics SC Optics GA BQ31Z UT WOS:000087919600016 ER PT S AU Cramer, KE Winfree, WP AF Cramer, KE Winfree, WP BE Dinwiddie, RB LeMieux, DH TI Application of the thermal line scanner to quantify material loss due to corrosion SO THERMOSENSE XXII SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Thermosense XXII Conference CY APR 25-27, 2000 CL ORLANDO, FL SP SPIE DE infrared; thermal; NDE; corrosion ID AIRCRAFT AB Recent advances in thermal imaging technology have spawned a number of new thermal NDE techniques that provide quantitative information about flaws in aircraft structures. Thermography has a number of advantages as an inspection technique for aircraft. It is a totally noncontacting, nondestructive, imaging technology capable of inspecting a large area in a matter of a few seconds. The development of fast, inexpensive image processors has aided in the attractiveness of thermography as an NDE technique. These image processors have increased the signal to noise ratio of thermography and facilitated significant advances in post-processing. The resulting digital images enable archival records for comparison with later inspections, thus providing a means of monitoring the evolution of damage in a particular structure. NASA Langley Research Center has developed a thermal NDE technique designed to image and quantitatively characterize the amount of thinning present in metallic materials. The technique involves the movement of a thermal line source across the outer surface of a sample followed by an infrared imager at a fixed distance behind the line source. Images of the material loss due to corrosion are reconstructed from measurements of the induced surface temperature variations. This paper presents a discussion of the development of the thermal imaging system as well as the techniques used to reconstruct images of flaws and to make quantitative thickness measurements. The application of the thermal line source coupled with the analysis technique represents a significant improvement over conventional thermal imaging in the quantification of flaws. Results of laboratory experiments on specimens with fabricated material loss regions are presented to demonstrate the capabilities of the technique. Additionally, field applications of the technique for both aluminum aircraft structures and steel power plant structures are presented. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Cramer, KE (reprint author), NASA, Langley Res Ctr, 3 E Taylor St,Mail Stop 231, Hampton, VA 23681 USA. NR 9 TC 4 Z9 4 U1 3 U2 4 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3646-1 J9 P SOC PHOTO-OPT INS PY 2000 VL 4020 BP 210 EP 219 DI 10.1117/12.381553 PG 10 WC Optics SC Optics GA BQ31Z UT WOS:000087919600026 ER PT S AU Sankovic, JM AF Sankovic, JM GP ESA ESA ESA TI NASA technology investments in electric propulsion: New directions in the new millennium SO THIRD INTERNATIONAL CONFERENCE ON SPACECRAFT PROPULSION SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 3rd International Conference on Spacecraft Propulsion CY OCT 10-13, 2000 CL CANNES, FRANCE SP CNES, European Space Agcy AB The last decade was a period of unprecedented acceptance of NASA developed electric propulsion by the user community. The benefits of high performance electric propulsion systems are now widely recognized, and new technologies have been accepted across the community. NASA clearly recognizes the need for new, high performance, electric propulsion technologies for future solar system missions and is sponsoring aggressive efforts in this area. These efforts are mainly conducted under the Office of Aerospace Technology. Plans over the next six years include the development of next generation ion thrusters for end of decade missions. Additional efforts are planned for the development of very high power thrusters, including magnetoplasmadynamic, pulsed inductive, and VASIMR, and clusters of Hall thrusters. In addition to the in-house technology efforts, NASA continues to work closely with both supplier and user communities to maximize the acceptance of new technology in a timely and cost-effective manner. This paper provides an overview of NASA's activities in the area of electric propulsion with an emphasis on future program directions. C1 NASA, John H Glenn Res Ctr Lewis Field, Cleveland, OH 44135 USA. RP Sankovic, JM (reprint author), NASA, John H Glenn Res Ctr Lewis Field, Cleveland, OH 44135 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-701-1 J9 ESA SP PUBL PY 2000 VL 465 BP 7 EP 19 PG 13 WC Engineering, Aerospace; Physics, Fluids & Plasmas SC Engineering; Physics GA BS05L UT WOS:000168480600001 ER PT S AU Oleson, SR Sankovic, JM AF Oleson, SR Sankovic, JM GP ESA ESA ESA TI Advanced Hall electric propulsion for future in-space transportation SO THIRD INTERNATIONAL CONFERENCE ON SPACECRAFT PROPULSION SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 3rd International Conference on Spacecraft Propulsion CY OCT 10-13, 2000 CL CANNES, FRANCE SP CNES, European Space Agcy AB The Hall thruster is an electric propulsion device used for multiple in-space applications including orbit raising, on-orbit maneuvers, and de-orbit functions. These in-space propulsion functions are currently performed by toxic hydrazine monopropellant or hydrazine derivative/nitrogen tetroxide bi-propellant thrusters. The Hall thruster operates nominally in the 1500 s specific impulse regime. It provides greater thrust to power than conventional gridded ion engines, thus reducing trip times and operational life when compared to that technology in Earth orbit applications. The technology in the far term, by adding a second acceleration stage, has shown promise of providing over 4000s Isp, the regime of the gridded ion engine and necessary for deep space applications. The Hall thruster system consists of three parts, the thruster, the power processor, and the propellant system. The technology is operational and commercially available at the 1.5 kW power level and 5 kW application is underway. NASA is looking toward 10 kW and eventually 50 kW-class engines for ambitious space transportation applications. The former allows launch vehicle step-down for GEO missions and demanding planetary missions such as Europa Lander, while the latter allows quick all-electric propulsion LEO to GEO transfers and non-nuclear transportation human Mars missions. C1 NASA, Glenn Res Ctr Lewis Field, Cleveland, OH 44135 USA. RP Oleson, SR (reprint author), NASA, Glenn Res Ctr Lewis Field, Cleveland, OH 44135 USA. NR 10 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-701-1 J9 ESA SP PUBL PY 2000 VL 465 BP 717 EP 726 PG 10 WC Engineering, Aerospace; Physics, Fluids & Plasmas SC Engineering; Physics GA BS05L UT WOS:000168480600089 ER PT S AU Gates, TS Brinson, LC Whitley, KS Bai, T AF Gates, TS Brinson, LC Whitley, KS Bai, T BE Schapery, RA Sun, CT TI Aging during elevated temperature stress relaxation of IM7/K3B composite SO TIME DEPENDENT AND NONLINEAR EFFECTS IN POLYMERS AND COMPOSITES SE AMERICAN SOCIETY FOR TESTING AND MATERIALS SPECIAL TECHNICAL PUBLICATION LA English DT Proceedings Paper CT Symposium on Time Dependent and Nonlinear Effects inPolymers and Composites CY MAY 04-05, 1998 CL ATLANTA, GA SP Amer Soc Testing & Mat, Comm D-30 Composite Mat DE polymeric composites; stress relaxation; physical aging; creep ID POLYMERS; CREEP; BEHAVIOR; PERFORMANCE; TIME AB An experimental and analytical study was performed on the use of tension stress relaxation to characterize the effects of elevated temperature and physical aging on the linear viscoelastic behavior of IM7/K3B. Isothermal stress relaxation tests on a [+/-45](2s) laminate were run over a range of sub-glass transition (T-g) temperatures. The sequenced test method most commonly employed for creep was successfully adapted to the stress relaxation test and from those sequenced tests, material parameters such as aging shift rates and momentary master curve coefficients were developed for use in the analytical model. The analytical viscoelastic model was based on classical lamination theory, the hereditary integral formulation type constitutive law, and affective time theory. Time-aging time superposition, effective time theory, and viscoelasticity were used to determine the physical aging related material parameters from the relaxation tests. Results were compared to previously measured isothermal creep compliance results via known relationships for the convolution of compliance to modulus. Time-temperature superposition was also used to evaluate master curves and related shift factors. All of the results illustrated that the relative influence of temperature and aging must be considered when assessing long-term performance and that the loading mode may have to be considered when accurate predictions of viscoelastic behavior are required. C1 NASA, Langley Res Ctr, Mat & Mech Branch, Hampton, VA 23681 USA. RP Gates, TS (reprint author), NASA, Langley Res Ctr, Mat & Mech Branch, MS 188E, Hampton, VA 23681 USA. RI Brinson, L Catherine/B-1315-2013 OI Brinson, L Catherine/0000-0003-2551-1563 NR 20 TC 2 Z9 2 U1 0 U2 4 PU AMERICAN SOCIETY TESTING AND MATERIALS PI W CONSHOHOCKEN PA 100 BARR HARBOR DRIVE, W CONSHOHOCKEN, PA 19428-2959 USA SN 1040-1695 BN 0-8031-2601-8 J9 AM SOC TEST MATER PY 2000 VL 1357 BP 141 EP 159 DI 10.1520/STP15833S PG 19 WC Materials Science, Characterization & Testing; Materials Science, Composites; Polymer Science SC Materials Science; Polymer Science GA BP76D UT WOS:000086082200008 ER PT S AU Castelli, MG Sutter, JK Benson, D AF Castelli, MG Sutter, JK Benson, D BE Schapery, RA Sun, CT TI Durability and damage tolerance of a polyimide chopped fiber composite subjected to thermomechanical fatigue missions and creep loadings SO TIME DEPENDENT AND NONLINEAR EFFECTS IN POLYMERS AND COMPOSITES SE AMERICAN SOCIETY FOR TESTING AND MATERIALS SPECIAL TECHNICAL PUBLICATION LA English DT Proceedings Paper CT Symposium on Time Dependent and Nonlinear Effects inPolymers and Composites CY MAY 04-05, 1998 CL ATLANTA, GA SP Amer Soc Testing & Mat, Comm D-30 Composite Mat DE thermomechanical fatigue; damage tolerance; sheet molding compound; PMR-15; creep; residual properties; micro-structural damage; fiber distribution; graphite fiber; T650-35; polymer matrix composites AB Although polyimide based composites have been used for many years in a wide variety of-elevated temperature applications, very little work has been done to examine the durability and damage behavior under more prototypical thermomechanical fatigue (TMF) loadings. Synergistic effects resulting from simultaneous temperature and load cycling can potentially lead to enhanced, if:not,unique., damage modes and contribute to a number of nonlinear deformation responses. The goal of this research waste examine the effects of a TMF loading spectrum, representative of a gas turbine engine compressor application, on a polyimide sheet molding compound (SMC). High performance SMCs present alternatives to prepreg forms with great potential for low cost component production through less labor intensive, more easily automated manufacturing. To examine the issues involved. with TMF, a detailed experimental investigation was conducted to characterize the durability of a T650-35/PMR-15 SMC subjected to TMF mission cycle loadings. Fatigue. damage progression was tracked through macroscopic deformation and elastic stiffness: Additional properties, Such as the glass transition temperature (T-g) and dynamic mechanical properties were examined. The fiber distribution orientation was characterized through a detailed quantitative image analysis. Damage tolerance was quantified on the basis of residual static tensile properties after a prescribed number of TMF missions. Detailed micro-structural examinations were conducted using optical and scanning electron microscopy to characterize the local damage. The:imposed baseline TMF missions had only a modest impact on inducing fatigue damage with no statistically significant degradation occurring in the measured macroscopic properties: Micro-structural damage was, however, observed subsequent to 100 h of TMF cycling which consisted primarily of fiber debonding and transverse cracking local to predominantly transverse fiber bundles. The TMF loadings did introduce creep related effects (strain accumulation) which led to rupture in some of the more aggressive stress scenarios examined. In some cases, this creep behavior occurred at temperatures in excess of 150 degrees C below commonly cited values for T-g. Thermomechanical exploratory creep tests revealed that the SMC was subject to time dependent deformation at stress/temperature thresholds of 150 MPa/230 degrees C and 170 MPa/180 degrees C. C1 NASA, Lewis Res Ctr, Ohio Aerosp Inst, Cleveland, OH 44135 USA. RP Castelli, MG (reprint author), NASA, Lewis Res Ctr, Ohio Aerosp Inst, MS 49-7, Cleveland, OH 44135 USA. NR 23 TC 1 Z9 1 U1 1 U2 3 PU AMERICAN SOCIETY TESTING AND MATERIALS PI W CONSHOHOCKEN PA 100 BARR HARBOR DRIVE, W CONSHOHOCKEN, PA 19428-2959 USA SN 1040-1695 BN 0-8031-2601-8 J9 AM SOC TEST MATER PY 2000 VL 1357 BP 285 EP 309 DI 10.1520/STP15839S PG 25 WC Materials Science, Characterization & Testing; Materials Science, Composites; Polymer Science SC Materials Science; Polymer Science GA BP76D UT WOS:000086082200014 ER PT S AU Reeder, JR Allen, DH Bradley, WL AF Reeder, JR Allen, DH Bradley, WL BE Schapery, RA Sun, CT TI Accelerated strength testing of thermoplastic composites SO TIME DEPENDENT AND NONLINEAR EFFECTS IN POLYMERS AND COMPOSITES SE AMERICAN SOCIETY FOR TESTING AND MATERIALS SPECIAL TECHNICAL PUBLICATION LA English DT Proceedings Paper CT Symposium on Time Dependent and Nonlinear Effects inPolymers and Composites CY MAY 04-05, 1998 CL ATLANTA, GA SP Amer Soc Testing & Mat, Comm D-30 Composite Mat DE accelerated testing; superposition; polymer matrix composites; strength ID MEDIA AB Constant ramp strength tests on unidirectional thermoplastic composite specimens oriented in the 90 degrees direction were conducted at constant temperatures ranging from 149 degrees C to 232 degrees C. Ramp rates spanning 5 orders of magnitude were tested so that failures occurred in the range from 0:5 s to 24 h (0.5 to 100 000 MPa/sec). Below 204 degrees C, time-temperature superposition held allowing strength at longer times to be estimated from strength tests at shorter times but higher temperatures. The data indicated that a 50% drop in strength might be expected for this material when the test time is increased by 9 orders of magnitude. The Shift factors derived from compliance data applied well to the strength results. To explain the link between compliance and strength, a viscoelastic fracture model was investigated. The model, which used compliance as input, was found to fit the strength data only if the critical fracture energy was allowed to vary with stress rate. This variation in the critical parameter severely limits its use in developing a robust time-dependent strength model. The significance of this research is therefore seen as providing both the indication that a more versatile acceleration method for strength can be developed and the evidence that such a method is needed. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Reeder, JR (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. NR 16 TC 0 Z9 0 U1 0 U2 0 PU AMERICAN SOCIETY TESTING AND MATERIALS PI W CONSHOHOCKEN PA 100 BARR HARBOR DRIVE, W CONSHOHOCKEN, PA 19428-2959 USA SN 1040-1695 BN 0-8031-2601-8 J9 AM SOC TEST MATER PY 2000 VL 1357 BP 318 EP 337 DI 10.1520/STP15841S PG 20 WC Materials Science, Characterization & Testing; Materials Science, Composites; Polymer Science SC Materials Science; Polymer Science GA BP76D UT WOS:000086082200016 ER PT B AU Wolpert, DH Macready, WG AF Wolpert, DH Macready, WG BE BarYam, Y TI Self-dissimilarity: An empirically observable complexity measure SO UNIFYING THEMES IN COMPLEX SYSTEMS SE NEW ENGLAND COMPLEX SYSTEMS INSTITUTE SERIES ON COMPLEXITY LA English DT Proceedings Paper CT 2nd International Conference on Complex Systems CY OCT 25-30, 1998 CL NEW ENGLAND COMPLEX SYST INST, NASHUA, NH SP Oxford Univ Press, Natl Sci Fdn, Coopers & Lybrand Consulting, McKinsey & Co, Addison Wesley Longman Publisher, John Benjamin Publisher, Santa Fe Inst, Soc Chaos Theory Psychol & Life Sci, Boston Univ, Coll Engn HO NEW ENGLAND COMPLEX SYST INST AB For many systems characterized as "complex/living/intelligent" the spatiotemporal patterns exhibited on different scales differ markedly from one another. For example the biomass distribution of a human body "looks very different" depending on the spatial scale at which one examines that biomass. Conversely, the density patterns at different scales in "dead/simple" systems (e.g., gases, mountains, crystals) do not vary significantly from one another. Accordingly, we argue that the degrees of self-dissimilarity between the various scales with which a system is examined constitute a complexity "signature" of that system. Such signatures can be empirically measured for many real-world data sets concerning spatio-temporal densities, be they mass densities, species densities, or symbol densities. This allows one to compare the complexity signatures of wholly different kinds of systems (e.g., systems involving information density in a digital computer, vs. species densities in a rain-forest, vs. capital density in an economy, etc.). Such signatures can also be clustered, to provide an empirically determined taxonomy of "kinds of systems" that share organizational traits. The precise measure of dissimilarity between scales that we propose is the amount of extra information on one scale beyond that which exists on a different scale. This "added information" is perhaps most naturally determined using a maximum entropy inference of the distribution of patterns at the second scale, based on the provided distribution at the first scale. We briefly discuss using our measure with Ether inference mechanisms (e.g., Kolmogorov complexity-based inference). C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Wolpert, DH (reprint author), NASA, Ames Res Ctr, MS269-2, Moffett Field, CA 94035 USA. NR 14 TC 1 Z9 1 U1 1 U2 2 PU PERSEUS PUBLISHING PI CAMBRIDGE PA 11 CAMBRIDGE CENTER, CAMBRIDGE, MA 02142 USA BN 0-7382-0049-2 J9 NEW ENGL COMPL SYST PY 2000 BP 625 EP 643 PG 19 WC Mathematics, Applied SC Mathematics GA BP77W UT WOS:000086160100053 ER PT B AU Dietrich, S Long, N Dittrich, D AF Dietrich, S Long, N Dittrich, D GP USENIX USENIX TI Analyzing distributed denial of service tools: The shaft case SO USENIX ASSOCIATION PROCEEDINGS OF THE FOURTEENTH SYSTEMS ADMINISTRATION CONFERENCE (LISA XIV) LA English DT Proceedings Paper CT 14th Systems Administration Conference CY DEC 03-08, 2000 CL NEW ORLEANS, LA SP USENIX Assoc, Syst Adm Guild AB In this paper we present an analysis of Shaft, an example of malware used in distributed denial of service (DDoS) attacks. This relatively recent occurrence combines well-known denial of service attacks (such as TCP SYN flood, smurf, and UDP flood) with a distributed and coordinated approach to create a powerful program, capable of slowing network communications to a grinding halt. Denial of service attack programs, root kits, and network sniffers have been around in the computer underground for a very long time. They have not gained nearly the same level of attention by the general public as did the Morris Internet Worm of 1988, but have slowly progressed in their development. As more and more systems have come to be required for business, research, education, the basic functioning of government, and now entertainment and commerce from people's homes, the increasingly large number of vulnerable systems has converged with the development of these tools to create a situation that resulted in distributed denial of service attacks that took down the largest e-commerce and media sites on the Internet. In contrast, we provide a comparative analysis of several distributed denial of service tools (e.g., Trinoo, TFN, Stacheldraht, and Mstream), look at emerging countermeasures against some of these tools. We look at practical examples of these techniques, provide some examples from test environments and finally talk about future trends of these distributed tools. C1 NASA, Goddard Space Flight Ctr, Raytheon ITSS, Greenbelt, MD 20771 USA. RP Dietrich, S (reprint author), NASA, Goddard Space Flight Ctr, Raytheon ITSS, Greenbelt, MD 20771 USA. NR 28 TC 13 Z9 15 U1 0 U2 0 PU USENIX ASSOC PI BERKELEY PA SUITE 215, 2560 NINTH ST, BERKELEY, CA 94710 USA BN 1-880446-13-8 PY 2000 BP 329 EP 339 PG 11 WC Computer Science, Hardware & Architecture; Computer Science, Software Engineering SC Computer Science GA BR87E UT WOS:000167889500032 ER PT S AU Mather, J AF Mather, J BE Breckinridge, JB Jakobsen, P TI Next Generation Space Telescope SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE infrared; space; telescope; instrumentation; NGST; NASA ID STAR-FORMING GALAXIES; LYMAN-BREAK GALAXIES; HUBBLE DEEP FIELD; HIGH-REDSHIFT; DATA REDUCTION; Z-GREATER-THAN-3; METALLICITY; POPULATION; PHOTOMETRY; EVOLUTION AB The Next Generation Space Telescope (NGST), planned for launch in 2009, will be an 8-m class radiatively cooled infrared telescope at the Lagrange point L2. It will cover the wavelength range from 0.6 to 28 mu m with cameras and spectrometers, to observe the first luminous objects after the Big Bang, and the formation, growth, clustering, and evolution of galaxies, stars, and protoplanetary clouds, leading to better understanding of our own Origins. It will seek evidence of the cosmic dark matter through its gravitational effects. With an aperture three times greater than the Hubble Space Telescope, it will provide extraordinary advances in capabilities and enable the discovery of many new phenomena. It is a joint project of the NASA, ESA, and CSA, and scientific operations will be provided by the Space Telescope Science Institute. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Mather, J (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM john.mather@gsfc.nasa.gov NR 39 TC 12 Z9 12 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3638-0 J9 PROC SPIE PY 2000 VL 4013 BP 2 EP 16 DI 10.1117/12.394042 PG 15 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600001 ER PT S AU Leisawitz, D Danchi, W DiPirro, M Feinberg, LD Gezari, D Hagopian, M Langer, WD Mather, JC Moseley, SH Shao, M Silverberg, RF Staguhn, J Swain, MR Yorke, HW Zhang, XL AF Leisawitz, D Danchi, W DiPirro, M Feinberg, LD Gezari, D Hagopian, M Langer, WD Mather, JC Moseley, SH Shao, M Silverberg, RF Staguhn, J Swain, MR Yorke, HW Zhang, XL BE Breckinridge, JB Jakobsen, P TI Scientific motivation and technology requirements for the SPIRIT and SPECS far-infrared/submillimeter space interferometers SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE infrared; submillimeter; interferometry; detectors; formation flying; cryogenic optics ID BACKGROUND EXPERIMENT SEARCH; FIRAS AB Far infrared interferometers in space would enable extraordinary measurements of the early universe, the formation of galaxies, stars, and planets, and would have great discovery potential. Since half the luminosity of the universe and 98% of the photons released since the Big Bang are now observable at far IR wavelengths (40 - 500 mu m), and the Earth's atmosphere prevents sensitive observations from the ground, this is one of the last unexplored frontiers of space astronomy. We present the engineering and technology requirements that stem from a set of compelling scientific goals and discuss possible configurations for two proposed NASA missions, the Space Infrared Interferometric Telescope (SPIRIT) and the Submillimeter Probe of the Evolution of Cosmic Structure (SPECS). C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Leisawitz, D (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 14 TC 31 Z9 32 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 36 EP 46 DI 10.1117/12.393957 PG 11 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600004 ER PT S AU Gallagher, DB Simmons, LL AF Gallagher, DB Simmons, LL BE Breckinridge, JB Jakobsen, P TI Development of the Space Infrared Telescope Facility (SIRTF) SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE SIRTF; infrared observatory; space telescope; infrared astronomy AB The Space Infrared Telescope Facility (SIRTF) is in the middle of the development phase and on track for a December, 2001 launch. This exciting mission takes advantage of innovative engineering choices to make groundbreaking science available in a cost-effective way. SIRTF, the fourth of NASA's Great Observatories, takes advantage of tremendous advances in infrared sensor technology as well as a high level of observatory efficiency in order to promise a rich scientific legacy. The presentation provides an overview of the SIRTF Project and describes the Cryogenic Telescope, Science Instruments, and Spacecraft. In addition, investigation opportunities for the scientific community are described. A detailed report on the current status and future plans is also provided. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Gallagher, DB (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 4 TC 9 Z9 9 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 80 EP 89 DI 10.1117/12.393970 PG 10 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600008 ER PT S AU Pearson, JC Guesten, R Klein, T Whyborn, ND AF Pearson, JC Guesten, R Klein, T Whyborn, ND BE Breckinridge, JB Jakobsen, P TI The local oscillator system for the heterodyne instrument for FIRST (HIFI) SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE sub-millimeter; heterodyne; far-infrared; FIRST; instruments ID POWER-AMPLIFIER MODULE; FREQUENCY-MULTIPLIERS AB The Heterodyne Instrument for FIRST (HIFI) is comprised of five SIS receiver channels covering 480-1250 GHz and two HEB receiver channels covering parts of 1410-1910 GHz and 2400-2700 GHz. Two local oscillator sub-bands derived from a common synthesizer will pump each receiver band. The synthesizer, control electronics and frequency distribution will be performed in the spacecraft service module. The service module will be connected to the local oscillator unit on the outside of the cryostat with a WR-28 waveguide for each of the 14 local oscillator sub-bands. The local oscillator unit will be passively cooled and thermally isolated from the cryostat wall. The module is comprised of seven units, one for each receiver band, containing two multiplier chains consisting of a k- to w-band multiplier, a MMIC power amplifier operating in one of five bands between 71 and 113 GHz, the high frequency multipliers, launching optics and electrical distribution. The entire assembly will be cooled to 120K. The local oscillator system has the two fold technical challenge of providing broad band frequency coverage at very high frequencies. This will be achieved through the use of high power GaAs MMIC amplifiers and planar diode multiplier technology in a passively cooled 120 Kelvin environment. The design criteria and the resulting overall system design will be presented along with a programmatic view of the development program and development progress. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Pearson, JC (reprint author), CALTECH, Jet Prop Lab, Mail Stop 183-301,4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 19 TC 12 Z9 12 U1 0 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 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 264 EP 274 DI 10.1117/12.393982 PG 11 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600025 ER PT S AU Samoska, L Gaier, T Peralta, A Weinreb, S Bruston, J Mehdi, I Chen, YC Liao, HH Nishimoto, M Lai, R Wang, H Leong, YC AF Samoska, L Gaier, T Peralta, A Weinreb, S Bruston, J Mehdi, I Chen, YC Liao, HH Nishimoto, M Lai, R Wang, H Leong, YC BE Breckinridge, JB Jakobsen, P TI MMIC power amplifiers as local oscillator drivers for FIRST SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE power amplifiers; MMIC; local oscillators; terahertz; FIRST; HIFI; millimeter-wave; 100 GHz; PHEMT AB The Heterodyne Instrument (HIFI) for the Far-Infrared and Sub-millimeter Telescope (FIRST) requires local oscillators well into the terahertz frequency range. The mechanism to realize the local oscillators will involve synthesizers, active multiplier chains (AMC's) with output frequencies from 71-112.5 GHz, power amplifiers to amplify the AMC signals, and chains of Schottky diode multipliers to achieve terahertz frequencies. We will present the latest state-of-the-art results on 70-115 GHz Monolithic Millimeter-wave Integrated Circuit (MMIC) power amplifier technology. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Samoska, L (reprint author), CALTECH, Jet Prop Lab, M-S 168-314,4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 10 TC 16 Z9 16 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 275 EP 284 DI 10.1117/12.393983 PG 10 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600026 ER PT S AU Bruston, J Schlecht, E Maestrini, A Maiwald, F Martin, SC Smith, RP Mehdi, I Siegel, PH Pearson, J AF Bruston, J Schlecht, E Maestrini, A Maiwald, F Martin, SC Smith, RP Mehdi, I Siegel, PH Pearson, J BE Breckinridge, JB Jakobsen, P TI Development of 200 GHz to 2.7 THz multiplier chains for submillimeter-wave heterodyne receivers SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE submillimeter; Schottky; multipliers; FIRST; HIFI; doubler; tripler; membrane; GaAs; diode ID DIODE AB Several astrophysics and Earth observation space missions planned for the near future will require submillimeter-wave heterodyne radiometers for spectral line observations. One of these, the Far InfraRed and Submillimeter Telescope (FIRST) will perform high-sensitivity, high-resolution spectroscopy in the 400 to 2700 GHz range with a seven channel super conducting heterodyne receiver complement. The local oscillators for all these channels will be constructed around state-of-the-art GaAs power amplifiers in the 71 to 115 GHz range, followed by planar Schottky diode multiplier chains. The Jet Propulsion Laboratory is responsible for developing the multiplier chains for the 1.2, 1.7, and 2.7 THz bands. This paper will focus on the designs and technologies being developed to enhance the current state-of-the-art, which is based on discrete planar or whisker contacted GaAs Schottky diode chips mounted in waveguide blocks. We are proposing a number of new planar integrated circuit and device topologies to implement multipliers at these high frequencies. Approaches include substrateless, framed and frameless GaAs membrane circuitry with single, and multiple planar integrated Schottky diodes. Circuits discussed include 200 and 400 GHz doublers, a 1.2 THz tripler and a 2.4 THz doubler. Progress to date, with the implications of this technology development for future Earth and space science instruments, is presented. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Bruston, J (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 21 TC 6 Z9 6 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 285 EP 295 DI 10.1117/12.393985 PG 11 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600027 ER PT S AU Seiffert, MD Gallego, JD Fernandez, IL Whyborn, ND Pearson, JC AF Seiffert, MD Gallego, JD Fernandez, IL Whyborn, ND Pearson, JC BE Breckinridge, JB Jakobsen, P TI IF amplifier stability for the Heterodyne Instrument for FIRST (HIFI) SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE FIRST; HIFI; heterodyne instrument; amplifier stability ID FREQUENCY; NOISE AB The Heterodyne Instrument for FIRST (HIFI) is a heterodyne receiver system which has an intermediate frequency (IF) amplifier that will likely exhibit 1/f-type gain fluctuations. Although the level of fluctuation is very small, wideband spectral observations require exceptional stability. A methodology for measuring 1/f fluctuations is described along with measurements of two amplifiers. Comparisons are made with previous 1/f measurements of HEMT amplifiers. The implications for HIFI are described. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Seiffert, MD (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 9 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 296 EP + DI 10.1117/12.393986 PG 9 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600028 ER PT S AU Cheng, ES Hill, RJ MacKenty, J Cawley, L Knezek, P Kutina, R Lisse, C Lupie, O Robberto, M Stiavelli, M O'Connell, R Balick, B Bond, H Calzetti, D Carollo, M Disney, M Dopita, M Frogel, J Hall, D Hester, J Holtzman, J Luppino, G McCarthy, P Paresce, F Saha, A Silk, J Trauger, J Walker, A Whitmore, B Windhorst, R Young, E AF Cheng, ES Hill, RJ MacKenty, J Cawley, L Knezek, P Kutina, R Lisse, C Lupie, O Robberto, M Stiavelli, M O'Connell, R Balick, B Bond, H Calzetti, D Carollo, M Disney, M Dopita, M Frogel, J Hall, D Hester, J Holtzman, J Luppino, G McCarthy, P Paresce, F Saha, A Silk, J Trauger, J Walker, A Whitmore, B Windhorst, R Young, E BE Breckinridge, JB Jakobsen, P TI Wide-field camera 3 for the Hubble Space Telescope SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE Hubble Space Telescope; HST; instrument; CCD; MCT AB In June 1997, NASA made the decision to extend the end of the Hubble Space Telescope (HST) mission from 2005 until 2010. As a result, the age of the instruments on board the HST became a consideration. After careful study, NASA decided to ensure the imaging capabilities of the HST by replacing the Wide Field Planetary Camera 2 (WFPC2) with a low-cost facility instrument, the Wide Field Camera 3 (WFC3). This paper provides an overview of the scientific goals and capabilities of the instrument. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Cheng, ES (reprint author), NASA, Goddard Space Flight Ctr, Code 685, Greenbelt, MD 20771 USA. RI Lisse, Carey/B-7772-2016; Dopita, Michael/P-5413-2014 OI Lisse, Carey/0000-0002-9548-1526; Dopita, Michael/0000-0003-0922-4986 NR 0 TC 4 Z9 4 U1 1 U2 4 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 367 EP 373 DI 10.1117/12.394020 PG 7 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600036 ER PT S AU Koch, DG Borucki, W Dunham, E Jenkins, J Webster, L Witteborn, F AF Koch, DG Borucki, W Dunham, E Jenkins, J Webster, L Witteborn, F BE Breckinridge, JB Jakobsen, P TI CCD photometry tests for a mission to detect Earth-size planets in the extended solar neighborhood SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE extrasolar planets; Earth-size planets; photometry; CCDs; planetary transits ID KEPLER AB The thirty or so extrasolar planets that have been discovered to date are all about as large as Jupiter or larger. Finding Earth-size planets is a substantially more difficult task. We propose the use of spacebased differential photometry to detect the periodic changes in brightness of several hours duration caused by planets transiting their parent stars. The change in brightness for a Sun-Earth analog transit is 8x10(-5) We describe the instrument and mission concepts that will monitor 100,000 main-sequence stars and detect on the order of 500 Earth-size planets, if terrestrial planets are common in the extended solar neighborhood. We have performed and will discuss end-to-end laboratory measurements that demonstrate the feasibility of differential photometry under realistic operating conditions. The tests included a realistic star field in which individual transits can be generated, fast optics with a realistic point spread function, and a flight-type back-illuminated CCD. Spacecraft motion was simulated using piezoelectric transducers. Data acquisition and processing used the same methods as planned for the space mission. A system-level differential-photometric precision of 10(-5) has been demonstrated under realistic conditions. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Koch, DG (reprint author), NASA, Ames Res Ctr, MS 245-6, Moffett Field, CA 94035 USA. NR 12 TC 16 Z9 16 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 508 EP 519 DI 10.1117/12.394034 PG 12 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600051 ER PT S AU Kimble, RA Goudfrooij, P Gilliland, RL AF Kimble, RA Goudfrooij, P Gilliland, RL BE Breckinridge, JB Jakobsen, P TI Radiation damage effects on the CCD detector of the space telescope imaging spectrograph SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE CCD; radiation damage; charge transfer efficiency; hot pixels; HST; STIS AB The CCD detector in the Space Telescope Imaging Spectrograph (STIS) on board the Hubble Space Telescope is a backside-illuminated, 1024 x 1024 pixel device developed by Scientific Imaging Technologies for the STIS program. It supports a wide-ranging observing program of imaging and spectroscopy over the 200-1000 nm wavelength range at the high angular resolution of HST. In the three years since launch, radiation damage to the CCD (primarily due to high energy protons encountered in crossings of the South Atlantic Anomaly) has caused a degradation in the charge transfer efficiency (CTE) and an increase in the dark current. The growth in "hot pixel" count has been readily observable over the entire period since launch; the CTE degradation has become apparent more slowly, as it has evolved with time and as in-flight calibration test methods have improved. We report here on the calibration tests developed to measure the CTE performance in flight, on the results of those tests, on the monitoring of the CCD dark current, and on potential amelioration strategies for minimizing the scientific impact of the decline in STIS CCD performance. C1 Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Kimble, RA (reprint author), Goddard Space Flight Ctr, Code 681, Greenbelt, MD 20771 USA. NR 6 TC 22 Z9 22 U1 0 U2 2 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 532 EP 544 DI 10.1117/12.393973 PG 13 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600053 ER PT S AU Redding, D Basinger, S Cohen, D Lowman, A Shi, F Bely, P Bowers, C Burg, R Burns, L Davila, P Dean, B Mosier, G Norton, T Petrone, P Perkins, B Wilson, M AF Redding, D Basinger, S Cohen, D Lowman, A Shi, F Bely, P Bowers, C Burg, R Burns, L Davila, P Dean, B Mosier, G Norton, T Petrone, P Perkins, B Wilson, M BE Breckinridge, JB Jakobsen, P TI Wavefront control for a segmented deployable space telescope SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc AB By segmenting and folding the primary mirror, quite large telescopes can be packed into the nose cone of a rocket. Deployed after launch, initial optical performance can be quite poor, due to deployment errors, thermal deformation, fabrication errors and other causes. We describe an automatic control system for capturing, aligning, phasing, and deforming the optics of such a telescope, going from initial cm-level wavefront errors to diffraction-limited observatory operations. This system was developed for the Next Generation Space Telescope and is being tested on the NGST Wavefront Control Testbed. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Redding, D (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 21 TC 12 Z9 12 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 546 EP 558 DI 10.1117/12.393971 PG 13 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600054 ER PT S AU Sandford, S Greene, T Allamandola, L Arno, R Bregman, J Cox, S Davis, PK Gonzales, A Haas, M Hanel, R Hines, M Hudgins, D Jackson, R Kittel, P Lozier, D Maa, S McCreight, C AF Sandford, S Greene, T Allamandola, L Arno, R Bregman, J Cox, S Davis, PK Gonzales, A Haas, M Hanel, R Hines, M Hudgins, D Jackson, R Kittel, P Lozier, D Maa, S McCreight, C BE Breckinridge, JB Jakobsen, P TI An explorer-class astrobiology mission SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE Astrobiology; infrared spectroscopy; Explorers; interstellar organics; telescope; spectrometer ID POLYCYCLIC AROMATIC-HYDROCARBONS; DIFFUSE INTERSTELLAR-MEDIUM AB In this paper we describe a potential new Explorer-class space mission, the AstroBiology Explorer (ABE), consisting of a relatively modest dedicated space observatory having a 50 cm aperture primary mirror which is passively cooled to T<65 K, resides in a low-background orbit (heliocentric orbit at 1 AU, Earth drift-away), and is equipped with a suite of three moderate resolution spectrographs equipped with first-order cross-dispersers and large format (1024x1024 pixel) near- and mid-IR detector arrays cooled by a modest amount of cryogen. Such a system would be capable of addressing outstanding problems in Astrochemistry and Astrophysics that are particularly relevant to Astrobiology and addressable via astronomical observation. The observational program of this mission would make fundamental scientific progress in each of the key areas of the cosmic history of molecular carbon, the distribution and chemistry of organic compounds in the diffuse and dense interstellar media, and the evolution of ices and organic matter in young planetary systems. ABE could make fundamental progress in all of these areas by conducting an approximately one year mission to obtain a coordinated set of infrared spectroscopic observations over the 2.5-20 mu m spectral range at spectral resolutions of R greater than or equal to 1000 of approximately 1000 galaxies, stars, planetary nebulae, and young star planetary systems. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Sandford, S (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 12 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 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 604 EP 615 DI 10.1117/12.393974 PG 12 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600060 ER PT S AU Basinger, SA Redding, DC Lowman, AE Burns, LA Liu, K Cohen, D AF Basinger, SA Redding, DC Lowman, AE Burns, LA Liu, K Cohen, D BE Breckinridge, JB Jakobsen, P TI Performance of wavefront sensing and control algorithms on a segmented telescope testbed SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE wavefront sensing; phase retrieval; Next Generation Space Telescope; phase unwrapping; adaptive optics ID GENERATION SPACE TELESCOPE AB We have developed a focus-diverse phase retrieval algorithm to measure and correct wavefront errors in segmented telescopes, such as the Next Generation Space Telescope. These algorithms incorporate new phase unwrapping techniques imbedded in the phase retrieval algorithms to measure aberrations larger than one wave. Through control of a deformable mirror and other actuators, these aberrations are successfully removed from the system to make the system diffraction limited. Results exceed requirements for the Wavefront Control Testbed. An overview of these techniques and performance results on the Wavefront Control Testbed are presented. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Basinger, SA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 5 TC 12 Z9 12 U1 1 U2 2 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 749 EP 756 DI 10.1117/12.394010 PG 8 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600076 ER PT S AU Shi, F Redding, D Bowers, C Lowman, A Basinger, S Norton, T Petrone, P Davila, P Wilson, M Boucarut, R AF Shi, F Redding, D Bowers, C Lowman, A Basinger, S Norton, T Petrone, P Davila, P Wilson, M Boucarut, R BE Breckinridge, JB Jakobsen, P TI DCATT dispersed fringe sensor: Modeling and experimenting with the transmissive phase plates SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE space telescope; wavefront detection; dispersed fringe sensor AB Control algorithms developed for coarse phasing the segmented mirrors of the Next Generation Space Telescope (NGST) are being tested in realistic modeling and on the NGST wavefront control testbed, also known as DCATT. A dispersed fringe sensor (DFS) is used to detect piston errors between mirror segments during the initial coarse phasing. Both experiments and modeling have shown that the DFS provides an accurate measurement of piston errors over a range from just under a millimeter to well under a micron. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Shi, F (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 4 TC 12 Z9 13 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 757 EP 762 DI 10.1117/12.394011 PG 6 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600077 ER PT S AU Bowers, C Davila, P Dean, B Perkins, B Wilson, M Redding, D Basinger, S Cohen, D Lowman, A Shi, F Burns, L Fitzmaurice, M Norton, T Petrone, P Wheeler, L AF Bowers, C Davila, P Dean, B Perkins, B Wilson, M Redding, D Basinger, S Cohen, D Lowman, A Shi, F Burns, L Fitzmaurice, M Norton, T Petrone, P Wheeler, L BE Breckinridge, JB Jakobsen, P TI Initial test results from the Next Generation Space Telescope (NGST) wavefront sensing and control testbed (WCT) SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc AB This gaper describes the results of a few of the initial series of tests being conducted with the first configuration of the Next Generation Space Telescope (NGST) Wavefront sensing and Control Testbed (WCT1). WCT1 is a 1:1, f/16.6 re-imaging system, incorporating two deformable mirrors (DM) located at pupil conjugate positions with 6 actuators/diameter (SM/DM) and 20 actuators/diameter (AO/DM). A CCD on a precision stage is used for obtaining defocused images providing phase diversity for wavefront determination using phase retrieval. In a typical experiment, wavefront error (WFE) is injected into the optical path with the SM/DM and then corrected using the more densely actuated AO/DM. Wavefront analysis is provided via a phase retrieval algorithm, and control software is used to reshape the AO/DM and correct the wavefront. A summary of the results of some initial tests are presented. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Bowers, C (reprint author), NASA, Goddard Space Flight Ctr, Code 661, Greenbelt, MD 20771 USA. NR 12 TC 5 Z9 5 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 763 EP 773 DI 10.1117/12.393972 PG 11 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600078 ER PT S AU Coulter, DR Jacobson, DN AF Coulter, DR Jacobson, DN BE Breckinridge, JB Jakobsen, P TI Technology for the next generation space telescope SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE NGST; telescope technology; large optics; cryogenic optics; IR astronomy AB The Next Generation Space Telescope (NGST) is a major element of NASA's Origins Program. It is planned to be a deployable infrared telescope with an 8m diameter aperture and a sensitivity approximate to 1000 times greater than any currently existing infrared telescope. The scientific goals of NGST include imaging and spectroscopic characterization of the earliest galaxies and proto-galaxies, which formed following the "big bang". Several years ago, NASA embarked on an aggressive technology development effort covering a number of technical areas including optics, detectors, deployable structures, wavefront control, passive cooling, operations, etc. This paper presents an overview of the status of the program NASA is pursuing to provide the necessary technologies, which will enable an exciting, affordable NGST mission. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Coulter, DR (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 17 TC 2 Z9 2 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 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 784 EP 794 DI 10.1117/12.394046 PG 11 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600080 ER PT S AU Greenhouse, MA Geithner, PH Jurotich, M Long, K McCreight, CR AF Greenhouse, MA Geithner, PH Jurotich, M Long, K McCreight, CR BE Breckinridge, JB Jakobsen, P TI NGST Integrated Science Instrument Module (ISIM) SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE NGST; ISIM; infrared instrumentation; spectrometer AB A brief overview of the Next Generation Space Telescope science instrument module is given, development plans for engineering design, enabling technologies, and science instruments are discussed. Up-coming schedule milestones of community interest are also presented. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Greenhouse, MA (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 0 TC 7 Z9 7 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 795 EP 799 DI 10.1117/12.394047 PG 5 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600081 ER PT S AU McCreight, CR Fowler, AM Greene, TP Greenhouse, MA Hall, DNB Long, KS MacKenty, JW Martineau, RJ Pipher, JL Ressler, MW Young, ET AF McCreight, CR Fowler, AM Greene, TP Greenhouse, MA Hall, DNB Long, KS MacKenty, JW Martineau, RJ Pipher, JL Ressler, MW Young, ET BE Breckinridge, JB Jakobsen, P TI Detector requirements for NGST SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE Next Generation Space Telescope; infrared detectors; focal plane arrays; infrared imaging; infrared spectroscopy; detector characterization AB This paper summarizes the findings of the Next Generation Space Telescope (NGST) Detector Requirements Review Panel. This panel was comprised of NGST Integrated Science Instrument Module (ISIM) study representatives, detector specialists, and members of the NGST project science team. It has produced a report that recommends detector performance levels, and has provided rationale for deriving these levels from basic, anticipated NGST science goals and programs. Key parameters such as detector array format, quantum efficiency, and noise are discussed and prioritized. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP McCreight, CR (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 1 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 800 EP 809 DI 10.1117/12.394048 PG 10 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600082 ER PT S AU Keski-Kuha, R Bely, P Burg, R Burge, J Davila, P Geary, J Hagopian, J Jacobson, D Lowman, A Macenka, S Mangus, J Perrygo, C Redding, D Saif, B Smith, S Wyant, J AF Keski-Kuha, R Bely, P Burg, R Burge, J Davila, P Geary, J Hagopian, J Jacobson, D Lowman, A Macenka, S Mangus, J Perrygo, C Redding, D Saif, B Smith, S Wyant, J BE Breckinridge, JB Jakobsen, P TI NGST OTA optical metrology instrumentation and conceptual approaches SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE Next Generation Space Telescope; NGST; optical testing AB An Integrated Product Team (IPT) was formed to develop a detailed concept for optical test methodology for testing of the NGST individual primary, secondary and tertiary mirrors and the full telescope system on the ground. The large, lightweight, deployable primary mirror, and the cryogenic operating environment make optical testing of NGST OTA (Optical Telescope Assembly) extremely challenging. A telescope of the complexity of NGST has never been built and tested on the ground in 1-g environment. A brief summary of the preliminary metrology test plan at the minor component and telescope system level is presented. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Keski-Kuha, R (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 10 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 826 EP 835 DI 10.1117/12.394050 PG 10 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600084 ER PT S AU Barry, RK Satyapal, S Greenhouse, MA Barclay, R Amato, D Arritt, B Brown, G Harvey, V Holt, C Kuhn, J Lesyna, L Fonneland, N Hilgeman, T AF Barry, RK Satyapal, S Greenhouse, MA Barclay, R Amato, D Arritt, B Brown, G Harvey, V Holt, C Kuhn, J Lesyna, L Fonneland, N Hilgeman, T BE Breckinridge, JB Jakobsen, P TI A near IR Fabry-Perot interferometer for wide field, low resolution hyperspectral imaging on the Next Generation Space Telescope SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE Fabry-Perot NGST infrared cryogenic interferometer etalon AB We discuss work in progress on a near-infrared tunable bandpass filter for the Goddard baseline wide field camera concept of the Next Generation Space Telescope (NGST) Integrated Science Instrument Module (ISIM). This filter, the Demonstration Unit for Low Order Cryogenic Etalon (DULCE), is designed to demonstrate a high efficiency scanning Fabry-Perot etalon operating in interference orders 1 - 4 at 30K with a high stability DSP based servo control system. DULCE is currently the only available tunable filter for lower order cryogenic operation in the near infrared. In this application, scanning etalons will illuminate the focal plane arrays with a single order of interference to enable wide field lower resolution hyperspectral imaging over a wide range of redshifts. We discuss why tunable filters are an important instrument component in future space-based observatories. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Barry, RK (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 4 TC 2 Z9 2 U1 1 U2 2 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 861 EP 871 DI 10.1117/12.393959 PG 11 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600087 ER PT S AU Pacini, L Lou, M Johnston, J Lienard, S AF Pacini, L Lou, M Johnston, J Lienard, S BE Breckinridge, JB Jakobsen, P TI Sunshield technology and flight experiment for the Next Generation Space Telescope SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE NGST; sunshield; inflatable technology; thermal performance AB The Next Generation Space Telescope (NGST) requires a sunshield to passively cool the telescope and detectors to temperatures between 60 degrees and 100 degrees Kelvin. The sunshield is a large, deployable, multilayer thin-film membrane structure. Characteristics of this design are ultra lightweight, high packaging efficiency, high deployment reliability, low life-cycle costs, and a 5 to 10 years mission life at L2. A thermal performance, or e*, requirement has been determined from integrated modeling. Performance of the sunshield is achievable, however, many hurdles remain. NGST is actively working to reduce the risk in the area of sunshield technology. Areas under study include: system deployment and stability, lifetime of materials, optical properties of materials, effects of micrometeoroid damage, and development of analytical models. An inflatable sunshield has been selected and included in the NGST yardstick architecture. As part of the technology development effort, NGST is performing a flight demonstration on the NGST Pathfinder 1 mission. The Inflatable Sunshield in Space (ISIS) experiment is scheduled for October 2001 on the Space Shuttle. This paper will discuss sunshield requirements, technology development, component and system level testing, development of analytical modeling tools, and the ISIS flight experiment. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Pacini, L (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 9 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 884 EP 893 DI 10.1117/12.393961 PG 10 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600089 ER PT S AU Blackwell, WC Minow, JI Evans, SW Hardage, DM Suggs, RM AF Blackwell, WC Minow, JI Evans, SW Hardage, DM Suggs, RM BE Breckinridge, JB Jakobsen, P TI Charged particle environment for NGST: Model development SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE NGST; L2; plasma; environment; magnetotail; magnetosheath; solar wind ID DISTANT MAGNETOTAIL; PLASMA REGIMES; GEOTAIL; ISEE-3; TAIL AB The Next Generation Space Telescope (NGST) will operate in a halo orbit about the L2 point, 1.5 million km from the Earth, where the spacecraft will periodically travel through the magnetotail region. There are a number of tools available to calculate the high energy, ionizing radiation particle environment from galactic cosmic rays and from solar disturbances. However, space environment tools are not generally available to provide assessments of the charged particle environment and its variations in the solar wind, magnetosheath, and magnetotail at L2 distances. An engineering-level phenomenology code (LRAD) was therefore developed to facilitate the definition of charged particle environments in the vicinity of the L2 point in support of the NGST program. LRAD contains models tied to satellite measurement data of the solar wind and magnetotail regions. The model provides particle flux and fluence calculations necessary to predict spacecraft charging conditions and the degradation of materials used in the construction of NGST. This paper describes the LRAD environment models for the deep magnetotail (X-GSE < -100 Re) and solar wind, and presents predictions of the charged particle environment for NGST. C1 Sverdrup Technol Inc, George C Marshall Space Flight Ctr Grp, Huntsville, AL 35806 USA. RP Blackwell, WC (reprint author), Sverdrup Technol Inc, George C Marshall Space Flight Ctr Grp, Huntsville, AL 35806 USA. NR 16 TC 1 Z9 1 U1 0 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 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 908 EP 919 PG 12 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600091 ER PT S AU Lowman, AE Shi, F Redding, DC Basinger, SA Bowers, CW Davila, PS AF Lowman, AE Shi, F Redding, DC Basinger, SA Bowers, CW Davila, PS BE Breckinridge, JB Jakobsen, P TI Telescope simulator for the Nexus wavefront control testbed SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE NGST; space optics; active optics; wavefront sensing; deformable mirror; segmented aperture ID GENERATION SPACE TELESCOPE AB A telescope simulator was built as part of the Nexus wavefront control testbed, an NGST technology experiment at NASA's Goddard Space Flight Center. This testbed was designed to demonstrate complete control of a segmented telescope, from initial capture of light, through coarse alignment and phasing, to fine phasing and wavefront control. The existing telescope simulator allows testing of the fine phasing and wavefront control steps. A small deformable mirror in the simulator allows generation of an unobscured aberrated wavefront, for use in exploring the range of measurement and correction using the testbed's image-based wavefront sensor and larger deformable mirror. An alternate path under development for the simulator will create a segmented wavefront using three spherical mirrors; three-degree-of-freedom mounts under each mirror enable alignment and phasing experiments that will cover most of the operation sequence. Details of the hardware design and performance will be presented. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Lowman, AE (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 9 TC 2 Z9 2 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 954 EP 961 DI 10.1117/12.394014 PG 8 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600095 ER PT S AU Powers, C Townsend, J Wooldridge, E Connell, J Dever, J Edwards, D Peters, W AF Powers, C Townsend, J Wooldridge, E Connell, J Dever, J Edwards, D Peters, W BE Breckinridge, JB Jakobsen, P TI Next Generation Space Telescope (NGST) thin film materials test program SO UV, OPTICAL, AND IR SPACE TELESCOPES AND INSTRUMENTS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on UV, Optical, and IR Space Telescopes and Instruments CY MAR 29-31, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE space environmental effects; thermal control film; Next Generation Space Telescope; sunshield; membrane AB A test program has been implemented to evaluate candidate thin film materials for the sun-facing layer of the Next Generation Space Telescope (NGST) sunshield. Various polymers are being tested to determine if any can survive the radiation environment of the proposed NGST orbit (the second Sun-Earth lagrangian point or L2). This testing will characterize the mechanical and thermal properties before and after exposure to a simulated NGST sunshield environment. In addition, because the sunshield will be folded and stowed before launch, the candidate materials will be folded, stowed and unfolded (deployed) to determine if they can survive this type of handling and storage. Based on the results of this testing, candidates will be down selected for further development and testing. Future development will include the addition of optical coatings, rip-stop for tear resistance, and seaming techniques. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Powers, C (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 4 TC 0 Z9 0 U1 0 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 0-8194-3638-0 J9 P SOC PHOTO-OPT INS PY 2000 VL 4013 BP 962 EP 969 DI 10.1117/12.393966 PG 8 WC Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70H UT WOS:000089219600096 ER PT J AU Beutter, BR Stone, LS AF Beutter, BR Stone, LS TI Motion coherence affects human perception and pursuit similarly SO VISUAL NEUROSCIENCE LA English DT Article DE eye movements; area MT; area MST; direction perception; models ID VISUAL AREA MT; SUPERIOR TEMPORAL SULCUS; EYE-MOVEMENTS; SMOOTH-PURSUIT; PERCEIVED MOTION; MACAQUE MONKEY; MICROSTIMULATION; DIRECTION; LESIONS; VELOCITY AB Pursuit and perception both require accurate information about the motion of objects. Recovering the motion of objects by integrating the motion of their components is a difficult visual task. Successful integration produces coherent global object motion, while a failure to integrate leaves the incoherent local motions of the components unlinked. We compared the ability of perception and pursuit to perform motion integration by measuring direction judgments and the concomitant eye-movement responses to line figure parallelograms moving behind stationary rectangular apertures. The apertures were constructed such that only the line segments corresponding to the parallelogram's sides were visible; thus, recovering global motion required the integration of the local segment motion. We investigated several potential motion-integration rules by using stimuli with different object, vector-average, and line-segment terminator-motion directions. We used an oculometric decision rule to directly compare direction discrimination for pursuit and perception. For visible apertures, the percept was a coherent object, and both the pursuit and perceptual performance were close to the object-motion prediction. For invisible apertures, the percept was incoherently moving segments, and both the pursuit and perceptual performance were close to the terminator-motion prediction. Furthermore, both psychometric and oculometric direction thresholds were much higher for invisible apertures than for visible apertures. We constructed a model in which both perception and pursuit are driven by a shared motion-processing stage, with perception having an additional input from an independent static-processing stage. Model simulations were consistent with our perceptual and oculomotor data. Based on these results, we propose the use of pursuit as an objective and continuous measure of perceptual coherence. Our results support the view that pursuit and perception share a common motion-integration stage, perhaps within areas MT or MST. C1 NASA, Ames Res Ctr, Human Informat Proc Res Branch, Moffett Field, CA 94035 USA. RP Beutter, BR (reprint author), NASA, Ames Res Ctr, Human Informat Proc Res Branch, MS 262-2, Moffett Field, CA 94035 USA. NR 54 TC 54 Z9 54 U1 1 U2 3 PU CAMBRIDGE UNIV PRESS PI NEW YORK PA 40 WEST 20TH STREET, NEW YORK, NY 10011-4211 USA SN 0952-5238 J9 VISUAL NEUROSCI JI Visual Neurosci. PD JAN-FEB PY 2000 VL 17 IS 1 BP 139 EP 153 PG 15 WC Neurosciences; Ophthalmology SC Neurosciences & Neurology; Ophthalmology GA 294TT UT WOS:000085927000014 PM 10750835 ER PT J AU Figueiredo, MA Gloster, CS Stephens, M Graves, CA Nakkar, M AF Figueiredo, MA Gloster, CS Stephens, M Graves, CA Nakkar, M TI Implementation of multispectral image classification on a remote adaptive computer SO VLSI DESIGN LA English DT Article DE reconfigurable computing; adaptive computing; neural networks; image processing; field programmable gate arrays (FPGAs); VHDL Modeling; image classification; probabilistic neural networks AB As the demand for higher performance computers for the processing of remote sensing science algorithms increases, the need to investigate:new computing paradigms is justified. Field Programmable Gate Arrays enable the implementation of algorithms at the hardware gate level, leading to orders of magnitude performance increase over microprocessor based systems. The automatic classification of spaceborne multispectral images is an example of a computation intensive application that can benefit from implementation on an FPGA-based custom computing machine (adaptive or reconfigurable computer). A probabilistic neural network is used here to classify pixels of a multispectral LANDSAT-2 image, The implementation described utilizes Java client/server application programs to access the adaptive computer from a remote site. Results verify that a remote hardware version of:the algorithm (implemented on an adaptive computer) is significantly faster than a local software version of the same algorithm (implemented on a typical general-purpose computer). C1 N Carolina State Univ, Raleigh, NC 27695 USA. NASA, Goddard Space Flight Ctr, GST Inc, Greenbelt, MD 20771 USA. RP Gloster, CS (reprint author), N Carolina State Univ, Box 7914, Raleigh, NC 27695 USA. NR 26 TC 1 Z9 1 U1 0 U2 0 PU GORDON BREACH SCI PUBL LTD PI READING PA C/O STBS LTD, PO BOX 90, READING RG1 8JL, BERKS, ENGLAND SN 1065-514X J9 VLSI DES JI VLSI Des. PY 2000 VL 10 IS 3 BP 307 EP 319 DI 10.1155/2000/31983 PG 13 WC Computer Science, Hardware & Architecture SC Computer Science GA 304MG UT WOS:000086487500005 ER PT S AU Murphy, DW AF Murphy, DW CA VSOP Int Team BE Hirabayashi, H Preston, RA Gurvits, LI TI The imaging capability of VSOP SO VSOP RESULTS AND THE FUTURE OF SPACE VLBI SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT E1 3 Symposium of COSPAR Scientific Commission E held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Comm Space Res AB One of the prime goals of the VSOP mission is to produce VLBI images of radio sources at unprecedented high angular resolution for a given observing frequency. Of crucial importance in the production of VSOP images is the choice of weighting schemes. The paper examines some of the issues involved in choosing an appropriate weighting scheme and shows that a couple of schemes in common use by VLBI astronomers are inadequate for making VSOP images. When the appropriate weighting scheme is chosen, VSOP images of moderate dynamic range (approximate to 1000:1) can be produced. (C) 2000 COSPAR. Published by Elsevier Science Ltd. C1 Jet Prop Lab, Pasadena, CA 91101 USA. RP Murphy, DW (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91101 USA. NR 2 TC 2 Z9 2 U1 0 U2 0 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2000 VL 26 IS 4 BP 609 EP 612 DI 10.1016/S0273-1177(99)01177-1 PG 4 WC Engineering, Aerospace SC Engineering GA BQ23F UT WOS:000087679700004 ER PT S AU Moellenbrock, GA Kobayashi, H Murphy, DW AF Moellenbrock, GA Kobayashi, H Murphy, DW BE Hirabayashi, H Preston, RA Gurvits, LI TI HALCA VLBI amplitude calibration performance SO VSOP RESULTS AND THE FUTURE OF SPACE VLBI SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT E1 3 Symposium of COSPAR Scientific Commission E held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Comm Space Res AB The amplitude calibration properties of the HALCA VLBI system are summarized. The HALCA System Equivalent Flux Densities (SEFD) are typically similar to 19500 Jy at L-band and similar to 15800 Jy at C-band, and are stable between and during orbits. (C) 2000 COSPAR. Published by Elsevier Science Ltd. C1 Inst Space & Astronaut Sci, Sagamihara, Kanagawa 229, Japan. CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Moellenbrock, GA (reprint author), Inst Space & Astronaut Sci, 3-1-1 Yoshinodai, Sagamihara, Kanagawa 229, Japan. NR 2 TC 3 Z9 3 U1 0 U2 0 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2000 VL 26 IS 4 BP 613 EP 616 DI 10.1016/S0273-1177(99)01178-3 PG 4 WC Engineering, Aerospace SC Engineering GA BQ23F UT WOS:000087679700005 ER PT S AU Meier, DL Fomalont, EB AF Meier, DL Fomalont, EB CA Int VSOP Team BE Hirabayashi, H Preston, RA Gurvits, LI TI Operating a telescope larger than the earth: How the VSOP space VLBI mission is scheduled SO VSOP RESULTS AND THE FUTURE OF SPACE VLBI SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT E1 3 Symposium of COSPAR Scientific Commission E held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Comm Space Res AB The Japanese VLBI space observatory programme (VSOP) mission is one of the most complex scientific endeavors ever attempted. It involves coordinating a spacecraft with detailed pointing constraints that vary on time scales ranging from years to hours, tracking stations in four different countries, ground radio telescopes in nearly 20 different countries with different capabilities at the VSOP observing frequencies, and correlation and tape copying facilities with four different recording formats. Scientific constraints on the quality of (u,v)-coverage obtainable force the scheduling to be done far in advance of the observation - over about 1.5 years time - so that the sources are observed when the orbital orientation is most favorable. In order that all these facilities work as a single astronomical instrument, the constraints on them also must be taken into account in the scheduling to the satisfaction of all parties involved, including the principal investigators as well as mission and observatory personnel. In this paper we outline the entire VSOP mission scheduling process. Special emphasis is placed on software required to decide when to observe the proposed sources and how to ensure the highest quality science while preserving the health of the spacecraft; We also discuss application of the process to the future space VLBI missions VSOP2, RadioAstron, and ARISE. (C) 2000 COSPAR. Published by Elsevier Science Ltd. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Natl Radio Astron Observ, Charlottesville, VA USA. RP Meier, DL (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 3 TC 0 Z9 1 U1 0 U2 0 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2000 VL 26 IS 4 BP 629 EP 635 DI 10.1016/S0273-1177(99)01181-3 PG 7 WC Engineering, Aerospace SC Engineering GA BQ23F UT WOS:000087679700008 ER PT S AU Smith, JG Meier, DL Murphy, DW Preston, RA Tingay, SJ Traub, DL Wietfeldt, RD AF Smith, JG Meier, DL Murphy, DW Preston, RA Tingay, SJ Traub, DL Wietfeldt, RD BE Hirabayashi, H Preston, RA Gurvits, LI TI JPL contribution to the VSOP mission SO VSOP RESULTS AND THE FUTURE OF SPACE VLBI SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT E1 3 Symposium of COSPAR Scientific Commission E held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Comm Space Res AB The Jet Propulsion Laboratory (JPL) is a participant in the VSOP Space VLBI mission, an extensive international collaboration led by Japan's Institute of Space and Astronautical Science (ISAS). The JPL effort is funded by the U.S. National Aeronautics and Space Administration (NASA). To obtain data from the orbital element of the VSOP mission, the Japanese HALCA satellite, the Deep Space Network (DSN) of JPL has built a new set of three Ii-meter tracking stations in California, Spain, and Australia. These stations have supported over 1000 HALCA passes during the first year of operation, and supply science, telemetry, and Doppler data for the mission. JPL is using the Doppler data to estimate the satellite orbital parameters that are needed by the tracking stations and VLBI data correlators. The DSN also modified their three 70-meter antennas to provide ground VLBI observing support for the mission. In addition to operational support, JPL has had significant involvement in the mission planning and scientific support aspects of the mission, including mission design, international data flow, scientific scheduling, and data analysis during in-orbit checkout. JPL has also aided the scientific community in the use of VSOP by developing a user software package, writing a guide for proposers, and establishing a proposer help desk. (C) 2000 COSPAR. Published by Elsevier Science Ltd. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Smith, JG (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RI Tingay, Steven/B-5271-2013 NR 0 TC 0 Z9 0 U1 0 U2 0 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2000 VL 26 IS 4 BP 637 EP 640 DI 10.1016/S0273-1177(99)01206-5 PG 4 WC Engineering, Aerospace SC Engineering GA BQ23F UT WOS:000087679700009 ER PT S AU Jauncey, DL Reynolds, JE Tzioumis, AK Ferris, RH Wilson, WE Sinclair, MW Moorey, GG Gough, RG Oestreich, M King, EA Otrupcek, R McCulloch, PM Costa, ME Dodson, RG Ellingsen, SP Gowland, GA Legge, DJ Moffett, DA Rayner, DP Nicolson, GD Quick, JFH Harbison, PA Lauf, JE Wietfeldt, R AF Jauncey, DL Reynolds, JE Tzioumis, AK Ferris, RH Wilson, WE Sinclair, MW Moorey, GG Gough, RG Oestreich, M King, EA Otrupcek, R McCulloch, PM Costa, ME Dodson, RG Ellingsen, SP Gowland, GA Legge, DJ Moffett, DA Rayner, DP Nicolson, GD Quick, JFH Harbison, PA Lauf, JE Wietfeldt, R BE Hirabayashi, H Preston, RA Gurvits, LI TI The southern hemisphere contribution to the VSOP mission SO VSOP RESULTS AND THE FUTURE OF SPACE VLBI SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT E1 3 Symposium of COSPAR Scientific Commission E held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Comm Space Res ID VLBI EXPERIMENT AB The Space VLBI mission, VSOP, involves the participation of 15 countries with up to 40 radio telescopes spread across the Earth observing in close coordination with the 8 m radio telescope on board the Japanese spacecraft HALCA (Hirabayashi, 1998, and this Proceedings). This paper describes the contributions to the mission's success from Southern Hemisphere radio telescopes, facilities and Institutes. (C) 2000 COSPAR. Published by Elsevier Science Ltd. C1 CSIRO, Australia Telescope Natl Facil, Epping, NSW 2121, Australia. Univ Tasmania, Dept Phys, Hobart, Tas 7001, Australia. Hartebeesthoek Radio Astron Observ, Krugersdorp, South Africa. British Aerosp Australia, Canberra Deep Space Commun Complex, Canberra, ACT 2601, Australia. CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Jauncey, DL (reprint author), CSIRO, Australia Telescope Natl Facil, Epping, NSW 2121, Australia. RI King, Edward/A-1473-2012; Ellingsen, Simon/J-7754-2014; Rayner, David/A-6414-2011 OI King, Edward/0000-0002-6898-2130; Ellingsen, Simon/0000-0002-1363-5457; Rayner, David/0000-0003-0545-3634 NR 7 TC 0 Z9 0 U1 0 U2 1 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2000 VL 26 IS 4 BP 645 EP 648 DI 10.1016/S0273-1177(99)01208-9 PG 4 WC Engineering, Aerospace SC Engineering GA BQ23F UT WOS:000087679700011 ER PT S AU Preston, RA Tingay, SJ Murphy, DW Meier, DL Pearson, TJ Readhead, ACS Hirabayashi, H Kobayashi, H Inoue, M Piner, BG AF Preston, RA Tingay, SJ Murphy, DW Meier, DL Pearson, TJ Readhead, ACS Hirabayashi, H Kobayashi, H Inoue, M Piner, BG BE Hirabayashi, H Preston, RA Gurvits, LI TI The Pearson-Readhead Survey from space SO VSOP RESULTS AND THE FUTURE OF SPACE VLBI SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT E1 3 Symposium of COSPAR Scientific Commission E held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Comm Space Res AB The VSOP Space VLBI mission uses the HALCA spacecraft, launched from Japan in February 1997, in conjunction with ground radio observatories around the world to create a high resolution radio-wavelength imaging facility. We are using this unique facility to observe a complete sample of Pearson-Readhead Survey sources (Pearson and Readhead 1988) at 4.8 GHz, to determine core brightness temperatures and pc-scale jet properties. In addition we are obtaining matched-resolution 15 GHz observations using the VLBA at epochs close in time to the space VLBI observations to investigate the spectral indices of these sources at high resolution. (C) 2000 COSPAR. Published by Elsevier Science Ltd. C1 CALTECH, Jet Prop Lab, MS238332, Pasadena, CA 91109 USA. CALTECH, Pasadena, CA 91125 USA. Inst Space & Astronaut Sci, Sagamihara, Kanagawa 229, Japan. Natl Astron Observ, Mitaka, Tokyo 1818588, Japan. RP Preston, RA (reprint author), CALTECH, Jet Prop Lab, MS238332, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RI Tingay, Steven/B-5271-2013; Pearson, Timothy/N-2376-2015 OI Pearson, Timothy/0000-0001-5213-6231 NR 1 TC 0 Z9 0 U1 0 U2 0 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2000 VL 26 IS 4 BP 661 EP 664 DI 10.1016/S0273-1177(99)01185-0 PG 4 WC Engineering, Aerospace SC Engineering GA BQ23F UT WOS:000087679700014 ER PT S AU Murphy, DW Tingay, SJ Preston, RA Meier, DL Guirado, JC Polatidis, A Conway, JE Hirabayashi, H Kobayashi, H Murata, Y AF Murphy, DW Tingay, SJ Preston, RA Meier, DL Guirado, JC Polatidis, A Conway, JE Hirabayashi, H Kobayashi, H Murata, Y BE Hirabayashi, H Preston, RA Gurvits, LI TI VSOP monitoring of the quasar 1928+738 SO VSOP RESULTS AND THE FUTURE OF SPACE VLBI SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT E1 3 Symposium of COSPAR Scientific Commission E held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Comm Space Res AB In the paper we describe the first results from a campaign to monitor the relatively low redshift (z=0.3) circumpolar superluminal quasar 1928+738 with VSOP. The three epochs of data that we have analyzed show that there have been substantial structural changes in this source near the core on the time-scale of a few months. (C) 2000 COSPAR. Published by Elsevier Science Ltd. C1 Jet Prop Lab, Pasadena, CA 91101 USA. Univ Valencia, Dpto Astron & Astrofis, E-46100 Burjassot, Spain. Joint Inst VLBI Europe, NL-7990 AA Dwingeloo, Netherlands. Chalmers Tech Univ, Onsala Space Observ, S-43992 Onsala, Sweden. Inst Space & Astronaut Sci, Kanagawa 229, Japan. RP Murphy, DW (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91101 USA. RI Tingay, Steven/B-5271-2013 NR 5 TC 2 Z9 2 U1 0 U2 0 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2000 VL 26 IS 4 BP 665 EP 668 DI 10.1016/S0273-1177(99)01186-2 PG 4 WC Engineering, Aerospace SC Engineering GA BQ23F UT WOS:000087679700015 ER PT S AU Lobanov, AP Zensus, JA Abraham, Z Carrara, E Unwin, SC Hirabayashi, H Bushimata, T AF Lobanov, AP Zensus, JA Abraham, Z Carrara, E Unwin, SC Hirabayashi, H Bushimata, T BE Hirabayashi, H Preston, RA Gurvits, LI TI Imaging and monitoring the parsec-scale jet in 3C 273 with the VSOP mission SO VSOP RESULTS AND THE FUTURE OF SPACE VLBI SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT E1 3 Symposium of COSPAR Scientific Commission E held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Comm Space Res AB We present results from the first observing epoch (December 1997) of 5 GHz VSOP monitoring program of the parsec-scale jet in 3C 273. At the resolution achieved by the VSOP observation, the jet is transversely resolved, and it exhibits significant edge brightening. The latter may result from velocity gradients or reacceleration zones existing in the jet, due to interactions between the faster jet plasma and slower, nonrelativistic outflow or ambient medium. (C) 2000 COSPAR. Published by Elsevier Science Ltd. C1 Max Planck Inst Radioastron, D-53121 Bonn, Germany. Univ Sao Paulo, Sao Paulo, Brazil. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Inst Space & Astronaut Sci, Tokyo 153, Japan. RP Lobanov, AP (reprint author), Max Planck Inst Radioastron, Hugel 69, D-53121 Bonn, Germany. RI Lobanov, Andrei/G-5891-2014 NR 5 TC 4 Z9 4 U1 0 U2 0 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2000 VL 26 IS 4 BP 669 EP 672 DI 10.1016/S0273-1177(99)01187-4 PG 4 WC Engineering, Aerospace SC Engineering GA BQ23F UT WOS:000087679700016 ER PT S AU Hirabayashi, H Edwards, PG Wehrle, AE Unwin, SC Piner, BG Lovell, JEJ Kobayashi, H Okayasu, R Makino, F Kii, T Valtaoja, E AF Hirabayashi, H Edwards, PG Wehrle, AE Unwin, SC Piner, BG Lovell, JEJ Kobayashi, H Okayasu, R Makino, F Kii, T Valtaoja, E BE Hirabayashi, H Preston, RA Gurvits, LI TI The first Space VLBI image of 3C279 SO VSOP RESULTS AND THE FUTURE OF SPACE VLBI SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT E1 3 Symposium of COSPAR Scientific Commission E held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Comm Space Res ID QUASAR 3C-279; INTERFEROMETRY AB The first 5 GHz VSOP (VLBI Space Observatory Programme) observation of the quasar 3C279 was conducted on 10 January 1998 with the satellite HALCA and as array of ground radio telescopes. The high dynamic range image presented here reveals that the core and the secondary component similar to 3 milli-arcseconds from the core dominate the compact radio emission, but that lower level features at intermediate distances from the core are also evident. (C) 2000 COSPAR. Published by Elsevier Science Ltd. C1 ISAS, Sagamihara, Kanagawa 2298510, Japan. CALTECH, Jet Prop Lab, IPAC, Pasadena, CA USA. Helsinki Univ Technol, FIN-02150 Espoo, Finland. RP Hirabayashi, H (reprint author), ISAS, Sagamihara, Kanagawa 2298510, Japan. NR 10 TC 1 Z9 1 U1 0 U2 0 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2000 VL 26 IS 4 BP 689 EP 692 DI 10.1016/S0273-1177(99)01192-8 PG 4 WC Engineering, Aerospace SC Engineering GA BQ23F UT WOS:000087679700021 ER PT S AU Lovell, JEJ King, EA Jauncey, DL Tzioumis, AK Reynolds, JE McCulloch, PM Costa, ME Preston, RA Tingay, SJ Murphy, DW Meier, DL Nicolson, GD Dewdney, PE Cannon, WH AF Lovell, JEJ King, EA Jauncey, DL Tzioumis, AK Reynolds, JE McCulloch, PM Costa, ME Preston, RA Tingay, SJ Murphy, DW Meier, DL Nicolson, GD Dewdney, PE Cannon, WH BE Hirabayashi, H Preston, RA Gurvits, LI TI First results of VSOP imaging of strong GPS sources SO VSOP RESULTS AND THE FUTURE OF SPACE VLBI SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT E1 3 Symposium of COSPAR Scientific Commission E held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Comm Space Res ID SPECTRUM RADIO-SOURCES AB We are using the VSOP spacecraft, HALCA, together with ground-based telescopes, to image six strong GPS sources with compact double structure. Space-ground baselines are needed to achieve the resolution to accurately measure component sizes at the frequency of the spectral peak, an essential requirement in distinguishing between free-free and synchrotron self absorption emission mechanisms. Many of the components of these sources are only just beginning to show signs of any internal structure on the longest Earth baselines and space VLBI is the only technique that permits investigation of their most compact structure at the frequency of the spectral peak. (C) 2000 COSPAR. Published by Elsevier Science Ltd. C1 Inst Space & Astronaut Sci, Sagamihara, Kanagawa 2298510, Japan. CSIRO, Earth Observat Ctr, Canberra, ACT 2601, Australia. Australia Telescope Natl Facil, Epping, NSW 1710, Australia. Univ Tasmania, Sch Phys, Hobart, Tas 7001, Australia. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Hartbeesthoek Radio Astron Observ, ZA-1740 Krugersdorp, South Africa. Domin Radio Astrophys Observ, Penticton, BC V2A 6K3, Canada. York Univ, CRESTech, Space Geodynam Lab, Downsview, ON M3J 3K1, Canada. RP Lovell, JEJ (reprint author), Inst Space & Astronaut Sci, Sagamihara, Kanagawa 2298510, Japan. RI Tingay, Steven/B-5271-2013; King, Edward/A-1473-2012 OI King, Edward/0000-0002-6898-2130 NR 7 TC 1 Z9 1 U1 0 U2 1 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2000 VL 26 IS 4 BP 715 EP 718 DI 10.1016/S0273-1177(99)01198-9 PG 4 WC Engineering, Aerospace SC Engineering GA BQ23F UT WOS:000087679700027 ER PT S AU Jones, DL Allen, RJ Basart, JP Bastian, T Blume, WH Bougeret, JL Dennison, BK Desch, MD Dwarakanath, KS Erickson, WC Farrell, W Finley, DG Gopalswamy, N Howard, RE Kaiser, ML Kassim, NE Kuiper, TBH MacDowall, RJ Mahoney, MJ Perley, RA Preston, RA Reiner, MJ Rodriguez, P Stone, RG Unwin, SC Weiler, KW Woan, G Woo, R AF Jones, DL Allen, RJ Basart, JP Bastian, T Blume, WH Bougeret, JL Dennison, BK Desch, MD Dwarakanath, KS Erickson, WC Farrell, W Finley, DG Gopalswamy, N Howard, RE Kaiser, ML Kassim, NE Kuiper, TBH MacDowall, RJ Mahoney, MJ Perley, RA Preston, RA Reiner, MJ Rodriguez, P Stone, RG Unwin, SC Weiler, KW Woan, G Woo, R BE Hirabayashi, H Preston, RA Gurvits, LI TI The ALFA medium explorer mission SO VSOP RESULTS AND THE FUTURE OF SPACE VLBI SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT E1 3 Symposium of COSPAR Scientific Commission E held at the 32nd COSPAR Scientific Assembly CY JUL 12-19, 1998 CL NAGOYA, JAPAN SP Comm Space Res AB The frequency range below a few tens of MHz is unexplored with high angular resolution due to the opacity of Earth's ionosphere. An interferometer array in space providing arcminute angular resolution images at frequencies of a few MHz would allow a wide range of problems in solar, planetary, galactic, and extragalactic astronomy to be attacked. These include the evolution of solar radio emissions associated with shocks driven by coronal mass ejections and searches for coherent radio emission from supernova remnants and relativistic jets, in addition, it is likely that unexpected objects or emission processes will be discovered by such an instrument, as has always happened when high resolution astronomical observations first become possible in a new region of the electromagnetic spectrum. The Astronomical Low Frequency Array (ALFA) mission will consist of 16 identical small satellites forming an aperture synthesis array. The satellites will cover the surface of a spherical region approximate to 100 km in diameter, thus providing good aperture plane coverage in all directions simultaneously. The array will operate in two modes: 1) "snapshot" imaging of strong, rapidly changing sources such as solar radio bursts and 2) long-term aperture synthesis observations for maximum sensitivity, high dynamic range imaging, in both cases a large number of array elements is needed. (C) 2000 COSPAR. Published by Elsevier Science Ltd. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Space Telescope Sci Inst, Baltimore, MD 21218 USA. Iowa State Univ, Ames, IA 50011 USA. Observ Paris, Meudon, France. Natl Radio Astron Observ, Socorro, NM 87801 USA. Virginia Polytech Inst & State Univ, Blacksburg, VA 24061 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Raman Res Inst, Bangalore 560080, Karnataka, India. Univ Maryland, College Pk, MD 20742 USA. Univ Tasmania, Hobart, Tas, Australia. USN, Res Lab, Washington, DC 20375 USA. Univ Glasgow, Glasgow, Lanark, Scotland. RP Jones, DL (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RI MacDowall, Robert/D-2773-2012; Gopalswamy, Nat/D-3659-2012; Dwarakanath, K /D-4876-2012; Astronomy & Astrophysics Group, Raman Res Institute/D-4046-2012; Farrell, William/I-4865-2013 NR 0 TC 10 Z9 10 U1 0 U2 0 PU PERGAMON PRESS LTD PI OXFORD PA THE BOULEVARD LANGFORD LANE KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2000 VL 26 IS 4 BP 743 EP 746 DI 10.1016/S0273-1177(99)01204-1 PG 4 WC Engineering, Aerospace SC Engineering GA BQ23F UT WOS:000087679700034 ER PT S AU Tucker, CJ Steininger, MK Townshend, JRG Killeen, TR Desch, A AF Tucker, CJ Steininger, MK Townshend, JRG Killeen, TR Desch, A BE Szu, HH Vetterli, M Campbell, WJ Buss, JR TI Tropical deforestation in the Bolivian Amazon SO WAVELET APPLICATIONS VII SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Wavelet Applications VII CY APR 26-28, 2000 CL ORLANDO, FL SP SPIE DE tropical forests; deforestation; habitat fragmentation; biological diversity; Landsat; GIS; Bolivia ID FOREST FRAGMENTS; BRAZIL; COMMUNITIES; VEGETATION; BIOMASS; FUTURE; FIRE AB Landsat satellite images from the mid-1980s and early 1990s were used to map tropical forest extent and deforestation in similar to 800,000 km(2) of Amazonian Bolivia. Forest cover extent, including tropical deciduous forest, totaled 472,000 km(2) while the area of natural non-forest formations totaled 298,000 km(2). The area deforested totaled 15,000 km(2) in the middle 1980s and 28,800 km(2) by the early 1990s. The rate of tropical deforestation in the >1,000 mm y(-1) precipitation forest zone of Bolivia was 2,200 km(2) y(-1) from 1985-1986 to 1992-1994. We document a spatially-concentrated "deforestation zone" in Santa Cruz Department where >60% of the Bolivian deforestation is occurring at an accelerating rate in areas of tropical deciduous dry forest. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Tucker, CJ (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 72 TC 0 Z9 0 U1 1 U2 4 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3682-8 J9 P SOC PHOTO-OPT INS PY 2000 VL 4056 BP 2 EP 11 DI 10.1117/12.381717 PG 10 WC Engineering, Electrical & Electronic; Optics SC Engineering; Optics GA BQ40G UT WOS:000088256200001 ER PT S AU Batchelor, DA AF Batchelor, DA BE Szu, HH Vetterli, M Campbell, WJ Buss, JR TI Solar astronomy from space: Recent advances in image analysis SO WAVELET APPLICATIONS VII SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Wavelet Applications VII CY APR 26-28, 2000 CL ORLANDO, FL SP SPIE DE image analysis; astronomy; Sun; comets ID LASCO AB Some recent developments in the rapidly advancing field of solar astronomy from space are described. Three-dimensional imaging of the Sun's corona, improved imaging of coronal mass ejections that cause electromagnetic distubances at the earth, and observations of comets approaching and striking the Sun are discussed. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Batchelor, DA (reprint author), NASA, Goddard Space Flight Ctr, Mail Code 933, Greenbelt, MD 20771 USA. NR 14 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3682-8 J9 P SOC PHOTO-OPT INS PY 2000 VL 4056 BP 77 EP 85 DI 10.1117/12.381670 PG 9 WC Engineering, Electrical & Electronic; Optics SC Engineering; Optics GA BQ40G UT WOS:000088256200006 ER PT S AU Lyon, RG Dorband, JE Hollis, JM AF Lyon, RG Dorband, JE Hollis, JM BE Szu, HH Vetterli, M Campbell, WJ Buss, JR TI Computational complexity in space based optical systems SO WAVELET APPLICATIONS VII SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Wavelet Applications VII CY APR 26-28, 2000 CL ORLANDO, FL SP SPIE AB Future space based imaging systems require increasingly larger aperture sizes to keep pace with the demand for higher spatial resolution for both Earth and Space sciences missions. The cost and weight becomes increasingly prohibitive for telescopes and instruments with apertures greater than 1 meter. A number of solutions are possible and are under investigation; these include: deployable segmented aperture systems, sparse aperture systems, interferometric imaging systems, computational deconvolution and superresolution techniques. The commonality of these techniques lies in increased reliance on sophisticated computational and information theoretic techniques. We give an overview of the complex optical and image processing techniques required for such systems to become operational. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Lyon, RG (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 9 TC 4 Z9 4 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3682-8 J9 P SOC PHOTO-OPT INS PY 2000 VL 4056 BP 86 EP 98 DI 10.1117/12.381671 PG 13 WC Engineering, Electrical & Electronic; Optics SC Engineering; Optics GA BQ40G UT WOS:000088256200007 ER PT S AU Le Moigne, J Zavorin, I AF Le Moigne, J Zavorin, I BE Szu, HH Vetterli, M Campbell, WJ Buss, JR TI Use of wavelets for image registration SO WAVELET APPLICATIONS VII SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Wavelet Applications VII CY APR 26-28, 2000 CL ORLANDO, FL SP SPIE DE image registration; wavelet decomposition; steerable filters; translation invariance AB Wavelet-based image registration has previously been proposed by the authors. In previous work, maxima obtained from orthogonal Daubechies filters as well as from Simoncelli steerable filters were utilized and compared to register images in a multi-resolution fashion. The first comparative results between both types of filters showed that despite the lack of translation-invariance of the orthogonal filters, both types of filters gave very encouraging results for non-noisy data and small transformations. But the accuracy obtained with orthogonal filters seemed to degrade very quickly for large rotations and large amounts of noise, while results obtained with steerable filters appeared much more stable under these conditions. In this work, we are performing a systematic study of the robustness of such methods as a function of translation, rotation and noise parameters, for both types of filters and using data from the Landsat/Thematic Mapper (TM). C1 NASA, Goddard Space Flight Ctr, Appl Informat Sci Branch, Greenbelt, MD 20771 USA. RP Le Moigne, J (reprint author), NASA, Goddard Space Flight Ctr, Appl Informat Sci Branch, Greenbelt, MD 20771 USA. NR 24 TC 3 Z9 3 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3682-8 J9 P SOC PHOTO-OPT INS PY 2000 VL 4056 BP 99 EP 108 DI 10.1117/12.381672 PG 10 WC Engineering, Electrical & Electronic; Optics SC Engineering; Optics GA BQ40G UT WOS:000088256200008 ER PT S AU Kiang, RK Kyle, HL AF Kiang, RK Kyle, HL BE Szu, HH Vetterli, M Campbell, WJ Buss, JR TI In search of sun-climate connection using solar irradiance measurements and climate records SO WAVELET APPLICATIONS VII SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Wavelet Applications VII CY APR 26-28, 2000 CL ORLANDO, FL SP SPIE DE wavelet transform; global warming; climate change; greenhouse gases ID ACTIVITY INDEXES; WAVELETS; CYCLE; PERIODICITIES; NIMBUS-7; OZONE AB The Earth's temperature has risen approximately 0.5 degree-C in the last 150 years. Because the atmospheric concentration of carbon dioxide has increased nearly 30% since the industrial revolution, a common conjecture, supported by various climate models, is that anthropogenic greenhouse gases have contributed to global warming. Another probable factor for the warming is the natural variation of solar irradiance. Although the variation is as small as 0.1%, it is hypothesized that it contributes to part of the temperature rise. Warmer or cooler ocean temperature at one part of the Globe may manifest as abnormally wet or dry weather patterns some months or years later at another part of the globe. Furthermore, the lower atmosphere can be affected through its coupling with the stratosphere, after the stratospheric ozone absorbs the ultraviolet portion of the solar irradiance. In this paper, we use wavelet transforms based on Morlet wavelet to analyze the time-frequency properties in several datasets, including the Radiation Budget measurements, the long-term total solar irradiance time series, the long-term temperature at two locations for the North and the South Hemisphere. The main solar cycle, approximately 11 years, are identified in the long-term total solar irradiance time series. The wavelet transform of the temperature datasets show annual cycle but not the solar cycle. Some correlation is seen between the length of the solar cycle extracted from the wavelet transform and the North Hemisphere temperature time series. The absence of the 11-year cycle in a time series does not necessarily imply that the geophysical parameter is not affected by the solar cycle; rather it simply reflects the complex nature of the Earth's response to climate forcings. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Kiang, RK (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 22 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3682-8 J9 P SOC PHOTO-OPT INS PY 2000 VL 4056 BP 110 EP 119 DI 10.1117/12.381673 PG 10 WC Engineering, Electrical & Electronic; Optics SC Engineering; Optics GA BQ40G UT WOS:000088256200009 ER PT S AU Huang, NE AF Huang, NE BE Szu, HH Vetterli, M Campbell, WJ Buss, JR TI A new method for nonlinear and nonstationary time series analysis: Empirical mode decomposition and Hilbert spectral analysis SO WAVELET APPLICATIONS VII SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Wavelet Applications VII CY APR 26-28, 2000 CL ORLANDO, FL SP SPIE DE time-frequency analysis; nonstationary and nonlinear; time series analysis; Hilbert spectrum; wavelet analysis; instantaneous frequency; empirical mode decomposition method ID FREQUENCY SIGNAL ANALYSIS; WIGNER DISTRIBUTION; TOOL AB A new method for analyzing nonlinear and nonstationary data has been developed. The key part of the method is the Empirical Mode Decomposition method with which any complicated data set can be decomposed into a finite and often small number of Intrinsic Mode Functions (IMF). An IMF is defined as any function having the same numbers of zero-crossing and extrema, and also having symmetric envelopes defined by the local maxima and minima respectively. The IMF also admits well-behaved Hilbert transform. This decomposition method is adaptive, and, therefore, highly efficient. Since the decomposition is based on the local characteristic time scale of the data, it is applicable to nonlinear and nonstationary processes. With the Hilbert transform, the Intrinsic Mode Functions yield instantaneous frequencies as functions of time that give sharp identifications of imbedded structures. The final presentation of the results is an energy-frequency-time distribution, designated as the Hilbert Spectrum. Comparisons with Wavelet and window Fourier analysis show the new method offers much better temporal and frequency resolutions. C1 NASA, Goddard Space Flight Ctr, Lab Hydrospher Proc, Greenbelt, MD 20771 USA. RP Huang, NE (reprint author), NASA, Goddard Space Flight Ctr, Lab Hydrospher Proc, Code 661, Greenbelt, MD 20771 USA. NR 26 TC 7 Z9 7 U1 3 U2 11 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3682-8 J9 P SOC PHOTO-OPT INS PY 2000 VL 4056 BP 197 EP 209 DI 10.1117/12.381681 PG 13 WC Engineering, Electrical & Electronic; Optics SC Engineering; Optics GA BQ40G UT WOS:000088256200017 ER PT S AU Ofman, L AF Ofman, L BE Verheest, F Goossens, M Hellberg, MA Bharuthram, R TI Three-fluid 2.5D MHD models of waves in solar coronal holes and the relation to SOHO/UVCS observations SO WAVES IN DUSTY, SOLAR, AND SPACE PLASMAS SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT International Workshop on Waves in Dusty, Solar, and Space Plasmas CY MAY 22-26, 2000 CL LEUVEN, BELGIUM SP Flemish Dept Sci & Technol ID WIND ACCELERATION; SOLITARY WAVES AB The physical properties of the minor ions in the corona provide clues on the coronal heating and solar wind acceleration mechanism. Recent observations show that protons and minor ions are hot (T-p > 10(6) K, T-i > 10(8) K) and anisotropic in coronal holes. A possible cause of the large perpendicular motions is unresolved Alfvenic fluctuations in the solar wind. Using the three-fluid 2.5D MHD model I have shown that that the unresolved Alfvenic fluctuations lead to apparent proton temperature and anisotropy consistent with UVCS observations. I show the calculated dependence of the apparent kinetic temperatures of protons and O5+ ions with heliocentric distance and compare the results to the UVCS observations. C1 NASA, Goddard Space Flight Ctr, Raytheon ITSS, Greenbelt, MD 20771 USA. RP Ofman, L (reprint author), NASA, Goddard Space Flight Ctr, Raytheon ITSS, Code 682, Greenbelt, MD 20771 USA. NR 12 TC 1 Z9 1 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-962-9 J9 AIP CONF PROC PY 2000 VL 537 BP 119 EP 125 PG 7 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BR02R UT WOS:000165407300015 ER PT S AU Bergman, LA Yeh, C Morookian, J AF Bergman, LA Yeh, C Morookian, J BE Chen, RT Lipscomb, GF TI New advances in time aligned parallel WDM transmission SO WDM AND PHOTONIC SWITCHING DEVICES FOR NETWORK APPLICATIONS SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on WDM and Photonic Switching Devices for Network Applications CY JAN 27-28, 2000 CL SAN JOSE, CA SP SPIE ID DIVISION-MULTIPLEXED BEAMS; NONLINEAR FIBER; PULSE AB For ultra-high-speed single media parallel interconnects, an all optical single fiber WDM format of transmitting parallel bits rather than a fiber ribbon format-where parallel bits are sent through corresponding parallel fibers in a ribbon format, can be the media of choice. Here, we shall discuss the realization of a multi-km x gbytes/sec bit-parallel WDM (BP-WDM) single fiber link. The distance-speed product of this single fiber link is more than several orders of magnitude higher than that of a fiber ribbon link. The design of a 12 bit-parallel channels WDM system operating at 1 Gbit/sec per channel rate through a single fiber will first be presented. Experimental results for a two channel system operating at that rate are given. Further improvement of distance-speed product for the BP-WDM link can be obtained with JPL's newly developed 20 Gbits/sec per channel laser diode array transmitter. Also, new computer simulation results on how a large amplitude co-propagating pulse may induce pulse compression on all the co-propagating data pulses, thereby improving the shaping of these pulses for a WDM system, will be presented and discussed. The existence of WDM solitons is also shown. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Bergman, LA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 126-201, Pasadena, CA 91109 USA. NR 14 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3566-X J9 P SOC PHOTO-OPT INS PY 2000 VL 3949 BP 25 EP 35 DI 10.1117/12.382890 PG 11 WC Engineering, Electrical & Electronic; Optics; Telecommunications SC Engineering; Optics; Telecommunications GA BQ18V UT WOS:000087385800003 ER PT S AU Gehrels, N AF Gehrels, N BE Flanagan, KA Siegmund, OHW TI The swift gamma ray burst MIDEX SO X-RAY AND GAMMA-RAY INSTRUMENTATION FOR ASTRONOMY XI SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on X-Ray and Gamma-Ray Instrumentation for Astronomy IX CY AUG 02-04, 2000 CL SAN DIEGO, CA SP SPIE DE Space Mission; gamma-ray; gamma-ray bursts; solid state detectors; CdZnTe ID 28 FEBRUARY 1997; HIGH-REDSHIFT; AFTERGLOW; GALAXIES AB Swift is a first of its kind multiwavelength transient observatory for gamma-ray burst astronomy. It has the optimum capabilities for the next breakthroughs in determining the origin of gamma-ray bursts and their afterglows as well as using bursts to probe the early Universe. Swift will also perform the first sensitive hard X-ray survey of the sky. The mission is being developed by an international collaboration and consists of three instruments, the Burst Alert Telescope (BAT), the X-ray Telescope (XRT), and the Ultraviolet and Optical Telescope (UVOT). The BAT, a wide-field gamma-ray detector will detect similar to1 gamma-ray burst per day with a sensitivity 5 times that of BATSE. The sensitive narrow-field XRT and UVOT will be autonomously slewed to the burst location in 20 to 70 seconds to determine 0.3-5.0 arcsec positions and perform optical, UV, and X-ray spectrophotometry. On-board measurements of redshift will also be done for hundreds of bursts. Swift will incorporate superb, low-cost instruments using existing flight-spare hardware and designs. Strong education/public outreach and follow-up programs will help to engage the public and astronomical community. Swift has been selected by NASA for development and launch in 2003. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Gehrels, N (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RI Gehrels, Neil/D-2971-2012 NR 28 TC 17 Z9 17 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3785-9 J9 P SOC PHOTO-OPT INS PY 2000 VL 4140 BP 42 EP 49 DI 10.1117/12.409142 PG 8 WC Astronomy & Astrophysics; Instruments & Instrumentation SC Astronomy & Astrophysics; Instruments & Instrumentation GA BR53H UT WOS:000166723400005 ER PT S AU Barthelmy, SD AF Barthelmy, SD CA Swift-BAT Instrument Team BE Flanagan, KA Siegmund, OHW TI The Burst Alert Telescope (BAT) on the Swift MIDEX mission SO X-RAY AND GAMMA-RAY INSTRUMENTATION FOR ASTRONOMY XI SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on X-Ray and Gamma-Ray Instrumentation for Astronomy IX CY AUG 02-04, 2000 CL SAN DIEGO, CA SP SPIE DE gamma-ray; GRB; hard x-ray; survey; burst; afterglow; CZT; coded aperture; astrophysics; cosmology ID GAMMA-RAY BURST; 28 FEBRUARY 1997 AB The Burst Alert telescope (BAT) is one of 3 instruments on the Swift MIDEX spacecraft to study gamma-ray bursts (GRBs). The BAT instrument is the instrument that first detects the GRB and localizes the burst direction to an accuracy of 1-4 arcmin within 10 sec after the start of the event. These locations cause the spacecraft to autonomously slew to point the two narrow-FOV instruments at the burst location within 20-70 sec to make follow-up x-ray and optical observations. BAT is a wide-FOV coded-aperture instrument with a CdZnTe detector plane. The detector plane is composed of 32,768 pieces of CdZnTe (4x4x2mm), and the coded-aperture mask is composed of similar to 50,000 pieces of lead (5x5x1mm) with a 1-m separation between mask and detector plane. The BAT operates over the 10-150 keV energy range with similar to7 keV resolution, a sensitivity of 0.2 ph/cm(2)-sec, and a 1.4 sr (half-coded) FOV. We expect to detect similar to 300 GRBs/yr for a 3-year mission. The BAT also performs an all-sky hard x-ray survey with a sensitivity of similar to1 mCrab (systematic limit) and as a hard x-ray transient monitor. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Barthelmy, SD (reprint author), NASA, Goddard Space Flight Ctr, Code 661, Greenbelt, MD 20771 USA. RI Barthelmy, Scott/D-2943-2012 NR 9 TC 37 Z9 37 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3785-9 J9 P SOC PHOTO-OPT INS PY 2000 VL 4140 BP 50 EP 63 DI 10.1117/12.409149 PG 14 WC Astronomy & Astrophysics; Instruments & Instrumentation SC Astronomy & Astrophysics; Instruments & Instrumentation GA BR53H UT WOS:000166723400006 ER PT S AU O'Dell, SL Bautz, MW Blackwell, WC Butt, YM Cameron, RA Elsner, RF Gussenhovene, MS Kolodziejczak, JJ Minow, JI Suggs, RM Swartz, DA Tennant, AF Virani, SN Warren, K AF O'Dell, SL Bautz, MW Blackwell, WC Butt, YM Cameron, RA Elsner, RF Gussenhovene, MS Kolodziejczak, JJ Minow, JI Suggs, RM Swartz, DA Tennant, AF Virani, SN Warren, K BE Flanagan, KA Siegmund, OHW TI Radiation environment of the Chandra X-ray Observatory SO X-RAY AND GAMMA-RAY INSTRUMENTATION FOR ASTRONOMY XI SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on X-Ray and Gamma-Ray Instrumentation for Astronomy IX CY AUG 02-04, 2000 CL SAN DIEGO, CA SP SPIE DE radiation; protons; CCDs; space environment; space missions ID ADVANCED-COMPOSITION-EXPLORER; ASTROPHYSICS FACILITY AXAF; ALPHA-MONITOR; CALIBRATION; SPECTROMETER; CCDS AB The Chandra X-ray Observatory, the x-ray component of NASA's Great Observatories, provides unprecedented subarcsecond imaging, imaging spectrometry, and high-resolution dispersive spectroscopy of cosmic x-ray sources. During the initial phase of operation, some of the focal-plane charge-coupled devices (CCDs) - namely, the front-illuminated devices - experienced an unanticipated increase in charge-transfer inefficiency (CTI). Investigation of this anomaly determined the root cause to be radiation damage by weakly penetrating protons, entering the telescope's aperture and scattered off the mirrors into the focal plane. Subsequent changes in operating procedures have slowed the rate of increase of the CTI of the front-illuminated CCDs to acceptable levels. There has been no measurable degradation of the back-illuminated CCDs. C1 NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP O'Dell, SL (reprint author), NASA, George C Marshall Space Flight Ctr, MSFC-SD50, Huntsville, AL 35812 USA. OI O'Dell, Stephen/0000-0002-1868-8056 NR 33 TC 18 Z9 18 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3785-9 J9 P SOC PHOTO-OPT INS PY 2000 VL 4140 BP 99 EP 110 DI 10.1117/12.409104 PG 12 WC Astronomy & Astrophysics; Instruments & Instrumentation SC Astronomy & Astrophysics; Instruments & Instrumentation GA BR53H UT WOS:000166723400010 ER PT S AU Kolodziejczak, JJ Elsner, RF Austin, RA O'Dell, SL AF Kolodziejczak, JJ Elsner, RF Austin, RA O'Dell, SL BE Flanagan, KA Siegmund, OHW TI Ion transmission to the focal plane of the Chandra X-ray Observatory SO X-RAY AND GAMMA-RAY INSTRUMENTATION FOR ASTRONOMY XI SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on X-Ray and Gamma-Ray Instrumentation for Astronomy IX CY AUG 02-04, 2000 CL SAN DIEGO, CA SP SPIE DE Chandra; ACIS; proton damage; ion scattering; ion transmission; x-ray; HRMA; CCD; space radiation hazard AB The ACIS instrument on-board the Chandra X-ray Observatory (CXO) experienced pronounced degradation in spectrometric performance during the spacecraft's orbital activation and calibration phase. This damage was associated with a sharp increase in charge-transfer inefficiency combined with relatively constant dark current. Damage occurred only during passage through the earth's radiation belts, and only when ACIS remained in the focal plane during the passage. Subsequent measurements and analyses support the conjecture that the damaging radiation entered through the Observatory's High-Resolution Mirror Assembly (HRMA) aperture. A mechanism whereby low-energy magnetospheric protons and heavier ions are scattered through the HRMA and reach the focal plane with just enough energy to stop in the CCD's charge transfer channel provides a reasonably consistent explanation of all observed phenomena. In this paper, we shall describe analyses which support this conclusion. We simulated the mirror surfaces and various path elements using a standard ion transmission code to generate a bi-directional reflectance distribution function (BRDF). We then convolved the BRDF with the geometry using a ray-trace code. This paper presents damage estimates using measured proton fluences and ground measurements of ACIS-type CCD damage versus proton energy and compares them with observed on-orbit damage. C1 NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Kolodziejczak, JJ (reprint author), NASA, George C Marshall Space Flight Ctr, SD50, Huntsville, AL 35812 USA. OI O'Dell, Stephen/0000-0002-1868-8056 NR 10 TC 10 Z9 10 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3785-9 J9 P SOC PHOTO-OPT INS PY 2000 VL 4140 BP 135 EP 143 DI 10.1117/12.409107 PG 9 WC Astronomy & Astrophysics; Instruments & Instrumentation SC Astronomy & Astrophysics; Instruments & Instrumentation GA BR53H UT WOS:000166723400013 ER PT S AU Black, JK Deines-Jones, P Hunter, SD Jahoda, K Huang, J Jackson, TN Klauk, H Qian, W AF Black, JK Deines-Jones, P Hunter, SD Jahoda, K Huang, J Jackson, TN Klauk, H Qian, W BE Flanagan, KA Siegmund, OHW TI Imaging micro-well detectors for X-ray and gamma-ray applications SO X-RAY AND GAMMA-RAY INSTRUMENTATION FOR ASTRONOMY XI SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on X-Ray and Gamma-Ray Instrumentation for Astronomy IX CY AUG 02-04, 2000 CL SAN DIEGO, CA SP SPIE DE micro-well; CAT; WELL; GEM; avalanche; gas detector; proportional counter; pixel detector; X-ray image ID GAS DETECTORS AB Gas proportional counter arrays based on the micro-well are an example of a new generation of detectors that exploit narrow anode-cathode gaps, rather than fine anodes, to create gas gain. These are inherently imaging pixel detectors that can be made very large for reasonable costs. Because of their intrinsic gain and room-temperature operation, they can be instrumented at very low power per unit area, making them valuable for a variety of space-flight applications where large-area X-ray imaging or particle tracking is required. We discuss micro-well detectors as focal plane imager for Lobster-LSS, a proposed soft X-ray all-sky monitor, and as electron trackers for the Next Generation High-Energy Gamma Ray mission. We have developed a fabrication technique using a masked UV laser that allows us both to machine micro-wells in polymer substrates and to pattern metal electrodes. We have used this technique to fabricate detectors which image X-rays by simultaneously reading out orthogonal anode and cathode strips. We present imaging results from these detectors, as well as gain and energy resolution measurements that agree well with results from other groups. C1 NASA, Goddard Space Flight Ctr, High Energy Astrophys Lab, Greenbelt, MD 20771 USA. RP Black, JK (reprint author), NASA, Goddard Space Flight Ctr, High Energy Astrophys Lab, Greenbelt, MD 20771 USA. RI Hunter, Stanley/D-2942-2012; Jahoda, Keith/D-5616-2012 NR 13 TC 9 Z9 9 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3785-9 J9 P SOC PHOTO-OPT INS PY 2000 VL 4140 BP 313 EP 323 DI 10.1117/12.409126 PG 11 WC Astronomy & Astrophysics; Instruments & Instrumentation SC Astronomy & Astrophysics; Instruments & Instrumentation GA BR53H UT WOS:000166723400031 ER PT S AU Stahle, CK Brekosky, RP Figueroa-Feliciano, E Finkbeiner, FM Gygax, JD Li, MJ Lindeman, MA Porter, FS Tralshawala, N AF Stahle, CK Brekosky, RP Figueroa-Feliciano, E Finkbeiner, FM Gygax, JD Li, MJ Lindeman, MA Porter, FS Tralshawala, N BE Flanagan, KA Siegmund, OHW TI Progress in the development of Mo/Au transition-edge sensors for x-ray spectroscopy SO X-RAY AND GAMMA-RAY INSTRUMENTATION FOR ASTRONOMY XI SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on X-Ray and Gamma-Ray Instrumentation for Astronomy IX CY AUG 02-04, 2000 CL SAN DIEGO, CA SP SPIE DE microcalorimeter; x-ray spectroscopy; imaging spectrometer AB X-ray microcalorimeters using transition-edge sensors (TES) show great promise for use in astronomical x-ray spectroscopy. We have obtained very high energy resolution (2.8 eV at 1.5 keV and 3.7 eV at 3.3 keV) in a large, isolated TES pixel using a Mo/Au proximity-effect bilayer on a silicon nitride membrane. We will discuss the performance and our characterization of that device. In order to be truly suitable for use behind an x-ray telescope, however, such devices need to be arrayed with a pixel size and focal-plane coverage commensurate with the telescope focal length and spatial resolution. Since this requires fitting the TES and its thermal link, a critical component of each calorimeter pixel, into a far more compact geometry than has previously been investigated, we must study the fundamental scaling laws in pixel optimization. We have designed a photolithography mask that will allow us to probe the range in thermal conductance that can be obtained by perforating the nitride membrane in a narrow perimeter around the sensor. This mask will also show the effects of reducing the TES area. Though we have not yet tested devices of the compact designs, we will present our progress in several of the key processing steps and discuss the parameter space of our intended investigations. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Stahle, CK (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RI Porter, Frederick/D-3501-2012 OI Porter, Frederick/0000-0002-6374-1119 NR 17 TC 15 Z9 15 U1 0 U2 3 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3785-9 J9 P SOC PHOTO-OPT INS PY 2000 VL 4140 BP 367 EP 375 DI 10.1117/12.409131 PG 9 WC Astronomy & Astrophysics; Instruments & Instrumentation SC Astronomy & Astrophysics; Instruments & Instrumentation GA BR53H UT WOS:000166723400036 ER PT S AU Porter, FS Audley, MD Beiersdorfer, P Boyce, KR Brekosky, RP Brown, GV Gendreau, KC Gygax, J Kahn, S Kelley, RL Stahle, CK Szymkowiak, AE AF Porter, FS Audley, MD Beiersdorfer, P Boyce, KR Brekosky, RP Brown, GV Gendreau, KC Gygax, J Kahn, S Kelley, RL Stahle, CK Szymkowiak, AE BE Flanagan, KA Siegmund, OHW TI Laboratory astrophysics using a spare XRS microcalorimeter SO X-RAY AND GAMMA-RAY INSTRUMENTATION FOR ASTRONOMY XI SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on X-Ray and Gamma-Ray Instrumentation for Astronomy IX CY AUG 02-04, 2000 CL SAN DIEGO, CA SP SPIE DE X-ray; laboratory astrophysics; cryogenic detector ID BEAM ION-TRAP; X-RAY SPECTROMETER; CALIBRATION; PERFORMANCE; SPECTRUM; DESIGN AB The XRS instrument on Astro-E is a fully self-contained microcalorimeter x-ray instrument capable of acquiring, optimally filtering, and characterizing events for 32 independent pixels. We have recently integrated a full engineering model XRS detector system into a laboratory cryostat for use on the electron beam ion trap (EBIT) at Lawrence Livermore National Laboratory. The detector system contains a microcalorimeter array with 32 instrumented pixels heat sunk to 60 mK using an adiabatic demagnetization refrigerator. The instrument has a composite resolution of 8eV at 1 keV and 1 1eV at 6 keV with a minimum of 98% quantum efficiency and a total collecting area of 13 mm(2). This will allow high spectral resolution, broadband observations of plasmas with known ionization states that are produced in the EBIT experiment. Unique to our instrument are exceptionally well characterized 1000 Angstrom thick aluminum on polyimide infrared blocking filters. The detailed transmission function including the edge fine structure of these filters has been measured in our laboratory using a variable spaced grating spectrometer. This will allow the instrument to perform the first broadband absolute flux measurements with the EBIT instrument. The instrument performance as well as the results of preliminary measurements of Fe K and L shell at fixed electron energy, Fe emission with Maxwellian electron distributions, and phase resolved spectroscopy of ionizing plasmas will be discussed. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Porter, FS (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RI Porter, Frederick/D-3501-2012; Kelley, Richard/K-4474-2012 OI Porter, Frederick/0000-0002-6374-1119; NR 18 TC 34 Z9 34 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3785-9 J9 P SOC PHOTO-OPT INS PY 2000 VL 4140 BP 407 EP 418 DI 10.1117/12.409137 PG 12 WC Astronomy & Astrophysics; Instruments & Instrumentation SC Astronomy & Astrophysics; Instruments & Instrumentation GA BR53H UT WOS:000166723400041 ER PT S AU Figueroa-Feliciano, E Stahle, CK Finkbeiner, FM Li, M Lindeman, MA Tralshawala, N Stahle, CM AF Figueroa-Feliciano, E Stahle, CK Finkbeiner, FM Li, M Lindeman, MA Tralshawala, N Stahle, CM BE Flanagan, KA Siegmund, OHW TI Position-sensing transition-edge sensors for large-field, high-energy-resolution X-ray imaging spectroscopy SO X-RAY AND GAMMA-RAY INSTRUMENTATION FOR ASTRONOMY XI SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on X-Ray and Gamma-Ray Instrumentation for Astronomy IX CY AUG 02-04, 2000 CL SAN DIEGO, CA SP SPIE DE X-ray; calorimeter; microcalorimeter; spectrometer; imaging spectrometer; TES; PoST AB In the X-ray astrophysics community, the desire for wide-field, high-resolution? X-ray imaging spectrometers has been growing for some time. We present a concept for such a detector called a Position-Sensing: Transition-edge sensor (PoST). A PoST is a calorimeter consisting of two Transition-Edge Sensors (TESs) on the ends of a long absorber to do one dimensional imaging spectroscopy. Comparing the rise time and energy estimates obtained from each TES for a given event, the position of that event in the PoST is determined. Energy is inferred front the sum of the two signals on the TESs. We have designed 7, 15, and 32 pixel PoSTs using our Mo/Au TESs and bismuth absorbers. We discuss the theory, modeling, operation and readout of PoSTs and the latest results from our development. C1 NASA, Goddard Space Flight Ctr, High Energy Astrophys Lab, Greenbelt, MD 20771 USA. RP Figueroa-Feliciano, E (reprint author), NASA, Goddard Space Flight Ctr, High Energy Astrophys Lab, Mail Code 662, Greenbelt, MD 20771 USA. NR 5 TC 2 Z9 2 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 0-8194-3785-9 J9 P SOC PHOTO-OPT INS PY 2000 VL 4140 BP 419 EP 427 DI 10.1117/12.409138 PG 9 WC Astronomy & Astrophysics; Instruments & Instrumentation SC Astronomy & Astrophysics; Instruments & Instrumentation GA BR53H UT WOS:000166723400042 ER PT S AU Pecher, K Kneedler, E Rothe, J Meigs, G Warwick, T Nealson, K Tonner, B AF Pecher, K Kneedler, E Rothe, J Meigs, G Warwick, T Nealson, K Tonner, B BE MeyerIlse, W Warwick, T Attwood, D TI Charge state mapping of mixed valent iron and manganese mineral particles using Scanning Transmission X-ray Microscopy (STXM) SO X-RAY MICROSCOPY, PROCEEDINGS SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 6th International Conference on X-Ray Microscopy CY AUG 02-06, 1999 CL BERKELEY, CA ID ADVANCED LIGHT-SOURCE; ABSORPTION-SPECTROSCOPY; TRANSITION-METALS; MATERIALS SCIENCE; OXIDATION-STATE; SPECTROMICROSCOPY; CHEMISTRY; COMPLEXES; FIELD AB The interfaces between solid mineral particles and water play a crucial role in partitioning and chemical transformation of many inorganic as well as organic pollutants in environmental systems. Among environmentally significant minerals, mixed-valent oxides and hydroxides of iron (e.g. magnetite, green rusts) and manganese (hausmanite, birnessite) have been recognized as particularly strong sorbents for metal ions. In addition, minerals containing Fe(II) have recently been proven to be powerful reductants for a wide range of pollutants. Chemical properties of these minerals strongly depend on the distribution and availability of reactive sites and little is known quantitatively about the nature of these sites. We have investigated the bulk distribution of charge states of manganese (Mn (II, III, IV)) and iron (Fe(II, III)) in single particles of natural manganese nodules and synthetic green rusts using Scanning Transmission X-ray SpectroMicroscopy (STXM). Pixel resolved spectra (XANES) extracted from stacks of images taken at different wave lengths across the metal absorption edge were fitted to total electron yield (TEY) spectra of single valent reference compounds. Two dimensional maps of bulk charge state distributions clearly reveal domains of different oxidation states within single particles of Mn-nodules and green rust precipitates. Changes of oxidation states of iron were followed as a result of reductive transformation of an environmental contaminant (CCl4) using green rust as the only reductant. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Pecher, K (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. NR 27 TC 1 Z9 1 U1 0 U2 3 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 1-56396-926-2 J9 AIP CONF PROC PY 2000 VL 507 BP 291 EP 300 PG 10 WC Instruments & Instrumentation; Microscopy SC Instruments & Instrumentation; Microscopy GA BX39K UT WOS:000185143000050 ER PT S AU Weisskopf, MC Tananbaum, HD Van Speybroeck, LP O'Dell, SL AF Weisskopf, MC Tananbaum, HD Van Speybroeck, LP O'Dell, SL BE Trumper, JE Aschenbach, B TI Chandra X-Ray Observatory (CXO): Overview SO X-RAY OPTICS, INSTRUMENTS, AND MISSIONS III SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on X-Ray Optics, Instruments, and Missions III CY MAR 27-29, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE Chandra; CXO; space missions; x rays; grazing-incidence optics; gratings; detectors; x-ray imaging; x-ray spectroscopy; x-ray astronomy ID HIGH-RESOLUTION CAMERA; TRANSMISSION GRATING SPECTROMETER; EFFECTIVE AREA; ASTROPHYSICS FACILITY; CALIBRATION FACILITY; AXAF CALIBRATION; PERFORMANCE; HETGS AB The Chandra X-nay Observatory (CXO), the x-ray component of NASA's Great Observatories, was launched early in the morning of 1999, July 23 by the Space Shuttle Columbia. The Shuttle launch was only the first step in placing the observatory in orbit. After release from the cargo bay, the Inertial Upper Stage performed two firings, and separated from the observatory as planned. Finally, after five firings of Chandra's own Integral Propulsion System - the last of which took place 15 days after launch - the observatory was placed in its highly elliptical orbit of similar to 140,000 km apogee and similar to 10,000 bm perigee. After activation, the first x-rays focussed by the telescope were observed on 1999, August 12. Beginning with these initial observations one could see that the telescope had survived the launch environment and was operating as expected. The month following the opening of the sunshade door was spent adjusting the focus for each set of instrument configurations, determining the optical axis, calibrating the star camera, establishing the relative response functions, determining energy scales, and taking a series of "publicity" images. Each observation proved to be far more revealing than was expected. Finally, and despite an initial surprise and setback due to the discovery that the Chandra x-ray telescope nas far more efficient for concentrating: low-energy protons than had been anticipated, the observatory is performing well and is returning superb scientific data. Together with other space observatories, most notably the recently activated XMM-Newton, it is clear that we are entering a new era of discovery in high-energy astrophysics. C1 NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Weisskopf, MC (reprint author), NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. OI O'Dell, Stephen/0000-0002-1868-8056 NR 41 TC 260 Z9 261 U1 0 U2 3 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3637-2 J9 P SOC PHOTO-OPT INS PY 2000 VL 4012 BP 2 EP 16 DI 10.1117/12.391545 PG 15 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70G UT WOS:000089219400001 ER PT S AU Joy, M Shipley, A Cash, W Carter, J Zissa, D Cuntz, M AF Joy, M Shipley, A Cash, W Carter, J Zissa, D Cuntz, M BE Trumper, JE Aschenbach, B TI Experimental results from a grazing incidence X-ray interferometer SO X-RAY OPTICS, INSTRUMENTS, AND MISSIONS III SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on X-Ray Optics, Instruments, and Missions III CY MAR 27-29, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE x-rays; interferometry; x-ray astronomy; grazing incidence x-ray optics ID LINE AB A prototype grazing incidence interferometer has been built and tested at EUV and X-ray wavelengths using a 120 meter long vacuum test facility at Marshall Space Flight Center. We describe the design and construction of the interferometer, the EUV and x-ray sources and detector systems, and compare the interferometric fringe measurements with theoretical predictions. C1 NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Joy, M (reprint author), NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. NR 3 TC 7 Z9 7 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3637-2 J9 P SOC PHOTO-OPT INS PY 2000 VL 4012 BP 270 EP 277 DI 10.1117/12.391562 PG 8 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70G UT WOS:000089219400025 ER PT S AU O'Dell, SL Jones, WD Ramsey, BD Engelhaupt, D Smith, WS Cohen, LM Van Speybroeck, LP AF O'Dell, SL Jones, WD Ramsey, BD Engelhaupt, D Smith, WS Cohen, LM Van Speybroeck, LP BE Trumper, JE Aschenbach, B TI Development of constellation-x optics technologies at MSFC SO X-RAY OPTICS, INSTRUMENTS, AND MISSIONS III SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on X-Ray Optics, Instruments, and Missions III CY MAR 27-29, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE grazing-incidence optics; replicated optics; space missions; electroforming ID ASTROPHYSICS FACILITY AXAF; RAY-CALIBRATION; MIRROR; TELESCOPE; PERFORMANCE; SPECTROMETER; MISSION AB The Constellation X-ray Mission is the next major x-ray-astronomy mission in the NASA Space Science road map. As a follow-on to the Chandra X-ray Observatory - neel the Advanced X-ray Astrophysics Facility (AXAF) - Constellation X will provide high-throughput. high-resolution spectroscopy to probe the gravitational field, kinematics. temperature, density, composition, and ionization state of cosmic sources. The Constellation-X observatory system comprises four separate satellites, each with one large Spectroscopy X-ray Telescope (SXT, with a pixelated microcalorimeter and a reflection-grating-CCD spectrometer) and three smaller Hard X-ray Telescopes (HXTs, with pixelated hard-x-ray detectors). Essential to the success of Constellation X is the development of large (1.6-m-diameter), lightweight oy ties for the SXT mirror assembly. With the Smithsonian Astrophysical Observatory (SAO), teams led by NASA's Marshall Space Flight Center (MSFC), by NASA's Goddard Space Flight Center (GSFC), and by Italy's Osservatorio Astronomico di Brera (OAB) are currently developing competing mirror technologies for Lightweight SXT optics, toward achieving the required system-level half-power diameter - better than 15 arcsec. MSFC has emphasized technologies for full-shell replicated optics. of electroformed nickel alloys. Having identified a passivation coating to effect low, controlled adhesion and having developed new high-strength nickel alloys, MSFC is refining the plating processes to achieve the requisite low residual stress and to stiffen the thin-walled optics with integral structures. In collaboration with SAG, MSFC is exploring less mature technologies, which may result in more robust (lighter and/or stiffer) x-ray optical systems. C1 NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP O'Dell, SL (reprint author), NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. OI O'Dell, Stephen/0000-0002-1868-8056 NR 30 TC 5 Z9 5 U1 0 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 0-8194-3637-2 J9 P SOC PHOTO-OPT INS PY 2000 VL 4012 BP 316 EP 327 DI 10.1117/12.391568 PG 12 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70G UT WOS:000089219400030 ER PT S AU Petre, R Chen, C Cohen, LM Content, DA Harms, RJ Monnelly, G Saha, TT Schattenburg, ML Serlemitsos, PJ Zhang, WW AF Petre, R Chen, C Cohen, LM Content, DA Harms, RJ Monnelly, G Saha, TT Schattenburg, ML Serlemitsos, PJ Zhang, WW BE Trumper, JE Aschenbach, B TI Development of segmented x-ray mirrors for Constellation-X SO X-RAY OPTICS, INSTRUMENTS, AND MISSIONS III SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on X-Ray Optics, Instruments, and Missions III CY MAR 27-29, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE high throughput X-ray optics; grazing incidence mirrors; Constellation-X ID TELESCOPE; HEFT AB We describe recent progress toward producing a segmented mirror that meets the mass and angular resolution requirements for the Constellation-X Spectroscopy X-ray Telescope (SXT). While the segmented approach has its heritage in conical thin foil X-ray mirrors pioneered at GSFC, the Constellation-X implementation introduces innovations in nearly all components. The baseline configuration uses thermally formed glass for reflector substrates; thermally formed Be is being investigated as an option. Alignment is performed using etched Si microstructures that locate reflectors to submicron accuracy. The only aspect preserved from previous mirrors is epoxy replication of the X-ray reflecting surface. Thus far, all developments have been at the component level. Nonetheless, we have made substantial progress toward meeting the Constellation-X SXT angular resolution goal. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Petre, R (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RI Zhang, William/D-3535-2012 NR 6 TC 5 Z9 5 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3637-2 J9 P SOC PHOTO-OPT INS PY 2000 VL 4012 BP 370 EP 378 DI 10.1117/12.391572 PG 9 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70G UT WOS:000089219400035 ER PT S AU Elsner, RF Kolodziejczak, JJ O'Dell, SL Swartz, DA Tennant, AF Weisskopf, MC AF Elsner, RF Kolodziejczak, JJ O'Dell, SL Swartz, DA Tennant, AF Weisskopf, MC BE Trumper, JE Aschenbach, B TI Measurements with the Chandra X-Ray Observatory's flight contamination monitor SO X-RAY OPTICS, INSTRUMENTS, AND MISSIONS III SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on X-Ray Optics, Instruments, and Missions III CY MAR 27-29, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE Chandra; CXO; space missions; x rays; grazing-incidence optics; calibration; contamination; x-ray missions ID CALIBRATION AB NASA's Chandra X-ray Observatory includes a Flight Contamination Monitor (FCM), a system of 16 radioactive calibration sources mounted to the inside of the Observatory's forward contamination cover. The purpose of the FCM is to verify the ground-to-orbit transfer of the Chandra flux scale, through comparison of data acquired during the ground calibration with those obtained in orbit, immediately prior to opening the Observatory's sun-shade door. Here we report results of these measurements, which place limits on the change in mirror-detector system response and, hence, on any accumulation of molecular contamination on the mirrors' iridium-coated surfaces. C1 NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Elsner, RF (reprint author), NASA, George C Marshall Space Flight Ctr, SD50, Huntsville, AL 35812 USA. OI O'Dell, Stephen/0000-0002-1868-8056 NR 10 TC 8 Z9 8 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3637-2 J9 P SOC PHOTO-OPT INS PY 2000 VL 4012 BP 612 EP 618 DI 10.1117/12.391600 PG 7 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70G UT WOS:000089219400059 ER PT S AU Owens, SM Okajima, T Ogasaka, Y Berendse, F Serlemitsos, PJ AF Owens, SM Okajima, T Ogasaka, Y Berendse, F Serlemitsos, PJ BE Trumper, JE Aschenbach, B TI Multilayer coated thin foil mirrors for InFOC mu S SO X-RAY OPTICS, INSTRUMENTS, AND MISSIONS III SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on X-Ray Optics, Instruments, and Missions III CY MAR 27-29, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE multilayer x-ray minor; x-ray supermirror; thin foil x-ray mirror; x-ray telescope; x-ray reflectivit ID RAY AB The ability of periodic and aperiodic multialyer structures to diffract x-rays at grazing angles has long been understood, and has been successfully exploited in the x-ray region, primarily on flat substrates. We have recently begun producing Pt/C multilayer coated thin foil mirrors for the InFOC mu S balloon mission. The mirrors are made by depositing the multilayer on glass mandrels and transferring the multilayer to the thin foil substrates using a replication process similar to that used for production of the recently lost ASTRO-E mirrors. Both periodic and broadband versions have been successfully replicated onto thin foils and characterized by grazing incidence x-ray scattering. Initial comparisons between mirrors deposited on flat float glass substrates and mirrors replicated onto thin foils indicate that the reflection properties of the multilayer are not damaged by the transfer from mandrel to foil. We describe the production and characterization facilities that have been developed in our lab, and the performance of our multilayer mirrors, with particular emphasis on the characterization of interfaces in the Pt/C system. C1 NASA, Goddard Space Flight Ctr, High Energy Astrophys Lab, Greenbelt, MD 20771 USA. RP Owens, SM (reprint author), NASA, Goddard Space Flight Ctr, High Energy Astrophys Lab, Code 662, Greenbelt, MD 20771 USA. NR 4 TC 13 Z9 13 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3637-2 J9 P SOC PHOTO-OPT INS PY 2000 VL 4012 BP 619 EP 625 DI 10.1117/12.391601 PG 7 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70G UT WOS:000089219400060 ER PT S AU Zhang, W AF Zhang, W BE Trumper, JE Aschenbach, B TI An optical design for testing and aligning light weight grazing incidence X-ray mirrors SO X-RAY OPTICS, INSTRUMENTS, AND MISSIONS III SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on X-Ray Optics, Instruments, and Missions III CY MAR 27-29, 2000 CL MUNICH, GERMANY SP SPIE, European SO Observ, DFM Engn Inc DE grazing incidence optics; X-rays; metrology; alignment AB Test and alignment of light weight X-ray optics have been a challenge for two reasons: (1) that the intrinsic mirror quality and distortions caused by handling can not be easily separated, and (2) the diffraction limits of the visible light become a severe problem at the order of one are-minute. Traditional methods of using a normal incident pencil or small parallel beam which monitors a tiny fraction of the mirror in question at a given time can not adequately monitor those distortions. We are developing a normal incidence setup that monitors a large fraction, if not the whole, of the mirror at any given time. It allow us to test and align thin X-ray mirrors to an accuracy of a few are seconds or to a limit dominated by the mirror intrinsic quality. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Zhang, W (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 1 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3637-2 J9 P SOC PHOTO-OPT INS PY 2000 VL 4012 BP 712 EP 719 DI 10.1117/12.391611 PG 8 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BQ70G UT WOS:000089219400069 ER PT S AU Elsner, RF Kolodziejczak, JJ O'Dell, SL Swartz, DA Tennant, AF Weisskopf, MC AF Elsner, RF Kolodziejczak, JJ O'Dell, SL Swartz, DA Tennant, AF Weisskopf, MC BE Hoover, RB Walker, ABC TI Measurements with the Chandra X-Ray Observatory's flight contamination monitor SO X-RAY OPTICS, INSTRUMENTS, AND MISSIONS IV SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on X-Ray Optics, Instruments, and Missions IV CY JUL 30-31, 2000 CL SAN DIEGO, CA SP SPIE DE Chandra; space missions; x rays; grazing-incidence optics; calibration; contamination; x-ray missions ID AXAF; CALIBRATION AB NASA's Chandra X-ray Observatory includes a Flight Contamination Monitor (FCM), a system of 16 radioactive calibration sources mounted on the inside of the Observatory's forward contamination cover. The purpose of the FCM is to verify the ground-to-orbit transfer of the Chandra flux scale, through comparison of data acquired during the ground calibration with those obtained in orbit, immediately prior to opening the Observatory's sun-shade door. Here we report results of these measurements, which limit the absolute value of the change in mirror-detector system response to less than 2% at Ag L alpha (similar to 3 keV) and Mn K alpha (similar to 6 keV). This limit is consistent with the prelaunch estimate of less than 10 Angstrom accumulation of molecular contamination between ground calibration and initial on-orbit operations. C1 NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Elsner, RF (reprint author), NASA, George C Marshall Space Flight Ctr, SD50, Huntsville, AL 35812 USA. OI O'Dell, Stephen/0000-0002-1868-8056 NR 11 TC 3 Z9 3 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3783-2 J9 P SOC PHOTO-OPT INS PY 2000 VL 4138 BP 1 EP 9 DI 10.1117/12.407552 PG 9 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BR62F UT WOS:000166964200001 ER PT S AU Petre, R Cohen, LM Content, DA Hein, JD Saha, T Schattenburg, M Zhang, W AF Petre, R Cohen, LM Content, DA Hein, JD Saha, T Schattenburg, M Zhang, W BE Hoover, RB Walker, ABC TI Progress towards meeting the Constellation-X performance goals using segmented x-ray mirrors SO X-RAY OPTICS, INSTRUMENTS, AND MISSIONS IV SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on X-Ray Optics, Instruments, and Missions IV CY JUL 30-31, 2000 CL SAN DIEGO, CA SP SPIE DE high throughput X-ray optics; grazing incidence mirrors; Constellation-X ID TELESCOPE; HEFT AB We present an overview of our recent progress toward the development of segmented X-ray mirrors for the Constellation-X mission. Our reference design incorporates thin glass reflector substrates, with axially curved X-ray reflecting surfaces applied via epoxy replication. Alignment is accomplished via a precision structure incorporating ultraprecise etched Si alignment microstructures (as described in associated papers). Recent efforts have been devoted to demonstrating that the figure of prototype small segments and the alignment process will allow us to meet the 15 " half-power diameter angular resolution requirement. We discuss the status of this, of our efforts to fabricate meter-class segments, and of the developments of supporting metrological techniques. We summarize our plans for a laboratory demonstration of a prototype mirror meeting the Constellation-X angular resolution and weight requirements. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Petre, R (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RI Zhang, William/D-3535-2012 NR 11 TC 3 Z9 3 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3783-2 J9 P SOC PHOTO-OPT INS PY 2000 VL 4138 BP 16 EP 24 DI 10.1117/12.407563 PG 9 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BR62F UT WOS:000166964200003 ER PT S AU Waluschka, E AF Waluschka, E BE Hoover, RB Walker, ABC TI Cylindrical optic figuring dwell time optimization SO X-RAY OPTICS, INSTRUMENTS, AND MISSIONS IV SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on X-Ray Optics, Instruments, and Missions IV CY JUL 30-31, 2000 CL SAN DIEGO, CA SP SPIE DE Constellation-X; X-ray grazing incidence optics; linear programming; Simplex method ID CONSTELLATION-X AB The Constellation-X, grazing incidence, x-ray telescope may be fabricated from replicated segments. A series of mandrels will serve as the "masters" in the replication processes. Diamond turning (milling) followed by abrasive figuring followed by a super polishing are the steps currently envisioned in making just one (of many) mandrel. The abrasive figuring of a mandrel is accomplished by moving a grinding tool along a helical path on this almost cylindrical surface. The measurement of the surface is, however, performed alone "axial" scan lines which intercept this helical path. This approach to figuring and measuring permits a relatively simple scheme to be implemented for the determination of the optimal dwell times of the figuring tool. These optimal dwell times are determined by a deconvolution which approaches the problem in a linear programming context and uses the Simplex Method. The approach maximizes the amount of material removed at any point subject to inequality constraints. The effects of using these "optimum" dwell times is to significantly improve the tools effectiveness at removing the higher spatial frequencies while staying (strictly) within the bounds and constraints imposed by the hardware. In addition, the ringing at the edges of the optic, frequently present in deconvolution problems, is completely eliminated. C1 NASA, Goddard Space Flight Ctr 551 0, Greenbelt, MD 20771 USA. RP Waluschka, E (reprint author), NASA, Goddard Space Flight Ctr 551 0, Greenbelt, MD 20771 USA. NR 7 TC 0 Z9 0 U1 0 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 0-8194-3783-2 J9 P SOC PHOTO-OPT INS PY 2000 VL 4138 BP 25 EP 32 DI 10.1117/12.407564 PG 8 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BR62F UT WOS:000166964200004 ER PT S AU Ramsey, BD Alexander, CD Apple, JA Austin, RA Benson, CM Dietz, KL Elsner, RF Engelhaupt, DE Kolodziejczak, JJ O'Dell, SL Speegle, CO Swartz, DA Weisskopf, MC Zirnstein, G AF Ramsey, BD Alexander, CD Apple, JA Austin, RA Benson, CM Dietz, KL Elsner, RF Engelhaupt, DE Kolodziejczak, JJ O'Dell, SL Speegle, CO Swartz, DA Weisskopf, MC Zirnstein, G BE Hoover, RB Walker, ABC TI HERO: High-energy replicated optics for a hard-x-ray balloon payload SO X-RAY OPTICS, INSTRUMENTS, AND MISSIONS IV SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on X-Ray Optics, Instruments, and Missions IV CY JUL 30-31, 2000 CL SAN DIEGO, CA SP SPIE DE hard x ray; optics; electroformed nickel replication AB We are developing high-energy grazing-incidence optics for a balloon-borne hard-x-ray telescope. When completed the instrument, termed HERO for High Energy Replicated Optics, will have 200 cm(2) effective collecting area at 40 keV and less than or equal to 30 arcsec angular resolution. The payload will offer unprecedented sensitivity in the hard-x-ray region, with milliCrab level sensitivity on a one-day balloon flight and 100 microCrab on an ultra-long-duration flight. While the full science payload is scheduled for flight in 2002, an engineering/proving flight is currently awaiting launch. This flight, consisting of just two mirror modules, each containing three nested shells above a pair of gas scintillation proportional counter focal plane detectors, is intended to test a newly designed gondola pointing and aspect system and to examine the stability of optical bench designs. This paper provides an overview of the HERO program. C1 NASA, George C Marshall Space Flight Ctr, Dept Space Sci, Huntsville, AL 35812 USA. RP Ramsey, BD (reprint author), NASA, George C Marshall Space Flight Ctr, Dept Space Sci, Huntsville, AL 35812 USA. OI O'Dell, Stephen/0000-0002-1868-8056 NR 2 TC 14 Z9 14 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-3783-2 J9 P SOC PHOTO-OPT INS PY 2000 VL 4138 BP 147 EP 153 DI 10.1117/12.407554 PG 7 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BR62F UT WOS:000166964200017 ER EF