FN Thomson Reuters Web of Science™ VR 1.0 PT J AU Rinsland, CP Goldman, A Elkins, JW Chiou, LS Hannigan, JW Wood, SW Mahieu, E Zander, R AF Rinsland, CP Goldman, A Elkins, JW Chiou, LS Hannigan, JW Wood, SW Mahieu, E Zander, R TI Long-term trend of CH4 at northern mid-latitudes: Comparison between ground-based infrared solar and surface sampling measurements SO JOURNAL OF QUANTITATIVE SPECTROSCOPY & RADIATIVE TRANSFER LA English DT Article DE remote sensing; troposphere; atmospheric chemistry; methane ID SPECTROSCOPIC MEASUREMENTS; TROPOSPHERIC METHANE; ATMOSPHERIC METHANE; WORLDWIDE INCREASE; CARBON-MONOXIDE; GROWTH-RATE; OZONE; HEMISPHERE AB We report average tropospheric CH4 volume mixing ratios retrieved from a 27 year time series of high spectral resolution infrared solar absorption measurements recorded between May 1977 and July 2004 at the US National Solar Observatory station on Kitt Peak (31.9 degrees N, 111.6 degrees W, 2.09 km altitude) and their comparison with surface in situ sampling measurements recorded between 1983 and 2004 at the Climate Monitoring and Diagnostics Laboratory (CMDL) station at Niwot Ridge, Colorado (40.0 degrees N, 105.5 degrees W, 3013 m altitude). The two measurement sets therefore overlap for the 1983-2004 time period. An average tropospheric volume mixing ratios of 1814 +/- 48 ppbv (1 ppbv = 10(-9) per unit volume) has been derived from the solar absorption time series with a best-fit increase rate trend equal to 8.26 +/- 2.20 ppbv yr(-1) in 1983 decreasing to 1.94 +/- 3.69 ppbv yr(-1) in 2003. The CMDL measurements also show a continuous long-term CH4 volume mixing ratio rise, with subsequent slowing down. A mean ratio of the retrieved average tropospheric volume mixing ratio to the CMDL volume mixing ratio for the overlapping time period of 1.038 +/- 0.034 indicates agreement between both data sets within the quantified experimental errors. (C) 2005 Elsevier Ltd. All rights reserved. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. Univ Denver, Dept Phys, Denver, CO 80208 USA. NOAA, Climate Monitoring & Diagnost Lab, Boulder, CO 80303 USA. Sci Applicat Int Corp, Hampton, VA USA. Natl Ctr Atmospher Res, Div Atmospher Chem, Boulder, CO 80307 USA. Natl Inst Water & Atmospher Res Ltd, Omakau, Central Otago, New Zealand. Univ Liege, Inst Astrophys & Geophys, B-4000 Liege, Belgium. RP Rinsland, CP (reprint author), NASA, Langley Res Ctr, Mail Stop 401A, Hampton, VA 23681 USA. EM curtis.p.rinsland@nasa.gov OI Mahieu, Emmanuel/0000-0002-5251-0286 NR 30 TC 9 Z9 9 U1 0 U2 1 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0022-4073 J9 J QUANT SPECTROSC RA JI J. Quant. Spectrosc. Radiat. Transf. PD FEB PY 2006 VL 97 IS 3 BP 457 EP 466 DI 10.1016/j.jqsrt.2005.07.002 PG 10 WC Optics; Spectroscopy SC Optics; Spectroscopy GA 997EE UT WOS:000234227000012 ER PT J AU Chaizhunusova, N Yang, TC Land, C Luckyanov, N Wu, H Apsalikov, KN Madieva, M AF Chaizhunusova, N Yang, TC Land, C Luckyanov, N Wu, H Apsalikov, KN Madieva, M TI Biodosimetry study in Dolon and Chekoman villages in the vicinity of Semipalatinsk Nuclear Test Site SO JOURNAL OF RADIATION RESEARCH LA English DT Article; Proceedings Paper CT 3rd Dosimetry Workshop on the Semipalatinsk Nuclear Test Site Area CY MAR 09-11, 2005 CL Hiroshima Univ, Hiroshima, JAPAN HO Hiroshima Univ ID HYBRIDIZATION; FREQUENCY; EXCHANGES AB In this paper, the results of a biodosimetry investigation are reported for two villages in the area of the Semipalatinsk nuclear testing site: Chekoman and Dolon. Chekoman village is considered to be relatively less affected by radiation in comparison with Dolon village. The distance between the two villages is about 100 km and the life styles of the residents are similar. Chromosome aberrations in lymphocytes collected from the residents of the two villages were analyzed using the fluorescence in situ hybridization technique. Our results showed that the average frequency of stable translocations for the Dolon group was significantly greater that of the Chekoman group. The elevated level of stable translocations with the Dolon residents corresponds to a dose of about 180 mSv. C1 Sci Res Inst Radiat Med & Ecol, Semipalatinsk 490050, Kazakhstan. NASA, Lyndon B Johnson Space Ctr, Radiat Biophys Lab, Houston, TX 77058 USA. NCI, Bethesda, MD 20892 USA. NASA, Lyndon B Johnson Space Ctr, Kelsey Selbold Clin, Houston, TX 77058 USA. RP Chaizhunusova, N (reprint author), Sci Res Inst Radiat Med & Ecol, Post Box 49, Semipalatinsk 490050, Kazakhstan. EM nii_rm@semsk.kz RI Apsalikov, Kazbek/C-2974-2014 NR 15 TC 4 Z9 5 U1 0 U2 4 PU JAPAN RADIATION RESEARCH SOC PI CHIBA PA C/O NAT INST RADIOLOGICAL SCI 9-1 ANAGAWA-4-CHOME INAGE-KU, CHIBA, 263, JAPAN SN 0449-3060 J9 J RADIAT RES JI J. Radiat. Res. PD FEB PY 2006 VL 47 SU A BP A165 EP A169 DI 10.1269/jrr.47.A165 PG 5 WC Biology; Radiology, Nuclear Medicine & Medical Imaging SC Life Sciences & Biomedicine - Other Topics; Radiology, Nuclear Medicine & Medical Imaging GA 043KL UT WOS:000237599800023 PM 16571933 ER PT J AU Kirkpatrick, MP Ackerman, AS Stevens, DE Mansour, NN AF Kirkpatrick, MP Ackerman, AS Stevens, DE Mansour, NN TI On the application of the dynamic Smagorinsky model to large-eddy simulations of the cloud-topped atmospheric boundary layer SO JOURNAL OF THE ATMOSPHERIC SCIENCES LA English DT Article ID SUBGRID-SCALE MODEL; NOCTURNAL MARINE STRATOCUMULUS; FREE DENSITY INTERFACES; NUMERICAL SIMULATIONS; TURBULENT FLOWS; ENTRAINMENT; CONVECTION; PARAMETERIZATION; CLOSURE; WAVES AB In this paper the dynamic Smagorinsky model originally developed for engineering flows is adapted for simulations of the cloud-topped atmospheric boundary layer in which an anelastic form of the governing equations is used. The adapted model accounts for local buoyancy sources, vertical density stratification, and poor resolution close to the surface and calculates additional model coefficients for the subgrid-scale fluxes of potential temperature and total water mixing ratio. Results obtained with the dynamic model are compared with those obtained using two nondynamic models for simulations of a nocturnal marine stratocumulus cloud deck observed during the first research flight of the second Dynamics and Chemistry of Marine Stratocumulus (DYCOMS-II) field experiment. The dynamic Smagorinsky model is found to give better agreement with the observations for all parameters and statistics. The dynamic model also gives improved spatial convergence and resolution independence over the nondynamic models. The good results obtained with the dynamic model appear to be due primarily to the fact that it calculates minimal subgrid-scale fluxes at the inversion. Based on other results in the literature, it is suggested that entrainment in the DYCOMS-II case is due predominantly to isolated mixing events associated with overturning internal waves. While the behavior of the dynamic model is consistent with this entrainment mechanism, a similar tendency to switch off subgrid-scale fluxes at an interface is also observed in a case in which gradient transport by small-scale eddies has been found to be important. This indicates that there may be problems associated with the application of the dynamic model close to flow interfaces. One issue here involves the plane-averaging procedure used to stabilize the model, which is not justified when the averaging plane intersects a deforming interface. More fundamental, however, is that the behavior may be due to insufficient resolution in this region of the flow. The implications of this are discussed with reference to both dynamic and nondynamic subgrid-scale models, and a new approach to turbulence modeling for large-eddy simulations is proposed. C1 Stanford Univ, Ctr Turbulence Res, Stanford, CA 94305 USA. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. Lawrence Livermore Natl Lab, Livermore, CA USA. RP Kirkpatrick, MP (reprint author), Univ Tasmania, Sch Engn, Private Bag 65, Hobart, Tas 7001, Australia. EM michael.kirkpatrick@utas.edu.au RI Ackerman, Andrew/D-4433-2012; OI Ackerman, Andrew/0000-0003-0254-6253; Kirkpatrick, Michael/0000-0002-7157-6440 NR 47 TC 18 Z9 18 U1 0 U2 2 PU AMER METEOROLOGICAL SOC PI BOSTON PA 45 BEACON ST, BOSTON, MA 02108-3693 USA SN 0022-4928 J9 J ATMOS SCI JI J. Atmos. Sci. PD FEB PY 2006 VL 63 IS 2 BP 526 EP 546 DI 10.1175/JAS3651.1 PG 21 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 019XG UT WOS:000235870900007 ER PT J AU Sun, WY Chern, JD AF Sun, WY Chern, JD TI Numerical study of the influence of central mountain ranges in Taiwan on a cold front SO JOURNAL OF THE METEOROLOGICAL SOCIETY OF JAPAN LA English DT Article ID AREA MESOSCALE EXPERIMENT; DIURNAL-VARIATION; SURROUNDING AREA; PARAMETERIZATION; CIRCULATION; SIMULATION; AUSTRALIA; EQUATIONS; VORTICES; RAINBAND AB The numerical simulations were performed to study the intrusion of a shallow cold front along the China coastal mountain range, and the deformation of the front by the Central Mountain Range (CMR) in Taiwan during the IOP-9 (1600 UTC June 14-1700 UTC June 15, 1987) of the Taiwan Area Mesoscale Experiment (TAMEX). The essential features of the observed front, such as the faster movement of the eastern part of the front than the western part, were well reproduced. The control and sensitivity simulations suggested that the frontal deformation in Taiwan was caused by the dynamical interaction between the front and the underlying topography. As the cold air approached northern Taiwan from the north, a relative high pressure with anticyclonic circulation built up on the windward side. More oncoming flow was diverted to the northeast of Taiwan than to the northwest and caused the difference of the frontal speed between the eastern and western parts of the front. The dynamics of the frontal movement along southeast China was similar to the dynamics of coastally trapped mesoscale ridges, or orographical jet. The momentum budget equation showed that the contribution of the nonlinear advection, ageostrophic forcing, and friction were equally important to the local change of the wind just behind the front. This might indicate that the dynamics of the front was more complicated than that described by the density current theory derived from an irrotational fluid. The invicid sensitivity simulation revealed a faster propagating front, and a stronger wind behind its leading edge in comparison with the control simulation. The front bears no dynamical resemblance to either an orographically trapped density current or a Kelvin wave, because the major forces in the momentum budget are the pressure gradient force, Coriolis force and advection terms. C1 Natl Ctr High Performance Comp, Shing Chu, Taiwan. NASA, Goddard Space Flight Ctr, Atmospheres Lab, Greenbelt, MD 20771 USA. RP Sun, WY (reprint author), Purdue Univ, Dept Earth & Atmospher Sci, W Lafayette, IN 47907 USA. EM wysun@purdue.edu NR 41 TC 2 Z9 2 U1 0 U2 1 PU METEOROLOGICAL SOC JPN PI TOKYO PA C/O JPN METEOROL AGENCY 1-3-4 OTE-MACHI, CHIYODA-KU, TOKYO, JAPAN SN 0026-1165 J9 J METEOROL SOC JPN JI J. Meteorol. Soc. Jpn. PD FEB PY 2006 VL 84 IS 1 BP 27 EP 46 DI 10.2151/jmsj.84.27 PG 20 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 030FI UT WOS:000236619300003 ER PT J AU Tzou, HS Chai, WK Arnold, SM AF Tzou, HS Chai, WK Arnold, SM TI Structronics and actuation of hybrid electrostrictive/piezoelectric thin shells SO JOURNAL OF VIBRATION AND ACOUSTICS-TRANSACTIONS OF THE ASME LA English DT Article ID CERAMIC MATERIALS; MODAL VOLTAGES; ELECTROSTRICTION AB Certain ferroelectric materials possess dual electrostrictive and piezoelectric characteristics, depending on their specific Curie temperatures. The nonlinear electro-mechanical effect of electrostrictive materials provides stronger actuation performance as compared with that of piezoelectric materials. Due to the complexity of the generic ferroelectric actuators, micro- electromechanics, structure-electronic (structronic) coupling and control characteristics of hybrid electrostrictive/piezoelectric dynamic systems deserve an in-depth investigation. In this study, dynamic electro -mechanical system equations and boundary conditions of hybrid electrostrictive/piezoelectric double-curvature shell continua are derived using the energy-based Hamilton's principle, elasticity theory, electrostrictive/piezoelectric constitutive relations, and Gibb's free energy function. These governing equations clearly reveal the coupling of electrostrictive, piezoelectric, and elastic fields and characteristics change triggered by the Curie temperature. The electric terms are used to manipulate and to control the static/dynamic behavior of hybrid electrostrictive/piezoelectric shells. To apply the hybrid shell system equations to other geometries, simplification procedures using two Lam parameters and two radii of curvature are demonstrated in two cases: A hybrid electrostrictivelpiezoelectric conical shell and a hybrid electrostrictivelpiezoelectric toroidal shell. Following the same procedures, one can apply the generic system equations to other common geometries, e.g., beams, arches, plates, rings, cylindrical shells, spherical shells, etc., or specific materials, e.g., electrostrictive or Piezoelectric, and further evaluate their electromechanical characteristics and actuation/control effectiveness. C1 Univ Kentucky, Dept Mech Engn, StrucTron Lab, Lexington, KY 40506 USA. NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Tzou, HS (reprint author), Univ Kentucky, Dept Mech Engn, StrucTron Lab, Lexington, KY 40506 USA. EM hstzou@engr.uky.edu NR 26 TC 7 Z9 7 U1 1 U2 3 PU ASME-AMER SOC MECHANICAL ENG PI NEW YORK PA THREE PARK AVE, NEW YORK, NY 10016-5990 USA SN 1048-9002 J9 J VIB ACOUST JI J. Vib. Acoust.-Trans. ASME PD FEB PY 2006 VL 128 IS 1 BP 79 EP 87 DI 10.1115/1.2149397 PG 9 WC Acoustics; Engineering, Mechanical; Mechanics SC Acoustics; Engineering; Mechanics GA 013KU UT WOS:000235409000010 ER PT J AU Graham, GA Teslich, N Dai, ZR Bradley, JP Kearsley, AT Horz, F AF Graham, GA Teslich, N Dai, ZR Bradley, JP Kearsley, AT Horz, F TI Focused ion beam recovery of hypervelocity impact residue in experimental craters on metallic foils SO METEORITICS & PLANETARY SCIENCE LA English DT Article ID DUST PARTICLES; COMETARY; STARDUST; AEROGEL AB The Stardust sample return capsule returned to Earth in January 2006 with primitive debris collected from comet 81P/Wild-2 during the flyby encounter in 2004. In addition to the cometary particles embedded in low-density silica aerogel, there are microcraters preserved in the aluminum foils (1100 series; 100 mu m thick) that are wrapped around the sample tray assembly. Soda lime spheres (similar to 49 mu m in diameter) have been accelerated with a light gas gun into flight-grade aluminum foils at 6.35 kin s(-1) to simulate the capture of cometary debris. The experimental craters have been analyzed using scanning electron microscopy (SEM) and X-ray energy dispersive spectroscopy (EDX) to locate and characterize remants of the projectile material remaining within the craters. In addition, ion beam-induced secondary electron imaging has proven particularly useful in identifying areas within the craters that contain residue material. Finally, high-precision focused ion beam (FIB) milling has been used to isolate and then extract an individual melt residue droplet from the interior wall of an impact. This has enabled further detailed elemental characterization that is free from the background contamination of the aluminum foil Substrate. The ability to recover "pure" melt residues using FIB will significantly extend the interpretations of the residue chemistry preserved in the aluminum foils returned by Stardust. C1 Lawrence Livermore Natl Lab, Inst Geophys & Planetary Phys, Livermore, CA 94551 USA. Nat Hist Museum, Dept Mineral, London SW7 5BD, England. NASA, Lyndon B Johnson Space Ctr, Astromat Res Off, Houston, TX 77058 USA. RP Graham, GA (reprint author), Lawrence Livermore Natl Lab, Inst Geophys & Planetary Phys, Livermore, CA 94551 USA. EM graham42@llnl.gov RI Dai, Zurong/E-6732-2010 NR 27 TC 12 Z9 12 U1 2 U2 5 PU METEORITICAL SOC PI FAYETTEVILLE PA DEPT CHEMISTRY/BIOCHEMISTRY, UNIV ARKANSAS, FAYETTEVILLE, AR 72701 USA SN 1086-9379 J9 METEORIT PLANET SCI JI Meteorit. Planet. Sci. PD FEB PY 2006 VL 41 IS 2 BP 159 EP 165 PG 7 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 021CR UT WOS:000235961200001 ER PT J AU Kearsley, AT Burchell, MJ Horz, F Cole, MJ Schwandt, CS AF Kearsley, AT Burchell, MJ Horz, F Cole, MJ Schwandt, CS TI Laboratory simulation of impacts on aluminum foils of the Stardust spacecraft: Calibration of dust particle size from comet Wild-2 SO METEORITICS & PLANETARY SCIENCE LA English DT Article ID HYPERVELOCITY IMPACTS; SOLAR-ARRAYS; CRATERS; MORPHOLOGY; SATELLITE; DENSITIES; RESIDUES; ANALYZER; TARGETS; DEBRIS AB Metallic aluminum alloy foils exposed oil the forward, comet-facing surface of the aerogel tray oil the Stardust spacecraft are likely to have been impacted by the same cometary particle Population as the dedicated impact sensors and the aerogel collector. The ability of soft aluminum alloy to record hypervelocity impacts as bowl-shaped craters offers all opportunistic substrate for recognition of impacts by particles of a potentially wide size range. In contrast to impact surveys conducted oil samples from low Earth orbit, the simple encounter geometry for Stardust and Wild-2, with a known and constant spacecraft-particle relative velocity and effective surface-perpendicular impact trajectories, permits closely comparable simulation in laboratory experiments. For a detailed calibration program, we have selected a suite of spherical glass projectiles of uniform density and hardness characteristics, with well-documented particle size range from 10 mu m to nearly 100 mu m. Light gas gun buckshot firings of these particles at approximately 6 kill s(-1) onto samples of the same foil as employed on Stardust have yielded large numbers of craters. Scanning electron microscopy of both projectiles and impact features has allowed construction of a calibration plot, showing a linear relationship between impacting particle size and impact crater diameter. The close match between our experimental conditions and the Stardust mission encounter parameters should provide another opportunity to measure particle size distributions and Mixes close to the nucleus of Wild-2, independent of the active impact detector instruments aboard the Stardust spacecraft. C1 Nat Hist Museum, Dept Mineral, Impact & Astromat Res Ctr, London SW7 5BD, England. Univ Kent, Ctr Astrophys & Planetary Sci, Sch Phys Sci, Canterbury CT2 7NH, Kent, England. NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Kearsley, AT (reprint author), Nat Hist Museum, Dept Mineral, Impact & Astromat Res Ctr, London SW7 5BD, England. EM antk@nhm.ac.uk OI Burchell, Mark/0000-0002-2680-8943 NR 35 TC 42 Z9 42 U1 2 U2 5 PU METEORITICAL SOC PI FAYETTEVILLE PA DEPT CHEMISTRY/BIOCHEMISTRY, UNIV ARKANSAS, FAYETTEVILLE, AR 72701 USA SN 1086-9379 J9 METEORIT PLANET SCI JI Meteorit. Planet. Sci. PD FEB PY 2006 VL 41 IS 2 BP 167 EP 180 PG 14 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 021CR UT WOS:000235961200002 ER PT J AU Lerouxi, H Borg, J Troadec, D Djouadi, Z Horz, F AF Lerouxi, H Borg, J Troadec, D Djouadi, Z Horz, F TI Microstructural study of micron-sized craters simulating Stardust impacts in aluminum 1100 targets SO METEORITICS & PLANETARY SCIENCE LA English DT Article ID LIME GLASS PROJECTILES; HYPERVELOCITY IMPACTS; METAL TARGETS; SPACE DEBRIS; SOLAR-CELLS; DUST; PENETRATION; VELOCITY AB Various microscopic techniques were used to characterize experimental microcraters in aluminium foils to prepare for the comprehensive analysis of the cometary and interstellar particle impacts in aluminium foils to be returned by the Stardust mission. First, scanning electron microscopy (SEM) and energy dispersive X-ray spectroscopy (EDS) were used to Study the morphology of the impact craters and the bulk composition of the residues left by soda-lime glass impactors. A more detailed structural and compositional Study of impactor remnants was then performed using transmission electron microscopy (TEM), EDS, and electron diffraction methods. The TEM samples were prepared by Focused ion beam (FIB) methods. This technique proved to be especially valuable ill Studying impact crater residues and impact crater morphology. Finally, we also showed that infrared microscopy (IR) call be a quick and reliable tool for Such investigations. The combination of all of these tools enables a complete microscopic characterization of the craters. C1 Univ Sci & Tech Lille Flandres Artois, Lab Struct & Proprietes Etat Solide, UMR 8008, CNRS, F-59655 Villeneuve Dascq, France. Univ Paris 11, Inst Astrophys Spatiale, F-91405 Orsay, France. CNRS, UMR 8617, F-91405 Orsay, France. Univ Sci & Tech Lille Flandres Artois, Inst Elect Microelect & Nanotechnol, UMR 8520, CNRS, F-59655 Villeneuve Dascq, France. NASA, Lyndon B Johnson Space Ctr, ARES, SR, Houston, TX 77058 USA. RP Lerouxi, H (reprint author), Univ Sci & Tech Lille Flandres Artois, Lab Struct & Proprietes Etat Solide, UMR 8008, CNRS, F-59655 Villeneuve Dascq, France. EM Hughes.Leroux@univ-lille1.fr NR 21 TC 7 Z9 7 U1 0 U2 2 PU METEORITICAL SOC PI FAYETTEVILLE PA DEPT CHEMISTRY/BIOCHEMISTRY, UNIV ARKANSAS, FAYETTEVILLE, AR 72701 USA SN 1086-9379 J9 METEORIT PLANET SCI JI Meteorit. Planet. Sci. PD FEB PY 2006 VL 41 IS 2 BP 181 EP 196 PG 16 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 021CR UT WOS:000235961200003 ER PT J AU Hoppe, P Stadermann, FJ Stephan, T Floss, C Leitner, J Marhas, KK Horz, F AF Hoppe, P Stadermann, FJ Stephan, T Floss, C Leitner, J Marhas, KK Horz, F TI SIMS studies of Allende projectiles fired into Stardust-type aluminum foils at 6 km/sec SO METEORITICS & PLANETARY SCIENCE LA English DT Article ID INTERPLANETARY DUST; SPINEL GRAINS; TOF-SIMS; PRESOLAR; COMPONENTS; METEORITES; SILICATE; CARBON; OXYGEN; STARS AB We have explored the feasibility of C, N, and O isotopic measurements by NanoSIMS and of elemental abundance determinations by time-of-flight secondary ion mass spectrometry (TOF-SIMS) oil residues of Allende projectiles that impacted Stardust-type aluminum foils in the laboratory at 6 km/sec. These investigations are part of a consortium study aimed at providing the foundation for the characterization of matter associated with microcraters that were produced during the encounter of the Stardust Space probe with cornet 81 P/Wild-2. Eleven experimental impact craters were studied by NanoSIMS and eighteen by TOF-SIMS. Crater sizes were between 3 and 190 mu m. The NanoSIMS measurements have shown that the crater morphology has only a minor effect on spatial resolution and oil instrumental mass fractionation. The achievable spatial resolution is always better than 200 rim, and C and 0 isotopic ratios can be measured with a precision or several percent at a scale of several 100 nm, which is the typical size of presolar grains. This clearly demonstrates that presolar matter, provided it survives the impact into the aluminum foil partly intact, is recognizable even it., embedded in material of solar system origin. TOF-SIMS studies are restricted to materials from the crater rim. The element ratios of the major rock-forming elements in the Allende projectiles are well-characterized by the TOF-SIMS measurements, indicating that fractionation of those elements during impact call be expected to be negligible. This permits chemical information oil the type of impactor material to be obtained. For any more detailed assignments to specific chondrite groups, however, information oil the abundances of the light elements, especially C, is crucial. This information could not be obtained in the present study due to Unavoidable contamination during impact experiments. C1 Max Planck Inst Chem, Particle Chem Dept, D-55020 Mainz, Germany. Washington Univ, Dept Phys, Space Sci Lab, St Louis, MO 63130 USA. Univ Munster, Inst Planetol, D-48149 Munster, Germany. NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Hoppe, P (reprint author), Max Planck Inst Chem, Particle Chem Dept, POB 3060, D-55020 Mainz, Germany. EM hoppe@mpch-mainz.mpg.de RI Leitner, Jan/A-7391-2015; Hoppe, Peter/B-3032-2015 OI Leitner, Jan/0000-0003-3655-6273; Hoppe, Peter/0000-0003-3681-050X NR 32 TC 10 Z9 10 U1 0 U2 1 PU WILEY-BLACKWELL PI MALDEN PA COMMERCE PLACE, 350 MAIN ST, MALDEN 02148, MA USA SN 1086-9379 J9 METEORIT PLANET SCI JI Meteorit. Planet. Sci. PD FEB PY 2006 VL 41 IS 2 BP 197 EP 209 PG 13 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 021CR UT WOS:000235961200004 ER PT J AU Stephan, T Butterworth, AL Horz, F Snead, CJ Westphal, AJ AF Stephan, T Butterworth, AL Horz, F Snead, CJ Westphal, AJ TI TOF-SIMS analysis of Allende projectiles shot into silica aerogel SO METEORITICS & PLANETARY SCIENCE LA English DT Article AB Powdered Allende projectiles were fired into silica aerogel at 6.1 km/sec: in order to evaluate particle retrieval and analysis techniques for samples from the Stardust Mission. Since particles may disintegrate and ablate along the penetration paths in a high-porosity aerogel, TOF-SIMS analysis may be a suitable method to determine the distribution Of Such materials along the tracks as well as potential compositional modifications. Therefore, two similar to 350 mu m-sized tracks, residing at the surface of a keystone specimen that was flattened between two silicon chips, were analyzed. TOF-SIMS allows for a detailed Study of the chemical composition of particles that survived the impact mostly intact and or fine-grained material from disintegrated projectiles. In the investigated keystone, material from light gas gun debris dominated. Besides the two tracks, a continuous, 40-mu m-thick Surface layer of implanted material-probably gun residue-was found. One of the two analyzed tracks is compositionally distinct from this surface layer and is likely to contain residual material of an Allende projectile. The analyses clearly demonstrate that tracks, resulting from impactors in the 5-10 mu m size range, can be Successfully analyzed with TOF-SIMS. C1 Univ Munster, Inst Planetol, D-48149 Munster, Germany. Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Stephan, T (reprint author), Univ Munster, Inst Planetol, Wilhelm Klemm Str 10, D-48149 Munster, Germany. EM stephan@uni-meunster.de NR 7 TC 5 Z9 5 U1 0 U2 1 PU METEORITICAL SOC PI FAYETTEVILLE PA DEPT CHEMISTRY/BIOCHEMISTRY, UNIV ARKANSAS, FAYETTEVILLE, AR 72701 USA SN 1086-9379 J9 METEORIT PLANET SCI JI Meteorit. Planet. Sci. PD FEB PY 2006 VL 41 IS 2 BP 211 EP 216 PG 6 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 021CR UT WOS:000235961200005 ER PT J AU Ramkumar, SM Ghaffarian, R Varanasi, A AF Ramkumar, SM Ghaffarian, R Varanasi, A TI Lead-free 0201 manufacturing, assembly and reliability test results SO MICROELECTRONICS RELIABILITY LA English DT Article AB The trend towards smaller, faster and cheaper electronic devices has led to an increase in the use of 0201 (L similar to 0.02 in.; W similar to 0.01 in.) and even smaller sized passive components. The size advantages of the 0201 component make it a popular choice among design engineers but not among manufacturing engineers. From a manufacturing perspective, the size of the 0201 package poses significant challenges to the printed circuit board (PCB) assembly process. The many challenges with 0201 assembly can be attributed to the solder paste volume, pad design, aperture design, board finish, type of solder paste, pick-and-place and reflow profile. If these factors are not optimized, they will introduce undesirable manufacturing defects. The small size of 0201 packages and undetected manufacturing defects will also raise concerns about their second level interconnect reliability, especially for lead-free solder alloys and surface finishes, with new processes and higher reflow requirements. To determine the optimum conditions, a design-of-experiment (DOE) study was carried out to investigate the effects of these parameters on assembly defects and solder joint reliability. This paper presents the test results and comparative literature data on the influence of a few key manufacturing parameters and defects associated with the 0201 component using lead-free and tin-lead solder alloys. Data pertaining to component shear strength before and after isothermal aging at 150 degrees C and intermetallic growth up to 500 h of aging are presented. A number of test vehicles were also subjected to thermal cycling (1500 cycles) in the range of -55/100 degrees C to determine the solder fatigue behavior. Shear test results for test vehicles subjected to thermal cycling is also presented. In addition, optical microscopy analysis of solder joint behavior during thermal cycling showing the progress of the solder damage and cross-sectional photos taken at 1500 cycles is included. (c) 2005 Elsevier Ltd. All rights reserved. C1 Rochester Inst Technol, Ctr Elect Mfg & Assembly, Rochester, NY 14623 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Ramkumar, SM (reprint author), Rochester Inst Technol, Ctr Elect Mfg & Assembly, Rochester, NY 14623 USA. EM smrmet@rit.edu; Reza.Ghaffarian@jpl.nasa.gov NR 19 TC 12 Z9 12 U1 0 U2 0 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0026-2714 J9 MICROELECTRON RELIAB JI Microelectron. Reliab. PD FEB-APR PY 2006 VL 46 IS 2-4 BP 244 EP 262 DI 10.1016/j.microrel.2005.09.007 PG 19 WC Engineering, Electrical & Electronic; Nanoscience & Nanotechnology; Physics, Applied SC Engineering; Science & Technology - Other Topics; Physics GA 013WQ UT WOS:000235441100004 ER PT J AU Venkatesan, J AF Venkatesan, J TI X-band microstrip Yagi array with dual-offset aperture-coupled feed SO MICROWAVE AND OPTICAL TECHNOLOGY LETTERS LA English DT Article DE microstrip Yagi; array; microstrip patch; aperture-coupled ID ANTENNA AB In this paper, a three-element microstrip Yagi array is designed for operation at the X-band. The driven patch of each microstrip Yagi element is fed using a dual-offset aperture-coupled feed to obtain circular polarization. Performance of the array when scanned electronically is investigated experimentally via measured field patterns. (C) 2005 Wiley Periodicals, Inc. C1 CALTECH, Jet Prop Lab, Spacecraft Antenna Res Grp, Pasadena, CA 91109 USA. RP Venkatesan, J (reprint author), CALTECH, Jet Prop Lab, Spacecraft Antenna Res Grp, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 10 TC 0 Z9 1 U1 0 U2 0 PU JOHN WILEY & SONS INC PI HOBOKEN PA 111 RIVER ST, HOBOKEN, NJ 07030 USA SN 0895-2477 J9 MICROW OPT TECHN LET JI Microw. Opt. Technol. Lett. PD FEB PY 2006 VL 48 IS 2 BP 341 EP 344 DI 10.1002/mop.21344 PG 4 WC Engineering, Electrical & Electronic; Optics SC Engineering; Optics GA 004PP UT WOS:000234765000039 ER PT J AU Venkatesan, J Scott, WR AF Venkatesan, J Scott, WR TI Measured patterns of a resistive V-dipole fed with a double-Y balun SO MICROWAVE AND OPTICAL TECHNOLOGY LETTERS LA English DT Article DE balun; double-Y; V-dipole; coplanar waveguide; coplanar strip ID UNIPLANAR BALUN AB The performance of a double-Y balun feeding a resistive V-dipole is evaluated via antenna-pattern measurements. All optical link is constructed for containing the feedline radiation to a laser receiver unit and the antenna under test (AUT), hence avoiding the uncertainty caused by cable radiation in a conventional antenna pattern-measurement setup. (C) 2005 Wiley Periodicals, Inc. C1 CALTECH, Jet Prop Lab, Spa, Pasadena, CA 91109 USA. Georgia Inst Technol, Dept Elect Engn, Atlanta, GA 30332 USA. RP Venkatesan, J (reprint author), CALTECH, Jet Prop Lab, Spa, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 8 TC 1 Z9 1 U1 0 U2 1 PU JOHN WILEY & SONS INC PI HOBOKEN PA 111 RIVER ST, HOBOKEN, NJ 07030 USA SN 0895-2477 J9 MICROW OPT TECHN LET JI Microw. Opt. Technol. Lett. PD FEB PY 2006 VL 48 IS 2 BP 380 EP 383 DI 10.1002/mop.21356 PG 4 WC Engineering, Electrical & Electronic; Optics SC Engineering; Optics GA 004PP UT WOS:000234765000051 ER PT J AU Brocksopp, C McGowan, KE Krimm, H Godet, O Roming, P Mason, KO Gehrels, N Still, M Page, K Moretti, A Shrader, CR Campana, S Kennea, J AF Brocksopp, C McGowan, KE Krimm, H Godet, O Roming, P Mason, KO Gehrels, N Still, M Page, K Moretti, A Shrader, CR Campana, S Kennea, J TI The 2005 outburst of GRO J1655-40: spectral evolution of the rise, as observed by Swift SO MONTHLY NOTICES OF THE ROYAL ASTRONOMICAL SOCIETY LA English DT Article DE accretion, accretion discs; stars : individual : GRO J1655; 40; X-rays : binaries ID CANDIDATE XTE J1550-564; X-RAY OUTBURSTS; SUPERLUMINAL SOURCE; RADIO-EMISSION; RELATIVISTIC JETS; EJECTION; STATES; MASS AB We present Swift observations of the black hole X-ray transient, GRO J1655-40, during the recent outburst. With its multiwavelength capabilities and flexible scheduling, Swift is extremely well suited for monitoring the spectral evolution of such an event. GRO J1655-40 was observed on 20 occasions and data were obtained by all instruments for the majority of epochs. X-ray spectroscopy revealed spectral shapes consistent with the 'canonical' low/hard, high/soft and very high states at various epochs. The soft X-ray source (0.3-10 keV) rose from quiescence and entered the low/hard state, when an iron emission line was detected. The soft X-ray source then softened and decayed, before beginning a slow rebrightening and then spending similar to 3 weeks in the very high state. The hard X-rays (14-150 keV) behaved similarly but their peaks preceded those of the soft X-rays by up to a few days; in addition, the average hard X-ray flux remained approximately constant during the slow soft X-ray rebrightening, increasing suddenly as the source entered the very high state. These observations indicate (and confirm previous suggestions) that the low/hard state is key to improving our understanding of the outburst trigger and mechanism. The optical/ultraviolet light curve behaved very differently from that of the X-rays; this might suggest that the soft X-ray light curve is actually a composite of the two known spectral components, one gradually increasing with the optical/ultraviolet emission (accretion disc) and the other following the behaviour of the hard X-rays (jet and/or corona). C1 UCL, Mullard Space Sci Lab, Dorking RH5 6NT, Surrey, England. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Univ Space Res Assoc, Columbia, MD 20144 USA. Univ Leicester, Dept Phys & Astron, Leicester LE1 7RH, Leics, England. Penn State Univ, Dept Astron & Astrophys, Davey Lab 525, University Pk, PA 16802 USA. S African Astron Observ, ZA-7935 Observatory, South Africa. Osserv Astron Brera, INAF, I-23807 Merate, LC, Italy. RP Brocksopp, C (reprint author), UCL, Mullard Space Sci Lab, Holmbury St Mary, Dorking RH5 6NT, Surrey, England. EM cb4@mssl.ucl.ac.uk RI Gehrels, Neil/D-2971-2012; OI Campana, Sergio/0000-0001-6278-1576; moretti, alberto/0000-0002-9770-0315 NR 43 TC 38 Z9 38 U1 0 U2 0 PU WILEY-BLACKWELL PI MALDEN PA COMMERCE PLACE, 350 MAIN ST, MALDEN 02148, MA USA SN 0035-8711 J9 MON NOT R ASTRON SOC JI Mon. Not. Roy. Astron. Soc. PD FEB 1 PY 2006 VL 365 IS 4 BP 1203 EP 1214 DI 10.1111/j.1365-2966.2005.09791.x PG 12 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 006DV UT WOS:000234876600014 ER PT J AU Allen, DR Coy, L Eckermann, SD McCormack, JP Manney, GL Hogan, TF Kim, YJ AF Allen, DR Coy, L Eckermann, SD McCormack, JP Manney, GL Hogan, TF Kim, YJ TI NOGAPS-ALPHA simulations of the 2002 Southern Hemisphere stratospheric major warming SO MONTHLY WEATHER REVIEW LA English DT Article ID GENERAL-CIRCULATION MODEL; QUASI-GEOSTROPHIC EDDIES; DATA ASSIMILATION SYSTEM; METEOROLOGICAL ANALYSES; NUMERICAL FORECASTS; PREDICTIVE SKILL; ANTARCTIC WINTER; UPPER-ATMOSPHERE; UNIFIED MODEL; TOTAL OZONE AB A high-altitude version of the Navy Operational Global Atmospheric Prediction System (NOGAPS) spectral forecast model is used to simulate the unusual September 2002 Southern Hemisphere stratospheric major warming. Designated as NOGAPS-Advanced Level Physics and High Altitude (NOGAPS-ALPHA), this model extends from the surface to 0.005 hPa (similar to 85 km altitude) and includes modifications to multiple components of the operational NOGAPS system, including a new radiative heating scheme, middle-atmosphere gravity wave drag parameterizations, hybrid vertical coordinate, upper-level meteorological initialization, and radiatively active prognostic ozone with parameterized photochemistry. NOGAPS-ALPHA forecasts (hindcasts) out to 6 days capture the main features of the major warming, such as the zonal mean wind reversal, planetary-scale wave amplification, large upward Eliassen-Palm (EP) fluxes, and splitting of the polar vortex in the middle stratosphere. Forecasts beyond 6 days have reduced upward EP flux in the lower stratosphere, reduced amplitude of zonal wavenumbers 2 and 3, and a middle stratospheric vortex that does not split. Three-dimensional EP-flux diagnostics in the troposphere reveal that the longer forecasts underestimate upward-propagating planetary wave energy emanating from a significant blocking pattern over the South Atlantic that played a large role in forcing the major warming. Forecasts of less than 6 days are initialized with the blocking in place, and therefore are not required to predict the blocking onset. For a more thorough skill assessment, NOGAPS-ALPHA forecasts over 3 weeks during September-October 2002 are compared with operational NOGAPS 5-day forecasts made at the time. NOGAPS-ALPHA forecasts initialized with 2002 operational NOGAPS analyses show a modest improvement in skill over the NOGAPS operational forecasts. An additional, larger improvement is obtained when NOGAPS-ALPHA is initialized with reanalyzed 2002 fields produced with the currently operational (as of October 2003) Naval Research Laboratory (NRL) Atmospheric Variational Data Assimilation System (NAVDAS). Thus the combination of higher model top, better physical parameterizations, and better initial conditions all yield improved forecasting skill over the NOGAPS forecasts issued operationally at the time. C1 USN, Res Lab, Remote Sensing Div, Washington, DC 20375 USA. USN, Res Lab, EO Hulburt Ctr Space Res, Washington, DC 20375 USA. New Mexico Highlands Univ, Las Vegas, NV USA. CALTECH, Jet Propuls Lab, Pasadena, CA 91125 USA. USN, Res Lab, Marine Meteorol Div, Monterey, CA USA. RP Dordt Coll, Dept Phys & Astron, 498 4th Ave NE, Sioux Ctr, IA 51250 USA. EM dallen@dordt.edu OI McCormack, John/0000-0002-3674-0508 NR 60 TC 26 Z9 26 U1 0 U2 2 PU AMER METEOROLOGICAL SOC PI BOSTON PA 45 BEACON ST, BOSTON, MA 02108-3693 USA SN 0027-0644 EI 1520-0493 J9 MON WEATHER REV JI Mon. Weather Rev. PD FEB PY 2006 VL 134 IS 2 BP 498 EP 518 DI 10.1175/MWR3086.1 PG 21 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 019NT UT WOS:000235844700004 ER PT J AU Prazenica, RJ Kurdila, AJ AF Prazenica, RJ Kurdila, AJ TI Multiwavelet constructions and Volterra kernel identification SO NONLINEAR DYNAMICS LA English DT Article DE intertwining; multiresolution analysis; multiwavelets; nonlinear system identification; Volterra series ID WAVELET TRANSFORMS; NONLINEAR-SYSTEM; OPERATORS; SERIES AB The Volterra series is commonly used for the modeling of nonlinear dynamical systems. In general, however, a large number of terms are needed to represent Volterra kernels, with the number of required terms increasing exponentially with the order of the kernel. Therefore, reduced-order kernel representations are needed in order to employ the Volterra series in engineering practice. This paper presents an approach whereby multiwavelets are used to obtain low-order estimates of first-, second-, and third-order Volterra kernels. A family of multiwavelets is constructed from the classical finite element basis functions using the technique of intertwining. The resulting multiwavelets are piecewise-polynomial, orthonormal, compactly-supported, and can be constructed with arbitrary approximation order. Furthermore, these multiwavelets are easily adapted to the domains of support of the Volterra kernels. In contrast, most wavelet families do not possess this characteristic. Higher-dimensional multiwavelets can easily be constructed by taking tensor products of the original one-dimensional functions. Therefore, it is straightforward to extend this approach to the representation of higher-order Volterra kernels. This kernel identification algorithm is demonstrated on a prototypical oscillator with a quadratic stiffness nonlinearity. For this system, it is shown that accurate kernel estimates can be obtained in terms of a relatively small number of wavelet coefficients. These results indicate the potential of the multiwavelet-based algorithm for obtaining reduced-order models for a large class of weakly nonlinear systems. C1 NASA, Dryden Flight Res Ctr, Edwards AFB, CA 93523 USA. Univ Florida, Dept Mech & Aerosp Engn, Gainesville, FL 32611 USA. RP Prazenica, RJ (reprint author), NASA, Dryden Flight Res Ctr, Edwards AFB, CA 93523 USA. EM rjp@gerc.eng.ufl.edu NR 29 TC 14 Z9 16 U1 0 U2 7 PU SPRINGER PI DORDRECHT PA VAN GODEWIJCKSTRAAT 30, 3311 GZ DORDRECHT, NETHERLANDS SN 0924-090X J9 NONLINEAR DYNAM JI Nonlinear Dyn. PD FEB PY 2006 VL 43 IS 3 BP 277 EP 310 DI 10.1007/s11071-006-8323-x PG 34 WC Engineering, Mechanical; Mechanics SC Engineering; Mechanics GA 020IV UT WOS:000235903100004 ER PT J AU Robinson, B Balasubramaniam, KS Gary, GA AF Robinson, B Balasubramaniam, KS Gary, GA TI Advanced technology solar telescope multiple Fabry-Perot interferometer telecentric optical design SO OPTICAL ENGINEERING LA English DT Article DE optical design; Fabry-Perot interferometer; spectrometer; telecentric mount; Beckers effect; solar telescope; spectroscopy; spectropolarimetry; triple etalon system ID RESOLUTION AB We present four preliminary designs for a telecentric optical train supporting the Advanced Technology Solar Telescope (ATST) multiple Fabry-Perot interferometer (MFPI), which is to be used as an imaging spectrometer and imaging spectropolarimeter. The point of departure for all three designs is the F/40 telecentric image at the Coude focus of the ATST. The first design, representing the high-spectral-resolution mode of operation, produces an intermediate F/300 telecentric image within the triple etalon system and a 34-arcsec field of view (FOV). The second design, intermediate between high- and low-spectral-resolution modes of operation, produces an intermediate F/150 telecentric image at the etalons and a 1.1-arcmin FOV. The third and fourth designs each represent a low-resolution mode of operation, producing an F/82 telecentric image at the etalons and a 2-arcmin FOV. Each design results in good telecentricity and image quality. Departures from telecentricity at the intermediate image plane cause field-dependent shifts of the band-pass peak, which are negligible compared to the bandpass FWHM. The root mean square (rms) geometric spot sizes at the final image plane fit well within the area of a camera pixel, which is itself in accordance with the Nyquist criterion, half the width of the 28-mu m-wide resolution element (as determined from the diffraction limit of the ATST). For each configuration, we also examine the impact that the Beckers effect (the pupil apodization caused by the angle-dependent amplitude transmittance of the MFPI) has on the image quality of the MFPI instrument. (c) 2006 Society of Photo-Optical Instrumentation Engineers. C1 Univ Alabama, Ctr Appl Opt, Huntsville, AL 35801 USA. Univ Alabama, ATST Project, Natl Solar Observ, Huntsville, AL 35801 USA. Natl Solar Observ, Sunspot, NM 88349 USA. NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Robinson, B (reprint author), Univ Alabama, Ctr Appl Opt, 301 Sparkman Dr,Opt Bldg Rm 400, Huntsville, AL 35801 USA. EM robinsob@email.uah.edu RI Robinson, Brian/A-7805-2009; OI Balasubramaniam, Krishnan/0000-0003-2221-0933 NR 12 TC 2 Z9 2 U1 0 U2 1 PU SPIE-INT SOCIETY OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98225 USA SN 0091-3286 J9 OPT ENG JI Opt. Eng. PD FEB PY 2006 VL 45 IS 2 AR 023001 DI 10.1117/1.2170594 PG 11 WC Optics SC Optics GA 024CO UT WOS:000236172800006 ER PT J AU Lee, JK Newman, TS Gary, GA AF Lee, JK Newman, TS Gary, GA TI Oriented connectivity-based method for segmenting solar loops SO PATTERN RECOGNITION LA English DT Article DE segmentation; solar loops; model-based processing; arc detection ID CURVILINEAR STRUCTURES; ACTIVE-REGION; RECONSTRUCTION; REPRESENTATION; APPROXIMATION; DETECTOR; CURVES; IMAGES; TRACE AB A method based on oriented connectivity that can automatically segment arc-like structures (solar loops) from intensity images of the Sun's corona is introduced. The method is a constructive approach that uses model-guided processing to enable extraction of credible loop structures. Since the solar loops are vestiges of the solar magnetic field, the model-guided processing exploits external estimates of this field's local orientations that are derived from a physical magnetic field model. Empirical studies of the method's effectiveness are also presented. The oriented connectivity-based method is the first automatic method for the segmentation of solar loops. (c) 2005 Pattern Recognition Society. Published by Elsevier Ltd. All rights reserved. C1 Univ Alabama, Dept Comp Sci, Huntsville, AL 35899 USA. NASA, George C Marshall Space Flight Ctr, Space Sci Branch, Huntsville, AL 35812 USA. RP Univ Alabama, Dept Comp Sci, Huntsville, AL 35899 USA. EM jlee@cs.uah.edu; tnewman@cs.uah.edu; Allen.Gary@nasa.gov NR 37 TC 15 Z9 17 U1 0 U2 0 PU ELSEVIER SCI LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, OXON, ENGLAND SN 0031-3203 EI 1873-5142 J9 PATTERN RECOGN JI Pattern Recognit. PD FEB PY 2006 VL 39 IS 2 BP 246 EP 259 DI 10.1016/j.patcog.2005.07.004 PG 14 WC Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic SC Computer Science; Engineering GA 988LZ UT WOS:000233604000009 ER PT J AU Agarwal, GS Kapale, KT AF Agarwal, GS Kapale, KT TI Generation of Werner states via collective decay of coherently driven atoms SO PHYSICAL REVIEW A LA English DT Article ID TELEPORTATION; ENTANGLEMENT; CHANNELS; BEHAVIOR; FIELD AB We show deterministic generation of Werner states as a steady state of the collective decay dynamics of a pair of neutral atoms coupled to a leaky cavity and strong coherent drive. We also show how the scheme can be extended to generate a 2N-particle analogue of the bipartite Werner states. C1 Oklahoma State Univ, Dept Phys, Stillwater, OK 74078 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Oklahoma State Univ, Dept Phys, Stillwater, OK 74078 USA. EM agirish@okstate.edu; Kishor.T.Kapale@jpl.nasa.gov NR 20 TC 14 Z9 14 U1 1 U2 1 PU AMER PHYSICAL SOC PI COLLEGE PK PA ONE PHYSICS ELLIPSE, COLLEGE PK, MD 20740-3844 USA SN 2469-9926 EI 2469-9934 J9 PHYS REV A JI Phys. Rev. A PD FEB PY 2006 VL 73 IS 2 AR 022315 DI 10.1103/PhysRevA.73.022315 PG 5 WC Optics; Physics, Atomic, Molecular & Chemical SC Optics; Physics GA 017BC UT WOS:000235668100054 ER PT J AU Kapale, KT Zubairy, MS AF Kapale, KT Zubairy, MS TI Subwavelength atom localization via amplitude and phase control of the absorption spectrum. II SO PHYSICAL REVIEW A LA English DT Article ID AUTLER-TOWNES MICROSCOPY; POSITION MEASUREMENT; OPTICAL-FIELDS; SINGLE-ATOM; DIFFRACTION; SPECTROSCOPY; INTERFERENCE; LIMIT AB Interaction of the internal states of an atom with spatially dependent standing-wave cavity field can impart position information of the atom passing through it leading to subwavelength atom localization. We recently demonstrated a different regime of atom localization [Phys. Rev. A 72, 013820 (2005)], namely sub-half-wavelength localization through phase control of electromagnetically induced transparency. This regime corresponds to extreme localization of atoms within a chosen half-wavelength region of the standing-wave cavity field. Here we present further investigation of the simplified model considered earlier and show interesting features of the proposal. We show how the model can be used to simulate a variety of energy-level schemes. Furthermore, the dressed-state analysis is employed to explain the emergence and suppression of the localization peaks, and the peak positions and widths. The range of parameters for obtaining clean sub-half-wavelength localization is identified. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Texas A&M Univ, Dept Phys, College Stn, TX 77843 USA. Texas A&M Univ, Inst Quantum Studies, College Stn, TX 77843 USA. RP Kapale, KT (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,Mail Stop 126-347, Pasadena, CA 91109 USA. EM Kishor.T.Kapale@jpl.nasa.gov; zubairy@physics.tamu.edu NR 30 TC 86 Z9 87 U1 0 U2 2 PU AMERICAN PHYSICAL SOC PI COLLEGE PK PA ONE PHYSICS ELLIPSE, COLLEGE PK, MD 20740-3844 USA SN 1050-2947 J9 PHYS REV A JI Phys. Rev. A PD FEB PY 2006 VL 73 IS 2 AR 023813 DI 10.1103/PhysRevA.73.023813 PG 11 WC Optics; Physics, Atomic, Molecular & Chemical SC Optics; Physics GA 017BC UT WOS:000235668100179 ER PT J AU Madzunkov, S Shortt, BJ MacAskill, JA Darrach, MR Chutjian, A AF Madzunkov, S Shortt, BJ MacAskill, JA Darrach, MR Chutjian, A TI Measurements of polyatomic molecule formation on an icy grain analog using fast atoms SO PHYSICAL REVIEW A LA English DT Article ID WATER ICE; ULTRAVIOLET PHOTOLYSIS; INTERSTELLAR-MEDIUM; ION IRRADIATION; O(P-3) ATOMS; GAS-PHASE; 10 K; CHEMISTRY; SURFACES; CO AB Measurements are reported for production of CO2 resulting from the impact of a monoenergetic O(P-3) beam upon a surface cooled to 4.8 K and covered with a CO ice. Using temperature-programmed desorption and mass spectrometer detection, one clearly detects increasing amounts of CO2 formation with O(P-3) energies of 2, 5, 10, and 14 eV. This is a measurement of polyatomic molecule formation on a surface in a new regime using superthermal atoms. The chosen surface coverage, surface temperature, and superthermal atom energy simulate conditions in shock-heated circumstellar and interstellar regions. C1 CALTECH, Jet Prop Lab, Atom & Mol Collis Grp, Pasadena, CA 91109 USA. Cork Inst Technol, Dept Appl Phys & Instrumentat, Cork, Ireland. RP Madzunkov, S (reprint author), CALTECH, Jet Prop Lab, Atom & Mol Collis Grp, Pasadena, CA 91109 USA. NR 21 TC 16 Z9 16 U1 0 U2 2 PU AMERICAN PHYSICAL SOC PI COLLEGE PK PA ONE PHYSICS ELLIPSE, COLLEGE PK, MD 20740-3844 USA SN 1050-2947 J9 PHYS REV A JI Phys. Rev. A PD FEB PY 2006 VL 73 IS 2 AR 020901 DI 10.1103/PhysRevA.73.020901 PG 4 WC Optics; Physics, Atomic, Molecular & Chemical SC Optics; Physics GA 017BC UT WOS:000235668100012 ER PT J AU Trabert, E Beiersdorfer, P Brown, GV Boyce, K Kelley, RL Kilbourne, CA Porter, FS Szymkowiak, A AF Trabert, E Beiersdorfer, P Brown, GV Boyce, K Kelley, RL Kilbourne, CA Porter, FS Szymkowiak, A TI Time-resolved soft-x-ray spectroscopy of a magnetic octupole transition in nickel-like xenon, cesium, and barium ions SO PHYSICAL REVIEW A LA English DT Article ID HIGHLY-CHARGED IONS; ATOMIC LIFETIME MEASUREMENTS; ISOELECTRONIC SEQUENCE; EXTREME-ULTRAVIOLET; SPECTRA; TRAP; LINES; MICROCALORIMETER; SPECTROMETER; WAVELENGTHS AB A microcalorimeter with event mode capability for time-resolved soft-x-ray spectroscopy, and a high-resolution flat-field extreme ultraviolet spectrometer have been employed at the Livermore EBIT-I electron beam ion trap for observations and wavelength measurements of M1, E2, and M3 decays of long-lived levels in the Ni-like ions Xe26+, Cs27+, and Ba28+. Of particular interest is the lowest excited level, 3d(9)4s D-3(3), which can only decay via a magnetic octupole (M3) transition. For this level in Xe, an excitation energy of (590.40 +/- 0.03 eV) and a level lifetime of (11.5 +/- 0.5 ms) have been determined. C1 Lawrence Livermore Natl Lab, High Temp & Plasma Phys Div, Livermore, CA 94550 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Lawrence Livermore Natl Lab, High Temp & Plasma Phys Div, POB 5508, Livermore, CA 94550 USA. EM trabert1@llnl.gov RI Porter, Frederick/D-3501-2012; Kelley, Richard/K-4474-2012 OI Porter, Frederick/0000-0002-6374-1119; NR 39 TC 34 Z9 34 U1 0 U2 8 PU AMER PHYSICAL SOC PI COLLEGE PK PA ONE PHYSICS ELLIPSE, COLLEGE PK, MD 20740-3844 USA SN 2469-9926 EI 2469-9934 J9 PHYS REV A JI Phys. Rev. A PD FEB PY 2006 VL 73 IS 2 AR 022508 DI 10.1103/PhysRevA.73.022508 PG 8 WC Optics; Physics, Atomic, Molecular & Chemical SC Optics; Physics GA 017BC UT WOS:000235668100094 ER PT J AU Cutler, C Harms, J AF Cutler, C Harms, J TI Big Bang Observer and the neutron-star-binary subtraction problem SO PHYSICAL REVIEW D LA English DT Article ID GRAVITATIONAL-WAVES; COMPACT BINARIES; POINT MASSES; PARAMETERS; RADIATION; INFLATION; DETECTORS; MOTION AB The Big Bang Observer (BBO) is a proposed space-based gravitational-wave (GW) mission designed primarily to search for an inflation-generated GW background in the frequency range similar to 10(-1) Hz-1 Hz. The major astrophysical foreground in this range is gravitational radiation from inspiralling compact binaries. This foreground is expected to be much larger than the inflation-generated background, so to accomplish its main goal, BBO must be sensitive enough to identify and subtract out practically all such binaries in the observable universe. It is somewhat subtle to decide whether BBO's current baseline design is sufficiently sensitive for this task, since, at least initially, the dominant noise source impeding identification of any one binary is confusion noise from all the others (rather than instrumental noise). Here we present a self-consistent scheme for deciding whether BBO's baseline design is indeed adequate for subtracting out the binary foreground. We conclude that the current baseline should be sufficient. However, if BBO's sensitivity were degraded by a factor 2 from the current baseline, then its ability to detect an underlying primordial background would depend critically on the value of rho(th), the threshold signal-to-noise ratio marking the boundary between detectable and undetectable sources. If BBO's sensitivity were degraded by a factor 4 from the current baseline, it could not detect a primordial background below Omega(GW)similar to 10(-15). It is impossible to perfectly subtract out each of the binary inspiral waveforms, so an important question is how to deal with the "residual" errors in the post-subtraction data stream. We sketch a strategy of "projecting out" these residual errors, at the cost of some effective bandwidth. We also provide estimates of the sizes of various post-Newtonian effects in the inspiral waveforms that must be accounted for in the BBO analysis. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Univ Hannover, D-30167 Hannover, Germany. Max Planck Inst Gravitationsphys, D-30167 Hannover, Germany. RP Cutler, C (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RI Harms, Jan/J-4359-2012 NR 36 TC 63 Z9 63 U1 0 U2 0 PU AMERICAN PHYSICAL SOC PI COLLEGE PK PA ONE PHYSICS ELLIPSE, COLLEGE PK, MD 20740-3844 USA SN 1550-7998 J9 PHYS REV D JI Phys. Rev. D PD FEB PY 2006 VL 73 IS 4 AR 042001 DI 10.1103/PhysRevD.73.042001 PG 21 WC Astronomy & Astrophysics; Physics, Particles & Fields SC Astronomy & Astrophysics; Physics GA 017BT UT WOS:000235669800006 ER PT J AU Herrin, ET Rosenbaum, DC Teplitz, VL AF Herrin, ET Rosenbaum, DC Teplitz, VL TI Seismic search for strange quark nuggets SO PHYSICAL REVIEW D LA English DT Article ID SEISMOGRAPHIC STATION REPORTS; UNEXPLAINED SETS; NUCLEARITES; MATTER; CONSISTENT; DENSITY; PASSAGE AB Bounds on masses and abundances of Strange Quark Nuggets (SQNs) are inferred from a seismic search on Earth. Potential SQN bounds from a possible seismic search on the Moon are reviewed and compared with Earth capabilities. Bounds are derived from the data taken by seismometers implanted on the Moon by the Apollo astronauts. We show that the Apollo data implies that the abundance of SQNs in the region of 10 kg to 1 ton must be at least an order of magnitude less than would saturate the dark matter in the solar neighborhood. C1 So Methodist Univ, Dept Geol, Dallas, TX 75275 USA. So Methodist Univ, Dept Phys, Dallas, TX 75275 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Herrin, ET (reprint author), So Methodist Univ, Dept Geol, Dallas, TX 75275 USA. NR 21 TC 23 Z9 24 U1 0 U2 0 PU AMERICAN PHYSICAL SOC PI COLLEGE PK PA ONE PHYSICS ELLIPSE, COLLEGE PK, MD 20740-3844 USA SN 1550-7998 J9 PHYS REV D JI Phys. Rev. D PD FEB PY 2006 VL 73 IS 4 AR 043511 DI 10.1103/PhysRevD.73.043511 PG 7 WC Astronomy & Astrophysics; Physics, Particles & Fields SC Astronomy & Astrophysics; Physics GA 017BT UT WOS:000235669800023 ER PT J AU Stanev, T De Marco, D Malkan, MA Stecker, FW AF Stanev, T De Marco, D Malkan, MA Stecker, FW TI Cosmogenic neutrinos from cosmic ray interactions with extragalactic infrared photons SO PHYSICAL REVIEW D LA English DT Article ID ULTRAHIGH-ENERGY; GAMMA-RAYS; SPECTRUM; EVOLUTION; PROPAGATION; ABSORPTION; GALAXIES; ORIGIN; VIEW AB We discuss the production of cosmogenic neutrinos on extragalactic infrared photons in a model of its cosmological evolution. The relative importance of these infrared photons as a target for proton interactions is significant, especially in the case of steep injection spectra of the ultrahigh energy cosmic rays. For an E-2.5 cosmic ray injection spectrum, for example, the event rate of neutrinos of energy above 1 PeV is more than doubled. C1 Univ Delaware, Bartol Res Inst, Newark, DE 19716 USA. Univ Calif Los Angeles, Dept Phys & Astron, Los Angeles, CA 90095 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Univ Delaware, Bartol Res Inst, Newark, DE 19716 USA. EM stanev@muon.bartol.udel.edu; ddm@bartol.udel.edu; malkan@astro.ucla.edu; Floyd.W.Stecker@nasa.gov RI Stecker, Floyd/D-3169-2012 NR 38 TC 12 Z9 12 U1 0 U2 0 PU AMER PHYSICAL SOC PI COLLEGE PK PA ONE PHYSICS ELLIPSE, COLLEGE PK, MD 20740-3844 USA SN 2470-0010 EI 2470-0029 J9 PHYS REV D JI Phys. Rev. D PD FEB PY 2006 VL 73 IS 4 AR 043003 DI 10.1103/PhysRevD.73.043003 PG 8 WC Astronomy & Astrophysics; Physics, Particles & Fields SC Astronomy & Astrophysics; Physics GA 017BT UT WOS:000235669800011 ER PT J AU Balasubramaniam, R Rashidnia, N Maxworthy, T Kuang, J AF Balasubramaniam, R Rashidnia, N Maxworthy, T Kuang, J TI Instability of miscible interfaces in a cylindrical tube (vol 17, art no 052103, 2005) SO PHYSICS OF FLUIDS LA English DT Correction C1 NASA, Glenn Res Ctr, Natl Ctr Micrograv Res Fluids & Combust, Cleveland, OH 44135 USA. Univ So Calif, Los Angeles, CA 90089 USA. RP Balasubramaniam, R (reprint author), NASA, Glenn Res Ctr, Natl Ctr Micrograv Res Fluids & Combust, Cleveland, OH 44135 USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA CIRCULATION & FULFILLMENT DIV, 2 HUNTINGTON QUADRANGLE, STE 1 N O 1, MELVILLE, NY 11747-4501 USA SN 1070-6631 J9 PHYS FLUIDS JI Phys. Fluids PD FEB PY 2006 VL 18 IS 2 AR 029901 DI 10.1063/1.2179821 PG 2 WC Mechanics; Physics, Fluids & Plasmas SC Mechanics; Physics GA 016ZK UT WOS:000235663700035 ER PT J AU Pruett, CD Thomas, BC Grosch, CE Gatski, TB AF Pruett, CD Thomas, BC Grosch, CE Gatski, TB TI A temporal approximate deconvolution model for large-eddy simulation SO PHYSICS OF FLUIDS LA English DT Article ID CHANNEL FLOW AB A temporal approximate deconvolution model (TADM) is developed for large-eddy simulation and is demonstrated for plane-channel flow at Re-tau=590. The TADM combines explicit causal time-domain filtering with linear deconvolution (defiltering) to approximate unfiltered fields and residual stress to arbitrarily high order. The TADM methodology appears to lead to a robust family of residual-stress models that should provide a viable alternative to conventional (spatial) filtering for applications in which spatial filtering is problematic, e.g., for problems requiring unstructured or highly stretched grids. (c) 2006 American Institute of Physics. C1 James Madison Univ, Dept Math & Stat, Harrisonburg, VA 22807 USA. Old Dominion Univ, Dept Ocean Earth Atmospher Sci, Norfolk, VA 23529 USA. Old Dominion Univ, Dept Comp Sci, Norfolk, VA 23529 USA. NASA, Langley Res Ctr, Computat AeroSci Branch, Hampton, VA 23681 USA. RP Pruett, CD (reprint author), James Madison Univ, Dept Math & Stat, Harrisonburg, VA 22807 USA. EM pruettcd@jmu.edu NR 8 TC 14 Z9 14 U1 0 U2 1 PU AMER INST PHYSICS PI MELVILLE PA CIRCULATION & FULFILLMENT DIV, 2 HUNTINGTON QUADRANGLE, STE 1 N O 1, MELVILLE, NY 11747-4501 USA SN 1070-6631 J9 PHYS FLUIDS JI Phys. Fluids PD FEB PY 2006 VL 18 IS 2 AR 028104 DI 10.1063/1.2173288 PG 4 WC Mechanics; Physics, Fluids & Plasmas SC Mechanics; Physics GA 016ZK UT WOS:000235663700032 ER PT J AU Futaana, Y Barabash, S Holmstrom, M Bhardwaj, A AF Futaana, Y Barabash, S Holmstrom, M Bhardwaj, A TI Low energy neutral atoms imaging of the Moon SO PLANETARY AND SPACE SCIENCE LA English DT Article DE Moon; energetic neutral atoms; solar wind; magnetic anomaly; ambipolar diffusion; space weathering ID ION MASS-SPECTROMETRY; SOLAR-WIND; LUNAR PROSPECTOR; EPITHERMAL NEUTRONS; SURFACE; SODIUM; SIMULATIONS; ATMOSPHERE; PARTICLE; MERCURY AB Imaging of low-energy neutral atoms (LENAs) in the vicinity of the Moon can provide wide knowledge of the Moon from the viewpoint of plasma physics and planetary physics. At the surface of the Moon, neutral atoms are mainly generated by photon-stimulated desorption, micrometeorite vaporization and sputtering by solar wind protons. LENAs, the energetic neutral atoms with energy range of 10-500 eV, are mainly created by sputtering of solar wind particles. We have made quantitative estimates of sputtered LENAs from the Moon surface. The results indicate that LENAs can be detected by a realistic instrument and that the measurement will provide the global element maps of sputtered particles, which substantially reflect the surface composition, and the magnetic anomalies. We have also found that LENAs around dark regions, such as the permanent shadow inside craters in the pole region, can be imaged. This is because the solar wind ions can penetrate shaded regions due to their finite gyro-radius and the pressure gradient between the solar wind and the wake region. LENAs also extend our knowledge about the magnetic anomalies and associated mini-magnetosphere systems, which are the smallest magnetospheres as far as one knows. It is thought that no LENAs are generated from mini-magnetosphere regions because no solar wind may penetrate inside them. Imaging such void areas of LENAs will provide another map of lunar magnetic anomalies. (c) 2005 Elsevier Ltd. All rights reserved. C1 Swedish Inst Space Phys, SE-98128 Kiruna, Sweden. NASA, George C Marshall Space Flight Ctr, NSSTC, XC12, Huntsville, AL 35805 USA. RP Futaana, Y (reprint author), Swedish Inst Space Phys, Box 812, SE-98128 Kiruna, Sweden. EM futaana@irf.se RI Futaana, Yoshifumi/P-5899-2014; OI Futaana, Yoshifumi/0000-0002-7056-3517; Bhardwaj, Anil/0000-0003-1693-453X NR 53 TC 22 Z9 22 U1 0 U2 2 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0032-0633 J9 PLANET SPACE SCI JI Planet Space Sci. PD FEB PY 2006 VL 54 IS 2 BP 132 EP 143 DI 10.1016/j.pss.2005.10.010 PG 12 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 015VN UT WOS:000235579400002 ER PT J AU Paulson, DB Allred, JC Anderson, RB Hawley, SL Cochran, WD Yelda, S AF Paulson, DB Allred, JC Anderson, RB Hawley, SL Cochran, WD Yelda, S TI Optical spectroscopy of a flare on Barnard's star SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF THE PACIFIC LA English DT Article ID SOLAR-FLARES; AD LEONIS; H-ALPHA; M-DWARFS; EMISSION; SPECTRA; LINES; VARIABILITY; KINEMATICS; RESOLUTION AB We present optical spectra of a flare on Barnard's star. Several photospheric and chromospheric species were enhanced by the flare heating. An analysis of the Balmer lines shows that their shapes are best explained by Stark broadening rather than chromospheric mass motions. We estimate the temperature of the flaring region in the lower atmosphere to be >= 8000 K and the electron density to be similar to 10(14) cm(-3), similar to values observed in other dM flares. Because Barnard's star is considered to be one of our oldest neighbors, a flare of this magnitude is probably quite rare. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Drexel Univ, Dept Phys, Philadelphia, PA 19104 USA. Univ Michigan, Dept Astron, Ann Arbor, MI 48109 USA. Univ Washington, Dept Astron, Seattle, WA 98195 USA. Univ Texas, McDonald Observ, Austin, TX 78712 USA. RP Paulson, DB (reprint author), NASA, Goddard Space Flight Ctr, Code 693, Greenbelt, MD 20771 USA. EM dpaulson@lepvax.gsfc.nasa.gov RI Allred, Joel/C-9550-2012 NR 44 TC 17 Z9 17 U1 0 U2 1 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-6280 J9 PUBL ASTRON SOC PAC JI Publ. Astron. Soc. Pac. PD FEB PY 2006 VL 118 IS 840 BP 227 EP 235 DI 10.1086/499497 PG 9 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 017BU UT WOS:000235669900004 ER PT J AU French, RG McGhee, CA Frey, M Hock, R Rounds, S Jacobson, R Verbiscer, A AF French, RG McGhee, CA Frey, M Hock, R Rounds, S Jacobson, R Verbiscer, A TI Astrometry of Saturn's satellites from the Hubble Space Telescope WFPC2 SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF THE PACIFIC LA English DT Article ID 8 MAJOR SATELLITES; PROMETHEUS-PANDORA SYSTEM; RING PLANE CROSSINGS; HST OBSERVATIONS; GENERAL-THEORY; PERIOD PERTURBATIONS; IMAGING SCIENCE; CCD ASTROMETRY; ORBITS; MOTION AB Highly accurate astrometric positions of 14 of Saturn's satellites have been obtained from 444 Hubble Space Telescope images taken with the Wide Field Planetary Camera 2 (WFPC2) between 1996 and 2005. In all, 1036 satellite positions were measured in Planetary Camera (PC) frames, with a typical uncertainty of sigma(PC) = 0".014 (80 km at Saturn), and 1403 positions from Wide Field (WF) frames, with sigma(WF) = 0".012(120 km at Saturn). A key part of the reduction involved the application of an improved WFPC2 distortion- correction scheme (Anderson & King) and precise determination of the relative positions of the PC and WF chips, which varied substantially over the full course of the observation period. The time span covered by the observations is more than twice the nominal duration of the Cassini mission and thus provides an important baseline of measurements that is particularly important for studying time-variable phenomena such as the orbital exchange of Janus and Epimetheus and the chaotic interactions of Prometheus and Pandora. These results have been incorporated into ephemerides that are being used for planning and analysis of Cassini satellite and ring observations. C1 Wellesley Coll, Dept Astron, Wellesley, MA 02481 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Univ Virginia, Dept Astron, Charlottesville, VA 22903 USA. RP French, RG (reprint author), Wellesley Coll, Dept Astron, Wellesley, MA 02481 USA. EM rfrench@wellesley.edu; cmcghee@wellesley.edu; mrfrey@wellesley.edu; rhock@wellesley.edu; srounds@wellesley.edu; raj@murphy.jpl.nasa.gov; verbiscer@virginia.edu NR 48 TC 10 Z9 14 U1 0 U2 1 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-6280 J9 PUBL ASTRON SOC PAC JI Publ. Astron. Soc. Pac. PD FEB PY 2006 VL 118 IS 840 BP 246 EP 259 DI 10.1086/499215 PG 14 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 017BU UT WOS:000235669900006 ER PT J AU Taylor, JR King, BA Steincamp, J Rakoczy, J AF Taylor, JR King, BA Steincamp, J Rakoczy, J TI Genetic algorithm phase retrieval for the systematic image-based optical alignment test bed SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF THE PACIFIC LA English DT Article ID HOBBY-EBERLY-TELESCOPE; PRIMARY MIRROR; PAMELA AB A real-valued genetic algorithm with random rank-based selection is shown to successfully estimate the multiple phases of a segmented optical system modeled on the seven-mirror Systematic Image-Based Optical Alignment test bed located at NASA's Marshall Space Flight Center. Comparisons are made between this and more traditional phase-retrieval methods. No significant increase in computational speed is observed using the genetic algorithm technique. C1 Austin Peay State Univ, Dept Phys & Astron, Clarksville, TN 37044 USA. NASA, George C Marshall Space Flight Ctr, Engn Directorate, Huntsville, AL 35812 USA. RP Taylor, JR (reprint author), Austin Peay State Univ, Dept Phys & Astron, POB 4608, Clarksville, TN 37044 USA. EM taylorjr@apsu.edu; kinga@apsu.edu; steincamp1729@comcast.net; John.M.Rakoczy@nasa.gov NR 15 TC 2 Z9 2 U1 0 U2 1 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-6280 J9 PUBL ASTRON SOC PAC JI Publ. Astron. Soc. Pac. PD FEB PY 2006 VL 118 IS 840 BP 319 EP 323 DI 10.1086/498827 PG 5 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 017BU UT WOS:000235669900012 ER PT J AU Stohlgren, TJ Schnase, JL AF Stohlgren, TJ Schnase, JL TI Risk analysis for biological hazards: What we need to know about invasive species SO RISK ANALYSIS LA English DT Article DE nonnative species; potential species distributions; risk assessment; risk management ID UNITED-STATES; PLANT DIVERSITY; RIPARIAN ZONES; INVASIBILITY; PATTERNS; CLASSIFICATION; BIODIVERSITY; COMMUNITIES; ECOSYSTEMS; GRASSLANDS AB Risk analysis for biological invasions is similar to other types of natural and human hazards. For example, risk analysis for chemical spills requires the evaluation of basic information on where a spill occurs; exposure level and toxicity of the chemical agent; knowledge of the physical processes involved in its rate and direction of spread; and potential impacts to the environment, economy, and human health relative to containment costs. Unlike typical chemical spills, biological invasions can have long lag times from introduction and establishment to successful invasion, they reproduce, and they can spread rapidly by physical and biological processes. We use a risk analysis framework to suggest a general strategy for risk analysis for invasive species and invaded habitats. It requires: (1) problem formation (scoping the problem, defining assessment endpoints); (2) analysis (information on species traits, matching species traits to suitable habitats, estimating exposure, surveys of current distribution and abundance); (3) risk characterization (understanding of data completeness, estimates of the "potential" distribution and abundance; estimates of the potential rate of spread; and probable risks, impacts, and costs); and (4) risk management (containment potential, costs, and opportunity costs; legal mandates and social considerations and information science and technology needs). C1 US Geol Survey, Natl Inst Ivas Species Sci, Ft Collins, CO 80526 USA. NASA, Goddard Space Flight Ctr, Computat & Informat Sci & Technol Off, Greenbelt, MD 20771 USA. RP Stohlgren, TJ (reprint author), Colorado State Univ, US Geol Survey, Nat Resources Ecol Lab, Ft Collins, CO 80523 USA. EM tom_stohlgren@USFS.gov NR 58 TC 109 Z9 119 U1 5 U2 42 PU BLACKWELL PUBLISHING PI OXFORD PA 9600 GARSINGTON RD, OXFORD OX4 2DQ, OXON, ENGLAND SN 0272-4332 J9 RISK ANAL JI Risk Anal. PD FEB PY 2006 VL 26 IS 1 BP 163 EP 173 DI 10.1111/j.1539-6924.2006.00707.x PG 11 WC Public, Environmental & Occupational Health; Mathematics, Interdisciplinary Applications; Social Sciences, Mathematical Methods SC Public, Environmental & Occupational Health; Mathematics; Mathematical Methods In Social Sciences GA 014GQ UT WOS:000235468000020 PM 16492190 ER PT J AU Sonnabend, G Wirtz, D Schieder, R Bernath, P AF Sonnabend, G Wirtz, D Schieder, R Bernath, P TI High-resolution infrared measurements of H2O and SiO in sunspots SO SOLAR PHYSICS LA English DT Article ID TUNABLE DIODE-LASER; HETERODYNE SPECTROMETER; WATER; SUN AB Ultra-high-resolution spectroscopic measurements (R approximate to 10(7)) of water vapor and silicon monoxide in sunspots are presented. Observations were performed using the Cologne Tunable Heterodyne Infrared Spectrometer (THIS) at the McMath-Pierce Solar Observatory. Mid-infrared molecular absorption lines around 10 mu m were recorded and resolved in full detail. The linewidth and shape can thus be determined with high precision and were used to calculate kinetic temperatures which are much higher than the physical temperatures of the sunspot. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Philips Res Labs, Hamburg, Germany. Univ Cologne, KOSMA, Cologne, Germany. Univ Waterloo, Dept Chem, Waterloo, ON N2L 3G1, Canada. RP Sonnabend, G (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM gsonnabend@lepvax.gsfc.nasa.gov RI Bernath, Peter/B-6567-2012 OI Bernath, Peter/0000-0002-1255-396X NR 19 TC 4 Z9 4 U1 2 U2 5 PU SPRINGER PI DORDRECHT PA VAN GODEWIJCKSTRAAT 30, 3311 GZ DORDRECHT, NETHERLANDS SN 0038-0938 J9 SOL PHYS JI Sol. Phys. PD FEB PY 2006 VL 233 IS 2 BP 205 EP 213 DI 10.1007/s11207-006-2488-9 PG 9 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 012VS UT WOS:000235369600002 ER PT J AU Haugerud, BM Pratapgarhwala, MM Comeau, JP Sutton, AK Prakash, APG Cressler, JD Marshall, PW Marshall, CJ Ladbury, RL El-Diwany, M Mitchell, C Rockett, L Bach, T Lawrence, R Haddad, N AF Haugerud, BM Pratapgarhwala, MM Comeau, JP Sutton, AK Prakash, APG Cressler, JD Marshall, PW Marshall, CJ Ladbury, RL El-Diwany, M Mitchell, C Rockett, L Bach, T Lawrence, R Haddad, N TI Proton and gamma radiation effects in a new first-generation SiGe HBT technology SO SOLID-STATE ELECTRONICS LA English DT Article DE SiGeHBT; proton; gamma irradiation; circuits; mismatch ID BICMOS TECHNOLOGY; IRRADIATION; TOLERANCE; PERFORMANCE; RF AB The effects of proton and gamma irradiation on a new commercially available SiGe technology are investigated for the first time. The results of proton irradiation on a differential SiGe HBT LC oscillator are also reported in order to gauge circuit-level impact. These findings indicate that the dc, ac, and RF circuit performance is total dose tolerant up to Mrad-level equivalent total dose. A technology comparison is drawn between the results of this work and the three other previously reported SiGe technologies. We find that all reported SiGe HBT technologies to date show acceptable proton radiation tolerance up to Mrad levels. Transistor mismatch is also investigated here for the first time in SiGe HBTs. Collector current mismatch data as a function of emitter geometry are reported both before and after exposure for this SiGe HBT technology. We find only minimal changes in device-to -device mismatch after radiation exposure, suggesting that these SiGe HBTs should be suitable for use in analog circuits, which are critically dependent on the matching characteristics of the requisite devices. (c) 2005 Elsevier Ltd. All rights reserved. C1 Georgia Inst Technol, Sch Elect & Comp Engn, Atlanta, GA 30308 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. GSFC, Orbital Sci, Greenbelt, MD 21770 USA. Natl Semicond Corp, Santa Clara, CA 95052 USA. BAE Syst, Manassas, VA 20110 USA. RP Haugerud, BM (reprint author), Georgia Inst Technol, Sch Elect & Comp Engn, Atlanta, GA 30308 USA. EM bhaugerud@hotmail.com RI A P, Gnana Prakash/G-8054-2012; Rockett, Leonard/M-8880-2015 OI Rockett, Leonard/0000-0001-6376-6845 NR 21 TC 11 Z9 13 U1 1 U2 6 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0038-1101 J9 SOLID STATE ELECTRON JI Solid-State Electron. PD FEB PY 2006 VL 50 IS 2 BP 181 EP 190 DI 10.1016/j.sse.2005.11.007 PG 10 WC Engineering, Electrical & Electronic; Physics, Applied; Physics, Condensed Matter SC Engineering; Physics GA 019VF UT WOS:000235864100014 ER PT J AU Funk, S Hokkanen, B Wang, J Burghaus, U Bozzolo, G Garces, JE AF Funk, S Hokkanen, B Wang, J Burghaus, U Bozzolo, G Garces, JE TI Adsorption dynamics of CO2 on Cu(110): A molecular beam study SO SURFACE SCIENCE LA English DT Article DE molecular beam scattering; CO2; copper; precursor states; Monte Carlo simulations ID MONTE-CARLO-SIMULATION; LOW-INDEX FACES; CARBON-DIOXIDE; COVERAGE DEPENDENCE; METHANOL SYNTHESIS; SURFACES; PT(111); PROBABILITIES; HYDROGEN; STICKING AB Molecular beam scattering measurements have been conducted to examine the adsorption dynamics of CO, on Cu(I 10). The initial adsorption probability, So. decreases exponentially from 0.43 +/- 0.03 to a value close to the detection limit (similar to 0.03) within the impact energy range of E-i = (0. 12-1.30) eV. S-0 is independent of the adsorption temperature, T-s, and the impact angle, alpha(i), i.e., the adsorption is non-activated and total energy scaling is obeyed. The coverage, Theta, dependent adsorption probability, S(Theta), agrees with precursor-assisted adsorption dynamics (Kisliuk type) above Ts similar to 91 K. However, below that temperature adsorbate-assisted adsorption (S increases With Theta) has been observed. That effect is most distinct at large E-i and low T-s. The S(Theta) data have been modeled by Monte Carlo simulations. No indications of CO2 dissociation were obtained from Auger Electron Spectroscopy or the molecular beam scattering data. (c) 2005 Elsevier B.V. All rights reserved. C1 N Dakota State Univ, Dept Chem Biochem & Mol Biol, Fargo, ND 58105 USA. Ohio Aerosp Inst, Cleveland, OH 44142 USA. NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. Comis Nacl Energia Atom, Ctr Atom Bariloche, RA-8400 San Carlos De Bariloche, Rio Negro, Argentina. RP Burghaus, U (reprint author), N Dakota State Univ, Dept Chem Biochem & Mol Biol, Fargo, ND 58105 USA. EM uwe.burghaus@ndsu.edu RI Wang, Jinhai/A-2488-2010 NR 57 TC 30 Z9 30 U1 4 U2 22 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 0039-6028 J9 SURF SCI JI Surf. Sci. PD FEB 1 PY 2006 VL 600 IS 3 BP 583 EP 590 DI 10.1016/j.susc.2005.11.013 PG 8 WC Chemistry, Physical; Physics, Condensed Matter SC Chemistry; Physics GA 014VU UT WOS:000235509300015 ER PT J AU Xiao, M Reddi, LN Steinberg, SL AF Xiao, M Reddi, LN Steinberg, SL TI Effect of vibrations on pore fluid distribution in porous media SO TRANSPORT IN POROUS MEDIA LA English DT Article DE vibrations; pore fluid distribution; network model ID IMMISCIBLE DISPLACEMENT; VIBRATORY MOBILIZATION; MODEL FORMULATION; GANGLIA; SCALE AB Understanding the role of shuttle vibrations in pore fluid distribution is an essential task in the exploration of plant growth in root modules aboard space flights. Results from experimental investigations are reported in this paper on the distribution of immiscible fluid phases in glass beads under vibrations. Hexadecane, a petroleum compound immiscible with and lighter than water, was used in the experiments. The higher freezing point of Hexadecane (18 degrees C) allowed the solidification of the entrapped blobs in the presence of water in porous media, so that their size distribution can be obtained. van Genuchten function, commonly used to express moisture retention curves, is found to be an adequate fit for blob size distribution at residual saturation. The effect of vibrations on the fate (mobilization, stranding, or breakup) of a solitary ganglion in porous media was studied using a network model. A mobility criterion considering viscous, gravity, and capillary forces was developed to determine the fate of a solitary ganglion in a porous medium. It is concluded that the effect of vibrations is to increase the likelihood of breakup and mobilization of blobs entrapped in porous media at residual saturation. The pore fluid distributions after vibrations are less uniform than those before vibrations. C1 Kansas State Univ, Dept Civil Engn, Manhattan, KS 66506 USA. NASA, Lyndon B Johnson Space Ctr, Univ Space Res Assoc, Houston, TX 77058 USA. RP Xiao, M (reprint author), Kansas State Univ, Dept Civil Engn, Manhattan, KS 66506 USA. EM mingxiao@ksu.edu NR 7 TC 3 Z9 3 U1 0 U2 2 PU SPRINGER PI NEW YORK PA 233 SPRING STREET, NEW YORK, NY 10013 USA SN 0169-3913 J9 TRANSPORT POROUS MED JI Transp. Porous Media PD FEB PY 2006 VL 62 IS 2 BP 187 EP 204 DI 10.1007/s11242-005-1734-1 PG 18 WC Engineering, Chemical SC Engineering GA 014NK UT WOS:000235486700004 ER PT J AU DellaCorte, C AF DellaCorte, C TI In this complex world, concentrate on the fundamentals SO TRIBOLOGY & LUBRICATION TECHNOLOGY LA English DT Editorial Material C1 NASA, Glenn Res Ctr, Cleveland, OH USA. RP DellaCorte, C (reprint author), NASA, Glenn Res Ctr, Cleveland, OH USA. EM cdellacorte@stle.org NR 0 TC 1 Z9 1 U1 0 U2 0 PU SOC TRIBOLOGISTS & LUBRICATION ENGINEERS PI PARK RIDGE PA 840 BUSSE HIGHWAY, PARK RIDGE, IL 60068 USA SN 0024-7154 J9 TRIBOL LUBR TECHNOL JI Tribol. Lubr. Technol. PD FEB PY 2006 VL 62 IS 2 BP 6 EP 6 PG 1 WC Engineering, Mechanical SC Engineering GA 013AC UT WOS:000235381000002 ER PT J AU Eckermann, SD Dornbrack, A Vosper, SB Flentje, H Mahoney, MJ Bui, TP Carslaw, KS AF Eckermann, SD Dornbrack, A Vosper, SB Flentje, H Mahoney, MJ Bui, TP Carslaw, KS TI Mountain wave-induced polar stratospheric cloud forecasts for aircraft science flights during SOLVE/THESEO 2000 SO WEATHER AND FORECASTING LA English DT Article ID INTERPOLATION ANALYSIS SYSTEM; OZONE DEPLETION; GRAVITY-WAVES; MIDDLE ATMOSPHERE; ARCTIC STRATOSPHERE; LIDAR MEASUREMENTS; MODEL SIMULATIONS; PREDICTIVE SKILL; APE-POLECAT; CHEMISTRY AB The results of a multimodel forecasting effort to predict mountain wave-induced polar stratospheric clouds (PSCs) for airborne science during the third Stratospheric Aerosol and Gas Experiment (SAGE 111) Ozone Loss and Validation Experiment (SOLVE)/Third European Stratospheric Experiment on Ozone (THESEO 2000) Arctic ozone campaign are assessed. The focus is on forecasts for five flights of NASA's instrumented DC-8 research aircraft in which PSCs observed by onboard aerosol lidars were identified as wave related. Aircraft PSC measurements over northern Scandinavia on 25-27 January 2000 were accurately forecast by the mountain wave models several clays in advance, permitting coordinated quasi-Lagrangian flights that measured their composition and structure in unprecedented detail. On 23 January 2000 mountain wave ice PSCs were forecast over eastern Greenland. Thick layers of wave-induced ice PSC were measured by DC-8 aerosol lidars in regions along the flight track where the forecasts predicted enhanced stratospheric mountain wave amplitudes. The data front these flights, which were planned using this forecast guidance, have substantially improved the overall understanding of PSC microphysics within mountain waves. Observations of PSCs south of the DC-8 flight track on 30 November 1999 are consistent with forecasts of mountain wave-induced ice clouds over southern Scandinavia, and are validated locally using radiosonde data. On the remaining two flights wavelike PSCs were reported in regions where no mountain wave PSCs were forecast. For 10 December 1999. it is shown that locally generated mountain waves could not have propagated into the stratosphere where the PSCs were observed, confirming conclusions of other recent studies. For the PSC observed on 14 January 2000 over northern Greenland, recent work indicates that nonorographic gravity waves radiated from the jet stream produced this PSC, confirming the original forecast of no mountain wave influence. This forecast is validated further by comparing with a nearby ER-2 flight segment to the south of the DC-8, which intercepted and measured local stratospheric mountain waves with properties similar to those predicted. In total, the original forecast guidance proves to be consistent with PSC data acquired from all five of these DC-8 flights. The work discussed herein highlights areas where improvements can be made in future wave PSC forecasting campaigns, such as use of anelastic rather than Boussinesq linearized gridpoint models and a need to forecast stratospheric gravity waves from sources other than mountains. C1 USN, Res Lab, EO Hulburt Ctr Space Res, Washington, DC 20375 USA. DLR, Oberpfaffenhofen, Germany. CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. NASA, Ames Res Ctr, Atmospher Chem & Dynam Branch, Moffett Field, CA 94035 USA. Univ Leeds, Sch Environm, Leeds, W Yorkshire, England. RP USN, Res Lab, EO Hulburt Ctr Space Res, Code 7646, Washington, DC 20375 USA. EM stephen.eckermann@nrl.navy.mil RI Carslaw, Ken/C-8514-2009 OI Carslaw, Ken/0000-0002-6800-154X NR 91 TC 27 Z9 27 U1 1 U2 8 PU AMER METEOROLOGICAL SOC PI BOSTON PA 45 BEACON ST, BOSTON, MA 02108-3693 USA SN 0882-8156 EI 1520-0434 J9 WEATHER FORECAST JI Weather Forecast. PD FEB PY 2006 VL 21 IS 1 BP 42 EP 68 DI 10.1175/WAF901.1 PG 27 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 024ZY UT WOS:000236236300003 ER PT J AU Remer, LA Kaufman, YJ AF Remer, LA Kaufman, YJ TI Aerosol direct radiative effect at the top of the atmosphere over cloud free ocean derived from four years of MODIS data SO ATMOSPHERIC CHEMISTRY AND PHYSICS LA English DT Article ID SAFARI 2000; RETRIEVALS; VALIDATION; INSTRUMENT; SATELLITE; AFRICA; MODELS; CERES AB A four year record of MODIS spaceborne data provides a new measurement tool to assess the aerosol direct radiative effect at the top of the atmosphere. MODIS derives the aerosol optical thickness and microphysical properties from the scattered sunlight at 0.55 - 2.1 mu m. The monthly MODIS data used here are accumulated measurements across a wide range of view and scattering angles and represent the aerosol's spectrally resolved angular properties. We use these data consistently to compute with estimated accuracy of +/- 0.6 Wm(-2) the reflected sunlight by the aerosol over global oceans in cloud free conditions. The MODIS high spatial resolution (0.5 km) allows observation of the aerosol impact between clouds that can be missed by other sensors with larger footprints. We found that over the clear-sky global ocean the aerosol reflected 5.3 +/- 0.6 Wm(-2) with an average radiative efficiency of -49 +/- 2 Wm(-2) per unit optical thickness. The seasonal and regional distribution of the aerosol radiative effects are discussed. The analysis adds a new measurement perspective to a climate change problem dominated so far by models. C1 NASA, Goddard Space Flight Ctr, Atmospheres Lab, Greenbelt, MD 20771 USA. RP NASA, Goddard Space Flight Ctr, Atmospheres Lab, Greenbelt, MD 20771 USA. EM lorraine.a.remer@nasa.gov NR 37 TC 75 Z9 77 U1 0 U2 10 PU COPERNICUS GESELLSCHAFT MBH PI GOTTINGEN PA BAHNHOFSALLEE 1E, GOTTINGEN, 37081, GERMANY SN 1680-7316 EI 1680-7324 J9 ATMOS CHEM PHYS JI Atmos. Chem. Phys. PD JAN 30 PY 2006 VL 6 BP 237 EP 253 PG 17 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 008AL UT WOS:000235012500001 ER PT J AU Seiz, G Davies, R AF Seiz, G Davies, R TI Reconstruction of cloud geometry from multi-view satellite images SO REMOTE SENSING OF ENVIRONMENT LA English DT Article DE atmosphere; clouds; multi-view; photogrammetry; radiative transfer ID RETRIEVAL; RADIANCE AB Reflected solar radiances measured by the pushbroom cameras of the Multiangle Imaging SpectroRadiorneter (MISR) on the Terra satellite at nine viewing angles are combined to give eight stereo pairs. These are analyzed with stereo-photogrammetric methods to measure the geometry of a convective cloud system. Both cloud-top heights and cloud sides are retrieved with a precision of about 200-300 m. Two case studies of deep, convective clouds over ocean are considered. The accuracy of the MISR retrieval is tested in the first case study by reference to coincident, higher resolution stereo data from ASTER, showing how the accuracy of the cloud-top height retrieval is improved using the oblique MISR views. In the second case study, the entire cross-section of the cloud aligned with the viewing azimuthal direction is measured, using all nine cameras. The methodology presented is an important step towards more routine retrievals of the 3D geometrical reconstruction of isolated, deep-convective clouds. Such reconstructions are a necessary prerequisite to the subsequent 3D radiative transfer modeling used to aid the remote sensing of the elusive microphysical properties of such clouds. (c) 2005 Elsevier Inc. All rights reserved. C1 ETH Hoenggerberg, Swiss Fed Inst Technol, Inst Geodesy & Photogrammetry, CH-8093 Zurich, Switzerland. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Seiz, G (reprint author), ETH Hoenggerberg, Swiss Fed Inst Technol, Inst Geodesy & Photogrammetry, CH-8093 Zurich, Switzerland. EM gabriela.seiz@esa.int RI Davies, Roger/D-4296-2009 OI Davies, Roger/0000-0002-2991-0409 NR 18 TC 6 Z9 6 U1 0 U2 7 PU ELSEVIER SCIENCE INC PI NEW YORK PA 360 PARK AVE SOUTH, NEW YORK, NY 10010-1710 USA SN 0034-4257 J9 REMOTE SENS ENVIRON JI Remote Sens. Environ. PD JAN 30 PY 2006 VL 100 IS 2 BP 143 EP 149 DI 10.1016/j.rse.2005.09.016 PG 7 WC Environmental Sciences; Remote Sensing; Imaging Science & Photographic Technology SC Environmental Sciences & Ecology; Remote Sensing; Imaging Science & Photographic Technology GA 009MG UT WOS:000235115500001 ER PT J AU Njoku, EG Chan, SK AF Njoku, EG Chan, SK TI Vegetation and surface roughness effects on AMSR-E land observations SO REMOTE SENSING OF ENVIRONMENT LA English DT Article DE vegetation; AMSR-E; soil roughness ID SOIL-MOISTURE RETRIEVAL; PLANT WATER-CONTENT; MICROWAVE RADIOMETERS; EMISSION; MISSION; INDEX; SPACE AB Characteristics of the land surface including soil moisture, vegetation cover, and soil roughness among others influence the microwave emissivity and brightness temperature of the surface as observed from space. Knowledge of the variability of microwave signatures of vegetation and soil roughness is necessary to separate these influences from those of soil moisture for remote sensing applications to global hydrology and climate. We describe here a characterization of vegetation and soil roughness at the frequencies and spatial resolution of the EOS Aqua Advanced Microwave Scanning Radiometer (AMSR-E). A single parameter has been used to approximate the combined effects of vegetation and roughness. AMSR-E data have been analyzed to determine the frequency dependence of this parameter and to generate a global vegetation/roughness map and an estimate of seasonal variability. A physical model is used for the analysis with approximations appropriate to the AMSR-E footprint scale and coefficients calibrated empirically against the AMSR-E data. The spatial variabilities of roughness and vegetation cannot be estimated independently using this approach, but their temporal dynamics allow separation of predominantly static roughness effects from time-varying vegetation effects using multitemporal analysis. Global signals of time-varying vegetation water content derived from this analysis of AMSR-E data are consistent with time-varying biomass estimates obtained by optical/infrared remote sensing techniques. (c) 2005 Elsevier Inc. All rights reserved. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Njoku, EG (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. EM eni.g.njoku@jpl.nasa.gov RI Xie, Xingmei/G-7311-2011 NR 26 TC 144 Z9 167 U1 4 U2 41 PU ELSEVIER SCIENCE INC PI NEW YORK PA 360 PARK AVE SOUTH, NEW YORK, NY 10010-1710 USA SN 0034-4257 J9 REMOTE SENS ENVIRON JI Remote Sens. Environ. PD JAN 30 PY 2006 VL 100 IS 2 BP 190 EP 199 DI 10.1016/j.rse.2005.10.017 PG 10 WC Environmental Sciences; Remote Sensing; Imaging Science & Photographic Technology SC Environmental Sciences & Ecology; Remote Sensing; Imaging Science & Photographic Technology GA 009MG UT WOS:000235115500005 ER PT J AU Dennison, PE Charoensiri, K Roberts, DA Peterson, SH Green, RO AF Dennison, PE Charoensiri, K Roberts, DA Peterson, SH Green, RO TI Wildfire temperature and land cover modeling using hyperspectral data SO REMOTE SENSING OF ENVIRONMENT LA English DT Article DE wildfire; fire temperature; radiance modeling; Airborne Visible Infrared Imaging Spectrometer (AVIRIS) ID IMAGING SPECTROMETER; ENDMEMBER SELECTION; WATER-CONTENT; VEGETATION; SATELLITE; RESOLUTION; ENERGY; BRAZIL; AVIRIS AB Wildfire temperature retrieval commonly uses measured radiance from a middle infrared channel and a thermal infrared channel to separate fire emitted radiance from the background emitted radiance. Emitted radiance at shorter wavelengths, including the shortwave infrared, is measurable for objects above a temperature of 500 K. The spectral shape and radiance of thermal emission within the shortwave infrared can be used to retrieve fire temperature. Airborne Visible Infrared Imaging Spectrometer (AVIRIS) data were used to estimate fire properties and background properties for the 2003 Simi Fire in Southern California, USA. A spectral library of emitted radiance endmembers corresponding to a temperature range of 500-1500 K was created using the MODTRAN radiative transfer model. A second spectral library of reflected solar radiance endmembers, corresponding to four vegetation types and two non-vegetated surfaces, was created using image spectra selected by minimum endmember average root mean square error (RMSE). The best fit combination of an emitted radiance endmember and a reflected solar radiance endmember was found for each spectrum in the AVIRIS scene. Spectra were subset to reduce the effects of variable column water vapor and smoke contamination over the fire. The best fit models were used to produce maps of fire temperature, fire fractional area, background land cover, land cover fraction, and RMSE. The highest fire temperatures were found along the fire front, and lower fire temperatures were found behind the fire front. Saturation of shortwave infrared channels limited modeling of the highest fire temperatures. Spectral similarity of land cover endmembers and smoke impacted the accuracy of modeled land cover. Sensitivity analysis of modeled fire temperatures revealed that the range of temperatures modeled within 5% of minimum RMSE was smallest between 750 and 950 K. Hyperspectral modeling of wildfire temperature and fuels has potential application for fire monitoring and modeling. (c) 2005 Elsevier Inc. All rights reserved. C1 Univ Utah, Dept Geog, Ctr Nat & Technol Hazards, Salt Lake City, UT 84112 USA. Univ Calif Santa Barbara, Dept Geog, Santa Barbara, CA 93106 USA. Univ Calif Santa Barbara, Inst Computat Earth Syst Sci, Santa Barbara, CA 93106 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Dennison, PE (reprint author), Univ Utah, Dept Geog, Ctr Nat & Technol Hazards, Salt Lake City, UT 84112 USA. EM dennison@geog.utah.edu OI Dennison, Philip/0000-0002-0241-1917 NR 28 TC 57 Z9 58 U1 2 U2 19 PU ELSEVIER SCIENCE INC PI NEW YORK PA 360 PARK AVE SOUTH, NEW YORK, NY 10010-1710 USA SN 0034-4257 J9 REMOTE SENS ENVIRON JI Remote Sens. Environ. PD JAN 30 PY 2006 VL 100 IS 2 BP 212 EP 222 DI 10.1016/j.rse.2005.10.007 PG 11 WC Environmental Sciences; Remote Sensing; Imaging Science & Photographic Technology SC Environmental Sciences & Ecology; Remote Sensing; Imaging Science & Photographic Technology GA 009MG UT WOS:000235115500007 ER PT J AU Liu, X Chance, K Sioris, CE Kurosu, TP Spurr, RJD Martin, RV Fu, TM Logan, JA Jacob, DJ Palmer, PI Newchurch, MJ Megretskaia, IA Chatfield, RB AF Liu, X Chance, K Sioris, CE Kurosu, TP Spurr, RJD Martin, RV Fu, TM Logan, JA Jacob, DJ Palmer, PI Newchurch, MJ Megretskaia, IA Chatfield, RB TI First directly retrieved global distribution of tropospheric column ozone from GOME: Comparison with the GEOS-CHEM model SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article ID MODIFIED-RESIDUAL METHOD; MOZAIC AIRBORNE PROGRAM; IN-SERVICE AIRCRAFT; 1997-1998 EL-NINO; SATELLITE MEASUREMENTS; MAPPING SPECTROMETER; TOMS MEASUREMENTS; UNITED-STATES; SURFACE OZONE; WATER-VAPOR AB [1] We present the first directly retrieved global distribution of tropospheric column ozone from Global Ozone Monitoring Experiment (GOME) ultraviolet measurements during December 1996 to November 1997. The retrievals clearly show signals due to convection, biomass burning, stratospheric influence, pollution, and transport. They are capable of capturing the spatiotemporal evolution of tropospheric column ozone in response to regional or short time-scale events such as the 1997 - 1998 El Nino event and a 10 - 20 DU change within a few days. The global distribution of tropospheric column ozone displays the well-known wave-1 pattern in the tropics, nearly zonal bands of enhanced tropospheric column ozone of 36 - 48 DU at 20 degrees S-30 degrees S during the austral spring and at 25 degrees N - 45 degrees N during the boreal spring and summer, low tropospheric column ozone of < 30 DU uniformly distributed south of 35 degrees S during all seasons, and relatively high tropospheric column ozone of > 33 DU at some northern high-latitudes during the spring. Simulation from a chemical transport model corroborates most of the above structures, with small biases of < +/- 5 DU and consistent seasonal cycles in most regions, especially in the southern hemisphere. However, significant positive biases of 5 - 20 DU occur in some northern tropical and subtropical regions such as the Middle East during summer. Comparison of GOME with monthly-averaged Measurement of Ozone and Water Vapor by Airbus in-service Aircraft (MOZAIC) tropospheric column ozone for these regions usually shows good consistency within 1 sigma standard deviations and retrieval uncertainties. Some biases can be accounted for by inadequate sensitivity to lower tropospheric ozone, the different spatiotemporal sampling and the spatiotemporal variations in tropospheric column ozone. C1 Harvard Smithsonian Ctr Astrophys, Atom & Mol Phys Div, Cambridge, MA 02138 USA. NASA, Ames Res Ctr, Atmospher Chem & Dynam Branch, Moffett Field, CA 94035 USA. Harvard Univ, Div Engn & Appl Sci, Cambridge, MA 02138 USA. Univ Alabama, Dept Atmospher Sci, Huntsville, AL 35805 USA. Univ Leeds, Sch Earth & Environm, Leeds LS2 9JT, W Yorkshire, England. RP Harvard Smithsonian Ctr Astrophys, Atom & Mol Phys Div, 60 Garden St, Cambridge, MA 02138 USA. EM xliu@cfa.harvard.edu RI Chem, GEOS/C-5595-2014; Martin, Randall/C-1205-2014; Palmer, Paul/F-7008-2010; Liu, Xiong/P-7186-2014; Fu, Tzung-May/N-3418-2015; Martin, Randall/A-2051-2008; OI Sioris, Christopher/0000-0003-1168-8755; Martin, Randall/0000-0003-2632-8402; Liu, Xiong/0000-0003-2939-574X; Chance, Kelly/0000-0002-7339-7577 NR 77 TC 65 Z9 66 U1 2 U2 2 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-897X EI 2169-8996 J9 J GEOPHYS RES-ATMOS JI J. Geophys. Res.-Atmos. PD JAN 28 PY 2006 VL 111 IS D2 AR D02308 DI 10.1029/2005JD006564 PG 17 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 008FY UT WOS:000235026800007 ER PT J AU Pahlow, M Feingold, G Jefferson, A Andrews, E Ogren, JA Wang, J Lee, YN Ferrare, RA Turner, DD AF Pahlow, M Feingold, G Jefferson, A Andrews, E Ogren, JA Wang, J Lee, YN Ferrare, RA Turner, DD TI Comparison between lidar and nephelometer measurements of aerosol hygroscopicity at the Southern Great Plains Atmospheric Radiation Measurement site SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article ID WATER-VAPOR; RAMAN LIDAR; HUMIDIFICATION FACTORS; OPTICAL-PROPERTIES; RELATIVE-HUMIDITY; SIZE; PARTICLES; SURFACE; BACKSCATTERING; SENSITIVITY AB [1] Aerosol hygroscopicity has a significant effect on radiative properties of aerosols. Here a lidar method, applicable to cloud-capped, well-mixed atmospheric boundary layers, is employed to determine the hygroscopic growth factor f(RH) under unperturbed, ambient atmospheric conditions. The data used for the analysis were collected under a wide range of atmospheric aerosol levels during both routine measurement periods and during the intensive operations period (IOP) in May 2003 at the Southern Great Plains (SGP) Climate Research Facility in Oklahoma, USA, as part of the Atmospheric Radiation Measurement ( ARM) program. There is a good correlation ( similar to 0.7) between a lidar-derived growth factor ( measured over the range 85% RH to 96% RH) with a nephelometer-derived growth factor measured over the RH range 40% to 85%. For these RH ranges, the slope of the lidar-derived growth curve is much steeper than that of the nephelometer-derived growth curve, reflecting the rapid increase in particle size with increasing RH. The results are corroborated by aerosol model calculations of lidar backscatter and nephelometer equivalent f( RH) based on in situ aerosol size and composition measurements during the IOP. It is suggested that the lidar method can provide useful measurements of the dependence of aerosol optical properties on relative humidity and under conditions closer to saturation than can currently be achieved with humidified nephelometers. C1 NOAA, Environm Technol Lab, Boulder, CO 80305 USA. NOAA, Climate Monitoring & Diagnost Lab, Boulder, CO 80305 USA. Brookhaven Natl Lab, Upton, NY 11973 USA. NASA, Langley Res Ctr, Hampton, VA 23681 USA. Pacific NW Natl Lab, Richland, WA 99352 USA. RP Pahlow, M (reprint author), Ruhr Univ Bochum, Lehrstuhl Hydrol Wasserwirtschaft & Umwelttech, D-44780 Bochum, Germany. EM markus.pahlow@rub.de; graham.feingold@noaa.gov; anne.jefferson@noaa.gov; betsy.andrews@noaa.gov; john.a.ogren@noaa.gov; jian@bnl.gov; ynlee@bnl.gov; richard.a.ferrare@nasa.gov; dave.turner@pnl.gov RI Jefferson, Anne/K-4793-2012; Feingold, Graham/B-6152-2009; Wang, Jian/G-9344-2011; Ogren, John/M-8255-2015; Manager, CSD Publications/B-2789-2015 OI Ogren, John/0000-0002-7895-9583; NR 27 TC 21 Z9 22 U1 1 U2 10 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-897X J9 J GEOPHYS RES-ATMOS JI J. Geophys. Res.-Atmos. PD JAN 28 PY 2006 VL 111 IS D5 AR D05S15 DI 10.1029/2004JD005646 PG 8 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 008GC UT WOS:000235027200001 ER PT J AU Farrell, WM Renno, N Delory, GT Cummer, SA Marshall, JR AF Farrell, WM Renno, N Delory, GT Cummer, SA Marshall, JR TI Integration of electrostatic and fluid dynamics within a dust devil SO JOURNAL OF GEOPHYSICAL RESEARCH-PLANETS LA English DT Article ID MARS PATHFINDER; ELECTRIC FIELD; ELECTRIFICATION; GENERATION; VORTICES AB [1] In this study we derive an analytical expression to describe the electrostatic field in a dust cloud with grain trajectories defined by fluid dynamics and grain charging via contact electrification. In order to solve for the electric field, we merge the fluid dynamic - driven grain motion directly into the basic electrostatic formalism to end up with an electric field dependent on meteorological variables within the dust cloud. We find that the E field is driven by two processes: the currents associated with the charging grains and the increasing velocity difference of varying-sized grains at early times. The resulting processes give rise to an exponentially growing electric field, which for Mars applications, quickly approaches breakdown values. Variations in the growth of the electric field are found with varying grains sizes and varying ambient atmospheric conductivity. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Univ Michigan, Ann Arbor, MI 48109 USA. Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. Duke Univ, Dept Elect & Comp Engn, Durham, NC 27708 USA. SETI Inst, Mountain View, CA 94043 USA. RP Farrell, WM (reprint author), NASA, Goddard Space Flight Ctr, Mail Code 695, Greenbelt, MD 20771 USA. EM william.farrell@gsfc.nasa.gov RI Cummer, Steven/A-6118-2008; Farrell, William/I-4865-2013 OI Cummer, Steven/0000-0002-0002-0613; NR 34 TC 15 Z9 15 U1 0 U2 3 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-9097 EI 2169-9100 J9 J GEOPHYS RES-PLANET JI J. Geophys. Res.-Planets PD JAN 28 PY 2006 VL 111 IS E1 AR E01006 DI 10.1029/2005JE002527 PG 10 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 008GI UT WOS:000235027800001 ER PT J AU Conway, G Torrejon, M Lin, S Reinsch, S AF Conway, G Torrejon, M Lin, S Reinsch, S TI Fluorescent tagged analysis of neural gene function using mosaics in zebrafish and Xenopus laevis SO BRAIN RESEARCH LA English DT Article DE mosaic expression; transgenic; neuron; EGFP; TAGUM ID NEURONAL EXPRESSION; TRANSGENIC MICE; EMBRYOS; PROMOTER; PROTEIN; GROWTH; DROSOPHILA; INVITRO; MARKER; GFP AB An important question in the neurosciences is the role of specific gene expression in the control of neural morphology and connectivity. To address this question, methods are needed for expression of exogenous genes in a subset of neurons. This limited and mosaic expression allows the assessment of gene expression in a cell autonomous fashion without environmental contributions from neighboring expressing cells. These methods must also label neurons so that detailed morphology and neural connections can be evaluated. The labeling method should label only a subset of neurons so that neuronal morphology can be viewed upon a non-stained background, in a Golgi staining fashion. Here, we report methods using plasmids called pTAGUM (tagged analysis of genes using mosaics) that accomplish these goals. These methods should prove useful for the analysis of neural gene function in two important model organisms, the zebrafish and Xenopus laevis. (c) 2005 Elsevier B.V. All rights reserved. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. Univ Calif Los Angeles, Los Angeles, CA 90095 USA. RP Conway, G (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM gconway@mail.arc.nasa.gov NR 28 TC 3 Z9 3 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 0006-8993 J9 BRAIN RES JI Brain Res. PD JAN 27 PY 2006 VL 1070 IS 1 BP 150 EP 159 DI 10.1016/j.brainres.2005.11.079 PG 10 WC Neurosciences SC Neurosciences & Neurology GA 023BB UT WOS:000236099000018 PM 16430873 ER PT J AU Ming, DW Mittlefehldt, DW Morris, RV Golden, DC Gellert, R Yen, A Clark, BC Squyres, SW Farrand, WH Ruff, SW Arvidson, RE Klingelhofer, G McSween, HY Rodionov, DS Schroder, C de Souza, PA Wang, A AF Ming, DW Mittlefehldt, DW Morris, RV Golden, DC Gellert, R Yen, A Clark, BC Squyres, SW Farrand, WH Ruff, SW Arvidson, RE Klingelhofer, G McSween, HY Rodionov, DS Schroder, C de Souza, PA Wang, A TI Geochemical and mineralogical indicators for aqueous processes in the Columbia Hills of Gusev crater, Mars SO JOURNAL OF GEOPHYSICAL RESEARCH-PLANETS LA English DT Article ID MERIDIANI-PLANUM; SPIRIT ROVER; CHEMICAL CLASSIFICATION; MOSSBAUER SPECTROMETER; MARTIAN METEORITES; VOLCANIC-ROCKS; SOILS; ENVIRONMENT; CHEMISTRY; HEMATITE AB [1] Water played a major role in the formation and alteration of rocks and soils in the Columbia Hills. The extent of alteration ranges from moderate to extensive. Five distinct rock compositional classes were identified; the order for degree of alteration is Watchtower congruent to Clovis > Wishstone congruent to Peace > Backstay. The rover's wheels uncovered one unusual soil (Paso Robles) that is the most S-rich material encountered. Clovis class rocks have compositions similar to Gusev plains soil but with higher Mg, Cl, and Br and lower Ca and Zn; Watchtower and Wishstone classes have high Al, Ti, and P and low Cr and Ni; Peace has high Mg and S and low Al, Na, and K; Backstay basalts have high Na and K compared to plains Adirondack basalts; and Paso Robles soil has high S and P. Some rocks are corundum-normative, indicating that their primary compositions were changed by loss and/or gain of rock-forming elements. Clovis materials consist of magnetite, nanophase ferric-oxides (npOx), hematite, goethite, Ca-phosphates, Ca- and Mg-sulfates, pyroxene, and secondary aluminosilicates. Wishstone and Watchtower rocks consist of Fe-oxides/oxyhydroxides, ilmenite, Ca- phosphate, pyroxene, feldspar, Mg-sulfates, and secondary aluminosilicates. Peace consists of magnetite, npOx, Mg- and Ca- sulfates, pyroxene, olivine, feldspar, apatite, halides, and secondary aluminosilicates. Paso Robles consists of Fe3+-, Mg-, Ca-, and other sulfates, Ca- phosphates, hematite, halite, allophane, and amorphous silica. Columbia Hills outcrops and rocks may have formed by the aqueous alteration of basaltic rocks, volcaniclastic materials, and/or impact ejecta by solutions that were rich in acid-volatile elements. C1 NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. ESCG, Jacobs Sverdrup, Houston, TX 77058 USA. Johannes Gutenberg Univ Mainz, Inst Inorgan & Analyt Chem, D-55099 Mainz, Germany. Max Planck Inst Chem, D-55128 Mainz, Germany. Univ Guelph, Guelph, ON N1G 2W1, Canada. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Lockheed Martin Corp, Littleton, CO 80127 USA. Cornell Univ, Dept Astron, Ithaca, NY 14853 USA. Space Sci Inst, Boulder, CO 80301 USA. Arizona State Univ, Dept Geol Sci, Tempe, AZ 85287 USA. Washington Univ, Dept Earth & Planetary Sci, St Louis, MO 63130 USA. Univ Tennessee, Dept Earth & Planetary Sci, Knoxville, TN 37996 USA. IKI, Space Res Inst, Moscow, Russia. RP NASA, Lyndon B Johnson Space Ctr, Mail Code KX,2101 NASA Rd, Houston, TX 77058 USA. EM douglas.w.ming@nasa.gov RI de Souza, Paulo/B-8961-2008; Schroder, Christian/B-3870-2009 OI de Souza, Paulo/0000-0002-0091-8925; Schroder, Christian/0000-0002-7935-6039 NR 66 TC 160 Z9 160 U1 3 U2 33 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-9097 EI 2169-9100 J9 J GEOPHYS RES-PLANET JI J. Geophys. Res.-Planets PD JAN 27 PY 2006 VL 111 IS E2 AR E02S12 DI 10.1029/2005JE002560 PG 23 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 008GM UT WOS:000235028200001 ER PT J AU Nakagawa, T Gopalswamy, N Yashiro, S AF Nakagawa, T Gopalswamy, N Yashiro, S TI Solar wind speed within 20 R-S of the Sun estimated from limb coronal mass ejections SO JOURNAL OF GEOPHYSICAL RESEARCH-SPACE PHYSICS LA English DT Article ID SPACECRAFT AB [1] An estimation of the solar wind speed in the vicinity of the Sun is carried out using the initial speed and acceleration of coronal mass ejections (CMEs) that appeared close to the solar limb. A linear relationship was found between the initial acceleration and the speed of the limb CMEs. It appears that a dragging force is acting on the CMEs, depending on the speed difference between the CMEs and the ambient plasma. The ambient solar wind speed within 20 solar radii estimated from low-latitude CMEs during 1998 - 2003 ranged from 100 to 700 km s(-1), while the solar wind speed measured at 1 AU ranged from 300 to 700 km s(-1). The estimated solar wind speeds in the vicinity of the Sun sometimes agreed with the simultaneous in situ measurements at 1 AU, but in other periods they were slower than the speeds measured at 1 AU. It is suggested that most of the time the low-latitude solar wind completes accelerating within 20 solar radii, but occasionally additional acceleration is present beyond 20 solar radii. C1 Tohoku Inst Technol, Taihaku Ku, Sendai, Miyagi 9828577, Japan. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Catholic Univ Amer, Washington, DC 20064 USA. RP Nakagawa, T (reprint author), Tohoku Inst Technol, Taihaku Ku, Sendai, Miyagi 9828577, Japan. EM nakagawa@tohtech.ac.jp RI Gopalswamy, Nat/D-3659-2012; OI Nakagawa, Tomoko/0000-0001-6267-3081 NR 16 TC 3 Z9 3 U1 0 U2 0 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0148-0227 J9 J GEOPHYS RES-SPACE JI J. Geophys. Res-Space Phys. PD JAN 27 PY 2006 VL 111 IS A1 AR A01108 DI 10.1029/2005JA011249 PG 11 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 008GS UT WOS:000235028800002 ER PT J AU Barratt, M AF Barratt, M TI Thinking about NASAs future SO SCIENCE LA English DT Letter C1 NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Barratt, M (reprint author), NASA, Lyndon B Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. NR 3 TC 0 Z9 0 U1 0 U2 1 PU AMER ASSOC ADVANCEMENT SCIENCE PI WASHINGTON PA 1200 NEW YORK AVE, NW, WASHINGTON, DC 20005 USA SN 0036-8075 J9 SCIENCE JI Science PD JAN 27 PY 2006 VL 311 IS 5760 BP 469 EP 469 PG 1 WC Multidisciplinary Sciences SC Science & Technology - Other Topics GA 008WM UT WOS:000235071400019 PM 16439645 ER PT J AU Brinksma, EJ Bracher, A Lolkema, DE Segers, AJ Boyd, IS Bramstedt, K Claude, H Godin-Beekmann, S Hansen, G Kopp, G Leblanc, T McDermid, IS Meijer, YJ Nakane, H Parrish, A von Savigny, C Stebel, K Swart, DPJ Taha, G Piters, AJM AF Brinksma, EJ Bracher, A Lolkema, DE Segers, AJ Boyd, IS Bramstedt, K Claude, H Godin-Beekmann, S Hansen, G Kopp, G Leblanc, T McDermid, IS Meijer, YJ Nakane, H Parrish, A von Savigny, C Stebel, K Swart, DPJ Taha, G Piters, AJM TI Geophysical validation of SCIAMACHY Limb Ozone Profiles SO ATMOSPHERIC CHEMISTRY AND PHYSICS LA English DT Article ID STRATOSPHERIC CHANGE; MISSION; NETWORK AB We discuss the quality of the two available SCIA-MACHY limb ozone profile products. They were retrieved with the University of Bremen IFE's algorithm version 1.61 ( hereafter IFE), and the official ESA offline algorithm ( hereafter OL) versions 2.4 and 2.5. The ozone profiles were compared to a suite of correlative measurements from ground-based lidar and microwave, sondes, SAGE II and SAGE III (Stratospheric Aerosol and Gas Experiment). To correct for the expected Envisat pointing errors, which have not been corrected implicitly in either of the algorithms, we applied a constant altitude shift of -1.5 km to the SCIA-MACHY ozone profiles. The IFE ozone profile data between 16 and 40 km are biased low by 3-6%. The average difference profiles have a typical standard deviation of 10% between 20 and 35 km. We show that more than 20% of the SCIAMACHY official ESA offline (OL) ozone profiles version 2.4 and 2.5 have unrealistic ozone values, most of these are north of 15 degrees S. The remaining OL profiles compare well to correlative instruments above 24 km. Between 20 and 24 km, they underestimate ozone by 15 +/- 5%. C1 KNMI, NL-3730 AE De Bilt, Netherlands. Univ Bremen, Inst Environm Phys IFE, D-28334 Bremen, Germany. Natl Inst Publ Hlth & Environm RIVM, Bilthoven, Netherlands. NIWA, Environm Res Inst, Ann Arbor, MI 48108 USA. Meteorol Observat, Deutsch Wetterdienst, D-82383 Hohenpeissenberg, Germany. CNRS, Serv Aeron, Inst Pierre Simon Lapl, F-75252 Paris 05, France. Norwegian Inst Air Res, Polar Environm Ctr, Tromso, Norway. Forschungszentrum Karlsruhe, IMK, Karlsruhe, Germany. Univ Karlsruhe, Karlsruhe, Germany. NASA, JPL, Wrightwood, CA USA. Natl Inst Environm Studies, Div Atmospher Environm, Tsukuba, Ibaraki 3058506, Japan. Univ Massachusetts, Amherst, MA 01003 USA. Sci Applicat Int Corp, Hampton, VA USA. NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Piters, AJM (reprint author), KNMI, Postbus 201, NL-3730 AE De Bilt, Netherlands. EM piters@knmi.nl RI Bracher, Astrid/B-7805-2013; von Savigny, Christian/B-3910-2014; Stebel, Kerstin/F-6465-2013; OI Bracher, Astrid/0000-0003-3025-5517; Stebel, Kerstin/0000-0002-6935-7564; Nakane, Hideaki/0000-0002-9032-6105 NR 25 TC 19 Z9 19 U1 0 U2 1 PU EUROPEAN GEOSCIENCES UNION PI KATLENBURG-LINDAU PA MAX-PLANCK-STR 13, 37191 KATLENBURG-LINDAU, GERMANY SN 1680-7324 J9 ATMOS CHEM PHYS JI Atmos. Chem. Phys. PD JAN 26 PY 2006 VL 6 BP 197 EP 209 PG 13 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 006JB UT WOS:000234892700003 ER PT J AU Rinsland, CP Mahieu, E Zander, R Nassar, R Bernath, P Boone, C Chiou, LS AF Rinsland, CP Mahieu, E Zander, R Nassar, R Bernath, P Boone, C Chiou, LS TI Long-term stratospheric carbon tetrafluoride (CF4) increase inferred from 1985-2004 infrared space-based solar occultation measurements SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID MOLECULAR SPECTROSCOPIC DATABASE; ATMOS OBSERVATIONS; RETRIEVALS; AIR; SF6 AB The long-term stratospheric carbon tetrafluoride (CF4) increase has been determined from infrared high spectral resolution solar occultation Fourier transform spectrometer measurements between 3 and 50 hPa (similar to 20 to 40 km altitude) and latitudes from 50 degrees N to 50 degrees S during 1985, 1992, 1993, 1994, and 2004. The 1985 to 1994 measurements were recorded from the ATMOS ( Atmospheric Trace MOlecule Spectroscopy) instrument at 0.01 cm(-1) resolution and in 2004 by the Atmospheric Chemistry Experiment ( ACE) instrument at 0.02 cm(-1) resolution. Stratospheric volume mixing ratios, inferred from a polynomial fit to averages from the time periods considered here, increased from 49.37 +/- 2.60 pptv (10(-12) per unit volume) in 1985 to 58.38 +/- 4.14 pptv in 1992, 60.46 +/- 2.97 pptv in 1993, 60.11 +/- 3.60 pptv in 1994 and to 70.45 +/- 3.40 pptv in 2004. The stratospheric CF4 mixing ratio has continued to increase but at a slower rate than in previous years, for example, (1.14 +/- 0.68)% yr(-1) in 2004 as compared to (2.77 +/- 0.47)% yr(-1) in 1985, 1 sigma. Correlations of CF4 with N2O taking into account the increase of N2O with time also show the increase in the stratospheric CF4 burden over the two decade measurement time span. Our space-based measurements show that the slowdown in the rate of CF4 accumulation previously reported from surface measurements through 1997 has propagated to the stratosphere and is continuing. Citation: Rinsland, C. P., E. Mahieu, R. Zander, R. Nassar, P. Bernath, C. Boone, and L. S. Chiou (2006), Long-term stratospheric carbon tetrafluoride (CF4) increase inferred from 1985-2004 infrared space-based solar occultation measurements, Geophys. Res. Lett., 33, L02808, doi:10.1029/2005GL024709. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. Univ Waterloo, Dept Chem, Waterloo, ON N2L 3G1, Canada. Sci Applicat Int Corp, Hampton, VA 23666 USA. Univ Liege, Inst Astrophys & Geophys, B-4000 Liege, Belgium. RP Rinsland, CP (reprint author), NASA, Langley Res Ctr, 21 Langley Blvd,Mail Stop 401A, Hampton, VA 23681 USA. EM c.p.rinsland@larc.nasa.gov; emmanuel.mahieu@ulg.ac.be; r.zander@ulg.ac.be; ray@acebox.uwaterloo.ca; bernath@uwaterloo.ca; cboone@acebox.uwaterloo.ca; l.s.chiou@larc.nasa.gov RI Bernath, Peter/B-6567-2012; OI Bernath, Peter/0000-0002-1255-396X; Mahieu, Emmanuel/0000-0002-5251-0286; Nassar, Ray/0000-0001-6282-1611 NR 24 TC 7 Z9 7 U1 0 U2 1 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0094-8276 J9 GEOPHYS RES LETT JI Geophys. Res. Lett. PD JAN 26 PY 2006 VL 33 IS 2 AR L02808 DI 10.1029/2005GL024709 PG 4 WC Geosciences, Multidisciplinary SC Geology GA 008FO UT WOS:000235025800004 ER PT J AU Bell, RE Studinger, M Fahnestock, MA Shuman, CA AF Bell, RE Studinger, M Fahnestock, MA Shuman, CA TI Tectonically controlled subglacial lakes on the flanks of the Gamburtsev Subglacial Mountains, East Antarctica SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID VOSTOK; ICE; FRAMEWORK; FLOW AB The morphology of surface lakes strongly influences their ecology and limnology (Wetzel, 2001). This morphology is a result of both the geologic processes that produce topographic basins and the regional climatic and local hydrologic processes that control water depth and sediment infilling (Carroll and Bohacs, 1999). Although basin forming processes range from glacial scour to meteorite impacts (Cohen, 2003), the deepest, oldest surface lakes are tectonically controlled (Meybeck, 1995) and contain diverse exotic ecosystems (Rossiterm and Kawanabe, 2000). Subglacial lakes are also thought to be ancient systems that may contain exotic biota (Bulat et al., 2004; Karl et al., 1999; Priscu et al., 1999). Here we present evidence for the scale and configuration of 2 large subglacial lakes in East Antarctica that together with Lake Vostok define a province of major lakes on the flanks of the Gamburtsev Subglacial Mountains. Spatially-defined in the new Moderate Resolution Imaging Spectroradiometer (MODIS) imagery of Antarctica (T. Scambos et al., A MODIS-based mosaic of Antarctica: MOA, submitted to Remote Sensing of Environment, 2005, hereinafter referred to as Scambos et al., submitted manuscript, 2005), these lakes are aligned parallel to Lake Vostok. Other data shows that they are distinguished by distinct gravity lows, flat ice surface slopes and have estimated water depths of at least 900 m. Surface elevation data indicates that large deep subglacial lakes have a profound influence on the regional ice sheet topography and probably ice sheet flow. These deep subglacial lakes with elongate, rectilinear morphology are tectonically controlled features. Unlike the shallow lakes in West Antarctica and beneath Dome Concordia, these deep subglacial lakes remained stable environments through many glacial cycles since their origin 10 -35 Ma enabling the development of novel ecosystems. C1 Columbia Univ, Lamont Doherty Geol Observ, Palisades, NY 10964 USA. Univ New Hampshire, Inst Study Earth Oceans & Space, Durham, NH 03824 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Bell, RE (reprint author), Columbia Univ, Lamont Doherty Geol Observ, Palisades, NY 10964 USA. EM robinb@ldeo.columbia.edu RI Fahnestock, Mark/N-2678-2013 NR 28 TC 33 Z9 33 U1 3 U2 15 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0094-8276 J9 GEOPHYS RES LETT JI Geophys. Res. Lett. PD JAN 25 PY 2006 VL 33 IS 2 AR L02504 DI 10.1029/2005GL025027 PG 4 WC Geosciences, Multidisciplinary SC Geology GA 008FM UT WOS:000235025600008 ER PT J AU Cede, A Kazadzis, S Kowalewski, M Bais, A Kouremeti, N Blumthaler, M Herman, J AF Cede, A Kazadzis, S Kowalewski, M Bais, A Kouremeti, N Blumthaler, M Herman, J TI Correction of direct irradiance measurements of Brewer spectrophotometers due to the effect of internal polarization SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID AEROSOL OPTICAL DEPTH; SOLAR UV MEASUREMENTS; SPECTRAL MEASUREMENTS; OZONE MEASUREMENTS; RETRIEVAL; THICKNESS; SPECTRORADIOMETER; RANGE AB Due to the combined effect of two polarization sensitive elements, the entrance window and grating, the sensitivity of Brewer spectrophotometers for direct-sun measurements changes with solar zenith angle (SZA). We determined this SZA-polarization dependence with four independent methods, which agreed within +/- 1.5%. For SZA < 50 degrees this effect is negligible. At SZA = 60 degrees, 70 degrees, and 80 degrees the Brewer's sensitivity is reduced by 1%, 4%, and 10%, relative to SZA = 35 degrees, when the direct solar irradiance is perpendicular to the entrance window. Differential absorption algorithms for retrieving trace gases ( e. g., ozone) are unaffected since the polarization effect is almost wavelength independent. However, systematic errors are introduced in Langley extrapolations (2-4% overestimation of the zero air mass factor), retrievals of aerosol optical depth ( overestimation of 0.01-0.04), and aerosol single scattering albedo. Therefore, Brewer direct irradiance measurements should be corrected for the SZA-polarization dependence. The effect in sky-radiance measurements can be removed only by hardware modifications. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Sci Syst & Applicat Inc, Lanham, MD USA. Aristotle Univ Thessaloniki, Lab Atmospher Phys, GR-54006 Thessaloniki, Greece. Univ Innsbruck, Div Biomed Phys, A-6020 Innsbruck, Austria. RP Cede, A (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM cede@gsfc.nasa.gov RI Kazadzis, Stelios/A-5628-2011; Kazadzis, Stelios/F-8667-2011; Bais, Alkiviadis/D-2230-2009 OI Bais, Alkiviadis/0000-0003-3899-2001 NR 24 TC 10 Z9 10 U1 0 U2 1 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0094-8276 J9 GEOPHYS RES LETT JI Geophys. Res. Lett. PD JAN 25 PY 2006 VL 33 IS 2 AR L02806 DI 10.1029/2005GL024860 PG 4 WC Geosciences, Multidisciplinary SC Geology GA 008FM UT WOS:000235025600006 ER PT J AU Luthcke, SB Rowlands, DD Lemoine, FG Klosko, SM Chinn, D McCarthy, JJ AF Luthcke, SB Rowlands, DD Lemoine, FG Klosko, SM Chinn, D McCarthy, JJ TI Monthly spherical harmonic gravity field solutions determined from GRACE inter-satellite range-rate data alone SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID MISSION; SYSTEM AB New monthly estimates of the Earth's gravity field determined solely from GRACE inter-satellite range- rate measurements using an improved method of accelerometer calibration and the use of a baseline state parameterization are presented in this paper. Our methodology exploits the inherent power of the inter-satellite range-rate data at the expense of the GPS data, which are used solely for establishing an accurate orbital reference and for calibrating accelerometers. Resulting gravity solutions show significantly less error than previously published GRACE solutions, especially for spherical harmonic terms of degree 2 and terms of order 15,16. C1 NASA, Goddard Space Flight Ctr, Space Geodesy Lab, Greenbelt, MD 20771 USA. SGT Inc, Div Sci, Greenbelt, MD 20770 USA. RP Luthcke, SB (reprint author), NASA, Goddard Space Flight Ctr, Space Geodesy Lab, Code 697, Greenbelt, MD 20771 USA. EM scott.b.luthcke@nasa.gov RI Rowlands, David/D-2751-2012; Luthcke, Scott/D-6283-2012; Lemoine, Frank/D-1215-2013 NR 13 TC 66 Z9 66 U1 2 U2 4 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0094-8276 J9 GEOPHYS RES LETT JI Geophys. Res. Lett. PD JAN 25 PY 2006 VL 33 IS 2 AR L02402 DI 10.1029/2005GL024846 PG 4 WC Geosciences, Multidisciplinary SC Geology GA 008FM UT WOS:000235025600005 ER PT J AU Ovchinnikov, V Piomelli, U Choudhari, MM AF Ovchinnikov, V Piomelli, U Choudhari, MM TI Numerical simulations of boundary-layer transition induced by a cylinder wake SO JOURNAL OF FLUID MECHANICS LA English DT Article ID FREE-STREAM TURBULENCE; SUBGRID-SCALE MODEL; CIRCULAR-CYLINDER; FLOW; FIELD AB Direct and large-eddy simulations of the interaction between a laminar boundary layer and a von Karman vortex street behind a circular cylinder are carried out for three values of the Reynolds number based oil the cylinder diameter and free-stream velocity: Re-D = 385, 1155 and 3900. Rapid, bypass-like transition to turbulence is observed in the two higher-Reynolds-number cases. Flow statistics in the transitional and turbulent regions are examined, followed by all investigation of the underlying transition mechanism. Qualitative similarities between wake-induced transition and bypass transition due to free-stream turbulence are discussed and the challenges of predicting boundary-layer transition in this complex environment are pointed out. C1 Univ Maryland, Dept Mech Engn, College Pk, MD 20742 USA. NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Ovchinnikov, V (reprint author), Univ Maryland, Dept Mech Engn, College Pk, MD 20742 USA. RI Choudhari, Meelan/F-6080-2017 OI Choudhari, Meelan/0000-0001-9120-7362 NR 35 TC 22 Z9 25 U1 1 U2 4 PU CAMBRIDGE UNIV PRESS PI NEW YORK PA 40 WEST 20TH ST, NEW YORK, NY 10011-4211 USA SN 0022-1120 J9 J FLUID MECH JI J. Fluid Mech. PD JAN 25 PY 2006 VL 547 BP 413 EP 441 DI 10.1017/S0022112005007342 PG 29 WC Mechanics; Physics, Fluids & Plasmas SC Mechanics; Physics GA 007IC UT WOS:000234961200020 ER PT J AU Ferrare, R Turner, D Clayton, M Schmid, B Redemann, J Covert, D Elleman, R Ogren, J Andrews, E Goldsmith, JEM Jonsson, H AF Ferrare, R Turner, D Clayton, M Schmid, B Redemann, J Covert, D Elleman, R Ogren, J Andrews, E Goldsmith, JEM Jonsson, H TI Evaluation of daytime measurements of aerosols and water vapor made by an operational Raman lidar over the Southern Great Plains SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article ID INTENSIVE OBSERVATION PERIODS; LOWER TROPOSPHERIC AEROSOL; GROUND-BASED MEASUREMENTS; SINGLE-SCATTERING ALBEDO; TO-BACKSCATTER RATIO; MID-ATLANTIC COAST; AIRBORNE IN-SITU; ATMOSPHERIC RADIATION; EARLINET PROJECT; SUN PHOTOMETER AB [1] Raman lidar water vapor and aerosol extinction profiles acquired during the daytime over the Department of Energy ( DOE) Atmospheric Radiation Measurement ( ARM) Southern Great Plains (SGP) site in northern Oklahoma (36.606 N, 97.50 W, 315 m) are evaluated using profiles measured by in situ and remote sensing instruments deployed during the May 2003 Aerosol Intensive Operations Period (IOP). The automated algorithms used to derive these profiles from the Raman lidar data were first modified to reduce the adverse effects associated with a general loss of sensitivity of the Raman lidar since early 2002. The Raman lidar water vapor measurements, which are calibrated to match precipitable water vapor (PWV) derived from coincident microwave radiometer (MWR) measurements were, on average, 5 - 10% (0.3 - 0.6 g/m(3)) higher than the other measurements. Some of this difference is due to out-of-date line parameters that were subsequently updated in the MWR PWV retrievals. The Raman lidar aerosol extinction measurements were, on average, about 0.03 km(-1) higher than aerosol measurements derived from airborne Sun photometer measurements of aerosol optical thickness and in situ measurements of aerosol scattering and absorption. This bias, which was about 50% of the mean aerosol extinction measured during this IOP, decreased to about 10% when aerosol extinction comparisons were restricted to aerosol extinction values larger than 0.15 km(-1). The lidar measurements of the aerosol extinction/ backscatter ratio and airborne Sun photometer measurements of the aerosol optical thickness were used along with in situ measurements of the aerosol size distribution to retrieve estimates of the aerosol single scattering albedo (omega(o)) and the effective complex refractive index. Retrieved values of omega(o) ranged from (0.91 - 0.98) and were in generally good agreement with omega(o) derived from airborne in situ measurements of scattering and absorption. Elevated aerosol layers located between about 2.6 and 3.6 km were observed by the Raman lidar on 25 and 27 May. The airborne measurements and lidar retrievals indicated that these layers, which were likely smoke produced by Siberian forest fires, were primarily composed of relatively large particles (r(eff) similar to 0.23 mu m) and that the layers were relatively nonabsorbing (omega(o) similar to 0.96 - 0.98). Preliminary results show that major modifications that were made to the Raman lidar system during 2004 have dramatically improved the sensitivity in the aerosol and water vapor channels and reduced random errors in the aerosol scattering ratio and water vapor retrievals by an order of magnitude. C1 NASA, Langley Res Ctr, Sci Applicat Int Corp, Hampton, VA 23681 USA. Pacific NW Natl Lab, Richland, WA 99352 USA. NASA, Ames Res Ctr, Bay Area Environm Res Inst, Moffett Field, CA 94035 USA. Univ Washington, Dept Atmospher Sci, Seattle, WA 98195 USA. NOAA, Earth Syst Res Lab, Global Monitoring Div, Boulder, CO 80305 USA. Sandia Natl Labs, Livermore, CA 94551 USA. Naval Postgrad Sch, Ctr Interdisciplinary Remotely Piloted Aircraft S, Marina, CA 93933 USA. RP NASA, Langley Res Ctr, Sci Applicat Int Corp, MS 401A, Hampton, VA 23681 USA. EM richard.a.ferrare@nasa.gov; dave.turner@pnl.gov; m.b.clayton@larc.nasa.gov; bschmid@mail.arc.nasa.gov; jredemann@mail.arc.nasa.gov; dcovert@u.washington.edu; rob@atmos.washington.edu; john.a.ogren@noaa.gov; betsy.andrews@noaa.gov; jgold@sandia.gov; hjonsson@nps.navy.mil RI Ogren, John/M-8255-2015 OI Ogren, John/0000-0002-7895-9583 NR 77 TC 51 Z9 51 U1 1 U2 9 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-897X EI 2169-8996 J9 J GEOPHYS RES-ATMOS JI J. Geophys. Res.-Atmos. PD JAN 25 PY 2006 VL 111 IS D5 AR D05S08 DI 10.1029/2005JD005836 PG 21 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 008GB UT WOS:000235027100001 ER PT J AU Ilhan, F Tyson, DS Stasko, DJ Kirschbaum, K Meador, MA AF Ilhan, F Tyson, DS Stasko, DJ Kirschbaum, K Meador, MA TI Twisted, Z-shaped perylene bisimide SO JOURNAL OF THE AMERICAN CHEMICAL SOCIETY LA English DT Article ID ELECTRON-TRANSFER; ELECTROGENERATED CHEMILUMINESCENCE; THIN-FILMS; DYES; DERIVATIVES; FLUORESCENCE C1 NASA, Glenn Res Ctr, Polymers Branch, Mat & Struct Div, Cleveland, OH 44135 USA. Ohio Aerosp Inst, Cleveland, OH 44142 USA. Univ So Maine, Lewiston, ME 04240 USA. Univ Toledo, Dept Chem, Toledo, OH 44306 USA. RP Meador, MA (reprint author), NASA, Glenn Res Ctr, Polymers Branch, Mat & Struct Div, 21000 Brookpk Rd, Cleveland, OH 44135 USA. EM Michael.A.Meador@nasa.gov NR 30 TC 17 Z9 18 U1 1 U2 11 PU AMER CHEMICAL SOC PI WASHINGTON PA 1155 16TH ST, NW, WASHINGTON, DC 20036 USA SN 0002-7863 J9 J AM CHEM SOC JI J. Am. Chem. Soc. PD JAN 25 PY 2006 VL 128 IS 3 BP 702 EP 703 DI 10.1021/ja056912o PG 2 WC Chemistry, Multidisciplinary SC Chemistry GA 005IE UT WOS:000234815000017 PM 16417343 ER PT J AU Katti, A Shimpi, N Roy, S Lu, HB Fabrizio, EF Dass, A Capadona, LA Leventis, N AF Katti, A Shimpi, N Roy, S Lu, HB Fabrizio, EF Dass, A Capadona, LA Leventis, N TI Chemical, physical, and mechanical characterization of isocyanate cross-linked amine-modified silica aerogels SO CHEMISTRY OF MATERIALS LA English DT Article ID THERMAL-CONDUCTIVITY; COMPOSITE AEROGELS; HYBRID COMPOSITES; HEAT-CAPACITY; SOL AB We describe a new mechanically strong lightweight porous composite material obtained by encapsulating the skeletal framework of amine-modified silica aerogels with polyurea. The conformal polymer coating preserves the mesoporous structure of the underlying silica framework and the thermal conductivity remains low at 0.041 +/- 0.001 W m(-1) K-1. The potential of the new cross-linked silica aerogels for load-carrying applications was determined through characterization of their mechanical behavior under compression, three-point bending, and dynamic mechanical analysis (DMA). A primary glass transition temperature of 130 degrees C was identified through DMA. At room temperature, results indicate a hyperfoam behavior where in compression cross-linked aerogels are linearly elastic under small strains ( < 4%) and then exhibit yield behavior (until 40% strain), followed by densification and inelastic hardening. At room temperature the compressive Young's modulus and the Poisson's ratio were determined to be 129 +/- 8 MPa and 0. 18, respectively, while the strain at ultimate failure is 77% and the average specific compressive stress at ultimate failure is 3.89 x 10(5) N in kg(-1). The specific flexural strength is 2.16 x 10(4) N in kg(-1). Effects on the compressive behavior of strain rate and low temperature were also evaluated. C1 Oklahoma State Univ, Sch Mech & Aerosp Engn, Stillwater, OK 74078 USA. Ohio Aerosp Inst, Cleveland, OH 44142 USA. Univ Missouri, Dept Chem, Rolla, MO 65409 USA. NASA, Glenn Res Ctr, Div Mat, Polymers Branch, Cleveland, OH 44135 USA. RP Roy, S (reprint author), Oklahoma State Univ, Sch Mech & Aerosp Engn, Stillwater, OK 74078 USA. EM sroy@eng.ua.edu; hongbin@ceat.okstate.edu; Nicholas.Leventis@nasa.gov RI Lu, Hongbing/A-1312-2011; Dass, Amal/A-2520-2011; Dass, Amala/H-4729-2012 OI Dass, Amala/0000-0001-6942-5451 NR 31 TC 128 Z9 136 U1 9 U2 82 PU AMER CHEMICAL SOC PI WASHINGTON PA 1155 16TH ST, NW, WASHINGTON, DC 20036 USA SN 0897-4756 J9 CHEM MATER JI Chem. Mat. PD JAN 24 PY 2006 VL 18 IS 2 BP 285 EP 296 DI 10.1021/cm0513841 PG 12 WC Chemistry, Physical; Materials Science, Multidisciplinary SC Chemistry; Materials Science GA 007KO UT WOS:000234967900010 ER PT J AU Tselioudis, G Rossow, WB AF Tselioudis, G Rossow, WB TI Climate feedback implied by observed radiation and precipitation changes with midlatitude storm strength and frequency SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID SULFATE AEROSOLS; GREENHOUSE GASES; PROJECT; CLOUD AB [1] Current climate observations are used to quantify the relationships between midlatitude storm strength and frequency and radiation and precipitation properties. Then, the derived radiation/precipitation-storm relationships along with the midlatitude storm changes with climate-warming predicted by a climate model are used to determine the radiation and precipitation changes resulting from an increase in midlatitude storm intensity and a decrease in midlatitude storm frequency. Increases in midlatitude storm intensity produce shortwave cooling and longwave warming while decreases in storm frequency produce the opposite effects. When the two changes are added together the increase in storm strength dominates producing a shortwave cooling effect of 0 - 3.5 W/m(2) and a longwave warming effect of 0.1 - 2.2 W/m(2). For precipitation, the increase in storm intensity also dominates the decrease in storm frequency and produces an increase in precipitation of 0.05 - 0.08 mm/day. C1 Columbia Univ, Dept Appl Phys & Appl Math, New York, NY 10025 USA. Columbia Univ, NASA, Goddard Inst Space Studies, New York, NY 10025 USA. RP Tselioudis, G (reprint author), Columbia Univ, Dept Appl Phys & Appl Math, 2880 Broadway, New York, NY 10025 USA. EM gtselioudis@giss.nasa.gov RI Rossow, William/F-3138-2015 NR 11 TC 17 Z9 17 U1 0 U2 5 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0094-8276 J9 GEOPHYS RES LETT JI Geophys. Res. Lett. PD JAN 24 PY 2006 VL 33 IS 2 AR L02704 DI 10.1029/2005GL024513 PG 5 WC Geosciences, Multidisciplinary SC Geology GA 008FK UT WOS:000235025400002 ER PT J AU Gellert, R Rieder, R Bruckner, J Clark, BC Dreibus, G Klingelhofer, G Lugmair, G Ming, DW Wanke, H Yen, A Zipfel, J Squyres, SW AF Gellert, R Rieder, R Bruckner, J Clark, BC Dreibus, G Klingelhofer, G Lugmair, G Ming, DW Wanke, H Yen, A Zipfel, J Squyres, SW TI Alpha particle X-ray spectrometer (APXS): Results from Gusev crater and calibration report SO JOURNAL OF GEOPHYSICAL RESEARCH-PLANETS LA English DT Article ID CHEMICAL-COMPOSITION; SPIRIT ROVER; MARS; ROCKS; SOILS; CHEMISTRY; SITE AB [ 1] The chemical composition of rocks and soils on Mars analyzed during the Mars Exploration Rover Spirit Mission was determined by X-ray analyses with the Alpha Particle X-Ray Spectrometer (APXS). Details of the data analysis method and the instrument calibration are presented. Measurements performed on Mars to address geometry effects and background contributions are shown. Cross calibration measurements among several instrument sensors and sources are discussed. An unintentional swap of the two flight instruments is evaluated. New concentration data acquired during the first 470 sols of rover Spirit in Gusev Crater are presented. There are two geological regions, the Gusev plains and the Columbia Hills. The plains contain soils that are very similar to previous landing sites on Mars. A meteoritic component in the soil is identified. Rocks in the plains revealed thin weathering rinds. The underlying abraded rock was classified as primitive basalt. One of these rocks contained significant Br that is probably associated with vein-filling material of different composition. One of the trenches showed large subsurface enrichments of Mg, S, and Br. Disturbed soils and rocks in the Columbia Hills revealed different elemental compositions. These rocks are significantly weathered and enriched in mobile elements, such as P, S, Cl, or Br. Even abraded rock surfaces have high Br concentrations. Thus, in contrast to the rocks and soils in the Gusev Plains, the Columbia Hills material shows more significant evidence of ancient aqueous alteration. C1 Max Planck Inst Chem, D-55020 Mainz, Germany. Univ Guelph, Dept Phys, Guelph, ON N1G 2W1, Canada. Lockheed Martin Corp, Littleton, CO 80127 USA. Johannes Gutenberg Univ Mainz, Inst Inorgan & Analyt Chem, D-55099 Mainz, Germany. NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Cornell Univ, Ctr Radiophys & Space Res, Ithaca, NY 14853 USA. RP Max Planck Inst Chem, Postfach 3060, D-55020 Mainz, Germany. EM brueckner@mpch-mainz.mpg.de NR 31 TC 185 Z9 185 U1 2 U2 37 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-9097 EI 2169-9100 J9 J GEOPHYS RES-PLANET JI J. Geophys. Res.-Planets PD JAN 24 PY 2006 VL 111 IS E2 AR E02S05 DI 10.1029/2005JE002555 PG 32 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 008GJ UT WOS:000235027900001 ER PT J AU LeGrande, AN Schmidt, GA Shindell, DT Field, CV Miller, RL Koch, DM Faluvegi, G Hoffmann, G AF LeGrande, AN Schmidt, GA Shindell, DT Field, CV Miller, RL Koch, DM Faluvegi, G Hoffmann, G TI Consistent simulations of multiple proxy responses to an abrupt climate change event SO PROCEEDINGS OF THE NATIONAL ACADEMY OF SCIENCES OF THE UNITED STATES OF AMERICA LA English DT Article DE North Atlantic Deep Water; paleoclimate ID LAST GLACIAL PERIOD; OXYGEN-ISOTOPE RECORDS; BP COLD EVENT; OCEAN MODEL; NORTH-ATLANTIC; ICE CORE; HOLOCENE; GREENLAND; ATMOSPHERE; PRECIPITATION AB Isotope, aerosol, and methane records document an abrupt cooling event across the Northern Hemisphere at 8.2 kiloyears before present (kyr), while separate geologic lines of evidence document the catastrophic drainage of the glacial Lakes Agassiz and Ojibway into the Hudson Bay at approximately the same time. This melt water pulse may have been the catalyst for a decrease in North Atlantic Deep Water formation and subsequent cooling around the Northern Hemisphere. However, lack of direct evidence for ocean cooling has lead to speculation that this abrupt event was purely local to Greenland and called into question this proposed mechanism. We simulate the response to this melt water pulse using a coupled general circulation model that explicitly tracks water isotopes and with atmosphere-only experiments that calculate changes in atmospheric aerosol deposition (specifically Be-10 and dust) and wetland methane emissions. The simulations produce a short period of significantly diminished North Atlantic Deep Water and are able to quantitatively match paleoclimate observations, including the lack of isotopic signal in the North Atlantic. This direct comparison with multiple proxy records provides compelling evidence that changes in ocean circulation played a major role in this abrupt climate change event. C1 NASA, Goddard Inst Space Studies, New York, NY 10025 USA. Columbia Univ, Ctr Climate Syst Res, New York, NY 10025 USA. CEA, Lab Sci Climat & Environm, F-91191 Gif Sur Yvette, France. RP LeGrande, AN (reprint author), NASA, Goddard Inst Space Studies, New York, NY 10025 USA. EM legrande@giss.nasa.gov RI Shindell, Drew/D-4636-2012; Schmidt, Gavin/D-4427-2012; LeGrande, Allegra/D-8920-2012; Miller, Ron/E-1902-2012 OI Schmidt, Gavin/0000-0002-2258-0486; LeGrande, Allegra/0000-0002-5295-0062; NR 33 TC 116 Z9 119 U1 7 U2 34 PU NATL ACAD SCIENCES PI WASHINGTON PA 2101 CONSTITUTION AVE NW, WASHINGTON, DC 20418 USA SN 0027-8424 J9 P NATL ACAD SCI USA JI Proc. Natl. Acad. Sci. U. S. A. PD JAN 24 PY 2006 VL 103 IS 4 BP 837 EP 842 DI 10.1073/pnas.0510095103 PG 6 WC Multidisciplinary Sciences SC Science & Technology - Other Topics GA 007AC UT WOS:000234938300003 PM 16415159 ER PT J AU Jewell, AD Jones, TJ Sinha, MP Nikzad, S AF Jewell, AD Jones, TJ Sinha, MP Nikzad, S TI Simultaneous direct detection of sub keV molecular and atomic ions with a delta-doped charge-coupled device at the focal plane of a miniature mass spectrometer SO APPLIED PHYSICS LETTERS LA English DT Article ID ARRAY AB A delta-doped charge-coupled device (CCD) was used for the simultaneous and direct detection of low-energy atomic and molecular ions dispersed along the focal plane of a miniature mass spectrometer (MMS). The measured detection threshold for charged particles with a delta-doped CCD has been extended down to 700 eV, representing over an order of magnitude improvement compared to conventional solid-state detectors. We report the direct detection of 700 eV energy ions by the mass spectral measurements of species such as iron pentacarbonyl. The combination of delta-doped CCD and MMS enables high-speed, precision mass spectrometry of ions and molecules on a small scale suitable for field and space applications. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Nikzad, S (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM april.d.jewell@jpl.nasa.gov; shouleh.nikzad@jpl.nasa.gov NR 12 TC 5 Z9 5 U1 1 U2 3 PU AMER INST PHYSICS PI MELVILLE PA CIRCULATION & FULFILLMENT DIV, 2 HUNTINGTON QUADRANGLE, STE 1 N O 1, MELVILLE, NY 11747-4501 USA SN 0003-6951 J9 APPL PHYS LETT JI Appl. Phys. Lett. PD JAN 23 PY 2006 VL 88 IS 4 AR 043501 DI 10.1063/1.2166701 PG 3 WC Physics, Applied SC Physics GA 007KV UT WOS:000234968600095 ER PT J AU De Pasquale, M Beardmore, AP Barthelmy, SD Boyd, P Burrows, DN Fink, R Gehrels, N Kobayashi, S Mason, KO McNought, R Nousek, JA Page, KL Palmer, DM Peterson, BA Price, PA Rich, J Roming, P Rosen, SR Sakamoto, T Schmidt, BP Tueller, J Wells, AA Zane, S Zhang, B Ziaeepour, H AF De Pasquale, M Beardmore, AP Barthelmy, SD Boyd, P Burrows, DN Fink, R Gehrels, N Kobayashi, S Mason, KO McNought, R Nousek, JA Page, KL Palmer, DM Peterson, BA Price, PA Rich, J Roming, P Rosen, SR Sakamoto, T Schmidt, BP Tueller, J Wells, AA Zane, S Zhang, B Ziaeepour, H TI Swift and optical observations of GRB 050401 SO MONTHLY NOTICES OF THE ROYAL ASTRONOMICAL SOCIETY LA English DT Article DE ISM : dust, extinction; gamma-rays : bursts ID GAMMA-RAY BURSTS; TIME-DEPENDENT PHOTOIONIZATION; CONTINUOUS ENERGY INJECTION; INTERSTELLAR-MEDIUM; MOLECULAR CLOUD; LIGHT CURVES; DUSTY MEDIUM; AFTERGLOWS; EMISSION; DESTRUCTION AB We present the results of the analysis of gamma-ray and X-ray data of GRB 050401 taken with the Swift satellite, together with a series of ground-based follow-up optical observations. The Swift X-ray light curve shows a clear break at about 4900 s after the gamma-ray burst (GRB). The decay indices before and after the break are consistent with a scenario of continuous injection of radiation from the 'central engine' of the GRB to the fireball. Alternatively, this behaviour could result if ejecta are released with a range of Lorentz factors, with the slower shells catching up the faster at the afterglow shock position. The two scenarios are observationally indistinguishable. The GRB 050401 afterglow is quite bright in the X-ray band, but weak in the optical, with an optical to X-ray flux ratio similar to those of 'dark bursts'. We detect a significant amount of absorption in the X-ray spectrum, with N-H= (1.7 +/- 0.2) x 10(22) cm(-2) at a redshift of z= 2.9, which is typical of a dense circumburst medium. Such high column density implies an unrealistic optical extinction of 30 mag if we adopt a Galactic extinction law, which would not be consistent with the optical detection of the afterglow. This suggests that the extinction law is different from the Galactic one. C1 UCL, Mullard Space Sci Lab, Dorking RH5 6NT, Surrey, England. Univ Leicester, Leicester LE1 7RH, Leics, England. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Penn State Univ, Dept Astron & Astrophys, Davey Lab 525, University Pk, PA 16802 USA. Penn State Univ, Ctr Gravitat Wave Phys, University Pk, PA 16802 USA. Mt Stromlo & Siding Spring Observ, Res Sch Astron & Astrophys, Weston, ACT 2611, Australia. Univ Calif Los Alamos Natl Labs, Los Alamos, NM 87545 USA. Univ Hawaii, Inst Astron, Honolulu, HI 96822 USA. Univ Nevada, Dept Phys, Las Vegas, NV 89154 USA. RP UCL, Mullard Space Sci Lab, Holmbury St Mary, Dorking RH5 6NT, Surrey, England. EM mdp@mssl.ucl.ac.uk RI Boyd, Patricia/D-3274-2012; Gehrels, Neil/D-2971-2012; Tueller, Jack/D-5334-2012; Barthelmy, Scott/D-2943-2012; Lujan Center, LANL/G-4896-2012; OI Schmidt, Brian/0000-0001-6589-1287; Schmidt, Brian/0000-0002-8538-9195 NR 65 TC 41 Z9 41 U1 0 U2 2 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0035-8711 EI 1365-2966 J9 MON NOT R ASTRON SOC JI Mon. Not. Roy. Astron. Soc. PD JAN 21 PY 2006 VL 365 IS 3 BP 1031 EP 1038 DI 10.1111/j.1365-2966.2005.09787.x PG 8 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 005VV UT WOS:000234853600030 ER PT J AU Overzier, RA Miley, GK Bouwens, RJ Cross, NJG Zirm, AW Benitez, N Blakeslee, JP Clampin, M Demarco, R Ford, HC Hartig, GF Illingworth, GD Martel, AR Rottgering, HJA Venemans, B Ardila, DR Bartko, F Bradley, LD Broadhurst, TJ Coe, D Feldman, PD Franx, M Golimowski, DA Goto, T Gronwall, C Holden, B Homeier, N Infante, L Kimble, RA Krist, JE Mei, S Menanteau, F Meurer, GR Motta, V Postman, M Rosati, P Sirianni, M Sparks, WB Tran, HD Tsvetanov, ZI White, RL Zheng, W AF Overzier, RA Miley, GK Bouwens, RJ Cross, NJG Zirm, AW Benitez, N Blakeslee, JP Clampin, M Demarco, R Ford, HC Hartig, GF Illingworth, GD Martel, AR Rottgering, HJA Venemans, B Ardila, DR Bartko, F Bradley, LD Broadhurst, TJ Coe, D Feldman, PD Franx, M Golimowski, DA Goto, T Gronwall, C Holden, B Homeier, N Infante, L Kimble, RA Krist, JE Mei, S Menanteau, F Meurer, GR Motta, V Postman, M Rosati, P Sirianni, M Sparks, WB Tran, HD Tsvetanov, ZI White, RL Zheng, W TI Clustering of star-forming galaxies near a radio galaxy at z=5.2 SO ASTROPHYSICAL JOURNAL LA English DT Article DE cosmology : observations; early universe; galaxies : clusters : general; galaxies : high-redshift; galaxies : individual (TN J0924-2201); galaxies : starburst; large-scale structure of universe ID LYMAN-BREAK GALAXIES; HIGH-REDSHIFT GALAXIES; SUBARU DEEP SURVEY; LY-ALPHA EMITTERS; ULTRAVIOLET LUMINOSITY DENSITY; HUBBLE-SPACE-TELESCOPE; LARGE-SCALE STRUCTURE; ADVANCED CAMERA; ELLIPTIC GALAXIES; STELLAR POPULATIONS AB We present HSTACS observations of the most distant radio galaxy known, TNJ0924-2201 at z = 5.2. This radio galaxy has six spectroscopically confirmed Ly alpha-emitting companion galaxies and appears to lie within an overdense region. The radio galaxy is marginally resolved in i(775) and z(850), showing continuum emission aligned with the radio axis, similar to what is observed for lower redshift radio galaxies. Both the half-light radius and the UV star formation rate are comparable to the typical values found for Lyman break galaxies at z similar to 4-5. The Ly alpha emitters are sub-L-* galaxies, with deduced star formation rates of 1-10 M-circle dot yr(-1). One of the Ly alpha emitters is only detected in Ly alpha. Based on the star formation rate of similar to 3 M-circle dot yr(-1) calculated from Ly alpha, the lack of continuum emission could be explained if the galaxy is younger than similar to 2 Myr and is producing its first stars. Observations in V(606)i(775)z(850) were used to identify additional Lyman break galaxies associated with this structure. In addition to the radio galaxy, there are 22 V-606 break (z similar to 5) galaxies with z(850) < 26.5 (5 sigma), two of which are also in the spectroscopic sample. We compare the surface density of similar to 2 arcmin(-2) to that of similarly selected V-606 dropouts extracted from GOODS and the UDF parallel fields. We find evidence for an overdensity to very high confidence (> 99%), based on a counts-in-cells analysis applied to the control field. The excess suggests that the V-606 break objects are associated with a forming cluster around the radio galaxy. C1 Leiden Observ, NL-2300 RA Leiden, Netherlands. Univ Calif Santa Cruz, Univ Calif Observ, Lick Observ, Santa Cruz, CA 95064 USA. Royal Observ, Edinburgh EH9 3HJ, Midlothian, Scotland. CSIC, Ist Astrofis Andalucia, E-18008 Granada, Spain. Johns Hopkins Univ, Dept Phys & Astron, Baltimore, MD 21218 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Space Telescope Sci Inst, Baltimore, MD 21218 USA. Bartko Sci & Technol, Brighton, CO 80602 USA. Hebrew Univ Jerusalem, Racah Inst Phys, IL-91904 Jerusalem, Israel. Penn State Univ, Dept Astron & Astrophys, Davey Lab 525, University Pk, PA 16802 USA. Pontificia Univ Catolica Chile, Dept Astron & Astrofis, Santiago 22, Chile. Jet Prop Lab, Pasadena, CA 91109 USA. European So Observ, D-85748 Garching, Germany. WM Keck Observ, Kamuela, HI 96743 USA. RP Leiden Observ, Postbus 9513, NL-2300 RA Leiden, Netherlands. EM overzier@strw.leidenuniv.nl RI White, Richard/A-8143-2012; Clampin, mark/D-2738-2012; Kimble, Randy/D-5317-2012; OI Benitez, Narciso/0000-0002-0403-7455; Blakeslee, John/0000-0002-5213-3548 NR 91 TC 47 Z9 48 U1 0 U2 2 PU IOP PUBLISHING LTD PI BRISTOL PA TEMPLE CIRCUS, TEMPLE WAY, BRISTOL BS1 6BE, ENGLAND SN 0004-637X EI 1538-4357 J9 ASTROPHYS J JI Astrophys. J. PD JAN 20 PY 2006 VL 637 IS 1 BP 58 EP 73 DI 10.1086/498234 PN 1 PG 16 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 009RT UT WOS:000235130800007 ER PT J AU Cortese, L Boselli, A Buat, V Gavazzi, G Boissier, S de Paz, AG Seibert, M Madore, BF Martin, DC AF Cortese, L Boselli, A Buat, V Gavazzi, G Boissier, S de Paz, AG Seibert, M Madore, BF Martin, DC TI UV dust attenuation in normal star-forming galaxies. I. Estimating the L-TIR/L-FUV ratio SO ASTROPHYSICAL JOURNAL LA English DT Article DE dust, extinction; galaxies : spiral; galaxies : starburst; ultraviolet : galaxies ID ALPHA SURFACE PHOTOMETRY; ULTRAVIOLET LUMINOSITY DENSITY; VIRGO CLUSTER AREA; DIGITAL SKY SURVEY; STARBURST GALAXIES; H-ALPHA; DISK GALAXIES; SPIRAL GALAXIES; FORMATION HISTORY; NEARBY GALAXIES AB We analyze the dust attenuation properties of a volume-limited, optically selected sample of normal star-forming galaxies in nearby clusters as observed by GALEX. The internal attenuation is estimated using three independent indicators, namely, the ratio of the total infrared to far-ultraviolet emission, the ultraviolet spectral slope beta, and the Balmer decrement. We confirm that normal galaxies follow a L-TIR/L-FUV-beta relation offset from the one observed for starburst galaxies. This offset is found to weakly correlate with the birthrate parameter and thus with the galaxy star formation history. We study the correlations of dust attenuation with other global properties, such as the metallicity, dynamical mass, ionized gas attenuation, H alpha emission, and mass surface density. Metal-rich, massive galaxies are, as expected, more heavily extinguished in the UV than are small systems. For the same gas metallicity normal galaxies have lower L-TIR/L-FUV ratios than starbursts, in agreement with the difference observed in the L-TIR/L-FUV-beta relation. Unexpectedly, however, we find that normal star-forming galaxies follow exactly the same relationship between metallicity and ultraviolet spectral slope beta determined for starbursts, complicating our understanding of dust properties. This result might indicate a different dust geometry between normal galaxies and starbursts, but it could also be due to aperture effects eventually present in the IUE starbursts data set. The present multiwavelength study allows us to provide some empirical relations from which the total infrared to far-ultraviolet ratio (L-TIR/L-FUV) can be estimated when far-infrared data are absent. C1 Lab Astrophys Marseille, F-13376 Marseille, France. Univ Milan, I-20126 Milan, Italy. Observ Carnegie Inst Washington, Pasadena, CA 91101 USA. CALTECH, NASA, IPAC Extragalact Database, Pasadena, CA 91125 USA. RP Cortese, L (reprint author), Lab Astrophys Marseille, BP8,Traverse Siphon, F-13376 Marseille, France. RI Gil de Paz, Armando/J-2874-2016 OI Gil de Paz, Armando/0000-0001-6150-2854 NR 80 TC 94 Z9 94 U1 0 U2 3 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 20 PY 2006 VL 637 IS 1 BP 242 EP 254 DI 10.1086/498296 PN 1 PG 13 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 009RT UT WOS:000235130800021 ER PT J AU Cordes, JM Freire, PCC Lorimer, DR Camilo, F Champion, DJ Nice, DJ Ramachandran, R Hessels, JWT Vlemmings, W van Leeuwen, J Ransom, SM Bhat, NDR Arzoumanian, Z McLaughlin, MA Kaspi, VM Kasian, L Deneva, JS Reid, B Chatterjee, S Han, JL Backer, DC Stairs, IH Deshpande, AA Faucher-Giguere, CA AF Cordes, JM Freire, PCC Lorimer, DR Camilo, F Champion, DJ Nice, DJ Ramachandran, R Hessels, JWT Vlemmings, W van Leeuwen, J Ransom, SM Bhat, NDR Arzoumanian, Z McLaughlin, MA Kaspi, VM Kasian, L Deneva, JS Reid, B Chatterjee, S Han, JL Backer, DC Stairs, IH Deshpande, AA Faucher-Giguere, CA TI Arecibo pulsar survey using alfa. I. Survey strategy and first discoveries SO ASTROPHYSICAL JOURNAL LA English DT Article DE pulsars : general; pulsars : individual (PSR J0628+09,PSR J1906+07; PSR J1928+1746); surveys ID HIGH-FREQUENCY SURVEY; BLACK-HOLE BINARIES; GAMMA-RAY SOURCES; GALACTIC PLANE; YOUNG PULSARS; RADIO PULSARS; RADIATION; SEARCHES; CATALOG; SYSTEMS AB We report results from the initial stage of a long-term pulsar survey of the Galactic plane using the Arecibo L-band Feed Array (ALFA), a seven-beam receiver operating at 1.4 GHz with 0.3 GHz bandwidth, and fast-dump digital spectrometers. The search targets lowGalactic latitudes, vertical bar b vertical bar greater than or similar to 5 degrees, in the accessible longitude ranges 32 degrees greater than or similar to l greater than or similar to 77 degrees and 168 degrees less than or similar to l less than or similar to 214 degrees. The instrumentation, data processing, initial survey observations, sensitivity, and database management are described. Data discussed here were collected over a 100 MHz passband centered on 1.42 GHz using a spectrometer that recorded 256 channels every 64 mu s. Analysis of the data with their full time and frequency resolutions is ongoing. Here we report the results of a preliminary, low-resolution analysis for which the data were decimated to speed up the processing. We have detected 29 previously known pulsars and discovered 11 new ones. One of these, PSR J1928+ 1746, with a period of 69 ms and a relatively low characteristic age of 82 kyr, is a plausible candidate for association with the unidentified EGRETsource 3EG J1928+1733. Another, PSR J1906+07, is a nonrecycled pulsar in a relativistic binary with an orbital period of 3.98 hr. In parallel with the periodicity analysis, we also search the data for isolated dispersed pulses. This technique has resulted in the discovery of PSR J0628+09, an extremely sporadic radio emitter with a spin period of 1.2s. Simulations we have carried out indicate that similar to 1000 new pulsars will be found in our ALFA survey. In addition to providing a large sample for use in population analyses and for probing the magnetoionic interstellar medium, the survey maximizes the chances of finding rapidly spinning millisecond pulsars and pulsars in compact binary systems. Our search algorithms exploit the multiple data streams from ALFA to discriminate between radio frequency interference and celestial signals, including pulsars and possibly new classes of transient radio sources. C1 Cornell Univ, Dept Astron, Ithaca, NY 14853 USA. Cornell Univ, NAIC, Ithaca, NY 14853 USA. Arecibo Observ, Natl Astron & Ionosphere Ctr, Arecibo, PR 00612 USA. Univ Manchester, Jodrell Bank Observ, Macclesfield SK11 9DL, Cheshire, England. Columbia Univ, Astrophys Lab, New York, NY 10027 USA. Princeton Univ, Dept Phys, Princeton, NJ 08544 USA. Univ Calif Berkeley, Dept Astron, Berkeley, CA 94720 USA. McGill Univ, Dept Phys, Montreal, PQ H3A 2T8, Canada. Univ British Columbia, Dept Phys & Astron, Vancouver, BC V6T 1Z1, Canada. Natl Radio Astron Observ, Charlottesville, VA 22903 USA. MIT, Haystack Observ, Westford, MA 01886 USA. Univ Space Res Assoc, EUD, NASA, Code 662, Greenbelt, MD 20771 USA. Harvard Smithsonian Ctr Astrophys, Cambridge, MA 02138 USA. Chinese Acad Sci, Natl Astron Observ, Beijing 100012, Peoples R China. RP Cordes, JM (reprint author), Cornell Univ, Dept Astron, Ithaca, NY 14853 USA. RI Deshpande, Avinash/D-4868-2012; Astronomy & Astrophysics Group, Raman Res Institute/D-4046-2012; Bhat, Ramesh/B-7396-2013; OI Nice, David/0000-0002-6709-2566; Ransom, Scott/0000-0001-5799-9714; /0000-0002-2700-9916 NR 46 TC 98 Z9 101 U1 0 U2 4 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 20 PY 2006 VL 637 IS 1 BP 446 EP 455 DI 10.1086/498335 PN 1 PG 10 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 009RT UT WOS:000235130800039 ER PT J AU Gogus, E Patel, SK Wilson, CA Woods, PM Finger, MH Kouveliotou, C AF Gogus, E Patel, SK Wilson, CA Woods, PM Finger, MH Kouveliotou, C TI Chandra localization of XTE J1906+090 and discovery of its optical and infrared counterparts (vol 632, pg 1069, 2005) SO ASTROPHYSICAL JOURNAL LA English DT Correction C1 Sabanci Univ, Fac Engn & Nat Sci, Istanbul, Turkey. Univ Space Res Assoc, NSSTC, Huntsville, AL 35805 USA. Natl Space Sci & Technol Ctr, XD12, Huntsville, AL 35805 USA. NASA, Marshall Space Flight Ctr, Washington, DC 20546 USA. RP Gogus, E (reprint author), Sabanci Univ, Fac Engn & Nat Sci, Istanbul, Turkey. EM ersing@sabanciuniv.edu NR 1 TC 0 Z9 0 U1 0 U2 2 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 20 PY 2006 VL 637 IS 1 BP 553 EP 553 DI 10.1086/499098 PN 1 PG 1 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 009RT UT WOS:000235130800051 ER PT J AU Kalas, P Graham, JR Clampin, MC Fitzgerald, MP AF Kalas, P Graham, JR Clampin, MC Fitzgerald, MP TI First scattered light images of debris disks around HD 53143 and HD 139664 SO ASTROPHYSICAL JOURNAL LA English DT Article DE circumstellar matter; stars : individual (HD 53143, HD 139664) ID PICTORIS DUST DISK; MAIN-SEQUENCE STARS; BETA-PICTORIS; SOLAR-SYSTEM; KUIPER-BELT; CIRCUMSTELLAR DISK; STELLAR ENCOUNTERS; SPACE-TELESCOPE; AU-MICROSCOPII; GIANT PLANETS AB We present the first scattered light images of debris disks around a K star (HD 53143) and an F star ( HD 139664) using the coronagraphic mode of the Advanced Camera for Surveys (ACS) on board the Hubble Space Telescope (HST). With ages of 0.3-1 Gyr, these are among the oldest optically detected debris disks. HD 53143, viewed similar to 45 degrees from edge-on, does not show radial variation in disk structure and has a width > 55 AU. HD 139664 is seen close to edge-on and has a beltlike morphology with a dust peak 83 AU from the star and a distinct outer boundary at 109 AU. We discuss evidence for significant diversity in the radial architecture of debris disks that appears unconnected to stellar spectral type or age. HD 139664 and possibly the solar system belong in a category of narrow belts 20-30 AU wide. HD 53143 represents a class of wide-disk architecture with a characteristic width 150 AU. C1 Univ Calif Berkeley, Dept Astron, Berkeley, CA 94720 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Kalas, P (reprint author), Univ Calif Berkeley, Dept Astron, 601 Campbell Hall, Berkeley, CA 94720 USA. RI Clampin, mark/D-2738-2012; Fitzgerald, Michael/C-2642-2009 OI Fitzgerald, Michael/0000-0002-0176-8973 NR 34 TC 50 Z9 50 U1 0 U2 4 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 20 PY 2006 VL 637 IS 1 BP L57 EP L60 DI 10.1086/500305 PN 2 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 009RW UT WOS:000235131100015 ER PT J AU Lovas, FJ Remijan, AJ Hollis, JM Jewell, PR Snyder, LE AF Lovas, FJ Remijan, AJ Hollis, JM Jewell, PR Snyder, LE TI Hyperfine structure identification of interstellar cyanoallene toward TMC-1 SO ASTROPHYSICAL JOURNAL LA English DT Article DE ISM : abundances; ISM : clouds; ISM : individual (Taurus molecular cloud); ISM : molecules; radio lines : ISM ID MILLIMETER-WAVE SPECTRUM; MICROWAVE-SPECTRA; METHYLCYANOACETYLENE; ISOMERS; BEAM AB Interstellar cyanoallene (CH2 CCHCN) has been detected with the 100 m Green Bank Telescope (GBT) toward the dark Taurus molecular cloud (TMC-1) by means of the 4(14)-3(13), 4(04)-3(03), 5(15)-4(14), and 5(05)-4(04) rotational transitions at 20.2, 20.6, 25.2, and 25.7 GHz, respectively. The hyperfine structure (hfs) of the 4(14)-3(13) transition is resolved; the remaining transitions have hfs components that are blended but are inferred owing to line width excesses atypical of TMC-1. An analysis of these four rotational transitions yields an average column density N-T = 2.0(5) x 10(12) cm(-2) at an assumed rotational temperature of 4 K. The cyanoallene isomer methylcyanoacetylene (CH3CCCN) has previously been observed in TMC-1 and found to have a rotational temperature of similar to 4 K by other investigators. Using the GBT, the K = 0 and K = 1 structure of the J(K) = 5(K)-4(K) transition of methylcyanoacetylene was resolved toward TMC-1 and a total column density of N-T = 4.5(4) x 10(11) cm(-2) was obtained for the 4 K rotational temperature. Thus, cyanoallene appears to be more abundant than methylcyanoacetylene toward TMC-1 by a factor of similar to 4.5. The implications of this result are discussed in terms of relative bonding energy differences and possible differences in formation chemistry. C1 Natl Inst Stand & Technol, Opt Technol Div, Gaithersburg, MD 20899 USA. NASA, Goddard Space Flight Ctr, Computat & Informat Sci & Technol Off, Greenbelt, MD 20771 USA. Natl Radio Astron Observ, Charlottesville, VA 22903 USA. Univ Illinois, Dept Astron, Urbana, IL 61801 USA. RP Lovas, FJ (reprint author), Natl Inst Stand & Technol, Opt Technol Div, 100 Bur Dr, Gaithersburg, MD 20899 USA. NR 18 TC 28 Z9 28 U1 0 U2 7 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 20 PY 2006 VL 637 IS 1 BP L37 EP L40 DI 10.1086/500431 PN 2 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 009RW UT WOS:000235131100010 ER PT J AU Page, KL King, AR Levan, AJ O'Brien, PT Osborne, JP Barthelmy, SD Beardmore, AP Burrows, DN Campana, S Gehrels, N Graham, J Goad, MR Godet, O Kaneko, Y Kennea, JA Markwardt, CB Reichart, DE Sakamoto, T Tanvir, NR AF Page, KL King, AR Levan, AJ O'Brien, PT Osborne, JP Barthelmy, SD Beardmore, AP Burrows, DN Campana, S Gehrels, N Graham, J Goad, MR Godet, O Kaneko, Y Kennea, JA Markwardt, CB Reichart, DE Sakamoto, T Tanvir, NR TI GRB 050911: A black hole-neutron star merger or a naked GRB SO ASTROPHYSICAL JOURNAL LA English DT Article DE gamma rays : bursts ID GAMMA-RAY BURSTS; BATSE OBSERVATIONS; OPTICAL AFTERGLOW; SHORT-DURATION; GALAXY; CONSTRAINTS; GRB-040924; SPECTRA; ORIGIN AB GRB 050911, discovered by the Swift Burst Alert Telescope, was not seen 4.6 hr later by the Swift X-ray Telescope, making it one of the very few X-ray nondetections of a gamma-ray burst (GRB) afterglow at early times. The gamma-ray light curve shows at least three peaks, the first two of which (similar to T-0 - 0.8 and T-0 + 0.2 s, where T-0 is the trigger time) were short, each lasting 0.5 s. This was followed by later emission 10 - 20 s postburst. The upper limit on the unabsorbed X-ray flux was 1.7 x 10(-14) ergs cm(-2) s(-1)(integrating 46 ks of data taken between September 11 and 18), indicating that the decay must have been rapid. All but one of the long bursts detected by Swift were above this limit at similar to 4.6 hr, whereas the afterglows of short bursts became undetectable more rapidly. Deep observations with Gemini also revealed no optical afterglow 12 hr after the burst, down to r = p (5 sigma limit). We speculate that GRB 050911 may have been formed through a compact object (black hole-24.0 neutron star) merger, with the later outbursts due to a longer disk lifetime linked to a large mass ratio between the merging objects. Alternatively, the burst may have occurred in a low-density environment, leading to a weak, or nonexistent, forward shock-the so-called "naked GRB" model. C1 Univ Leicester, Dept Phys & Astron, Leicester LE1 7RH, Leics, England. Univ Hertfordshire, Ctr Astrophys Res, Hatfield AL10 9AB, Herts, England. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Penn State Univ, Dept Astron & Astrophys, Davey Lab 525, University Pk, PA 16802 USA. Osserv Astron Brera, INAF, I-23807 Merate, LC, Italy. Space Telescope Sci Inst, Baltimore, MD 21218 USA. Univ Alabama, Natl Space Sci & Technol Ctr, Huntsville, AL 35805 USA. Univ N Carolina, Dept Phys & Astron, Chapel Hill, NC 27599 USA. RP Page, KL (reprint author), Univ Leicester, Dept Phys & Astron, Univ Rd, Leicester LE1 7RH, Leics, England. EM kpa@star.le.ac.uk RI Gehrels, Neil/D-2971-2012; Barthelmy, Scott/D-2943-2012 NR 51 TC 29 Z9 29 U1 0 U2 2 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 20 PY 2006 VL 637 IS 1 BP L13 EP L16 DI 10.1086/500430 PN 2 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 009RW UT WOS:000235131100004 ER PT J AU Hintze, PE Calle, LM AF Hintze, PE Calle, LM TI Electrochemical properties and corrosion protection of organosilane self-assembled monolayers on aluminum 2024-T3 SO ELECTROCHIMICA ACTA LA English DT Article; Proceedings Paper CT 6th International Symposium on Electrochemical Impedance Spectroscopy CY MAY 16-21, 2004 CL Cocoa Beach, FL DE self-assembled monolayer; organosilane; aluminum alloy; corrosion ID ORGANIZED MOLECULAR ASSEMBLIES; NORMAL-ALKANOIC ACIDS; ALKANETHIOL MONOLAYERS; CHEMICAL MODIFICATION; SURFACES; FILMS; IRON; GOLD AB Aluminum 2024-T3 surfaces were modified by the deposition of organosilane self-assembled monolayers (SAMs) and studied by surface characterization and electrochemical measurements. The SAMs were hydrophobic and had infrared spectral trends consistent with a densely packed hydrocarbon SAM. Electrochemical testing indicated that anodic dissolution was suppressed on the SAM modified surfaces while cathodic reduction of oxygen was not. Polarization resistance and capacitance values front EIS measurements were used to evaluate the corrosion protection of the SAMs. On exposure to 0.5 M NaCl, the polarization resistance values of the SAM modified surfaces quickly converge to values similar to the bare surface even though the capacitance values indicate the continued presence of the SAM. There are a large number of defects on SAM modified 2024-T3 relative to SAMs on pure substrates. The defects probably occur over copper enriched particles found on the 2024-T3 surface. The copper enriched particles must be protected by a coating since localized corrosion originates on the particles. (c) 2005 Elsevier Ltd. All rights reserved. C1 NASA, Kennedy Space Ctr, Kennedy Space Ctr, FL 32899 USA. Natl Res Council Resident Res Assoc, Kennedy Space Ctr, FL 32899 USA. RP Calle, LM (reprint author), NASA, Kennedy Space Ctr, YA-C2-T, Kennedy Space Ctr, FL 32899 USA. EM Luz.M.Calle@nasa.gov OI Hintze, Paul/0000-0002-9962-2955 NR 24 TC 60 Z9 64 U1 1 U2 24 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0013-4686 J9 ELECTROCHIM ACTA JI Electrochim. Acta PD JAN 20 PY 2006 VL 51 IS 8-9 BP 1761 EP 1766 DI 10.1016/j.electacta.2005.02.147 PG 6 WC Electrochemistry SC Electrochemistry GA 013DV UT WOS:000235390700045 ER PT J AU Liou, JC Johnson, NL AF Liou, JC Johnson, NL TI Planetary science - Risks in space from orbiting debris SO SCIENCE LA English DT Editorial Material ID MODEL C1 NASA, Lyndon B Johnson Space Ctr, Engn Sci Contract Grp, ERC, Houston, TX 77058 USA. NASA, Lyndon B Johnson Space Ctr, Orbital Debris Program Off, Houston, TX 77058 USA. RP Liou, JC (reprint author), NASA, Lyndon B Johnson Space Ctr, Engn Sci Contract Grp, ERC, Mail Code JE104,2224 Bay Area Blvd,Box 7, Houston, TX 77058 USA. EM jer-chyi.liou1@jsc.nasa.gov NR 17 TC 82 Z9 85 U1 1 U2 18 PU AMER ASSOC ADVANCEMENT SCIENCE PI WASHINGTON PA 1200 NEW YORK AVE, NW, WASHINGTON, DC 20005 USA SN 0036-8075 J9 SCIENCE JI Science PD JAN 20 PY 2006 VL 311 IS 5759 BP 340 EP 341 DI 10.1126/science1121337 PG 2 WC Multidisciplinary Sciences SC Science & Technology - Other Topics GA 007AE UT WOS:000234938500029 PM 16424326 ER PT J AU Forget, F Haberle, RM Montmessin, F Levrard, B Heads, JW AF Forget, F Haberle, RM Montmessin, F Levrard, B Heads, JW TI Formation of glaciers on Mars by atmospheric precipitation at high obliquity SO SCIENCE LA English DT Article ID DEBRIS APRONS; ICE; CIRCULATION; LATITUDES; DEPOSITS; GULLIES; SURFACE; FLOWS; SNOW AB Surface conditions on Mars are currently cold and dry, with water ice unstable on the surface except near the poles. However, geologically recent glacierlike landforms have been identified in the tropics and the midlatitudes of Mars. The ice has been proposed to originate from either a subsurface reservoir or the atmosphere. We present high-resolution climate simulations performed with a model designed to simulate the present-day Mars water cycle but assuming a 45 degrees obliquity as experienced by Mars a few million years ago. The model predicts ice accumulation in regions where glacier landforms are observed, on the western flanks of the great volcanoes and in the eastern Hellas region. This agreement points to an atmospheric origin for the ice and reveals how precipitation could have formed glaciers on Mars. C1 Univ Paris 06, Inst Pierre Simon Laplace, Meteorol Dynam Lab, F-75252 Paris 05, France. NASA, Div Space Sci, Ames Res Ctr, Moffett Field, CA 94035 USA. Univ Paris 06, Inst Pierre Simon Laplace, Serv Aeron, F-75252 Paris 05, France. Inst Mecan Celeste, F-75014 Paris, France. Brown Univ, Dept Geol Sci, Providence, RI 02912 USA. RP Univ Paris 06, Inst Pierre Simon Laplace, Meteorol Dynam Lab, Boite Postale 99, F-75252 Paris 05, France. EM forget@lmd.jussieu.fr NR 26 TC 213 Z9 212 U1 6 U2 35 PU AMER ASSOC ADVANCEMENT SCIENCE PI WASHINGTON PA 1200 NEW YORK AVE, NW, WASHINGTON, DC 20005 USA SN 0036-8075 EI 1095-9203 J9 SCIENCE JI Science PD JAN 20 PY 2006 VL 311 IS 5759 BP 368 EP 371 DI 10.1126/science.1120335 PG 4 WC Multidisciplinary Sciences SC Science & Technology - Other Topics GA 007AE UT WOS:000234938500041 PM 16424337 ER PT J AU Li, HW Chin, AH Sunkara, MK AF Li, HW Chin, AH Sunkara, MK TI Direction-dependent homoepitaxial growth of GaN nanowires SO ADVANCED MATERIALS LA English DT Article ID GALLIUM NITRIDE; SURFACE-DIFFUSION; NANOSTRUCTURE; POWDERS; EPITAXY AB GaN nanowires with vastly different morphologies depending upon the growth direction are produced by direct nitridation and vapor transport of Gain disassociated ammonia. Nanowires grown homoepitaxially along the c-direction develop hexagonal-prism island morphologies (see Figure, left, and Cover), while wires grown along the a-direction form uniform, belt-shaped morphologies (Figure, right). A "ballistic" transport phenomenon for adatoms is proposed to explain the observed prismatic island morphologies. C1 NASA, Ames Res Ctr, ELORET, Moffett Field, CA 94035 USA. RP Sunkara, MK (reprint author), Univ Louisville, Dept Chem Engn, 106 Ernst Hall, Louisville, KY 40292 USA. EM mahendra@louisville.edu RI Sunkara, Mahendra/A-3033-2008 NR 24 TC 44 Z9 44 U1 1 U2 18 PU WILEY-BLACKWELL PI MALDEN PA COMMERCE PLACE, 350 MAIN ST, MALDEN 02148, MA USA SN 0935-9648 J9 ADV MATER JI Adv. Mater. PD JAN 19 PY 2006 VL 18 IS 2 BP 216 EP + DI 10.1002/adma.200501716 PG 6 WC Chemistry, Multidisciplinary; Chemistry, Physical; Nanoscience & Nanotechnology; Materials Science, Multidisciplinary; Physics, Applied; Physics, Condensed Matter SC Chemistry; Science & Technology - Other Topics; Materials Science; Physics GA 007TV UT WOS:000234993700015 ER PT J AU Andersen, SB Weatherhead, EC Stevermer, A Austin, J Bruhl, C Fleming, EL de Grandpre, J Grewe, V Isaksen, I Pitari, G Portmann, RW Rognerud, B Rosenfield, JE Smyshlyaev, S Nagashima, T Velders, GJM Weisenstein, DK Xia, J AF Andersen, SB Weatherhead, EC Stevermer, A Austin, J Bruhl, C Fleming, EL de Grandpre, J Grewe, V Isaksen, I Pitari, G Portmann, RW Rognerud, B Rosenfield, JE Smyshlyaev, S Nagashima, T Velders, GJM Weisenstein, DK Xia, J TI Comparison of recent modeled and observed trends in total column ozone SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article ID GENERAL-CIRCULATION MODEL; STRATOSPHERIC OZONE; ATMOSPHERIC CHEMISTRY; INTERACTIVE CHEMISTRY; 2-DIMENSIONAL MODEL; RECOVERY; CLIMATE; IMPACT; SIMULATION; TRANSPORT AB We present a comparison of trends in total column ozone from 10 two-dimensional and 4 three-dimensional models and solar backscatter ultraviolet-2 (SBUV/2) satellite observations from the period 1979-2003. Trends for the past (1979-2000), the recent 7 years (1996-2003), and the future (2000-2050) are compared. We have analyzed the data using both simple linear trends and linear trends derived with a hockey stick method including a turnaround point in 1996. If the last 7 years, 1996-2003, are analyzed in isolation, the SBUV/2 observations show no increase in ozone, and most of the models predict continued depletion, although at a lesser rate. In sharp contrast to this, the recent data show positive trends for the Northern and the Southern Hemispheres if the hockey stick method with a turnaround point in 1996 is employed for the models and observations. The analysis shows that the observed positive trends in both hemispheres in the recent 7-year period are much larger than what is predicted by the models. The trends derived with the hockey stick method are very dependent on the values just before the turnaround point. The analysis of the recent data therefore depends greatly on these years being representative of the overall trend. Most models underestimate the past trends at middle and high latitudes. This is particularly pronounced in the Northern Hemisphere. Quantitatively, there is much disagreement among the models concerning future trends. However, the models agree that future trends are expected to be positive and less than half the magnitude of the past downward trends. Examination of the model projections shows that there is virtually no correlation between the past and future trends from the individual models. C1 Danish Meteorol Inst, Dept Res & Dev, DK-2100 Copenhagen E, Denmark. Univ Colorado, Cooperat Inst Res Environm Sci, Boulder, CO 80309 USA. Princeton Univ, Geophys Fluid Dynam Lab, Univ Corp Atmospher Res, Princeton, NJ 08450 USA. Max Planck Inst Chem, D-55128 Mainz, Germany. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. McGill Univ, Dept Atmospher & Ocean Sci, Montreal, PQ H3A 2T5, Canada. Deutsch Zentrum Luft & Raumfahrt Oberpfaffenhofen, D-82234 Wessling, Germany. Univ Oslo, Dept Geosci, N-0315 Oslo, Norway. Univ Aquila, Dept Phys, I-67040 Laquila, Italy. NOAA, Aeron Lab, Boulder, CO 80305 USA. Russian State Hydrometeorol Univ, St Petersburg 195196, Russia. Natl Inst Environm Studies, Tsukuba, Ibaraki 3058506, Japan. Natl Inst Publ Hlth & Environm, NL-3720 BA Bilthoven, Netherlands. Atmospher & Environm Res Inc, Lexington, MA 02421 USA. Univ Illinois, Dept Atmospher Sci, Urbana, IL 61801 USA. RP Andersen, SB (reprint author), Danish Meteorol Inst, Dept Res & Dev, Lyngbyvej 100, DK-2100 Copenhagen E, Denmark. EM sba@dmi.dk RI Portmann, Robert/C-4903-2009; Grewe, Volker/A-6147-2011; andersen, signe/C-4809-2013; Weatherhead, Elizabeth/I-7091-2015; Pitari, Giovanni/O-7458-2016; Manager, CSD Publications/B-2789-2015; OI Portmann, Robert/0000-0002-0279-6087; Grewe, Volker/0000-0002-8012-6783; andersen, signe/0000-0002-8216-0141; Weatherhead, Elizabeth/0000-0002-9252-4228; Pitari, Giovanni/0000-0001-7051-9578; Rognerud, Bjorg/0000-0001-5958-4547 NR 37 TC 19 Z9 20 U1 0 U2 9 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-897X J9 J GEOPHYS RES-ATMOS JI J. Geophys. Res.-Atmos. PD JAN 19 PY 2006 VL 111 IS D2 AR D02303 DI 10.1029/2005JD006091 PG 10 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 007VO UT WOS:000234999200004 ER PT J AU Ghan, SJ Rissman, TA Elleman, R Ferrare, RA Turner, D Flynn, C Wang, J Ogren, J Hudson, J Jonsson, HH VanReken, T Flagan, RC Seinfeld, JH AF Ghan, SJ Rissman, TA Elleman, R Ferrare, RA Turner, D Flynn, C Wang, J Ogren, J Hudson, J Jonsson, HH VanReken, T Flagan, RC Seinfeld, JH TI Use of in situ cloud condensation nuclei, extinction, and aerosol size distribution measurements to test a method for retrieving cloud condensation nuclei profiles from surface measurements SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article ID SOUTHERN GREAT-PLAINS; PARTICLE CRITICAL SUPERSATURATION; HYGROSCOPIC GROWTH MEASUREMENTS; RAMAN LIDAR MEASUREMENTS; TO-BACKSCATTER RATIO; HUMIDIFIED TDMA; WATER-VAPOR; CLOSURE; PARAMETERIZATIONS; THERMODYNAMICS AB If the aerosol composition and size distribution below cloud are uniform, the vertical profile of cloud condensation nuclei concentration can be retrieved entirely from surface measurements of CCN concentration and particle humidification function and surface-based retrievals of relative humidity and aerosol extinction or backscatter. This provides the potential for long-term measurements of CCN concentrations near cloud base. We have used a combination of aircraft, surface in situ, and surface remote sensing measurements to test various aspects of the retrieval scheme. Our analysis leads us to the following conclusions. The retrieval works better for supersaturations of 0.1% than for 1% because CCN concentrations at 0.1% are controlled by the same particles that control extinction and backscatter. If in situ measurements of extinction are used, the retrieval explains a majority of the CCN variance at high supersaturation for at least two and perhaps five of the eight flights examined. The retrieval of the vertical profile of the humidification factor is not the major limitation of the CCN retrieval scheme. Vertical structure in the aerosol size distribution and composition is the dominant source of error in the CCN retrieval, but this vertical structure is difficult to measure from remote sensing at visible wavelengths. C1 Pacific NW Natl Lab, Richland, WA 99352 USA. CALTECH, Pasadena, CA 91125 USA. Univ Washington, Dept Atmospher Sci, Seattle, WA 98195 USA. NASA, Langley Res Ctr, Hampton, VA 23681 USA. Brookhaven Natl Lab, Upton, NY 11973 USA. NOAA, Climate Monitoring & Diagnost Lab, Boulder, CO 80303 USA. Desert Res Inst, Reno, NV 89512 USA. USN, Postgrad Sch, Monterey, CA 93943 USA. RP Ghan, SJ (reprint author), Pacific NW Natl Lab, Richland, WA 99352 USA. EM steve.ghan@arm.gov RI Wang, Jian/G-9344-2011; Ghan, Steven/H-4301-2011 OI Ghan, Steven/0000-0001-8355-8699 NR 42 TC 14 Z9 14 U1 3 U2 12 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-897X EI 2169-8996 J9 J GEOPHYS RES-ATMOS JI J. Geophys. Res.-Atmos. PD JAN 19 PY 2006 VL 111 IS D5 AR D05S10 DI 10.1029/2004JD005752 PG 15 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 007VQ UT WOS:000234999400001 ER PT J AU Gu, GJ Adler, RF AF Gu, GJ Adler, RF TI Interannual rainfall variability in the tropical Atlantic region SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article ID SEA-SURFACE TEMPERATURE; INTERTROPICAL CONVERGENCE ZONE; SAHARAN WEATHER ANOMALIES; NINO-SOUTHERN-OSCILLATION; EQUATORIAL ATLANTIC; ENSO TELECONNECTION; CLIMATE VARIABILITY; ANNUAL CYCLE; ATMOSPHERIC CIRCULATION; MONTHLY PRECIPITATION AB Rainfall variability on seasonal and interannual-to-interdecadal timescales in the tropical Atlantic is quantified using a 25-year (1979-2003) monthly rainfall data set from the Global Precipitation Climatology Project. The Intertropical Convergence Zone (ITCZ), measured by monthly rainfall between 15 degrees and 37.5 degrees W, attains its peak as it moves to the northernmost latitude (similar to 8 degrees-10 degrees N) during July-September, during which the most total rainfall is observed in the tropical Atlantic basin (17.5 degrees S to 22.5 degrees N, 15 degrees-37.5 degrees W); the ITCZ becomes weakest during January-February, with the least total rainfall observed as it moves to the south. In contrast, rainfall variability on interannual-to-interdecadal timescales shows a quite different seasonal preference. The most intense interannual variability occurs during March-May, when the ITCZ tends to be near the equator and becomes weaker. The relationships between rainfall anomalies in the tropical Atlantic and three distinct sea surface temperature (SST) modes are further explored on interannual-to-interdecadal timescales. The ITCZ strength and total rainfall amount in the tropical Atlantic basin are significantly modulated by the Pacific El Nino and the Atlantic equatorial mode (or Atlantic Nino) particularly during boreal spring and summer, whereas the impact of the Atlantic interhemispheric mode is considerably weaker. Regarding the anomalous latitudes of the ITCZ, the influence could come from both local, i.e., the Atlantic interhemispheric and equatorial modes, and remote forcings, i.e., El Nino; however, a direct impact of El Nino on the latitudes of the ITCZ can only be found during April-July, not in winter and early spring, during which the largest SST anomalies are usually observed in the equatorial Pacific. C1 NASA, Atmospheres Lab, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Univ Maryland Baltimore Cty, Goddard Earth Sci & Technol Ctr, Baltimore, MD 21228 USA. RP Gu, GJ (reprint author), NASA, Atmospheres Lab, Goddard Space Flight Ctr, Code 613-1, Greenbelt, MD 20771 USA. EM ggu@agnes.gsfc.nasa.gov; adler@agnes.gsfc.nasa.gov NR 45 TC 11 Z9 12 U1 1 U2 2 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-897X J9 J GEOPHYS RES-ATMOS JI J. Geophys. Res.-Atmos. PD JAN 19 PY 2006 VL 111 IS D2 AR D02106 DI 10.1029/2005JD005944 PG 12 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 007VO UT WOS:000234999200003 ER PT J AU Reid, JS Brooks, B Crahan, KK Hegg, DA Eck, TF O'Neill, N de Leeuw, G Reid, EA Anderson, KD AF Reid, JS Brooks, B Crahan, KK Hegg, DA Eck, TF O'Neill, N de Leeuw, G Reid, EA Anderson, KD TI Reconciliation of coarse mode sea-salt aerosol particle size measurements and parameterizations at a subtropical ocean receptor site SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article ID SCATTERING SPECTROMETER PROBE; COLUMN RADIATIVE CLOSURE; MARINE BOUNDARY-LAYER; OPTICAL-PROPERTIES; CHEMICAL-COMPOSITION; MEASURING SYSTEMS; ORGANIC AEROSOLS; LIGHT-SCATTERING; BREAKING WAVES; WATER-CONTENT AB In August/September of 2001, the R/P FLIP and CIRPAS Twin Otter research aircraft were deployed to the eastern coast of Oahu, Hawaii, as part of the Rough Evaporation Duct (RED) experiment. Goals included the study of the air/sea exchange, turbulence, and sea-salt aerosol particle characteristics at the subtropical marine Pacific site. Here we examine coarse mode particle size distributions. Similar to what has been shown for airborne dust, optical particle counters such as the Forward Scattering Spectrometer Probe (FSSP), Classical Scattering Aerosol Spectrometer Probe (CSASP) and the Cloud Aerosol Spectrometer (CAS) within the Cloud Aerosol and Precipitation Spectrometer (CAPS) instrument systematically overestimate particle size, and consequently volume, for sea salt particles. Ground-based aerodynamic particle sizers (APS) and AERONET inversions yield much more reasonable results. A wing pod mounted APS gave mixed results and may not be appropriate for marine boundary layer studies. Relating our findings to previous studies does much to explain the bulk of the differences in the literature and leads us to conclude that the largest uncertainty facing flux and airborne cloud/aerosol interaction studies is likely due to the instrumentation itself. To our knowledge, there does not exist an in situ aircraft system that adequately measures the ambient volume distribution of coarse mode sea salt particles. Most empirically based sea salt flux parameterizations can trace their heritage to a clearly biased measurement technique. The current "state of the art'' in this field prevents any true form of clear sky radiative "closure'' for clean marine environments. C1 USN, Res Lab, Marine Meteorol Div, Monterey, CA 93943 USA. Univ Leeds, Sch Earth & Environm, Leeds LS2 9JT, W Yorkshire, England. Univ Washington, Dept Atmospher Sci, Seattle, WA 98195 USA. Univ Maryland Baltimore Cty, Goddard Earth Sci & Technol Ctr, Baltimore, MD 21228 USA. Univ Sherbrooke, Ctr Applicat & Rech Teledetect, Sherbrooke, PQ J1K 2R1, Canada. Netherlands Org Appl Sci Res, The Hague, Netherlands. Space & Naval Warfare Syst Ctr, San Diego, CA USA. RP Reid, JS (reprint author), USN, Res Lab, Marine Meteorol Div, 7 Grace Hopper St,Stop 2, Monterey, CA 93943 USA. EM jeffrey.reid@nrlmry.navy.mil RI ECK, THOMAS/D-7407-2012; Reid, Jeffrey/B-7633-2014 OI Reid, Jeffrey/0000-0002-5147-7955 NR 76 TC 11 Z9 11 U1 0 U2 10 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-897X J9 J GEOPHYS RES-ATMOS JI J. Geophys. Res.-Atmos. PD JAN 19 PY 2006 VL 111 IS D2 AR D02202 DI 10.1029/2005JD006200 PG 26 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 007VO UT WOS:000234999200006 ER PT J AU Salawitch, RJ AF Salawitch, RJ TI Atmospheric chemistry - Biogenic bromine SO NATURE LA English DT Editorial Material ID BRO MEASUREMENTS; TROPOSPHERE C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Salawitch, RJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM ross.salawitch@jpl.nasa.gov RI Salawitch, Ross/B-4605-2009 OI Salawitch, Ross/0000-0001-8597-5832 NR 13 TC 58 Z9 58 U1 4 U2 19 PU NATURE PUBLISHING GROUP PI LONDON PA MACMILLAN BUILDING, 4 CRINAN ST, LONDON N1 9XW, ENGLAND SN 0028-0836 EI 1476-4687 J9 NATURE JI Nature PD JAN 19 PY 2006 VL 439 IS 7074 BP 275 EP 277 DI 10.1038/439275a PG 3 WC Multidisciplinary Sciences SC Science & Technology - Other Topics GA 003LA UT WOS:000234682100027 PM 16421554 ER PT J AU Yamato, K Abe, K Fuke, H Haino, S Makida, Y Matsuda, S Matsumoto, H Mitchell, JW Moiseev, AA Nishimura, J Nozaki, M Orito, S Ormes, JF Sanuki, T Sasaki, M Seo, ES Shikaze, Y Streitmatter, RE Suzuki, J Tanaka, K Yamagami, T Yamamoto, A Yoshida, T Yoshimura, K AF Yamato, K Abe, K Fuke, H Haino, S Makida, Y Matsuda, S Matsumoto, H Mitchell, JW Moiseev, AA Nishimura, J Nozaki, M Orito, S Ormes, JF Sanuki, T Sasaki, M Seo, ES Shikaze, Y Streitmatter, RE Suzuki, J Tanaka, K Yamagami, T Yamamoto, A Yoshida, T Yoshimura, K TI Measurements of atmospheric antiprotons SO PHYSICS LETTERS B LA English DT Article DE atmospheric cosmic rays; cosmic-ray antiprotons; superconducting spectrometers ID COSMIC-RAY PROTON; BESS SPECTROMETER; SPECTRUM; HELIUM; DEPTHS AB We measured atmospheric antiproton spectra in the energy range 0.2 to 3.4 GeV, at sea level and at balloon altitude in the atmospheric depth range 4.5 to 26 g/cm(2). The observed energy spectra, including our previous measurements at mountain altitude, were compared with estimated spectra calculated on various assumptions regarding the energy distribution of antiprotons that interacted with air nuclei. (c) 2005 Elsevier B.V. All rights reserved. C1 Univ Tokyo, Tokyo 1130033, Japan. Kobe Univ, Kobe, Hyogo 6578501, Japan. Japan Aerosp Explorat Agcy, ISAS, Sagamihara, Kanagawa 2298510, Japan. High Energy Accelerator Res Org KEK, Tsukuba, Ibaraki 3050801, Japan. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Univ Maryland, College Pk, MD 20742 USA. RP Sanuki, T (reprint author), Univ Tokyo, Tokyo 1130033, Japan. EM sanuki@icepp.s.u-tokyo.ac.jp OI Seo, Eun-Suk/0000-0001-8682-805X NR 23 TC 6 Z9 6 U1 0 U2 3 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 0370-2693 J9 PHYS LETT B JI Phys. Lett. B PD JAN 19 PY 2006 VL 632 IS 4 BP 475 EP 479 DI 10.1016/j.physletb.2005.11.042 PG 5 WC Astronomy & Astrophysics; Physics, Nuclear; Physics, Particles & Fields SC Astronomy & Astrophysics; Physics GA 004BP UT WOS:000234727300006 ER PT J AU Liang, MC Irion, FW Weibel, JD Miller, CE Blake, GA Yung, YL AF Liang, MC Irion, FW Weibel, JD Miller, CE Blake, GA Yung, YL TI Isotopic composition of stratospheric ozone SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article ID CROSS-SECTION MEASUREMENTS; CARBON-DIOXIDE; TEMPERATURE-DEPENDENCE; HEAVY OZONE; WAVELENGTH REGION; RATE COEFFICIENTS; INTRAMOLECULAR THEORY; TROPOSPHERIC OZONE; MIDDLE ATMOSPHERE; HIGH-RESOLUTION AB We present a kinetic calculation for the isotopic composition of stratospheric ozone. The calculated enrichments of O-49(3) and O-50(3) are in agreement with atmospheric measurements made at midlatitudes. Integrating the kinetic fractionation processes in the formation and photolysis of ozone, we obtain enrichments of similar to 7.5-10.5 and similar to 7.5-12.5% (referenced to atmospheric O-2) for delta O-49(3) and delta O-50(3), respectively, at altitudes between 20 and 35 km; the photolysis in the Hartley band of ozone is responsible for the observed altitude variation. The overall magnitude of the ozone enrichments (similar to 10%) is large compared with that commonly known in atmospheric chemistry and geochemistry. The heavy oxygen atom in ozone is therefore useful as a tracer of chemical species and pathways that involve ozone or its derived products. For example, the mass anomalies of oxygen in two greenhouse gases, CO2 and N2O, are likely the consequences of the transfer of heavy oxygen atoms from ozone. C1 CALTECH, Div Geol & Planetary Sci, Pasadena, CA 91125 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Liang, MC (reprint author), CALTECH, Div Geol & Planetary Sci, MS150-21,1200 E Calif Blvd, Pasadena, CA 91125 USA. EM mcl@gps.caltech.edu; bill.irion@jpl.nasa.gov; weibel@gps.caltech.edu; charles.e.miller@jpl.nasa.gov; gab@gps.caltech.edu NR 56 TC 30 Z9 30 U1 1 U2 8 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-897X J9 J GEOPHYS RES-ATMOS JI J. Geophys. Res.-Atmos. PD JAN 18 PY 2006 VL 111 IS D2 AR D02302 DI 10.1029/2005JD006342 PG 11 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 007VM UT WOS:000234999000004 ER PT J AU McGuinness, LM Salganik, M Vega, L Pickering, KD Kerkhof, LJ AF McGuinness, LM Salganik, M Vega, L Pickering, KD Kerkhof, LJ TI Replicability of bacterial communities in denitrifying bioreactors as measured by PCR/T-RFLP analysis SO ENVIRONMENTAL SCIENCE & TECHNOLOGY LA English DT Article ID LENGTH-POLYMORPHISM ANALYSIS; WATER TREATMENT REACTORS; RIBOSOMAL-RNA; MICROBIAL COMMUNITY; WASTE-WATER; MARINE-SEDIMENTS; DIVERSITY; DYNAMICS; GENES; BIOFILM AB Bioreactors hold great promise for treating graywater in an advanced life support system for space applications. However, questions remain regarding the reproducibility and reliability of biological systems for long-term use. Although there have been numerous studies on ground-based biological systems, most studies focus on a single reactor or a simple (single carbon) waste stream. There have been very few studies on microbial communities in replicate reactors using a nonsterile, complex waste stream. In this report, we describe the characterization of five replicate denitrifying reactors receiving a complex feed, including urine and limb washes from donors at Johnson Space Center over a 100-day period. Denitrifying conditions were employed because of the ease in adding a terminal electron acceptor to the bioreactor. Bacterial populations were tracked by 16S rRNA and nosZ genes T-RFLP analysis to target the total and denitrifying microbial communities. The results demonstrated reproducible biological communities with nearly identical performance that slowly changed with time and exhibited low variability with respect to the bacterial community (T-RFLP peak area) in all reactors. These results suggest that, when designed for replication, bioreactors are not stochastic systems exhibiting chaotic behavior, but are biological systems that can be highly reproducible and reliable. C1 Rutgers State Univ, Inst Marine & Coastal Sci, Cook Coll, New Brunswick, NJ 08901 USA. NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Kerkhof, LJ (reprint author), Rutgers State Univ, Inst Marine & Coastal Sci, Cook Coll, Cook Campus,71 Dudley Rd, New Brunswick, NJ 08901 USA. EM kerkhof@marine.rutgers.edu NR 25 TC 41 Z9 43 U1 2 U2 26 PU AMER CHEMICAL SOC PI WASHINGTON PA 1155 16TH ST, NW, WASHINGTON, DC 20036 USA SN 0013-936X J9 ENVIRON SCI TECHNOL JI Environ. Sci. Technol. PD JAN 15 PY 2006 VL 40 IS 2 BP 509 EP 515 DI 10.1021/es0509001 PG 7 WC Engineering, Environmental; Environmental Sciences SC Engineering; Environmental Sciences & Ecology GA 006SG UT WOS:000234916700018 PM 16468396 ER PT J AU McCoy, TJ Carlson, WD Nittler, LR Stroud, RM Bogard, DD Garrison, DH AF McCoy, TJ Carlson, WD Nittler, LR Stroud, RM Bogard, DD Garrison, DH TI Graves Nunataks 95209: A snapshot of metal segregation and core formation SO GEOCHIMICA ET COSMOCHIMICA ACTA LA English DT Article ID INTERPLANETARY DUST PARTICLES; TRANSMISSION ELECTRON-MICROSCOPE; GRANULITE-FACIES GRAPHITE; ORDINARY CHONDRITES; ACAPULCO METEORITE; PARENT BODY; ISOTOPIC COMPOSITION; NITROGEN ISOTOPE; THERMAL HISTORY; OXYGEN-ISOTOPE AB GRA 95209 may provide our best opportunity to date to understand the earliest stages of core formation in asteroidal bodies. This lodranite preserves a physically, chemically, and mineralogically complex set of metal-sulfide veins. High-resolution X-ray computed tomography revealed three distinct lithologies. The dominant mixed metal-silicate-sulfide matrix is cut by metal-rich, graphite-bearing veins exceeding I cm in width and grades into a volumetrically minor metal-poor region. Silicate compositions and modal abundances are typical for lodranites, while the mineralogy of the metal-sulfide component is complex and differs among the three lithologies. Kamacite and troilite occur with chromite, tetrataenite, schreibersite, graphite, and a range of phosphates. An Ar-39-Ar-40 age of 4.521 +/- 0.006 Ga measures the time of closure of the K-Ar system. Carbon rosettes within the metal-rich vein are nitrogen-poor, well crystallized, include kamacite sub-grains of composition comparable to the host metal, and are essentially isotopically homogeneous (delta(13)C similar to -33 parts per thousand). In contrast, carbon rosettes within metal of the metal-poor lithology are N-poor, poorly crystallized, include kamacite grains that are Ni-poor compared to their host metal, and are isotopically heterogeneous (delta(13)C ranging from -50 to +80 parts per thousand) even within a single metal grain. The silicate portion of GRA 95209 is similar to the lodranite EET 84302, sharing a common texture, silicate mineral compositions, and Ar-Ar age. GRA 95209 and EET 84302 are intermediate between acapulcoites and lodranites. Both experienced Fe,Ni-FeS melting with extensive melt migration, but record only the onset of silicate partial melting with limited migration of silicate melt. The complex metal-sulfide veins in GRA 95209 resulted from low-degree partial melting and melt migration and intruded the matrix lithology. Reactions between solid minerals and melt, including oxidation-reduction reactions, produced the array of phosphates, schreibersite, and tetrataenite. Extensive reduction in the metal-rich vein resulted from its origin in a hotter portion of the asteroid. This difference in thermal history is supported by the graphite structures and isotopic compositions. The graphite rosettes in the metal-rich vein are consistent with high-temperature igneous processing. In contrast, the carbon in the metal-poor lithology appears to preserve a record of formation in the nebula prior to parent-body formation. Carbon incorporated from the solar nebula into a differentiating asteroid is preferentially incorporated in metal-sulfide melts that form a core, but does not achieve isotopic homogeneity until extensive thermal processing occurs. (c) 2005 Elsevier Inc. All rights reserved. C1 Smithsonian Inst, Natl Museum Nat Hist, Dept Mineral Sci, Washington, DC 20560 USA. Univ Texas, Dept Geol Sci, Austin, TX 78712 USA. Carnegie Inst Washington, Dept Terr Magnetism, Washington, DC 20015 USA. USN, Res Lab, Washington, DC 20375 USA. NASA, Lyndon B Johnson Space Ctr, AREA, Code KA, Houston, TX 77058 USA. RP McCoy, TJ (reprint author), Smithsonian Inst, Natl Museum Nat Hist, Dept Mineral Sci, Washington, DC 20560 USA. EM mccoy.tim@nmnh.si.edu RI Carlson, William/A-5807-2008; Stroud, Rhonda/C-5503-2008 OI Carlson, William/0000-0002-2954-5886; Stroud, Rhonda/0000-0001-5242-8015 NR 56 TC 26 Z9 26 U1 0 U2 4 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0016-7037 J9 GEOCHIM COSMOCHIM AC JI Geochim. Cosmochim. Acta PD JAN 15 PY 2006 VL 70 IS 2 BP 516 EP 531 DI 10.1016/j.gca.2005.09.019 PG 16 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 009PI UT WOS:000235124000016 ER PT J AU Maslov, AV Bakunov, MI Ning, CZ AF Maslov, AV Bakunov, MI Ning, CZ TI Distribution of optical emission between guided modes and free space in a semiconductor nanowire SO JOURNAL OF APPLIED PHYSICS LA English DT Article ID DIELECTRIC ROD; WAVE-GUIDES; LASER; GAIN AB We study the distribution of the emitted power between the free-space modes and guided modes in a semiconductor nanowire. We analyze all possible dipole orientations and nanowire radii in the range from very small to comparable to the wavelength. Our theoretical approach is based on the Fourier transform technique and equivalent to the construction of Green's function for a dipole at an arbitrary location inside the nanowire. We show that the total emitted power can exhibit rather pronounced oscillations as a function of the frequency and radius. The far-field pattern is also very sensitive to the frequency and radius, especially in the regime when leaky (or whispering gallery) modes with finite axial wave numbers are excited. We discuss the enhancement of emission into guided modes due to formation of Fabry-Perot cavity in a finite length nanowire. Our results yield directly the extraction efficiencies and angular distribution of radiation of light-emitting diodes made of nanowires. (c) 2006 American Institute of Physics. C1 NASA, Ames Res Ctr, Ctr Nanotechnol, Moffett Field, CA 94035 USA. Univ Nizhny Novgorod, Dept Radiophys, Nizhnii Novgorod 603950, Russia. RP Maslov, AV (reprint author), NASA, Ames Res Ctr, Ctr Nanotechnol, Mail Stop 229-1, Moffett Field, CA 94035 USA. EM amaslov@mail.arc.nasa.gov; cning@mail.arc.nasa.gov RI Maslov, Alexey/E-5158-2011; Ning, C. Z./D-4699-2009; Bakunov, Michael/E-2875-2017 OI Maslov, Alexey/0000-0002-7835-2474; Ning, C. Z./0000-0003-4583-8889; Bakunov, Michael/0000-0002-4209-1372 NR 28 TC 51 Z9 52 U1 2 U2 20 PU AMER INST PHYSICS PI MELVILLE PA CIRCULATION & FULFILLMENT DIV, 2 HUNTINGTON QUADRANGLE, STE 1 N O 1, MELVILLE, NY 11747-4501 USA SN 0021-8979 J9 J APPL PHYS JI J. Appl. Phys. PD JAN 15 PY 2006 VL 99 IS 2 AR 024314 DI 10.1063/1.2164538 PG 10 WC Physics, Applied SC Physics GA 008BH UT WOS:000235014700078 ER PT J AU Katzberg, SJ Torres, O Grant, MS Masters, D AF Katzberg, SJ Torres, O Grant, MS Masters, D TI Utilizing calibrated GPS reflected signals to estimate soil reflectivity and dielectric constant: Results from SMEX02 SO REMOTE SENSING OF ENVIRONMENT LA English DT Article DE GPS; reflected GPS; soil dielectric constant; soil moisture; remote sensing; SMEX02 ID OCEAN SALINITY; MOISTURE; RETRIEVAL; SENSOR; BAND AB Extensive reflected GPS data was collected using a GPS reflectometer installed on an HC130 aircraft during the Soil Moisture Experiment 2002 (SMEX02) near Ames, Iowa. At the same time, widespread surface truth data was acquired in the form of point soil moisture profiles, areal sampling of near-surface soil moisture, total green biomass and precipitation history, among others. Previously, there have been no reported efforts to calibrate reflected GPS data sets acquired over land. This paper reports the results of two approaches to calibration of the data that yield consistent results. It is shown that estimating the strength of the reflected signals by either (1) assuming an approximately specular surface reflection or (2) inferring the surface slope probability density and associated normalization constants give essentially the same results for the conditions encountered in SMEX02. The corrected data is converted to surface reflectivity and then to dielectric constant as a test of the calibration approaches. Utilizing the extensive in-situ soil moisture related data this paper also presents the results of comparing the GPS-inferred relative dielectric constant with the Wang-Schmugge model frequently used to relate volume moisture content to dielectric constant. It is shown that the calibrated GPS reflectivity estimates follow the expected dependence of permittivity with volume moisture, but with the following qualification: The soil moisture value governing the reflectivity appears to come from only the top 1-2 cm of soil, a result consistent with results found for other microwave techniques operating at L-band. Nevertheless, the experimentally derived dielectric constant is generally lower than predicted. Possible explanations are presented to explain this result. (C) 2005 Elsevier Inc. All rights reserved. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. Univ Colorado, Boulder, CO 80309 USA. RP Torres, O (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM omar.torres-1@nasa.gov NR 25 TC 74 Z9 78 U1 0 U2 11 PU ELSEVIER SCIENCE INC PI NEW YORK PA 360 PARK AVE SOUTH, NEW YORK, NY 10010-1710 USA SN 0034-4257 J9 REMOTE SENS ENVIRON JI Remote Sens. Environ. PD JAN 15 PY 2006 VL 100 IS 1 BP 17 EP 28 DI 10.1016/j.rse.2005.09.015 PG 12 WC Environmental Sciences; Remote Sensing; Imaging Science & Photographic Technology SC Environmental Sciences & Ecology; Remote Sensing; Imaging Science & Photographic Technology GA 004ZH UT WOS:000234790800002 ER PT J AU Xie, H Gopalswamy, N Manoharan, PK Lara, A Yashiro, S Lepri, S AF Xie, H Gopalswamy, N Manoharan, PK Lara, A Yashiro, S Lepri, S TI Long-lived geomagnetic storms and coronal mass ejections SO JOURNAL OF GEOPHYSICAL RESEARCH-SPACE PHYSICS LA English DT Article ID RING-CURRENT; SOLAR-WIND; MAGNETIC CLOUDS; HEAVY-IONS; DECAY; CMES; INJECTION; MODEL; IRON; DST AB Coronal mass ejections (CMEs) are major solar events that are known to cause large geomagnetic storms (Dst<-100 nT). Isolated geomagnetic storms typically have a main phase of 3-12 hours and a recovery phase of around 1 day. However, there are some storms with main and recovery phases exceeding similar to 3 days. We trace the origin of these long-lived geomagnetic storms (LLGMS) to frontside halo CMEs. We studied 37 LLGMS events with Dst<-100 nT and the associated CMEs which occurred during 1998-2002. It is found that LLGMS events are caused by (1) successive CMEs, accounting for similar to 64.9% (24 of 37); (2) single CMEs, accounting for similar to 21.6% (8 of 37); and (3) high-speed streams (HSS) in corotating interaction regions (CIRs) with no related CME, accounting for similar to 13.5% (5 of 37). The long duration of the LLGMS events was found to be due to successive CMEs and HSS events; the high intensity of the LLGMS events was related to the interaction of CMEs with other CMEs and HSS events. We find that the duration of LLGMS is well correlated to the number of participating CMEs (correlation coefficient r=0.78). We also find that the intensity of LLGMS has a good correlation with the degree of interaction (the number of CMEs interacting with a HSS event or with themselves) (r=0.67). The role of preconditioning in LLGMS events, where the Dst development occurred in multiple steps in the main and recovery phases, has been investigated. It is found that preconditioning does not affect the main phase of the LLGMS events, while it plays an important role during the recovery phase of the LLGMS events. C1 Catholic Univ Amer, Dept Phys, Washington, DC 20064 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Tata Inst Fundamental Res, Natl Ctr Radio Astron, Ooty 843001, Tamil Nadu, India. Univ Nacl Autonoma Mexico, Inst Geofis, Mexico City 04510, DF, Mexico. Univ Michigan, Ann Arbor, MI 48109 USA. RP Xie, H (reprint author), Catholic Univ Amer, Dept Phys, 200 Hannan Hall,640 Michigan Ave NE, Washington, DC 20064 USA. EM hong.xie@ssedmail.gsfc.nasa.gov RI Gopalswamy, Nat/D-3659-2012; Lepri, Susan/I-8611-2012; OI Manoharan, Periasamy K/0000-0003-4274-211X NR 41 TC 31 Z9 32 U1 0 U2 2 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0148-0227 J9 J GEOPHYS RES-SPACE JI J. Geophys. Res-Space Phys. PD JAN 13 PY 2006 VL 111 IS A1 AR A01103 DI 10.1029/2005JA011287 PG 17 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 007UX UT WOS:000234996800003 ER PT J AU Rannou, P Montmessin, F Hourdin, F Lebonnois, S AF Rannou, P Montmessin, F Hourdin, F Lebonnois, S TI The latitudinal distribution of clouds on Titan SO SCIENCE LA English DT Article ID NORTH POLAR STRATOSPHERE; TROPOSPHERIC CLOUDS; MIDLATITUDE CLOUDS; ATMOSPHERE; HAZE; ABUNDANCES; SURFACE; WINDS; MODEL AB Clouds have been observed recently on Titan, through the thick haze, using near-infrared spectroscopy and images near the south pole and in temperate regions near 40 degrees S. Recent telescope and Cassini orbiter observations are now providing an insight into cloud climatology. To study clouds, we have developed a general circulation model of Titan that includes cloud microphysics. We identify and explain the formation of several types of ethane and methane clouds, including south polar clouds and sporadic clouds in temperate regions and especially at 40 degrees in the summer hemisphere. The locations, frequencies, and composition of these cloud types are essentially explained by the large-scale circulation. C1 Univ Versailles St Quentin, Inst Pierre Simon Laplace, Serv Aeron, F-91371 Verrieres Le Buisson, France. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. Univ Paris 06, Meteorol Dynam Lab, IPSL, F-75252 Paris, France. RP Rannou, P (reprint author), Univ Versailles St Quentin, Inst Pierre Simon Laplace, Serv Aeron, BP3, F-91371 Verrieres Le Buisson, France. EM pra@aero.jussieu.fr RI RANNOU, Pascal/I-9059-2012 NR 29 TC 136 Z9 137 U1 0 U2 5 PU AMER ASSOC ADVANCEMENT SCIENCE PI WASHINGTON PA 1200 NEW YORK AVE, NW, WASHINGTON, DC 20005 USA SN 0036-8075 J9 SCIENCE JI Science PD JAN 13 PY 2006 VL 311 IS 5758 BP 201 EP 205 DI 10.1126/science.1118424 PG 5 WC Multidisciplinary Sciences SC Science & Technology - Other Topics GA 003ZQ UT WOS:000234722200034 PM 16410519 ER PT J AU Yamaguchi, KE Ohmoto, H AF Yamaguchi, KE Ohmoto, H TI Comment on "Iron isotope constraints on the archean and paleoproterozoic ocean redox state" SO SCIENCE LA English DT Editorial Material AB Rouxel et al. (Reports, 18 February 2005, p. 1088) argued that changes in the iron isotopic composition of sedimentary sulfides reflect changes in the oxidation state of the atmosphere-ocean system between 2.3 and 1.8 million years ago. We show that misinterpretations of the origins of these minerals undermine their conclusions. C1 JAMSTEC, IFREE, Yokosuka, Kanagawa 2370061, Japan. NASA, Astrobiol Inst, Washington, DC 20546 USA. Penn State Univ, Astrobiol Res Ctr, University Pk, PA 16802 USA. Penn State Univ, Dept Geosci, University Pk, PA 16802 USA. RP Yamaguchi, KE (reprint author), JAMSTEC, IFREE, 2-15 Natsushima, Yokosuka, Kanagawa 2370061, Japan. EM kosei@jamstec.go.jp NR 9 TC 1 Z9 1 U1 1 U2 10 PU AMER ASSOC ADVANCEMENT SCIENCE PI WASHINGTON PA 1200 NEW YORK AVE, NW, WASHINGTON, DC 20005 USA SN 0036-8075 J9 SCIENCE JI Science PD JAN 13 PY 2006 VL 311 IS 5758 DI 10.1126/science.1118221 PG 1 WC Multidisciplinary Sciences SC Science & Technology - Other Topics GA 003ZQ UT WOS:000234722200016 ER PT J AU Golombek, MP Crumpler, LS Grant, JA Greeley, R Cabrol, NA Parker, TJ Rice, JW Ward, JG Arvidson, RE Moersch, JE Fergason, RL Christensen, PR Castano, A Castano, R Haldemann, AFC Li, R Bell, JF Squyres, SW AF Golombek, MP Crumpler, LS Grant, JA Greeley, R Cabrol, NA Parker, TJ Rice, JW Ward, JG Arvidson, RE Moersch, JE Fergason, RL Christensen, PR Castano, A Castano, R Haldemann, AFC Li, R Bell, JF Squyres, SW TI Geology of the Gusev cratered plains from the Spirit rover transverse SO JOURNAL OF GEOPHYSICAL RESEARCH-PLANETS LA English DT Article ID SIZE-FREQUENCY DISTRIBUTIONS; LANDING SITE PREDICTIONS; MINI-TES EXPERIMENT; MAADIM-VALLIS; MARS PATHFINDER; BRITTLE SOLIDS; FRAGMENT SIZE; ROCKS; RATES; SURFACE AB [1] The cratered plains of Gusev traversed by Spirit are generally low-relief rocky plains dominated by impact and eolian processes. Ubiquitous shallow, soil-filled, circular depressions, called hollows, are modified impact craters. Rocks are dark, fine-grained basalts, and the upper 10 m of the cratered plains appears to be an impact-generated regolith developed over intact basalt flows. Systematic field observations across the cratered plains identified vesicular clasts and rare scoria similar to original lava flow tops, consistent with an upper inflated surface of lava flows with adjacent collapse depressions. Crater and hollow morphometry are consistent with most being secondaries. The size-frequency distribution of rocks > 0.1 m diameter generally follows exponential functions similar to other landing sites for total rock abundances of 5-35%. Systematic clast counts show that areas with higher rock abundance and more large rocks have higher thermal inertia. Plains with lower thermal inertia have fewer rocks and substantially more pebbles that are well sorted and evenly spaced, similar to a desert pavement or lag. Eolian bed forms (ripples and wind tails) have coarse surface lags, and many are dust covered and thus likely inactive. Deflation of the surface similar to 5-25 cm likely exposed two-toned rocks and elevated ventifacts and transported fines into craters creating the hollows. This observed redistribution yields extremely slow average erosion rates of similar to 0.03 nm/yr and argues for very little long-term net change of the surface and a dry and desiccating environment similar to today's since the Hesperian (or similar to 3 Ga). C1 CALTECH, Jet Propuls Lab, Pasadena, CA 91125 USA. New Mexico Museum Nat Hist & Sci, Albuquerque, NM USA. Smithsonian Inst, Washington, DC 20560 USA. Arizona State Univ, Dept Geol Sci, Tempe, AZ USA. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. Washington Univ, Dept Earth & Planetary Sci, St Louis, MO 63130 USA. Univ Tennessee, Dept Geol Sci, Knoxville, TN 37996 USA. Ohio State Univ, Dept Civil & Environm Engn & Geodet Sci, Columbus, OH 43210 USA. Cornell Univ, Dept Astron, Ithaca, NY 14853 USA. RP CALTECH, Jet Propuls Lab, Pasadena, CA 91125 USA. EM mgolombek@jpl.nasa.gov RI Moersch, Jeffrey/F-7189-2010 NR 79 TC 63 Z9 64 U1 2 U2 8 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-9097 EI 2169-9100 J9 J GEOPHYS RES-PLANET JI J. Geophys. Res.-Planets PD JAN 12 PY 2006 VL 111 IS E2 AR E02S07 DI 10.1029/2005JE002503 PG 27 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 007UT UT WOS:000234996400002 ER PT J AU Li, RX Archinal, BA Arvidson, RE Bell, J Christensen, P Crumpler, L Des Marais, DJ Di, KC Duxbury, T Golombek, M Grant, J Greeley, R Guinn, J Johnson, A Kirk, RL Maimone, M Matthies, LH Malin, M Parker, T Sims, M Thompson, S Squyres, SW Soderblom, LA AF Li, RX Archinal, BA Arvidson, RE Bell, J Christensen, P Crumpler, L Des Marais, DJ Di, KC Duxbury, T Golombek, M Grant, J Greeley, R Guinn, J Johnson, A Kirk, RL Maimone, M Matthies, LH Malin, M Parker, T Sims, M Thompson, S Squyres, SW Soderblom, LA TI Spirit rover localization and topographic mapping at the landing site of Gusev crater, Mars SO JOURNAL OF GEOPHYSICAL RESEARCH-PLANETS LA English DT Article AB [1] By sol 440, the Spirit rover has traversed a distance of 3.76 km (actual distance traveled instead of odometry). Localization of the lander and the rover along the traverse has been successfully performed at the Gusev crater landing site. We localized the lander in the Gusev crater using two-way Doppler radio positioning and cartographic triangulations through landmarks visible in both orbital and ground images. Additional high-resolution orbital images were used to verify the determined lander position. Visual odometry and bundle adjustment technologies were applied to compensate for wheel slippage, azimuthal angle drift, and other navigation errors (which were as large as 10.5% in the Husband Hill area). We generated topographic products, including 72 ortho maps and three-dimensional (3-D) digital terrain models, 11 horizontal and vertical traverse profiles, and one 3-D crater model (up to sol 440). Also discussed in this paper are uses of the data for science operations planning, geological traverse surveys, surveys of wind-related features, and other science applications. C1 Ohio State Univ, Dept Civil & Environm Engn & Geodet Sci, Columbus, OH 43210 USA. US Geol Survey, Flagstaff, AZ 86001 USA. Washington Univ, Dept Earth & Planetary Sci, St Louis, MO 63130 USA. Cornell Univ, Dept Astron, Ithaca, NY 14853 USA. Arizona State Univ, Dept Geol Sci, Tempe, AZ 85287 USA. New Mexico Museum Nat Hist & Sci, Albuquerque, NM 87104 USA. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. Jet Propuls Lab, Pasadena, CA 91109 USA. Smithsonian Inst, Washington, DC 20560 USA. Malin Space Sci Syst, San Diego, CA 92191 USA. RP Li, RX (reprint author), Ohio State Univ, Dept Civil & Environm Engn & Geodet Sci, Columbus, OH 43210 USA. EM li.282@osu.edu NR 28 TC 26 Z9 27 U1 2 U2 2 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0148-0227 J9 J GEOPHYS RES-PLANET JI J. Geophys. Res.-Planets PD JAN 12 PY 2006 VL 111 IS E2 AR E02S06 DI 10.1029/2005JE002486 PG 13 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 007UT UT WOS:000234996400001 ER PT J AU Phan, TD Gosling, JT Davis, MS Skoug, RM Oieroset, M Lin, RP Lepping, RP McComas, DJ Smith, CW Reme, H Balogh, A AF Phan, TD Gosling, JT Davis, MS Skoug, RM Oieroset, M Lin, RP Lepping, RP McComas, DJ Smith, CW Reme, H Balogh, A TI A magnetic reconnection X-line extending more than 390 Earth radii in the solar wind SO NATURE LA English DT Article ID FLUX-TRANSFER EVENTS; MAGNETOPAUSE; FIELD; PLASMA AB Magnetic reconnection in a current sheet converts magnetic energy into particle energy, a process that is important in many laboratory(1), space(2,3) and astrophysical contexts(4-6). It is not known at present whether reconnection is fundamentally a process that can occur over an extended region in space or whether it is patchy and unpredictable in nature(7). Frequent reports of small-scale flux ropes and flow channels associated with reconnection(8-13) in the Earth's magnetosphere raise the possibility that reconnection is intrinsically patchy, with each reconnection X-line ( the line along which oppositely directed magnetic field lines reconnect) extending at most a few Earth radii (R-E), even though the associated current sheets span many tens or hundreds of R-E. Here we report three-spacecraft observations of accelerated flow associated with reconnection in a current sheet embedded in the solar wind flow, where the reconnection X-line extended at least 390R(E) ( or 2.5 x 10(6) km). Observations of this and 27 similar events imply that reconnection is fundamentally a large-scale process. Patchy reconnection observed in the Earth's magnetosphere is therefore likely to be a geophysical effect associated with fluctuating boundary conditions, rather than a fundamental property of reconnection. Our observations also reveal, surprisingly, that reconnection can operate in a quasi-steady-state manner even when undriven by the external flow. C1 Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. Univ Colorado, Atmospher & Space Phys Lab, Boulder, CO 80303 USA. Los Alamos Natl Lab, Los Alamos, NM 87545 USA. NASA, Goddard Space Flight Ctr, Lab Solar & Space Phys, Greenbelt, MD 20771 USA. SW Res Inst, Space Sci & Engn Div, San Antonio, TX 78228 USA. Univ New Hampshire, Dept Phys, Durham, NH 03824 USA. Univ New Hampshire, Ctr Space Sci, Durham, NH 03824 USA. Ctr Etud Spatiale Rayonnements, F-31029 Toulouse, France. Univ London Imperial Coll Sci Technol & Med, Space & Atmospher Phys Grp, London SW7 2BZ, England. RP Phan, TD (reprint author), Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. EM phan@ssl.berkeley.edu NR 26 TC 149 Z9 154 U1 1 U2 15 PU NATURE PUBLISHING GROUP PI LONDON PA MACMILLAN BUILDING, 4 CRINAN ST, LONDON N1 9XW, ENGLAND SN 0028-0836 J9 NATURE JI Nature PD JAN 12 PY 2006 VL 439 IS 7073 BP 175 EP 178 DI 10.1038/nature04393 PG 4 WC Multidisciplinary Sciences SC Science & Technology - Other Topics GA 001MT UT WOS:000234538400033 PM 16407946 ER PT J AU Smith, GP Sand, DJ Egami, E Stern, D Eisenhardt, PR AF Smith, GP Sand, DJ Egami, E Stern, D Eisenhardt, PR TI Optical and infrared nondetection of the z=10 galaxy behind Abell 1835 SO ASTROPHYSICAL JOURNAL LA English DT Article DE cosmology : observations; early universe; galaxies : evolution; galaxies : formation; infrared : galaxies ID TELESCOPE LENSING SURVEY; SUBMILLIMETER-SELECTED GALAXIES; ULTRA-DEEP-FIELD; SPACE-TELESCOPE; PHOTOMETRIC REDSHIFTS; CLUSTERS; Z-SIMILAR-TO-6; DISCOVERY; REIONIZATION; CANDIDATE AB Gravitational lensing by massive galaxy clusters is a powerful tool for the discovery and study of high-redshift galaxies, including those at z >= 6 likely responsible for cosmic reionization. Pello et al. recently used this technique to discover a candidate gravitationally magnified galaxy at z = 10 behind the massive cluster lens Abell 1835 (z = 0.25). We present new Keck and Spitzer Space Telescope observations of the z = 10 candidate (hereafter #1916, following Pello et al.'s nomenclature) together with a reanalysis of archival optical and near-infrared imaging from the Hubble Space Telescope and Very Large Telescope, respectively. Our analysis extends from the atmospheric cutoff at lambda(obs) similar or equal to 0.35 mu m out to lambda(obs) similar or equal to 5 mu m. The z = 10 galaxy is not detected in any of these data, including an independent reduction of Pello et al.'s discovery H- and K-band imaging. We conclude that there is no statistically reliable evidence for the existence of #1916. We also assess the implications of our results for ground-based near-infrared searches for gravitationally magnified galaxies at z greater than or similar to 7. The broad conclusion is that such experiments remain feasible, assuming that space-based optical and mid-infrared imaging are available to break the degeneracy with low-redshift interlopers (e.g., z similar to 2-3) when fitting spectral templates to the photometric data. C1 CALTECH, Dept Astron, Pasadena, CA 91125 USA. Univ Arizona, Steward Observ, Tucson, AZ 85721 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Smith, GP (reprint author), CALTECH, Dept Astron, Mail Code 105-24, Pasadena, CA 91125 USA. EM gps@astro.caltech.edu NR 48 TC 2 Z9 2 U1 0 U2 3 PU IOP PUBLISHING LTD PI BRISTOL PA TEMPLE CIRCUS, TEMPLE WAY, BRISTOL BS1 6BE, ENGLAND SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 10 PY 2006 VL 636 IS 2 BP 575 EP 581 DI 10.1086/497979 PN 1 PG 7 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 000NR UT WOS:000234469400002 ER PT J AU Williger, GM Heap, SR Weymann, RJ Dave, R Ellingson, E Carswell, RF Tripp, TM Jenkins, EB AF Williger, GM Heap, SR Weymann, RJ Dave, R Ellingson, E Carswell, RF Tripp, TM Jenkins, EB TI The low-redshift Ly alpha forest toward PKS 0405-123 SO ASTROPHYSICAL JOURNAL LA English DT Article DE cosmology : observations; intergalactic medium; quasars : absorption lines ID HOT INTERGALACTIC MEDIUM; MEDIUM-GALAXY CONNECTION; ABSORPTION-LINE SYSTEMS; PHYSICAL-PROPERTIES; SIGHT LINE; STIS OBSERVATIONS; OF-SIGHT; ABSORBERS; QUASAR; OVI AB We present results for Ly alpha forest and metal absorbers from similar to 7 km s(-1) resolution Space Telescope Imaging Spectrograph data for QSO PKS 0405-123 (z = 0.574). We analyze strong and weak samples of Ly alpha forest lines, containing 60 absorbers with column density log N(H I) >= 13.3 over 0.002 < z < 0.423 and 44 with log N(H I) >= 13.1 over 0: 020 < z < 0: 234, respectively. Seven absorbers contain metals, all with associated O VI and often offset in velocity from Ly alpha. The strong and weak Doppler parameter distributions have < b > = 47 +/- 22 and 44 +/- 21 km s(-1), respectively. Simulated spectra suggest that line blending and signal-to-noise ratio effects inflate b. For absorbers with 13.1 < log N H I < 14.0, we find a redshift overdensity of similar to 0.2-0.3 dex at 0.127 < z < 0.234, which we attribute to cosmic variance. There is a void in the strong sample at 0: 0320 < z < 0: 0814 with probability of random occurrence P < 0.0004. We detect Ly alpha-Ly alpha clustering in our sample on a scale of Delta v <= 250 km s(-1) for log N (H I) < 13.3, consistent with a numerical model of structure evolution. We detect velocity correlations of up to 250 km s(-1) between Ly alpha absorbers and 39 galaxies at z < 0.43 out to a transverse distance of 1.6 h(70)(-1) local frame Mpc. The Ly alpha-galaxy two-point correlation function is significant out to Delta v < 250 km s(-1) and grows with minimum H I column density. The strongest signal occurs for log N (H I) greater than or similar to 13.5-14.0 absorbers and is similar to the galaxy-galaxy correlation, implying that such Ly alpha absorbers have masses log (M/M(circle dot)) = 11.3(-0.6)(+1.0) We find a correlation between local galaxy counts and local summed H I column density, with peak significance on scales of 4000-6000 km s(-1) and probability of random occurrence P = 0.0009. Finally, we present column densities for a number of Galactic species. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Univ Arizona, Dept Astron, Tucson, AZ 85721 USA. Univ Colorado, Ctr Astrophys & Space Astron, Boulder, CO 80309 USA. Univ Cambridge, Inst Astron, Cambridge CB3 0HA, England. Univ Massachusetts, Dept Astron, Amherst, MA 01003 USA. Princeton Univ Observ, Princeton, NJ 08544 USA. RP Williger, GM (reprint author), Johns Hopkins Univ, Dept Phys & Astron, Charles & 34th St, Baltimore, MD 21218 USA. RI Jenkins, Edward/P-5684-2014 OI Jenkins, Edward/0000-0003-1892-4423 NR 79 TC 31 Z9 31 U1 0 U2 2 PU IOP PUBLISHING LTD PI BRISTOL PA TEMPLE CIRCUS, TEMPLE WAY, BRISTOL BS1 6BE, ENGLAND SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 10 PY 2006 VL 636 IS 2 BP 631 EP 653 DI 10.1086/498127 PN 1 PG 23 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 000NR UT WOS:000234469400006 ER PT J AU Seward, FD Gorenstein, P Smith, RK AF Seward, FD Gorenstein, P Smith, RK TI Chandra observations of the X-ray halo around the Crab Nebula SO ASTROPHYSICAL JOURNAL LA English DT Article DE ISM : individual (Crab Nebula); supernova remnants; X-rays : ISM ID LARGE-MAGELLANIC-CLOUD; INTERSTELLAR GRAINS; SUPERNOVA-REMNANTS; SYNCHROTRON NEBULA; DUST; SCATTERING; PULSAR; EMISSION; SHELL; CONSTRAINTS AB Two Chandra observations have been used to search for thermal X-ray emission from within and around the Crab Nebula. Dead time was minimized by excluding the brightest part of the nebula from the field of view. A dust-scattered halo comprising 5% of the strength of the Crab is clearly detected, with surface brightness measured out to a radial distance of 18'. Coverage is 100% at 4', 50% at 12', and 25% at 18'. The observed halo is compared with predictions based on three different interstellar grain models, and one can be adjusted to fit the observation. This dust halo and mirror scattering form a high background region that has been searched for emission from shock-heated material in an outer shell. We find no evidence for such emission. We can set upper limits a factor of 10 - 1000 less than the surface brightness observed from outer shells around similar remnants. The upper limit for X-ray luminosity of an outer shell is approximate to 10(34) ergs s(-1). Although it is possible to reconcile our observation with an 8 - 13 M circle dot progenitor, we argue that this is unlikely. C1 Smithsonian Astrophys Observ, Cambridge, MA 02138 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Johns Hopkins Univ, Baltimore, MD 21218 USA. RP Seward, FD (reprint author), Smithsonian Astrophys Observ, 60 Garden St, Cambridge, MA 02138 USA. NR 44 TC 22 Z9 22 U1 0 U2 2 PU IOP PUBLISHING LTD PI BRISTOL PA TEMPLE CIRCUS, TEMPLE WAY, BRISTOL BS1 6BE, ENGLAND SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 10 PY 2006 VL 636 IS 2 BP 873 EP 880 DI 10.1086/498105 PN 1 PG 8 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 000NR UT WOS:000234469400024 ER PT J AU Watson, D Vaughan, SA Willingale, R Hjorth, J Foley, S Fynbo, JPU Jakobsson, P Levan, A O'Brien, PT Osborne, JP Pedersen, K Reeves, JN Tedds, JA Watson, MG AF Watson, D Vaughan, SA Willingale, R Hjorth, J Foley, S Fynbo, JPU Jakobsson, P Levan, A O'Brien, PT Osborne, JP Pedersen, K Reeves, JN Tedds, JA Watson, MG TI The soft X-ray blast in the apparently subluminous GRB 031203 SO ASTROPHYSICAL JOURNAL LA English DT Article DE gamma rays : bursts; X-rays : general; X-rays : ISM ID INTERSTELLAR GRAINS; LOW-LUMINOSITY; PEAK-ENERGY; BURST; SCATTERING; FLASH; HALOS; SUPERNOVA; BEPPOSAX AB GRB 031203 was a very low apparent luminosity gamma-ray burst ( GRB). Coincidentally, it was also the first GRB with a dust-scattered X-ray halo. The observation of the halo allowed us to infer the presence of a large soft X-ray fluence in the total burst output. It has also been claimed, however, that GRB 031203 was intrinsically subenergetic, representative of a class of spectrally hard, low-energy bursts quite different from other GRBs. A careful reanalysis of the available data confirms our original finding that GRB 031203 had a very large soft X-ray component, the time of which can be constrained to within a few minutes after the burst, strongly suggesting that while GRB 031203 did indeed have a very low apparent luminosity, it was also very soft. Notions propagated in the literature regarding the uncertainties in the determination of the soft X-ray fluence from the halo data and on the available constraints from the hard X-ray data are addressed: the properties of the scattering dust along the line of sight ( grain sizes, precise location, and geometry) are determined directly from the high-quality X-ray data so that there is little uncertainty about the scatterer; constraints on the X-ray light curve from the INTEGRAL spacecraft at the time of the soft X-ray blast are not complete because of a slew in the spacecraft pointing shortly after the burst. Claims that GRB 031203 was intrinsically underenergetic and that it represents a deviation from the luminosity-peak-energy relation do not appear to be substantiated by the data, regardless of whether the soft X-ray component is ( arbitrarily) declared part of the prompt emission or the afterglow. We conclude that the difference between the soft and hard X-ray spectra from XMM-Newton and INTEGRAL indicate that a second soft pulse probably occurred in this burst, as has been observed in other GRBs, notably GRB 050502B. C1 Univ Copenhagen, Niels Bohr Inst, Dark Cosmol Ctr, DK-2100 Copenhagen O, Denmark. Univ Leicester, Dept Phys & Astron, Xray Astron Grp, Leicester LE1 7RH, Leics, England. Univ Coll Dublin, Dept Expt Phys, Dublin 4, Ireland. NASA Goddard Space Flight Ctr, Lab High Energy Astrophys, Greenbelt, MD 20771 USA. RP Watson, D (reprint author), Univ Copenhagen, Niels Bohr Inst, Dark Cosmol Ctr, Juliane Maries Vej 30, DK-2100 Copenhagen O, Denmark. EM darach@astro.ku.dk; anl@star.le.ac.uk; pto@star.le.ac.uk; jens@astro.ku.dk; sfoley@bermuda.ucd.ie; jens@astro.ku.dk; pallja@astro.ku.dk; rw@star.le.ac.uk; julo@star.le.ac.uk; sav2@star.le.ac.uk; kp@astro.ku.dk; jnr@milkyway.gsfc.nasa.gov; jat@star.le.ac.uk; mjw@star.le.ac.uk RI Fynbo, Johan/L-8496-2014; Hjorth, Jens/M-5787-2014; Watson, Darach/E-4521-2015; Jakobsson, Pall/L-9950-2015; OI Fynbo, Johan/0000-0002-8149-8298; Hjorth, Jens/0000-0002-4571-2306; Watson, Darach/0000-0002-4465-8264; Jakobsson, Pall/0000-0002-9404-5650; Tedds, Jonathan/0000-0003-2829-4584 NR 27 TC 20 Z9 21 U1 0 U2 2 PU IOP PUBLISHING LTD PI BRISTOL PA TEMPLE CIRCUS, TEMPLE WAY, BRISTOL BS1 6BE, ENGLAND SN 0004-637X EI 1538-4357 J9 ASTROPHYS J JI Astrophys. J. PD JAN 10 PY 2006 VL 636 IS 2 BP 967 EP 970 DI 10.1086/498089 PN 1 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 000NR UT WOS:000234469400034 ER PT J AU Muterspaugh, MW Lane, BF Konacki, M Wiktorowicz, S Burke, BF Colavita, MM Kulkarni, SR Shao, M AF Muterspaugh, MW Lane, BF Konacki, M Wiktorowicz, S Burke, BF Colavita, MM Kulkarni, SR Shao, M TI Phases differential astrometry and iodine cell radial velocities of the kappa Pegasi triple star system SO ASTROPHYSICAL JOURNAL LA English DT Review DE astrometry; binaries : close; binaries : visual; stars : distances; stars : individual (kappa Pegasi); techniques : interferometric ID ICCD SPECKLE OBSERVATIONS; VISUAL DOUBLE STARS; PIC-DU-MIDI; PALOMAR TESTBED INTERFEROMETER; PROBLEM HIPPARCOS BINARIES; PEAK 4-M TELESCOPE; KITT-PEAK; MICROMETER MEASURES; MOUNT-HAMILTON; TIDAL FRICTION AB kappa Pegasi is a well-known, nearby triple star system. It consists of a "wide'' pair with semimajor axis = 235 mas, one component of which is a single-line spectroscopic binary (semimajor axis = 2.5 mas). Using high- precision differential astrometry and radial velocity observations, the masses for all three components are determined and the relative inclination between the wide and narrow pairs' orbits is found to be 43.degrees 8 +/- 3.degrees 0, just over the threshold for the threebody Kozai resonance. The system distance is determined to be 34: 60 +/- 0:21 pc and is consistent with trigonometric parallax measurements. C1 MIT Dept Phys, MIT Kavli Inst Astrophys & Space Res, Cambridge, MA 02139 USA. CALTECH, Dept Geol & Planetary Sci, Pasadena, CA 91125 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Polish Acad Sci, Nicholaus Copernicus Astron Ctr, PL-87100 Torun, Poland. CALTECH, Div Phys Math & Astron, Pasadena, CA 91125 USA. RP Muterspaugh, MW (reprint author), MIT Dept Phys, MIT Kavli Inst Astrophys & Space Res, 70 Vassar St, Cambridge, MA 02139 USA. EM matthew1@mit.edu; blane@mit.edu; maciej@gps.caltech.edu RI Konacki, Maciej/A-1220-2007 NR 212 TC 16 Z9 16 U1 0 U2 4 PU IOP PUBLISHING LTD PI BRISTOL PA TEMPLE CIRCUS, TEMPLE WAY, BRISTOL BS1 6BE, ENGLAND SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 10 PY 2006 VL 636 IS 2 BP 1020 EP 1032 DI 10.1086/498209 PN 1 PG 13 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 000NR UT WOS:000234469400040 ER PT J AU Bryden, G Beichman, CA Trilling, DE Rieke, GH Holmes, EK Lawler, SM Stapelfeldt, KR Werner, MW Gautier, TN Blaylock, M Gordon, KD Stansberry, JA Su, KYL AF Bryden, G Beichman, CA Trilling, DE Rieke, GH Holmes, EK Lawler, SM Stapelfeldt, KR Werner, MW Gautier, TN Blaylock, M Gordon, KD Stansberry, JA Su, KYL TI Frequency of debris disks around solar-type stars: First results from a Spitzer MIPS survey SO ASTROPHYSICAL JOURNAL LA English DT Article DE circumstellar matter; infrared : stars; Kuiper Belt; planetary systems : formation ID MAIN-SEQUENCE STARS; MULTIBAND IMAGING PHOTOMETER; VEGA PHENOMENON; FE/H DETERMINATIONS; AGE-DEPENDENCE; STELLAR ATMOSPHERES; EXTRASOLAR PLANETS; ABUNDANCE ANALYSES; MODEL ATMOSPHERES; INFRARED EXCESSES AB We have searched for infrared excesses around a well-defined sample of 69 FGK main-sequence field stars. These stars were selected without regard to their age, metallicity, or any previous detection of IR excess; they have a median age of similar to 4 Gyr. We have detected 70 mu m excesses around seven stars at the 3 sigma confidence level. This extra emission is produced by cool material (< 100 K) located beyond 10 AU, well outside the "habitable zones'' of these systems and consistent with the presence of Kuiper Belt analogs with similar to 100 times more emitting surface area than in our own planetary system. Only one star, HD 69830, shows excess emission at 24 mu m, corresponding to dust with temperatures greater than or similar to 300 K located inside of 1 AU. While debris disks with L(dust) /L(*) >= 10(-3) are rare around old FGK stars, we find that the disk frequency increases from 2% +/- 2% for L(dust)/L(*) >= 10(-4) to 12% +/- 5% for L(dust)/L(*) >= 10(-5). This trend in the disk luminosity distribution is consistent with the estimated dust in our solar system being within an order of magnitude greater or less than the typical level around similar nearby stars. Although there is no correlation of IR excess with metallicity or spectral type, there is a weak correlation with stellar age, with stars younger than a gigayear more likely to have excess emission. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. CALTECH, Michelson Sci Ctr, Pasadena, CA 91125 USA. Univ Arizona, Steward Observ, Tucson, AZ 85721 USA. RP Bryden, G (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RI Stapelfeldt, Karl/D-2721-2012; OI Su, Kate/0000-0002-3532-5580 NR 82 TC 215 Z9 216 U1 0 U2 4 PU IOP PUBLISHING LTD PI BRISTOL PA TEMPLE CIRCUS, TEMPLE WAY, BRISTOL BS1 6BE, ENGLAND SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 10 PY 2006 VL 636 IS 2 BP 1098 EP 1113 DI 10.1086/498093 PN 1 PG 16 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 000NR UT WOS:000234469400047 ER PT J AU Bhattacharyya, S Strohmayer, TE AF Bhattacharyya, S Strohmayer, TE TI A non-pre double-peaked burst from 4U 1636-536: Evidence of burning front propagation SO ASTROPHYSICAL JOURNAL LA English DT Article DE accretion, accretion disks; relativity; stars : neutron; X-rays : binaries; X-rays : bursts; X-rays : individual (4U 1636-536) ID X-RAY-BURSTS; ROTATING NEUTRON-STARS; MILLISECOND PULSAR; RADIUS EXPANSION; RISING PHASE; OSCILLATIONS; DISCOVERY; MODULATION; ACCRETION; PROFILES AB We analyze Rossi X- Ray Timing Explorer ( RXTE) Proportional Counter Array ( PCA) data of a double- peaked burst from the low- mass X- ray binary ( LMXB) 4U 1636 - 536 that shows no evidence of photospheric radius expansion ( PRE). We find that the X- ray - emitting area on the star increases with time as the burst progresses, even though the photosphere does not expand. We argue that this is a strong indication of thermonuclear flame spreading on the stellar surface during such bursts. We propose a model for such double- peaked bursts, based on thermonuclear flame spreading, that can qualitatively explain their essential features as well as the rarity of these bursts. C1 Univ Maryland, Dept Astron, College Pk, MD 20742 USA. NASA, Goddard Space Flight Ctr, Explorat Universe Div, Xray Astrophys Lab, Greenbelt, MD 20771 USA. RP Bhattacharyya, S (reprint author), Univ Maryland, Dept Astron, College Pk, MD 20742 USA. EM sudip@milkyway.gsfc.nasa.gov; stroh@clarence.gsfc.nasa.gov NR 27 TC 27 Z9 27 U1 0 U2 2 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 10 PY 2006 VL 636 IS 2 BP L121 EP L124 DI 10.1086/500199 PN 2 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 000NU UT WOS:000234469700016 ER PT J AU Brown, TM Smith, E Guhathakurta, P Rich, RM Ferguson, HC Renzini, A Sweigart, AV Kimble, RA AF Brown, TM Smith, E Guhathakurta, P Rich, RM Ferguson, HC Renzini, A Sweigart, AV Kimble, RA TI Deep photometry of Andromeda reveals striking similarities in the tidal stream and spheroid populations SO ASTROPHYSICAL JOURNAL LA English DT Article DE galaxies : evolution; galaxies : halos; galaxies : individual (M31); galaxies : stellar content ID MAIN-SEQUENCE PHOTOMETRY; ADVANCED CAMERA; GIANT STREAM; M31 HALO; GALAXY; SUBSTRUCTURE; CLUSTER; STARS; DISK AB We present a color-magnitude diagram (CMD) for a field in the giant tidal stream of the Andromeda galaxy (M31). These observations, taken with the Advanced Camera for Surveys on the Hubble Space Telescope, are 50% complete at mag, reaching 1 mag below the oldest main-sequence turnoff. Striking similarities V approximate to 30 between the stream and a previous spheroid CMD imply that they have very similar age and metallicity distributions, but present something of an enigma; we speculate on possible interpretations of this result, but we note that none are without problems. Distinct multiple turnoffs, as might be expected from pulses of star formation caused by interaction with Andromeda, are not apparent in the stream CMD. Star formation in both fields lasted about 6 billion years, building up to relatively high metallicities and being largely complete 6 billion years ago. The close similarity of the spheroid and stream suggests that both may have derived from the same event; it would be worth exploring to what extent stars in these structures are the remnants of a disk galaxy that interacted with M31 or even were disrupted from the M31 disk itself by the interaction. C1 Space Telescope Sci Inst, Baltimore, MD 21218 USA. Univ Calif Santa Cruz, Lick Observ, Santa Cruz, CA 95064 USA. Univ Calif Los Angeles, Dept Phys & Astron, Div Astron, Los Angeles, CA 90095 USA. Osserv Astron Padova, I-35122 Padua, Italy. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Brown, TM (reprint author), Space Telescope Sci Inst, 3700 San Martin Dr, Baltimore, MD 21218 USA. EM tbrown@stsci.edu; edsmith@stsci.edu; raja@ucolick.org; rmr@astro.ucla.edu; ferguson@stsci.edu; arenzini@pd.astro.it; allen.v.sweigart@nasa.gov; randy.a.kimble@nasa.gov RI Kimble, Randy/D-5317-2012; OI Brown, Thomas/0000-0002-1793-9968 NR 27 TC 26 Z9 27 U1 0 U2 3 PU IOP PUBLISHING LTD PI BRISTOL PA TEMPLE CIRCUS, TEMPLE WAY, BRISTOL BS1 6BE, ENGLAND SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 10 PY 2006 VL 636 IS 2 BP L89 EP L92 DI 10.1086/500089 PN 2 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 000NU UT WOS:000234469700008 ER PT J AU Sakamoto, T Barbier, L Barthelmy, SD Cummings, JR Fenimore, EE Gehrels, N Hullinger, D Krimm, HA Markwardt, CB Palmer, DM Parsons, AM Sato, G Tueller, J AF Sakamoto, T Barbier, L Barthelmy, SD Cummings, JR Fenimore, EE Gehrels, N Hullinger, D Krimm, HA Markwardt, CB Palmer, DM Parsons, AM Sato, G Tueller, J TI Confirmation of the E(peak)(src)-E(iso)(AMATI) relation from the X-ray flash XRF 050416A by the Swift Burst Alert Telescope SO ASTROPHYSICAL JOURNAL LA English DT Article DE gamma rays : bursts ID AFTERGLOW LIGHT CURVES; SPECTRAL CHARACTERISTICS; INTRINSIC SPECTRA; MODEL; ENERGY; UNIVERSAL; JETS; VARIABILITY; LUMINOSITY; ENERGETICS AB We report Swift Burst Alert Telescope ( BAT) observations of the X-ray flash (XRF) XRF 050416A. The fluence ratio between the 15-25 and 25-50 keV energy bands of this event is 1.1, thus making it the softest gamma-ray burst (GRB) observed by BAT so far. The spectrum is well fitted by a Band function with of k(peak)(obs) 15.0(-2.7)(+2.3) keV. Assuming the redshift of the host galaxy (E(peak)(src)), the isotropic equivalent radiated energy E(iso) and the peak z = 0.6535 energy at the GRB rest frame (E(peak)(src)) of XRF 050416A are not only consistent with the correlation found by Amati (E(peak)(src)) et al. and extended to XRFs by Sakamoto et al. but also fill in the gap of this relation around the 30-80 keV range of. This result tightens the validity of the relation from XRFs to GRBs. We also find that the jet break time estimated using the empirical relation between E(peak)(src) and the collimation corrected energy E(gamma) is inconsistent with the afterglow observation by the Swift X-Ray Telescope. This could be due to the extra external shock emission overlaid around the jet break time or to the nonexistence of a jet break feature for XRFs, which might be a further challenge for GRB jet emission models and XRF/GRB unification scenarios. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. CNR, Washington, DC 20418 USA. Los Alamos Natl Lab, Los Alamos, NM 87545 USA. Univ Maryland, Dept Phys, College Pk, MD 20742 USA. Univ Space Res Assoc, Columbia, MD 21044 USA. JAXA, Inst Space & Astronaut Sci, Kanagawa 2298510, Japan. RP Sakamoto, T (reprint author), NASA, Goddard Space Flight Ctr, Code 661, Greenbelt, MD 20771 USA. RI Gehrels, Neil/D-2971-2012; Tueller, Jack/D-5334-2012; Barthelmy, Scott/D-2943-2012; Parsons, Ann/I-6604-2012 NR 52 TC 41 Z9 41 U1 0 U2 3 PU IOP PUBLISHING LTD PI BRISTOL PA TEMPLE CIRCUS, TEMPLE WAY, BRISTOL BS1 6BE, ENGLAND SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 10 PY 2006 VL 636 IS 2 BP L73 EP L76 DI 10.1086/500261 PN 2 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 000NU UT WOS:000234469700004 ER PT J AU Hinchey, MG Rash, JL Rouff, CA Gracanin, D AF Hinchey, MG Rash, JL Rouff, CA Gracanin, D TI Achieving dependability in sensor networks through automated requirements-based programming SO COMPUTER COMMUNICATIONS LA English DT Article DE sensor networks; formal methods; automatic code generation AB A sensor network can be viewed as a distributed system consisting of many nodes (processes) that communicate and exchange data. Such a system, including an application running on top of the sensor network, is inherently difficult to model and validate. System requirements and actual application code may not be consistent, with the implementation failing to implement all of the requirements, or failing to implement them correctly. Requirements can be expressed as a set of services that the sensor network should provide. Each service may be described using one or more scenarios. For the classes of systems whose behavior can be described as a finite (but significant) set of scenarios, we offer a method for mechanically transforming requirements (expressed in restricted natural language, or in other appropriate notations) into a provably equivalent formal model that can be used as the basis for code generation and other transformations. This represents a significant step forward toward high-dependability system engineering for numerous possible application domains, including sensor networks. (C) 2005 Elsevier B.V. All rights reserved. C1 NASA, Goddard Space Flight Ctr, Informat Syst Div, Greenbelt, MD 20771 USA. Sci Applicat Int Corp, Adv Concepts Business Unit, Mclean, VA 22102 USA. Virginia Tech, Dept Comp Sci, Blacksburg, VA 24061 USA. RP NASA, Goddard Space Flight Ctr, Informat Syst Div, Code 580, Greenbelt, MD 20771 USA. EM michael.g.hinchey@nasa.gov; james.l.rash@nasa.gov; rouffc@saic.com; gracanin@vt.edu NR 31 TC 4 Z9 4 U1 0 U2 3 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 0140-3664 EI 1873-703X J9 COMPUT COMMUN JI Comput. Commun. PD JAN 10 PY 2006 VL 29 IS 2 BP 246 EP 256 DI 10.1016/j.comcom.2005.05.020 PG 11 WC Computer Science, Information Systems; Engineering, Electrical & Electronic; Telecommunications SC Computer Science; Engineering; Telecommunications GA 006AW UT WOS:000234868500009 ER PT J AU Pickett, HM Drouin, BJ Canty, T Kovalenko, LJ Salawitch, RJ Livesey, NJ Read, WG Waters, JW Jucks, KW Traub, WA AF Pickett, HM Drouin, BJ Canty, T Kovalenko, LJ Salawitch, RJ Livesey, NJ Read, WG Waters, JW Jucks, KW Traub, WA TI Validation of Aura MLS HOx measurements with remote-sensing balloon instruments SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID OH AB Satellite measurements of OH and HO2 obtained by the Aura MLS instrument are compared to the balloon-borne BOH and FIRS-2 instruments. All measurements are also compared with constrained photochemical model calculations. On average, both balloon measurements of OH agree with MLS within 17% over 25 - 40 km and the measurements agree with the model within 12%. The three measurements for column of OH above 40 km agree within 8% and the mean is 12% below the model. Measurements of HO2 from FIRS-2 and MLS agree on average within 23% over 25 - 40 km and the differences are generally within the experimental precision. The HO2 measurements agree with the model within 14%. Measurements of HO2 for the column over 40 - 60 km agree within 16% and the mean measured column agrees with the model within the experimental precision. Our observations do not appear to indicate a "HOx dilemma''. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Harvard Smithsonian Ctr Astrophys, Cambridge, MA 02138 USA. RP Pickett, HM (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM herbert.m.pickett@jpl.nasa.gov RI Salawitch, Ross/B-4605-2009; Canty, Timothy/F-2631-2010 OI Salawitch, Ross/0000-0001-8597-5832; Canty, Timothy/0000-0003-0618-056X NR 8 TC 25 Z9 25 U1 0 U2 0 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0094-8276 J9 GEOPHYS RES LETT JI Geophys. Res. Lett. PD JAN 10 PY 2006 VL 33 IS 1 AR L01808 DI 10.1029/2005GL024048 PG 4 WC Geosciences, Multidisciplinary SC Geology GA 007UE UT WOS:000234994700002 ER PT J AU Zhao, M Running, SW Nemani, RR AF Zhao, Maosheng Running, Steven W. Nemani, Ramakrishna R. TI Sensitivity of Moderate Resolution Imaging Spectroradiometer (MODIS) terrestrial primary production to the accuracy of meteorological reanalyses SO JOURNAL OF GEOPHYSICAL RESEARCH-BIOGEOSCIENCES LA English DT Article ID NET PRIMARY PRODUCTION; SPACE-TIME CLIMATE; LEAF-AREA; VARIABILITY; SATELLITE; MODEL; ECOSYSTEMS; INCREASES; EXCHANGE; FORESTS AB [1] The Moderate Resolution Imaging Spectroradiometer (MODIS) on board NASA's satellites, Terra and Aqua, dramatically improves our ability to accurately and continuously monitor the terrestrial biosphere. MODIS information is used to estimate global terrestrial primary production weekly and annually in near-real time at a 1-km resolution. MODIS terrestrial primary production requires daily gridded assimilation meteorological data as inputs, and the accuracy of the existing meteorological reanalysis data sets show marked differences both spatially and temporally. This study compares surface meteorological data sets from three well-documented global reanalyses, NASA Data Assimilation Office (DAO), European Centre for Medium-Range Weather Forecasts (ECMWF) (ERA-40) and National Centers for Environmental Prediction/National Center for Atmospheric Research (NCEP/NCAR) reanalysis 1, with observed weather station data and other gridded data interpolated from the observations, to evaluate the sensitivity of MODIS global terrestrial gross and net primary production (GPP and NPP) to the uncertainties of meteorological inputs both in the United States and the global vegetated areas. NCEP tends to overestimate surface solar radiation, and underestimate both temperature and vapor pressure deficit (VPD). ECMWF has the highest accuracy but its radiation is lower in tropical regions, and the accuracy of DAO lies between NCEP and ECMWF. Biases in temperature are mainly responsible for large VPD biases in reanalyses. MODIS NPP contains more uncertainties than GPP. Global total MODIS GPP and NPP driven by DAO, ECMWF, and NCEP show notable differences (> 20 Pg C/yr) with the highest estimates from NCEP and the lowest from ECMWF. Again, the DAO results lie somewhere between NCEP and ECMWF estimates. Spatially, the larger discrepancies among reanalyses and their derived MODIS GPP and NPP occur in the tropics. These results reveal that the biases in meteorological reanalyses can introduce substantial error into GPP and NPP estimations, and emphasize the need to minimize these biases to improve the quality of MODIS GPP and NPP products. C1 Univ Montana, Dept Ecosyst & Conservat Sci, Numer Terradynam Simulat Grp, Missoula, MT 59812 USA. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Zhao, M (reprint author), Univ Montana, Dept Ecosyst & Conservat Sci, Numer Terradynam Simulat Grp, Missoula, MT 59812 USA. EM zhao@ntsg.umt.edu RI Zhao, Maosheng/G-5706-2010 NR 49 TC 210 Z9 213 U1 5 U2 37 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-8953 EI 2169-8961 J9 J GEOPHYS RES-BIOGEO JI J. Geophys. Res.-Biogeosci. PD JAN 10 PY 2006 VL 111 IS G1 AR G01002 DI 10.1029/2004JG000004 PG 13 WC Environmental Sciences; Geosciences, Multidisciplinary SC Environmental Sciences & Ecology; Geology GA 090WU UT WOS:000240985300002 ER PT J AU Tigelaar, DM Meador, MAB Kinder, JD Bennett, WR AF Tigelaar, DM Meador, MAB Kinder, JD Bennett, WR TI New APTES cross-linked polymers from poly(ethylene oxide)s and cyanuric chloride for lithium batteries SO MACROMOLECULES LA English DT Article ID ELECTROCHEMICAL PROPERTIES; CONDUCTIVITY BEHAVIOR; CONVERGENT SYNTHESES; THERMAL-PROPERTIES; ELECTROLYTES; DENDRIMERS; MELAMINE; TRANSPORT; ORMOLYTES; LICF3SO3 AB A new series of hyperbranched polymer electrolytes for use as membranes for lithium batteries are described. Electrolytes were made by polymerization between cyanuric chloride and diamino-terminated poly(ethylene oxide)s, followed by cross-linking via a sol-gel process. The cross-linking improves the mechanical integrity of the polymer films over other PEO-based electrolytes previously described without deleteriously affecting the ionic conductivity. Thermal analysis and lithium conductivity of free-standing polymer films were studied. The effects of several variables on conductivity were investigated, such as length of backbone PEO chain, length of branching PEO chain, extent of branching, extent of cross-linking, salt content, and salt counterion. Polymer films with the highest percentage of PEO were found to be the most conductive, with a maximum lithium conductivity of 3.9 x 10(-5) S/cm at 25 degrees C, but more mechanically robust films with as much as 50% cross-linker were only slightly lower in conductivity (3.7 x 10(-5) S/cm) at 25 degrees C. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Tigelaar, DM (reprint author), NASA, Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. EM dean.m.tigelaar@grc.nasa.gov OI Meador, Mary Ann/0000-0003-2513-7372 NR 31 TC 23 Z9 24 U1 1 U2 25 PU AMER CHEMICAL SOC PI WASHINGTON PA 1155 16TH ST, NW, WASHINGTON, DC 20036 USA SN 0024-9297 J9 MACROMOLECULES JI Macromolecules PD JAN 10 PY 2006 VL 39 IS 1 BP 120 EP 127 DI 10.1021/ma051657d PG 8 WC Polymer Science SC Polymer Science GA 000ZA UT WOS:000234500100022 ER PT J AU Lee, S von Allmen, P AF Lee, S von Allmen, P TI Tight-binding modeling of thermoelectric properties of bismuth telluride SO APPLIED PHYSICS LETTERS LA English DT Article ID QUANTUM-WELL; MERIT; FIGURE; NANOWIRES; SUPERLATTICES AB A parameterized orthogonal tight-binding model with sp(3)d(5)s(*) orbitals, nearest-neighbor interactions, and spin-orbit coupling is developed for bismuth telluride (Bi2Te3) and used to study its thermoelectric properties. Thermoelectric transport coefficients and figures of merit for n-doped and p-doped Bi2Te3 are calculated by solving Boltzmann's transport equation within the constant-relaxation-time approximation. The dependence of the computed thermoelectric figure of merit on the electrical conductivity is in good agreement with experiment. The parameterized tight-binding model serves as a basis for studies of confined Bi2Te3 systems in search of enhanced thermoelectric properties. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Lee, S (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM seungwon.lee@jpl.nasa.gov NR 23 TC 36 Z9 37 U1 1 U2 18 PU AMER INST PHYSICS PI MELVILLE PA CIRCULATION & FULFILLMENT DIV, 2 HUNTINGTON QUADRANGLE, STE 1 N O 1, MELVILLE, NY 11747-4501 USA SN 0003-6951 EI 1077-3118 J9 APPL PHYS LETT JI Appl. Phys. Lett. PD JAN 9 PY 2006 VL 88 IS 2 AR 022107 DI 10.1063/1.2162863 PG 3 WC Physics, Applied SC Physics GA 002JE UT WOS:000234606900033 ER PT J AU Baker, DF Law, RM Gurney, KR Rayner, P Peylin, P Denning, AS Bousquet, P Bruhwiler, L Chen, YH Ciais, P Fung, IY Heimann, M John, J Maki, T Maksyutov, S Masarie, K Prather, M Pak, B Taguchi, S Zhu, Z AF Baker, DF Law, RM Gurney, KR Rayner, P Peylin, P Denning, AS Bousquet, P Bruhwiler, L Chen, YH Ciais, P Fung, IY Heimann, M John, J Maki, T Maksyutov, S Masarie, K Prather, M Pak, B Taguchi, S Zhu, Z TI TransCom 3 inversion intercomparison: Impact of transport model errors on the interannual variability of regional CO2 fluxes, 1988-2003 SO GLOBAL BIOGEOCHEMICAL CYCLES LA English DT Article ID ATMOSPHERIC CARBON-DIOXIDE; SENSITIVITY; DELTA-C-13; SINKS; CYCLE AB Monthly CO2 fluxes are estimated across 1988-2003 for 22 emission regions using data from 78 CO2 measurement sites. The same inversion (method, priors, data) is performed with 13 different atmospheric transport models, and the spread in the results is taken as a measure of transport model error. Interannual variability (IAV) in the winds is not modeled, so any IAV in the measurements is attributed to IAV in the fluxes. When both this transport error and the random estimation errors are considered, the flux IAV obtained is statistically significant at P <= 0.05 when the fluxes are grouped into land and ocean components for three broad latitude bands, but is much less so when grouped into continents and basins. The transport errors have the largest impact in the extratropical northern latitudes. A third of the 22 emission regions have significant IAV, including the Tropical East Pacific (with physically plausible uptake/release across the 1997-2000 El Nino/La Nina) and Tropical Asia (with strong release in 1997/1998 coinciding with large-scale fires there). Most of the global IAV is attributed robustly to the tropical/southern land biosphere, including both the large release during the 1997/1998 El Nino and the post-Pinatubo uptake. C1 Princeton Univ, Program Atmospher & Ocean Sci, Princeton, NJ 08544 USA. CSIRO Marine & Atmospher Res, Aspendale, Vic 3195, Australia. Colorado State Univ, Dept Atmospher Sci, Ft Collins, CO 80523 USA. Lab Sci Climat & Environm, F-91198 Gif Sur Yvette, France. NOAA, Climate Monitoring & Diagnost Lab, Boulder, CO 80303 USA. MIT, Dept Earth Atmospher & Planetary Sci, Cambridge, MA 02139 USA. Univ Calif Berkeley, Ctr Atmospher Sci, Berkeley, CA 94720 USA. Max Planck Inst Biogeochem, Dept Biogeochem Syst, D-07701 Jena, Germany. Japan Meteorol Agcy, Observat Dept, Div Atmospher Environm, Qual Assurance Sect,Chiyoda Ku, Tokyo 1008122, Japan. Japan Agcy Marine Earth Sci & Technol, Frontier Res Ctr Global Change, Inst Global Change Res, Yokohama, Kanagawa 2360001, Japan. Univ Calif Irvine, Dept Earth Syst Sci, Irvine, CA 92697 USA. Natl Inst Adv Ind Sci & Technol, Res Inst Environm Management Technol, Global Environm Study Grp, Tsukuba, Ibaraki 3058569, Japan. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Baker, DF (reprint author), Natl Ctr Atmospher Res, Terr Sci Sect, Climate & Global Dynam Div, 1850 Table Mesa Dr, Boulder, CO 80305 USA. EM dfb@ucar.edu; rachel.law@csiro.au; keving@atmos.colostate.edu; peter.rayner@cea.fr; peylin@lsce.saclay.cea.fr; denning@atmos.colostate.edu; bousquet@lsce.saclay.cea.fr; lori.bruhwiler@noaa.gov; didi@mit.edu; ciais@lsce.saclay.cea.fr; ifung@uclink4.berkeley.edu; martin.heimann@bgc.jena.mpg.de; jasmin@atmos.berkeley.edu; maki@met.kishou.go.jp; shamil@jamstec.go.jp; kenneth.masarie@noaa.gov; mprather@uci.edu; bernard.pak@csiro.au; s.taguchi@aist.go.jp; zhu@mulan.gsfc.nasa.gov RI Law, Rachel/A-1969-2012; Denning, Scott/F-4974-2011; Pak, Bernard/F-4326-2015; Maksyutov, Shamil/G-6494-2011; Vuichard, Nicolas/A-6629-2011; Heimann, Martin/H-7807-2016 OI Law, Rachel/0000-0002-7346-0927; Denning, Scott/0000-0003-3032-7875; Pak, Bernard/0000-0002-2137-8171; Maksyutov, Shamil/0000-0002-1200-9577; Heimann, Martin/0000-0001-6296-5113 NR 32 TC 104 Z9 105 U1 3 U2 39 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0886-6236 J9 GLOBAL BIOGEOCHEM CY JI Glob. Biogeochem. Cycle PD JAN 7 PY 2006 VL 20 IS 1 AR GB1002 DI 10.1029/2004GB002439 PG 17 WC Environmental Sciences; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Environmental Sciences & Ecology; Geology; Meteorology & Atmospheric Sciences GA 001CB UT WOS:000234509600001 ER PT J AU Ma, Q Tipping, RH Boulet, C AF Ma, Q Tipping, RH Boulet, C TI Irreducible correlation functions of the (S)over-cap matrix in the coordinate representation: Application in calculating Lorentzian half-widths and shifts SO JOURNAL OF CHEMICAL PHYSICS LA English DT Article ID ASYMMETRIC-TOP MOLECULES; ROTATION-VIBRATION LINES; DENSITY-MATRIX; SPECTRAL-LINES; H2O; SHAPES; TEMPERATURES; LINEWIDTHS; RANGE; N2 AB By introducing the coordinate representation, the derivation of the perturbation expansion of the Liouville S matrix is formulated in terms of classically behaved autocorrelation functions. Because these functions are characterized by a pair of irreducible tensors, their number is limited to a few. They represent how the overlaps of the potential components change with a time displacement, and under normal conditions, their magnitudes decrease by several orders of magnitude when the displacement reaches several picoseconds. The correlation functions contain all dynamical information of the collision processes necessary in calculating half-widths and shifts and can be easily derived with high accuracy. Their well-behaved profiles, especially the rapid decrease of the magnitude, enables one to transform easily the dynamical information contained in them from the time domain to the frequency domain. More specifically, because these correlation functions are well time limited, their continuous Fourier transforms should be band limited. Then, the latter can be accurately replaced by discrete Fourier transforms and calculated with a standard fast Fourier transform method. Besides, one can easily calculate their Cauchy principal integrations and derive all functions necessary in calculating half-widths and shifts. A great advantage resulting from introducing the coordinate representation and choosing the correlation functions as the starting point is that one is able to calculate the half-widths and shifts with high accuracy, no matter how complicated the potential models are and no matter what kind of trajectories are chosen. In any case, the convergence of the calculated results is always guaranteed. As a result, with this new method, one can remove some uncertainties incorporated in the current width and shift studies. As a test, we present calculated Raman Q linewidths for the N-2-N-2 pair based on several trajectories, including the more accurate "exact" ones. Finally, by using this new method as a benchmark, we have carried out convergence checks for calculated values based on usual methods and have found that some results in the literature are not converged. (c) 2006 American Institute of Physics. C1 NASA, Goddard Inst Space Studies, New York, NY 10025 USA. Columbia Univ, Dept Appl Phys & Appl Math, New York, NY 10025 USA. Univ Alabama, Dept Phys & Astron, Tuscaloosa, AL 35487 USA. Univ Paris 12, CNRS, LISA, F-94010 Creteil, France. Univ Paris 07, CNRS, LISA, F-94010 Creteil, France. Univ Paris 11, Photophys Mol Lab, F-91405 Orsay, France. RP NASA, Goddard Inst Space Studies, New York, NY 10025 USA. EM qma@giss.nasa.gov NR 32 TC 14 Z9 15 U1 0 U2 4 PU AMER INST PHYSICS PI MELVILLE PA 1305 WALT WHITMAN RD, STE 300, MELVILLE, NY 11747-4501 USA SN 0021-9606 EI 1089-7690 J9 J CHEM PHYS JI J. Chem. Phys. PD JAN 7 PY 2006 VL 124 IS 1 AR 014109 DI 10.1063/1.2139671 PG 14 WC Chemistry, Physical; Physics, Atomic, Molecular & Chemical SC Chemistry; Physics GA 999YU UT WOS:000234428900011 PM 16409026 ER PT J AU Hegedus, R Horvath, A Horvath, G AF Hegedus, R Horvath, A Horvath, G TI Why do dusk-active cockchafers detect polarization in the green? - The polarization vision in Melolontha melolontha is tuned to the high polarized intensity of downwelling light under canopies during sunset SO JOURNAL OF THEORETICAL BIOLOGY LA English DT Article DE European cockchafer; Melolontha melolontha; polarization vision; dusk activity; sunset light; canopylight; green sensitivity; downwelling light ID SKY IMAGING POLARIMETRY; DORSAL RIM AREA; COMPOUND EYE; SKYLIGHT POLARIZATION; ANIMAL ORIENTATION; SOLAR IRRADIANCE; SENSITIVITY; PATTERNS; CRICKETS; INSECTS AB In the retina of dusk-active European cockchafers, Melolontha melolontha, the linear polarization of downwelling light (skylight or light from the tree canopy) is detected by photoreceptors in upward-pointing ommatidia with maximal sensitivity at 520 rim in the green portion of the spectrum. To date no attempt has been made to answer the question of why these beetles detect polarization in the green. Here we present an atmospheric optical and receptor-physiological explanation of why longer wavelengths are advantageous for the perception of polarization of downwelling light under canopies illuminated by the setting sun. Our explanation focuses on illumination situations during sunset in canopied optical environments, because cockchafers are active at sunset and fly predominantly under canopies during their swarming, feeding, and mating periods. Using three simple atmospheric optical models, we computed the degree of linear polarization, the linearly polarized intensity of downwelling light, the quantum catch, and quantum catch difference between polarization detectors with orthogonal microvilli under canopies illuminated by the setting sun as functions of wavelength and solar zenith angle. Based upon these computations, we show that the green sensitivity of polarization detectors in M. melolontha is tuned to the high polarized intensity of downwelling light in the green under canopies during sunset, an optimal compromise between simultaneous maximization of the quantum catch and the quantum catch difference. We also briefly discuss how green-sensitive polarization detectors can function efficiently enough during the pre-feeding and egg-laying flights of cockchafers, which always occur prior to sunset and under the sky. (c) 2005 Elsevier Ltd. All rights reserved. C1 Eotvos Lorand Univ, Bioopt Lab, Dept Biol Phys, H-1117 Budapest, Hungary. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Horvath, G (reprint author), Eotvos Lorand Univ, Bioopt Lab, Dept Biol Phys, Pazmany Peter Setany 1, H-1117 Budapest, Hungary. EM gh@arago.elte.hu RI Horvath, Akos/A-2453-2008 OI Horvath, Akos/0000-0002-5860-2368 NR 32 TC 12 Z9 13 U1 0 U2 10 PU ACADEMIC PRESS LTD- ELSEVIER SCIENCE LTD PI LONDON PA 24-28 OVAL RD, LONDON NW1 7DX, ENGLAND SN 0022-5193 J9 J THEOR BIOL JI J. Theor. Biol. PD JAN 7 PY 2006 VL 238 IS 1 BP 230 EP 244 DI 10.1016/j.jtbi.2005.05.033 PG 15 WC Biology; Mathematical & Computational Biology SC Life Sciences & Biomedicine - Other Topics; Mathematical & Computational Biology GA 996DI UT WOS:000234154200020 PM 16043191 ER PT J AU Ciszak, EM Makal, A Hong, YS Vettaikkorumakankauv, AK Korotchkina, LG Patel, MS AF Ciszak, EM Makal, A Hong, YS Vettaikkorumakankauv, AK Korotchkina, LG Patel, MS TI How dihydrolipoamide dehydrogenase-binding protein binds dihydrolipoamide dehydrogenase in the human pyruvate dehydrogenase complex SO JOURNAL OF BIOLOGICAL CHEMISTRY LA English DT Article ID REFINED CRYSTAL-STRUCTURE; LIPOAMIDE DEHYDROGENASE; MULTIENZYME COMPLEX; 3-DIMENSIONAL STRUCTURE; BACILLUS-STEAROTHERMOPHILUS; ACETYLTRANSFERASE COMPONENT; AZOTOBACTER-VINELANDII; GLUTATHIONE-REDUCTASE; ANGSTROM RESOLUTION; ESCHERICHIA-COLI AB The dihydrolipoamide dehydrogenase-binding protein (E3BP) and the dihydrolipoamide acetyltransferase (E2) component enzyme form the structural core of the human pyruvate dehydrogenase complex by providing the binding sites for two other component proteins, dihydrolipoamide dehydrogenase (E3) and pyruvate dehydrogenase (E1), as well as pyruvate dehydrogenase kinases and phosphatases. Despite a high similarity between the primary structures of E3BP and E2, the E3-binding domain of human E3BP is highly specific to human E3, whereas the E1-binding domain of human E2 is highly specific to human E1. In this study, we characterized binding of human E3 to the E3-binding domain of E3BP by x-ray crystallography at 2.6-angstrom resolution, and we used this structural information to interpret the specificity for selective binding. Two subunits of E3 form a single recognition site for the E3-binding domain of E3BP through their hydrophobic interface. The hydrophobic residues Pro(133), Pro(154), and Ile(157) in the E3-binding domain of E3BP insert themselves into the surface of both E3 polypeptide chains. Numerous ionic and hydrogen bonds between the residues of three interacting polypeptide chains adjacent to the central hydrophobic patch add to the stability of the subcomplex. The specificity of pairing for human E3BP with E3 is interpreted from its subcomplex structure to be most likely due to conformational rigidity of the binding fragment of the E3-binding domain of E3BP and its exquisite amino acid match with the E3 target interface. C1 Univ Alabama, Natl Space Sci & Technol Ctr, Struct Biol Lab, Huntsville, AL 35805 USA. NASA, George C Marshall Space Flight Ctr, Biol & Phys Space Res Lab, Huntsville, AL 35805 USA. SUNY Buffalo, Dept Biochem, Sch Med & Biochem Sci, Buffalo, NY 14214 USA. RP Ciszak, EM (reprint author), Univ Alabama, Natl Space Sci & Technol Ctr, Struct Biol Lab, 320 Sparkman Dr, Huntsville, AL 35805 USA. EM ciszakE@uah.edu FU NIDDK NIH HHS [DK42885] NR 49 TC 34 Z9 40 U1 0 U2 10 PU AMER SOC BIOCHEMISTRY MOLECULAR BIOLOGY INC PI BETHESDA PA 9650 ROCKVILLE PIKE, BETHESDA, MD 20814-3996 USA SN 0021-9258 J9 J BIOL CHEM JI J. Biol. Chem. PD JAN 6 PY 2006 VL 281 IS 1 BP 648 EP 655 PG 8 WC Biochemistry & Molecular Biology SC Biochemistry & Molecular Biology GA 998GS UT WOS:000234307200077 PM 16263718 ER PT J AU Arvidson, RE Squyres, SW Anderson, RC Bell, JF Blaney, D Bruckner, J Cabrol, NA Calvin, WM Carr, MH Christensen, PR Clark, BC Crumpler, L Des Marais, DJ de Souza, PA d'Uston, C Economou, T Farmer, J Farrand, WH Folkner, W Golombek, M Gorevan, S Grant, JA Greeley, R Grotzinger, J Guinness, E Hahn, BC Haskin, L Herkenhoff, KE Hurowitz, JA Hviid, S Johnson, JR Klingelhofer, G Knoll, AH Landis, G Leff, C Lemmon, M Li, R Madsen, MB Malin, MC McLennan, SM McSween, HY Ming, DW Moersch, J Morris, RV Parker, T Rice, JW Richter, L Rieder, R Rodionov, DS Schroder, C Sims, M Smith, M Smith, P Soderblom, LA Sullivan, R Thompson, SD Tosca, NJ Wang, A Wanke, H Ward, J Wdowiak, T Wolff, M Yen, A AF Arvidson, RE Squyres, SW Anderson, RC Bell, JF Blaney, D Bruckner, J Cabrol, NA Calvin, WM Carr, MH Christensen, PR Clark, BC Crumpler, L Des Marais, DJ de Souza, PA d'Uston, C Economou, T Farmer, J Farrand, WH Folkner, W Golombek, M Gorevan, S Grant, JA Greeley, R Grotzinger, J Guinness, E Hahn, BC Haskin, L Herkenhoff, KE Hurowitz, JA Hviid, S Johnson, JR Klingelhofer, G Knoll, AH Landis, G Leff, C Lemmon, M Li, R Madsen, MB Malin, MC McLennan, SM McSween, HY Ming, DW Moersch, J Morris, RV Parker, T Rice, JW Richter, L Rieder, R Rodionov, DS Schroder, C Sims, M Smith, M Smith, P Soderblom, LA Sullivan, R Thompson, SD Tosca, NJ Wang, A Wanke, H Ward, J Wdowiak, T Wolff, M Yen, A TI Overview of the Spirit Mars Exploration Rover Mission to Gusev Crater: Landing site to Backstay Rock in the Columbia Hills SO JOURNAL OF GEOPHYSICAL RESEARCH-PLANETS LA English DT Article ID MINI-TES; SOILS; SPECTROMETER; OPPORTUNITY; MINERALOGY; CHEMISTRY AB Spirit landed on the floor of Gusev Crater and conducted initial operations on soil-covered, rock-strewn cratered plains underlain by olivine-bearing basalts. Plains surface rocks are covered by wind-blown dust and show evidence for surface enrichment of soluble species as vein and void-filling materials and coatings. The surface enrichment is the result of a minor amount of transport and deposition by aqueous processes. Layered granular deposits were discovered in the Columbia Hills, with outcrops that tend to dip conformably with the topography. The granular rocks are interpreted to be volcanic ash and/or impact ejecta deposits that have been modified by aqueous fluids during and/or after emplacement. Soils consist of basaltic deposits that are weakly cohesive, relatively poorly sorted, and covered by a veneer of wind-blown dust. The soils have been homogenized by wind transport over at least the several kilometer length scale traversed by the rover. Mobilization of soluble species has occurred within at least two soil deposits examined. The presence of monolayers of coarse sand on wind-blown bedforms, together with even spacing of granule-sized surface clasts, suggests that some of the soil surfaces encountered by Spirit have not been modified by wind for some time. On the other hand, dust deposits on the surface and rover deck have changed during the course of the mission. Detection of dust devils, monitoring of the dust opacity and lower boundary layer, and coordinated experiments with orbiters provided new insights into atmosphere-surface dynamics. C1 Washington Univ, Dept Earth & Planetary Sci, St Louis, MO 63130 USA. Cornell Univ, Dept Astron, Ithaca, NY 14853 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Max Planck Inst Chem, D-55020 Mainz, Germany. NASA, Ames SETI Inst, Moffett Field, CA 94035 USA. Univ Nevada, Reno, NV 89557 USA. US Geol Survey, Menlo Pk, CA 94025 USA. Arizona State Univ, Dept Geol Sci, Tempe, AZ 85287 USA. Lockheed Martin Corp, Littleton, CO 80127 USA. New Mexico Museum Nat Hist & Sci, Albuquerque, NM 87104 USA. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. Companhia Vale Rio Doce, BR-20030900 Rio De Janeiro, Brazil. Ctr Etud Spatiale Rayonnements, F-31028 Toulouse, France. Univ Chicago, Enrico Fermi Inst, Chicago, IL 60637 USA. Space Sci Inst, Boulder, CO 80301 USA. Honeybee Robot, New York, NY 10012 USA. Smithsonian Inst, Ctr Earth & Planetary Studies, Washington, DC 20560 USA. Massachusetts Inst Technol Earth Atmosphere & Pla, Cambridge, MA 02139 USA. SUNY Stony Brook, Dept Geosci, Stony Brook, NY 11794 USA. US Geol Survey, Flagstaff, AZ 86001 USA. Max Planck Inst Sonnensyst Forsch, Katlenburg Lindau, Germany. Johannes Gutenberg Univ Mainz, Inst Anorgan & Analyt Chem, D-55128 Mainz, Germany. Harvard Univ, Bot Museum, Cambridge, MA 02138 USA. NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. Texas A&M Univ, Dept Atmospher Sci, College Stn, TX 77843 USA. Ohio State Univ, Dept Civil & Environm Engn & Geodet Sci, Columbus, OH 43210 USA. Univ Copenhagen, Niels Bohr Inst, DK-2100 Copenhagen, Denmark. Malin Space Sci Syst, San Diego, CA 92191 USA. Univ Tennessee, Dept Earth & Planetary Sci, Knoxville, TN 37996 USA. NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. DLR Inst Space Simulat, Cologne, Germany. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Univ Arizona, Lunar & Planetary Lab, Tucson, AZ 85721 USA. Univ Alabama Birmingham, Dept Phys, Birmingham, AL 35294 USA. Space Sci Inst, Martinez, GA USA. RP Washington Univ, Dept Earth & Planetary Sci, Campus Box 1169,1 Brookings Dr, St Louis, MO 63130 USA. EM arvidson@wunder.wustl.edu RI Moersch, Jeffrey/F-7189-2010; Lemmon, Mark/E-9983-2010; Johnson, Jeffrey/F-3972-2015; Madsen, Morten/D-2082-2011; Schroder, Christian/B-3870-2009; de Souza, Paulo/B-8961-2008; Smith, Michael/C-8875-2012; Hurowitz, Joel/A-8862-2008 OI Lemmon, Mark/0000-0002-4504-5136; Madsen, Morten/0000-0001-8909-5111; Schroder, Christian/0000-0002-7935-6039; de Souza, Paulo/0000-0002-0091-8925; NR 43 TC 116 Z9 117 U1 3 U2 3 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-9097 EI 2169-9100 J9 J GEOPHYS RES-PLANET JI J. Geophys. Res.-Planets PD JAN 6 PY 2006 VL 111 IS E2 AR E02S01 DI 10.1029/2005JE002499 PG 22 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 001CG UT WOS:000234510100006 ER PT J AU Farrand, WH Bell, JF Johnson, JR Squyres, SW Soderblom, J Ming, DW AF Farrand, WH Bell, JF Johnson, JR Squyres, SW Soderblom, J Ming, DW TI Spectral variability among rocks in visible and near-infrared multispectral Pancam data collected at Gusev crater: Examinations using spectral mixture analysis and related techniques SO JOURNAL OF GEOPHYSICAL RESEARCH-PLANETS LA English DT Article ID MARS-PATHFINDER; SPIRIT ROVER; OPPORTUNITY; COLOR; SITE; SOIL AB Visible and near-infrared ( VNIR) multispectral observations of rocks made by the Mars Exploration Rover Spirit's Panoramic camera ( Pancam) have been analyzed using a spectral mixture analysis ( SMA) methodology. Scenes have been examined from the Gusev crater plains into the Columbia Hills. Most scenes on the plains and in the Columbia Hills could be modeled as three end-member mixtures of a bright material, rock, and shade. Scenes of rocks disturbed by the rover's Rock Abrasion Tool ( RAT) required additional end-members. In the Columbia Hills, there were a number of scenes in which additional rock end-members were required. The SMA methodology identified relatively dust-free areas on undisturbed rock surfaces as well as spectrally unique areas on RAT abraded rocks. Spectral parameters from these areas were examined, and six spectral classes were identified. These classes are named after a type rock or area and are Adirondack, Lower West Spur, Clovis, Wishstone, Peace, and Watchtower. These classes are discriminable based, primarily, on near-infrared ( NIR) spectral parameters. Clovis and Watchtower class rocks appear more oxidized than Wishstone class rocks and Adirondack basalts based on their having higher 535 nm band depths. Comparison of the spectral parameters of these Gusev crater rocks to parameters of glass-dominated basaltic tuffs indicates correspondence between measurements of Clovis and Watchtower classes but divergence for the Wishstone class rocks, which appear to have a higher fraction of crystalline ferrous iron-bearing phases. Despite a high sulfur content, the rock Peace has NIR properties resembling plains basalts. C1 Space Sci Inst, Boulder, CO 80301 USA. Cornell Univ, Dept Astron, Ithaca, NY 14853 USA. US Geol Survey, Flagstaff, AZ 86001 USA. NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Space Sci Inst, 4750 Walnut St, Boulder, CO 80301 USA. EM farrand@spacescience.org RI Johnson, Jeffrey/F-3972-2015 NR 44 TC 47 Z9 46 U1 0 U2 8 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-9097 EI 2169-9100 J9 J GEOPHYS RES-PLANET JI J. Geophys. Res.-Planets PD JAN 6 PY 2006 VL 111 IS E2 AR E02S15 DI 10.1029/2005JE002495 PG 25 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 001CG UT WOS:000234510100005 ER PT J AU Grant, JA Arvidson, RE Crumpler, LS Golombek, MP Hahn, B Haldemann, AFC Li, R Soderblom, LA Squyres, SW Wright, SP Watters, WA AF Grant, JA Arvidson, RE Crumpler, LS Golombek, MP Hahn, B Haldemann, AFC Li, R Soderblom, LA Squyres, SW Wright, SP Watters, WA TI Crater gradation in Gusev crater and Meridiani Planum, Mars SO JOURNAL OF GEOPHYSICAL RESEARCH-PLANETS LA English DT Article ID ROVER LANDING SITE; IMPACT CRATERS; SPIRIT ROVER; EJECTA EMPLACEMENT; MICROSCOPIC IMAGER; TERRA-MERIDIANI; BURNS FORMATION; DEGRADATION; DEPOSITS; SOILS AB The Mars Exploration Rovers investigated numerous craters in Gusev crater and Meridiani Planum during the first similar to 400 sols of their missions. Craters vary in size and preservation state but are mostly due to secondary impacts at Gusev and primary impacts at Meridiani. Craters at both locations are modified primarily by eolian erosion and infilling and lack evidence for modification by aqueous processes. Effects of gradation on crater form are dependent on size, local lithology, slopes, and availability of mobile sediments. At Gusev, impacts into basaltic rubble create shallow craters and ejecta composed of resistant rocks. Ejecta initially experience eolian stripping, which becomes weathering-limited as lags develop on ejecta surfaces and sediments are trapped within craters. Subsequent eolian gradation depends on the slow production of fines by weathering and impacts and is accompanied by minor mass wasting. At Meridiani the sulfate-rich bedrock is more susceptible to eolian erosion, and exposed crater rims, walls, and ejecta are eroded, while lower interiors and low-relief surfaces are increasingly infilled and buried by mostly basaltic sediments. Eolian processes outpace early mass wasting, often produce meters of erosion, and mantle some surfaces. Some small craters were likely completely eroded/buried. Craters >100 m in diameter on the Hesperian-aged floor of Gusev are generally more pristine than on the Amazonian-aged Meridiani plains. This conclusion contradicts interpretations from orbital views, which do not readily distinguish crater gradation state at Meridiani and reveal apparently subdued crater forms at Gusev that may suggest more gradation than has occurred. C1 Smithsonian Inst, Ctr Earth & Planetary Studies, Natl Air & Space Museum, Washington, DC 20560 USA. Washington Univ, Dept Earth & Planetary Sci, St Louis, MO 63130 USA. New Mexico Museum Nat Hist & Sci, Albuquerque, NM 87104 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. SUNY Stony Brook, Dept Geosci, Stony Brook, NY 11790 USA. Ohio State Univ, Dept Civil & Environm Engn & Geodet Sci, Columbus, OH 43210 USA. US Geol Survey, Flagstaff, AZ 86001 USA. Cornell Univ, Dept Astron, Ithaca, NY 14853 USA. Arizona State Univ, Dept Geol Sci, Tempe, AZ 85287 USA. MIT, Dept Earth Atmospher & Planetary Sci, Cambridge, MA 02139 USA. RP Smithsonian Inst, Ctr Earth & Planetary Studies, Natl Air & Space Museum, 6th & Independence SW, Washington, DC 20560 USA. EM grantj@si.edu NR 50 TC 41 Z9 41 U1 1 U2 5 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-9097 EI 2169-9100 J9 J GEOPHYS RES-PLANET JI J. Geophys. Res.-Planets PD JAN 6 PY 2006 VL 111 IS E2 AR E02S08 DI 10.1029/2005JE002465 PG 23 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 001CG UT WOS:000234510100002 ER PT J AU Greeley, R Arvidson, RE Barlett, PW Blaney, D Cabrol, NA Christensen, PR Fergason, RL Golombek, MP Landis, GA Lemmon, MT McLennan, SM Maki, JN Michaels, T Moersch, JE Neakrase, LDV Rafkin, SCR Richter, L Squyres, SW de Souza, PA Sullivan, RJ Thompson, SD Whelley, PL AF Greeley, R Arvidson, RE Barlett, PW Blaney, D Cabrol, NA Christensen, PR Fergason, RL Golombek, MP Landis, GA Lemmon, MT McLennan, SM Maki, JN Michaels, T Moersch, JE Neakrase, LDV Rafkin, SCR Richter, L Squyres, SW de Souza, PA Sullivan, RJ Thompson, SD Whelley, PL TI Gusev crater: Wind-related features and processes observed by the Mars Exploration Rover Spirit SO JOURNAL OF GEOPHYSICAL RESEARCH-PLANETS LA English DT Article ID PATHFINDER LANDING SITE; GENERAL-CIRCULATION; MISSION; SURFACE; ROCKS; SPECTROMETER; SIMULATIONS; PREDICTIONS; ABRASION; EROSION AB Wind-related features observed by the rover Spirit in Gusev crater, Mars, include patches of soil on the surface, some of which are organized into bed forms. Windblown grains include dust ( inferred to be <3 mu m in diameter), sands ( up to a few hundred mu m in diameter), and granules (>2 mm in diameter). Microscopic Imager data show the sands and granules to be rounded and relatively spherical, typical of grains transported long distances by the wind. The interior of bed forms exposed by rover operations suggests the infiltration of dust among the grains, indicating that these sands are not currently experiencing saltation. Orientations of 1520 features ( such as bed forms and ventifacts) along Spirit's traverse from the landing site ( the Columbia Memorial Station) to West Spur in the Columbia Hills suggest primary formative winds from the north-northwest, which correlate with measurements of features seen in orbiter images and is consistent with afternoon winds predicted by atmospheric models. A secondary wind from the southeast is also suggested, which correlates with predictions for nighttime/early morning winds. Wind abrasion is indicated by ventifacts in the form of facets and grooves cut into rocks, the orientations of which also indicate prevailing winds from the north-northwest. Orientations of many aeolian features in the West Spur area, however, have more scatter than elsewhere along the traverse, which is attributed to the influence of local topography on the patterns of wind. Active dust devils observed on the floor of Gusev from the Columbia Hills demonstrate that dust is currently mobile. Sequential images of some dust devils show movement as rapid as 3.8 m/s, consistent with wind velocities predicted by atmospheric models for the afternoon, when most of the dust devils were observed. Sands accumulated on the rover deck in the same period suggest that some sands in the Columbia Hills experience active saltation. "Two-toned'' rocks having a light band coating at their bases are considered to represent partial burial by soils and subsequent exposure, while "perched'' rocks could represent materials lowered onto other rocks by deflation of supporting soils. Measurements of the heights of the light bands and the perched rocks range from <1 cm to 27 cm, indicating local deflation by as much as 27 cm. C1 Arizona State Univ, Dept Geol Sci, Tempe, AZ 85287 USA. Washington Univ, St Louis, MO 63130 USA. Honeybee Robot, New York, NY 10001 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. Texas A&M Univ, Dept Atmospher Sci, College Stn, TX 77843 USA. SUNY Stony Brook, Dept Geosci, Stony Brook, NY 11794 USA. SW Res Inst, Boulder, CO 80302 USA. Univ Tennessee, Dept Earth & Planetary Sci, Knoxville, TN 37996 USA. Deutsch Zentrum Luft & Raumfahrt, Inst Raumsimulat, D-51170 Cologne, Germany. Cornell Univ, Dept Astron, Ithaca, NY 14853 USA. CVRD Grp, BR-29090900 Vitoria, Brazil. RP Arizona State Univ, Dept Geol Sci, Box 871404, Tempe, AZ 85287 USA. EM greeley@asu.edu; arvidson@wunder.wustl.edu; bartlett@honeybeerobotics.com; diana.blaney@jpl.nasa.gov; ncabrol@mail.arc.nasa.gov; phil.christensen@asu.edu; robin.fergason@asu.edu; mgolombek@jpl.nasa.gov; geoffrey.a.landis@nasa.gov; lemmon@tamu.edu; scott.mclen-nan@sunysb.edu; tmichael@boulder.swri.edu; jmoersch@utk.edu; srafkin@boulder.swri.edu; lutz.richter@dlr.de; squyres@astro.cornell.edu; pasouza03@yahoo.com.br; rjs33@cornell.edu; shane.d.thompson@asu.edu; pwhelley@asu.edu RI de Souza, Paulo/B-8961-2008; Lemmon, Mark/E-9983-2010; Moersch, Jeffrey/F-7189-2010; Whelley, Patrick/B-9560-2012 OI de Souza, Paulo/0000-0002-0091-8925; Lemmon, Mark/0000-0002-4504-5136; Whelley, Patrick/0000-0003-3266-9772 NR 65 TC 152 Z9 152 U1 6 U2 6 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-9097 EI 2169-9100 J9 J GEOPHYS RES-PLANET JI J. Geophys. Res.-Planets PD JAN 6 PY 2006 VL 111 IS E2 AR E02S09 DI 10.1029/2005JE002491 PG 29 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 001CG UT WOS:000234510100004 ER PT J AU Hurowitz, JA McLennan, SM Tosca, NJ Arvidson, RE Michalski, JR Ming, DW Schroder, C Squyres, SW AF Hurowitz, JA McLennan, SM Tosca, NJ Arvidson, RE Michalski, JR Ming, DW Schroder, C Squyres, SW TI In situ and experimental evidence for acidic weathering of rocks and soils on Mars SO JOURNAL OF GEOPHYSICAL RESEARCH-PLANETS LA English DT Article ID X-RAY SPECTROMETER; GUSEV CRATER; MOSSBAUER SPECTROMETER; MERIDIANI-PLANUM; SPIRIT ROVER; SILICICLASTIC SEDIMENTS; DISSOLUTION KINETICS; BASALT; CHEMISTRY; PETROGENESIS AB Experimental data for alteration of synthetic Martian basalts at pH = 0-1 indicate that chemical fractionations at low pH are vastly different from those observed during terrestrial weathering. Rock surface analyses from Gusev crater are well described by the relationships apparent from low-pH experimental alteration data. A model for rock surface alteration is developed, which indicates that a leached alteration zone is present on rock surfaces at Gusev. This zone is not chemically fractionated to a large degree from the underlying rock interior, indicating that the rock surface alteration process has occurred at low water to rock ratio. The geochemistry of natural rock surfaces analyzed by APXS is consistent with a mixture between adhering soil/dust and the leached alteration zone. The chemistry of rock surfaces analyzed after brushing with the RAT is largely representative of the leached alteration zone. The chemistry of rock surfaces analyzed after grinding with the RAT is largely representative of the interior of the rock, relatively unaffected by the alteration process occurring at the rock surface. Elemental measurements from the Spirit, Opportunity, Pathfinder, and Viking 1 landing sites indicate that soil chemistry from widely separated locations is consistent with the low-pH, low water to rock ratio alteration relationships developed for Gusev rocks. Soils are affected principally by mobility of Fe and Mg, consistent with alteration of olivine-bearing basalt and subsequent precipitation of Fe- and Mg-bearing secondary minerals as the primary control on soil geochemistry. C1 SUNY Stony Brook, Dept Geosci, Stony Brook, NY 11794 USA. Washington Univ, Dept Earth & Planetary Sci, St Louis, MO 63130 USA. Arizona State Univ, Dept Geol Sci, Tempe, AZ 85287 USA. NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. Johannes Gutenberg Univ Mainz, Inst Anorgan & Analyt Chem, D-55128 Mainz, Germany. Cornell Univ, Dept Astron, Ithaca, NY 14853 USA. RP SUNY Stony Brook, Dept Geosci, Stony Brook, NY 11794 USA. EM joel.hurowitz@stonybrook.edu RI Hurowitz, Joel/A-8862-2008; Schroder, Christian/B-3870-2009 OI Schroder, Christian/0000-0002-7935-6039 NR 77 TC 107 Z9 108 U1 1 U2 29 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-9097 EI 2169-9100 J9 J GEOPHYS RES-PLANET JI J. Geophys. Res.-Planets PD JAN 6 PY 2006 VL 111 IS E2 AR E02S19 DI 10.1029/2005JE002515 PG 16 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 001CG UT WOS:000234510100007 ER PT J AU McSween, HY Wyatt, MB Gellert, R Bell, JF Morris, RV Herkenhoff, KE Crumpler, LS Milam, KA Stockstill, KR Tornabene, LL Arvidson, RE Bartlett, P Blaney, D Cabrol, NA Christensen, PR Clark, BC Crisp, JA Des Marais, DJ Economou, T Farmer, JD Farrand, W Ghosh, A Golombek, M Gorevan, S Greeley, R Hamilton, VE Johnson, JR Joliff, BL Klingelhofer, G Knudson, AT McLennan, S Ming, D Moersch, JE Rieder, R Ruff, SW Schroder, C de Souza, PA Squyres, SW Wanke, H Wang, A Yen, A Zipfel, J AF McSween, HY Wyatt, MB Gellert, R Bell, JF Morris, RV Herkenhoff, KE Crumpler, LS Milam, KA Stockstill, KR Tornabene, LL Arvidson, RE Bartlett, P Blaney, D Cabrol, NA Christensen, PR Clark, BC Crisp, JA Des Marais, DJ Economou, T Farmer, JD Farrand, W Ghosh, A Golombek, M Gorevan, S Greeley, R Hamilton, VE Johnson, JR Joliff, BL Klingelhofer, G Knudson, AT McLennan, S Ming, D Moersch, JE Rieder, R Ruff, SW Schroder, C de Souza, PA Squyres, SW Wanke, H Wang, A Yen, A Zipfel, J TI Characterization and petrologic interpretation of olivine-rich basalts at Gusev Crater, Mars SO JOURNAL OF GEOPHYSICAL RESEARCH-PLANETS LA English DT Article ID THERMAL EMISSION SPECTROMETER; ELEPHANT MORAINE A79001; X-RAY SPECTROMETER; SPIRIT ROVER; MARTIAN METEORITE; TRACE-ELEMENT; MGS-TES; SHERGOTTITE; ROCKS; SURFACE AB Rocks on the floor of Gusev crater are basalts of uniform composition and mineralogy. Olivine, the only mineral to have been identified or inferred from data by all instruments on the Spirit rover, is especially abundant in these rocks. These picritic basalts are similar in many respects to certain Martian meteorites ( olivine-phyric shergottites). The olivine megacrysts in both have intermediate compositions, with modal abundances ranging up to 20-30%. Associated minerals in both include low-calcium and high-calcium pyroxenes, plagioclase of intermediate composition, iron-titanium-chromium oxides, and phosphate. These rocks also share minor element trends, reflected in their nickel-magnesium and chromium-magnesium ratios. Gusev basalts and shergottites appear to have formed from primitive magmas produced by melting an undepleted mantle at depth and erupted without significant fractionation. However, apparent differences between Gusev rocks and shergottites in their ages, plagioclase abundances, and volatile contents preclude direct correlation. Orbital determinations of global olivine distribution and compositions by thermal emission spectroscopy suggest that olivine-rich rocks may be widespread. Because weathering under acidic conditions preferentially attacks olivine and disguises such rocks beneath alteration rinds, picritic basalts formed from primitive magmas may even be a common component of the Martian crust formed during ancient and recent times. C1 Univ Tennessee, Dept Earth & Planetary Sci, Knoxville, TN 37996 USA. Arizona State Univ, Dept Geol Sci, Tempe, AZ 85287 USA. Max Planck Inst Chem, D-55099 Mainz, Germany. Cornell Univ, Dept Astron, Ithaca, NY 14853 USA. NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. US Geol Survey, Flagstaff, AZ 86001 USA. New Mexico Museum Nat Hist & Sci, Albuquerque, NM 87104 USA. Washington Univ, Dept Earth & Planetary Sci, St Louis, MO 63130 USA. Honeybee Robot, New York, NY 10012 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. Lockheed Martin Corp, Littleton, CO 80127 USA. Univ Chicago, Enrico Fermi Inst, Chicago, IL 60637 USA. Space Sci Inst, Boulder, CO 80301 USA. Univ Hawaii, Hawaii Inst Geophys & Planetol, Honolulu, HI 96822 USA. Johannes Gutenberg Univ Mainz, Inst Anorgan & Analyt Chem, D-55128 Mainz, Germany. SUNY Stony Brook, Dept Geosci, Stony Brook, NY 11794 USA. Companhia Vale Rio Doce, BR-20030900 Rio De Janeiro, Brazil. RP McSween, HY (reprint author), Univ Tennessee, Dept Earth & Planetary Sci, Knoxville, TN 37996 USA. EM mcsween@utk.edu; michael.wyatt@asu.edu; gellert@mpch-mainz.mpg.de; jfb8@cornell.edu; richard.v.morris@nasa.gov; kherkenhoff@usgs.gov; larry_crumpler@mac.com; kmilam@utk.edu; kstockst@utk.edu; ltornabe@utk.edu; arvidson@wunder.wustl.edu; bartlett@honeybeerobotics.com; blaney@jpl.nasa.gov; ncabrol@mail.arc.nasa.gov; phil.christensen@asu.edu; benton.c.clark@lmco.com; joy.crisp@jpl.nasa.gov; david.j.desmarais@nasa.gov; tecon@tecon.uchicago.edu; jfarmer@asu.edu; farrand@colorado.edu; aghosh@cs.utk.edu; matt.golombek@jpl.nasa.gov; govervan@honeybeerobotics.com; greeley@asu.edu; hamilton@higp.hawaii.edu; jrjohnson@usgs.gov; blj@levee.wustl.edu; klingel@mail.uni-mainz.de; amy.knudson@asu.edu; scott.mclennan@sunysb.edu; douglas.w.ming1@jsc.nasa.gov; jmoersch@utk.edu; rieder@mpch-mainz.mpg.de; steve.ruff@asu.edu; schroedc@uni-mainz.de; pasouza03@yahoo.com.br; squyres@astrosun2.astrosun.cornell.edu; waenke@mpch-mainz.mpg.de; alianw@levee.wustl.edu; albert.yen@jpl.nasa.gov; zipfel@mpch-mainz.mpg.de RI de Souza, Paulo/B-8961-2008; Schroder, Christian/B-3870-2009; Moersch, Jeffrey/F-7189-2010; Johnson, Jeffrey/F-3972-2015; Crisp, Joy/H-8287-2016 OI de Souza, Paulo/0000-0002-0091-8925; Schroder, Christian/0000-0002-7935-6039; Crisp, Joy/0000-0002-3202-4416 NR 64 TC 157 Z9 158 U1 5 U2 27 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-9097 EI 2169-9100 J9 J GEOPHYS RES-PLANET JI J. Geophys. Res.-Planets PD JAN 6 PY 2006 VL 111 IS E2 AR E02S10 DI 10.1029/2005JE002477 PG 17 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 001CG UT WOS:000234510100003 ER PT J AU Smith, DE Zuber, MT Sun, XL Neumann, GA Cavanaugh, JF McGarry, JF Zagwodzki, TW AF Smith, DE Zuber, MT Sun, XL Neumann, GA Cavanaugh, JF McGarry, JF Zagwodzki, TW TI Two-way laser link over interplanetary distance SO SCIENCE LA English DT Article C1 NASA, Goddard Space Flight Ctr, Solar Syst Explorat Div, Greenbelt, MD 20771 USA. MIT, Cambridge, MA 02139 USA. RP Smith, DE (reprint author), NASA, Goddard Space Flight Ctr, Solar Syst Explorat Div, Greenbelt, MD 20771 USA. EM dsmith@tharsis.gsfc.nasa.gov RI Sun, Xiaoli/B-5120-2013; McGarry, Jan/C-4109-2013; Neumann, Gregory/I-5591-2013 OI Neumann, Gregory/0000-0003-0644-9944 NR 7 TC 66 Z9 68 U1 2 U2 9 PU AMER ASSOC ADVANCEMENT SCIENCE PI WASHINGTON PA 1200 NEW YORK AVE, NW, WASHINGTON, DC 20005 USA SN 0036-8075 J9 SCIENCE JI Science PD JAN 6 PY 2006 VL 311 IS 5757 BP 53 EP 53 DI 10.1126/science.1120091 PG 1 WC Multidisciplinary Sciences SC Science & Technology - Other Topics GA 001ON UT WOS:000234546300028 PM 16400141 ER PT J AU Sulima, OV Swaminathan, K Refaat, TF Faleev, NN Semenov, AN Solov'ev, VA Ivanov, SV Abedin, MN Singh, UN Prather, D AF Sulima, OV Swaminathan, K Refaat, TF Faleev, NN Semenov, AN Solov'ev, VA Ivanov, SV Abedin, MN Singh, UN Prather, D TI 2.4 mu m Cutoff wavelength AlGaAsSb/InGaAsSb phototransistors SO ELECTRONICS LETTERS LA English DT Article ID RANGE AB The first AlGaAsSb/InGaAsSb phototransistors with a cutoff wavelength (50% of peak responsivity) of 2.4 mu m operating in a broad range of temperatures are reported, These devices are also the first AlGaAsSb/InGaAsSb heterojunction phototransistors (HPT) grown by molecular beam epitaxy (MBE). The new MBF-grown HPT exhibited both high responsivity R (up to 2334A/W for lambda = 2.05 mu m at -20 degrees C) and specific detectivity D* (up to 2.1 x 10(II) cmHz(1/2)/W for lambda=2.05 mu m at -20 degrees C). C1 Univ Delaware, Dept Elect & Comp Engn, Newark, DE 19716 USA. Sci & Technol Corp, Hampton, VA 23666 USA. Ioffe Inst, St Petersburg 194021, Russia. NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Sulima, OV (reprint author), Univ Delaware, Dept Elect & Comp Engn, 140 Evans Hall, Newark, DE 19716 USA. EM osulima@udel.com RI Ivanov, Sergey/C-1177-2014; Semenov, Alexey/E-3203-2014; Solov'ev, Viktor/E-4026-2014 NR 7 TC 4 Z9 4 U1 0 U2 1 PU IEE-INST ELEC ENG PI HERTFORD PA MICHAEL FARADAY HOUSE SIX HILLS WAY STEVENAGE, HERTFORD SG1 2AY, ENGLAND SN 0013-5194 J9 ELECTRON LETT JI Electron. Lett. PD JAN 5 PY 2006 VL 42 IS 1 BP 55 EP 56 DI 10.1049/el:20063904 PG 2 WC Engineering, Electrical & Electronic SC Engineering GA 012FC UT WOS:000235322600036 ER PT J AU Brain, DA Halekas, JS Peticolas, LM Lin, RP Luhmann, JG Mitchell, DL Delory, GT Bougher, SW Acuna, MH Reme, H AF Brain, DA Halekas, JS Peticolas, LM Lin, RP Luhmann, JG Mitchell, DL Delory, GT Bougher, SW Acuna, MH Reme, H TI On the origin of aurorae on Mars SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID MAGNETIC-FIELD; PARTICLE PRECIPITATION; IONOSPHERE AB We report observations by Mars Global Surveyor (MGS) of thousands of peaked electron energy spectra similar to terrestrial auroral electrons. They are observed on the Martian nightside, near strong crustal magnetic sources. The spectra have peak energies ranging from 100 eV-2.5 keV, and fluxes near the peak are 10-10000 times higher than typical nightside spectra. They occur on magnetic field lines that connect the shocked solar wind to crustal magnetic fields, and on adjacent closed field lines. Their detection is directly controlled by the solar wind, suggesting that magnetic reconnection is required for their observation. We calculate that the most energetic distributions could produce atmospheric emission with intensity comparable to that recently reported from the Mars Express (MEX) spacecraft. Half of the most energetic examples occur during the passage of space weather events past Mars, suggesting that a disturbed plasma environment is favorable for electron acceleration along magnetic field lines. C1 Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. Univ Michigan, Dept Space Sci, Ann Arbor, MI 48109 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Ctr Etud Spatiale Rayonnements, F-31028 Toulouse, France. RP Brain, DA (reprint author), Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. EM brain@ssl.berkeley.edu RI Bougher, Stephen/C-1913-2013; OI Bougher, Stephen/0000-0002-4178-2729; Halekas, Jasper/0000-0001-5258-6128 NR 18 TC 80 Z9 81 U1 0 U2 0 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0094-8276 J9 GEOPHYS RES LETT JI Geophys. Res. Lett. PD JAN 5 PY 2006 VL 33 IS 1 AR L01201 DI 10.1029/2005GL024782 PG 4 WC Geosciences, Multidisciplinary SC Geology GA 001BX UT WOS:000234509200005 ER PT J AU Deshler, T Anderson-Sprecher, R Jager, H Barnes, J Hofmann, DJ Clemesha, B Simonich, D Osborn, M Grainger, RG Godin-Beekmann, S AF Deshler, T Anderson-Sprecher, R Jager, H Barnes, J Hofmann, DJ Clemesha, B Simonich, D Osborn, M Grainger, RG Godin-Beekmann, S TI Trends in the nonvolcanic component of stratospheric aerosol over the period 1971-2004 SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article ID SAGE-II; EL-CHICHON; VOLCANIC-ERUPTIONS; OZONE DEPLETION; NORTHERN MIDLATITUDES; LIDAR MEASUREMENTS; PINATUBO ERUPTION; GAS EXPERIMENT; VERTICAL DISTRIBUTION; BACKGROUND AEROSOL AB [1] The six longest records of stratospheric aerosol ( in situ measurements at Laramie, Wyoming, lidar records at: Garmisch-Partenkirchen, Germany; Hampton, Virginia; Mauna Loa, Hawaii; Sao Jose dos Campos, Brazil, and SAGE II measurements) were investigated for trend by ( 1) comparing measurements in the 3 volcanically quiescent periods since 1970 using standard analysis of variance techniques, and ( 2) analyzing residuals from a time/volcano dependent empirical model applied to entire data sets. A standard squared-error residual minimization technique was used to estimate optimum parameters for each measurement set, allowing for first order autocorrelation, which increases standard errors of trends but does not change magnitude. Analysis of variance over the 3 volcanically quiescent periods is controlled by the end points (pre-El Chichon and post-Pinatubo), and indicates either no change (Garmisch, Hampton, Sao Jose dos Campos, Laramie-0.15 mu m) or a slight, statistically insignificant, decrease ( Mauna Loa, Laramie-0.25 mu m), - 1 +/- 0.5% yr(-1). The empirical model was applied to the same records plus 1020 nm SAGE II data separated into 33 latitude/altitude bins. No trend in stratospheric aerosol was apparent for 31 of 33 SAGE II data sets, 3 of 4 lidar records, and in situ measurements at 0.15 mu m. For Hampton and Laramie-0.25 mu m, the results suggest a weak negative trend, - 2 +/- 0.5% yr(-1), while 2 SAGE II data sets ( 30 - 35 km, 30 degrees and 40 degrees N) suggest a positive trend of similar magnitude. Overall we conclude that no long-term change in background stratospheric aerosol has occurred over the period 1970 - 2004. C1 Univ Wyoming, Dept Atmospher Sci, Laramie, WY 82071 USA. Univ Wyoming, Dept Stat, Laramie, WY 82071 USA. Forschungszentrum Karlsruhe, IMK IFU, D-82467 Garmisch Partenkirchen, Germany. Natl Ocean & Atmospher Adm, Boulder, CO 80305 USA. Inst Nacl Pesquisas Espaciais, BR-12227010 Sao Jose Dos Campos, Brazil. NASA, Langley Res Ctr, Hampton, VA 23666 USA. Univ Oxford, Oxford OX1 3PU, England. CNRS, Inst Pierre Simon Laplace, Serv Aeron, F-75252 Paris, France. RP Deshler, T (reprint author), Univ Wyoming, Dept Atmospher Sci, Laramie, WY 82071 USA. EM deshler@uwyo.edu RI Grainger, Roy/E-8823-2011; Garmisch-Pa, Ifu/H-9902-2014 OI Grainger, Roy/0000-0003-0709-1315; NR 97 TC 40 Z9 45 U1 0 U2 9 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-897X J9 J GEOPHYS RES-ATMOS JI J. Geophys. Res.-Atmos. PD JAN 5 PY 2006 VL 111 IS D1 AR D01201 DI 10.1029/2005JD006089 PG 21 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 001CD UT WOS:000234509800001 ER PT J AU Sauvage, B Thouret, V Thompson, AM Witte, JC Cammas, JP Nedelec, P Athier, G AF Sauvage, B Thouret, V Thompson, AM Witte, JC Cammas, JP Nedelec, P Athier, G TI Enhanced view of the "tropical Atlantic ozone paradox'' and "zonal wave one'' from the in situ MOZAIC and SHADOZ data SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article ID MAPPING SPECTROMETER TOMS; TROPOSPHERIC COLUMN OZONE; HEMISPHERE WINTER SEASON; BIOMASS FIRE EMISSIONS; TRACE-A; VERTICAL TRANSPORTS; REGIONAL ASPECTS; CLIMATOLOGY; AIRCRAFT; MAXIMUM AB [1] Ozone vertical profiles from the Measurements of Ozone from Airbus In-service Aircraft (MOZAIC) program over Africa are used to complement pictures of the wave-one pattern and the "tropical Atlantic paradox'' identified through soundings in the Southern Hemisphere Additional Ozonesondes (SHADOZ) network. The Atlantic paradox refers to a greater tropospheric ozone column amount over the South Atlantic than the North Atlantic during the West African biomass burning season. SHADOZ and MOZAIC data from 1998 - 2002 and 1997 - 2004, respectively, are used to show that these two phenomena are linked. The combined data are used to address the following: Does the ( continental) MOZAIC data modify the appearance of the paradox? Do lower tropospheric MOZAIC data lead to new conclusions about ozone in the wave-one maximum region? During December, January, and February (DJF), the lower troposphere over Africa exhibits a higher ozone signal in the burning hemisphere, that is, north of the equator, so the "paradox'' does not appear over the African continent. The MOZAIC data set over Africa highlights another component of the wave-one feature when the tropospheric ozone mixing ratio is viewed in zonal cross section. The lower troposphere makes a nonnegligible contribution to the regionally higher ozone column during the biomass burning periods of each hemisphere ( DJF) for West Africa and June, July, and August (JJA) for the central Africa region. A southern preference for the wave-one character, previously deduced from satellite data, is confirmed with a stronger maximum in September, October, and November ( SON). Both the paradox and wave-one phenomena are consistent with a view that the African continent is a major source of biomass burning and lightning emissions. C1 Univ Toulouse 3, Observ Midi Pyrenees, Lab Aerol, UMR 5560, F-31400 Toulouse, France. Penn State Univ, Dept Meteorol, University Pk, PA 16802 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Sci Syst & Applicat Inc, Lanham, MD USA. RP Univ Toulouse 3, Observ Midi Pyrenees, Lab Aerol, UMR 5560, 14 Ave E Belin, F-31400 Toulouse, France. EM saub@aero.obs-mip.fr RI Thompson, Anne /C-3649-2014 OI Thompson, Anne /0000-0002-7829-0920 NR 37 TC 38 Z9 38 U1 0 U2 9 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-897X EI 2169-8996 J9 J GEOPHYS RES-ATMOS JI J. Geophys. Res.-Atmos. PD JAN 5 PY 2006 VL 111 IS D1 AR D01301 DI 10.1029/2005JD006241 PG 10 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 001CD UT WOS:000234509800003 ER PT J AU Bradshaw, RC Arsenault, AD Hyers, RW Rogers, JR Rathz, TJ Lee, GW Gangopadhyay, AK Kelton, KF AF Bradshaw, RC Arsenault, AD Hyers, RW Rogers, JR Rathz, TJ Lee, GW Gangopadhyay, AK Kelton, KF TI Nonlinearities in the undercooled properties of Ti39.5Zr39.5Ni21 SO PHILOSOPHICAL MAGAZINE LA English DT Article; Proceedings Paper CT 9th International Conference on Quasicrystals (ICQ9) CY MAY 22-26, 2005 CL Iowa State Univ Ames, Ames, IA HO Iowa State Univ Ames AB Using electrostatic-levitator (ESL)-based containerless processing combined with non-contact measuring techniques, surface tension and viscosity have been measured for Ti39.5Zr39.5Ni21, using the oscillating-drop method, in the superheated and metastable undercooled liquid states. Viscosity measurements show a non-Arrhenius behaviour that more closely matches a Vogel-Tamman Fulcher trend, and a sudden divergence away from a high-temperature linear trend in surface tension has been observed for this composition. An overview of the measurement technique as well as the measurements are presented. C1 Univ Massachusetts, Dept Mech & Ind Engn, Amherst, MA 01003 USA. NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. Univ Alabama, Mat Res Ctr, Huntsville, AL 35899 USA. Lawrence Livermore Natl Lab, Livermore, CA 94550 USA. Washington Univ, Dept Phys, St Louis, MO 63130 USA. RP Hyers, RW (reprint author), Univ Massachusetts, Dept Mech & Ind Engn, Amherst, MA 01003 USA. EM hyers@ecs.umass.edu RI Hyers, Robert/G-3755-2010 NR 20 TC 5 Z9 5 U1 0 U2 3 PU TAYLOR & FRANCIS LTD PI ABINGDON PA 4 PARK SQUARE, MILTON PARK, ABINGDON OX14 4RN, OXON, ENGLAND SN 1478-6435 J9 PHILOS MAG JI Philos. Mag. PY 2006 VL 86 IS 3-5 BP 341 EP 347 DI 10.1080/14786430500253968 PG 7 WC Materials Science, Multidisciplinary; Metallurgy & Metallurgical Engineering; Physics, Applied; Physics, Condensed Matter SC Materials Science; Metallurgy & Metallurgical Engineering; Physics GA 003VX UT WOS:000234711000014 ER PT J AU Sun, GY AF Sun, GY TI Rotor drop and following thermal growth simulations using detailed auxiliary bearing and damper models SO JOURNAL OF SOUND AND VIBRATION LA English DT Article ID DYNAMICS AB Catcher bearings (CBs) or auxiliary bearings provide mechanical backup protection in the events of magnetic bearing failure. This paper presents numerical analysis for a rotor drop on CBs and following thermal growths due to their mechanical rub using detailed CB and damper models. The detailed CB model is determined based on its material, geometry, speed and preload using the nonlinear Hertzian load-deflection formula, and the thermal growths of bearing components during the rotor drop are estimated using a ID thermal model. A finite-element squeeze film damper provides the pressure profile of an annular oil film and the resulting viscous damping force. Numerical simulations of an energy storage flywheel with magnetic suspensions failed reveal that an optimal CB design using the detailed simulation models stabilizes the rotor drop dynamics and lowers the thermal growths while preventing the high-speed backward whirl. Furthermore, CB design guides based on the simulation results are presented. (c) 2005 Elsevier Ltd. All rights reserved. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Sun, GY (reprint author), NASA, Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. EM guangdol@hotmail.com NR 20 TC 23 Z9 28 U1 1 U2 12 PU ACADEMIC PRESS LTD ELSEVIER SCIENCE LTD PI LONDON PA 24-28 OVAL RD, LONDON NW1 7DX, ENGLAND SN 0022-460X J9 J SOUND VIB JI J. Sound Vibr. PD JAN 3 PY 2006 VL 289 IS 1-2 BP 334 EP 359 DI 10.1016/j.jsv.2005.02.008 PG 26 WC Acoustics; Engineering, Mechanical; Mechanics SC Acoustics; Engineering; Mechanics GA 985RV UT WOS:000233396900018 ER PT J AU Bozzolo, G Lukaszew, RA Garces, JE AF Bozzolo, G Lukaszew, RA Garces, JE TI Atomistic modeling of surface alloy ordering and segregation in the Fe-Pt system SO APPLIED PHYSICS LETTERS LA English DT Article ID THIN-FILMS AB A unified description of Pt segregation in Fe-Pt alloys and alloy ordering after Fe deposition on a Pt substrate is provided. Atomistic modeling using the Bozzolo-Ferrante-Smith quantum approximate method for alloys explains the mechanisms leading to full Pt segregation in the first case and a stable mixed Fe-Pt surface with subsurface ordering in the second. (c) 2006 American Institute of Physics. C1 Ohio Aerosp Inst, Cleveland, OH 44142 USA. NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. Univ Toledo, Dept Phys & Astron, Toledo, OH 43606 USA. Comis Nacl Energia Atom, Ctr Atom Bariloche, RA-8400 San Carlos De Bariloche, Rio Negro, Argentina. RP Bozzolo, G (reprint author), Ohio Aerosp Inst, Cleveland, OH 44142 USA. EM guillermobozzolo@oai.org NR 11 TC 11 Z9 11 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA CIRCULATION & FULFILLMENT DIV, 2 HUNTINGTON QUADRANGLE, STE 1 N O 1, MELVILLE, NY 11747-4501 USA SN 0003-6951 J9 APPL PHYS LETT JI Appl. Phys. Lett. PD JAN 2 PY 2006 VL 88 IS 1 AR 011915 DI 10.1063/1.2158515 PG 3 WC Physics, Applied SC Physics GA 999YM UT WOS:000234428100029 ER PT J AU Liu, Y Ruden, PP Xie, J Morkoc, H Son, KA AF Liu, Y Ruden, PP Xie, J Morkoc, H Son, KA TI Effect of hydrostatic pressure on the dc characteristics of AlGaN/GaN heterojunction field effect transistors SO APPLIED PHYSICS LETTERS LA English DT Article ID HETEROSTRUCTURES; POLARIZATION; HEMTS; GAN AB We report the effect of compressive hydrostatic pressure on the current-voltage characteristics of AlGaN/GaN heterojunction field effect transistors (HFETs) on a sapphire substrate. The drain current increases with hydrostatic pressure and the maximum relative increase occurs when the gate bias is near threshold and drain bias is slightly larger than saturation bias. The increase of the drain current is associated with a pressure induced shift of the threshold voltage by -8.0 mV/kbar that is attributed to an increase of the polarization charge density at the AlGaN/GaN interface due to the piezoelectric effect. The results demonstrate the considerable potential of AlGaN/GaN HFETs for strain sensor applications. (c) 2006 American Institute of Physics. C1 Univ Minnesota, Dept Elect & Comp Engn, Minneapolis, MN 55455 USA. Virginia Commonwealth Univ, Dept Elect Engn, Richmond, VA 23284 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Liu, Y (reprint author), Univ Minnesota, Dept Elect & Comp Engn, 200 Union St SE, Minneapolis, MN 55455 USA. EM liux0280@umn.edu NR 15 TC 29 Z9 29 U1 1 U2 9 PU AMER INST PHYSICS PI MELVILLE PA CIRCULATION & FULFILLMENT DIV, 2 HUNTINGTON QUADRANGLE, STE 1 N O 1, MELVILLE, NY 11747-4501 USA SN 0003-6951 J9 APPL PHYS LETT JI Appl. Phys. Lett. PD JAN 2 PY 2006 VL 88 IS 1 AR 013505 DI 10.1063/1.2161812 PG 3 WC Physics, Applied SC Physics GA 999YM UT WOS:000234428100084 ER PT J AU Terdik, G Woyczynski, WA Piryatinska, A AF Terdik, G Woyczynski, WA Piryatinska, A TI Fractional- and integer-order moments, and multiscaling for smoothly truncated Levy flights SO PHYSICS LETTERS A LA English DT Article DE truncated Levy flights; multiscaling; fractional- and integer-order moments ID STOCHASTIC-PROCESS; CONVERGENCE AB We study multiscale properties of smoothly truncated Levy flights. The behavior of both fractional- and integer-order moments Pulsed Cavity Ringdown Laser Absorption Spectroscopy in a Hollow Waveguide SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID ION AB Cavity Ringdown(1,2) Laser Absorption Spectroscopy (CRDS) is a modified version of standard absorption spectroscopy (AS) for providing extremely sensitive measurements of gas species absorbing at a particular wavelength in a gas cell volume. Typically, the enhancement in sensitivity with CRDS is a 10(2)-10(3) improvement over AS. Herein, we analyze incorporating pulsed CRDS into a hollow-waveguide (HWG) both for reducing the sample volume as well as enhancing the signal-to-noise ratio (SNR) by up to similar to 10(4) by injecting light into the HWG cavity through a small aperture in one of the cell mirrors. For low power instrument applications (i.e. planetary science), the enhancement in SNR results in a potential similar to 10(4) reduction in laser power for a comparable PRDS terrestrial laboratory measurement at one extreme, or a potential similar to 10(8) improvement in CRDS temporal resolution through reduced sample averaging with a fixed low-power laser source. A pulsed (vs. CW) laser source is employed to remove the requirement for a precision tuned laser cavity at similar to wavelength spatial resolutions. C1 [Mungas, Greg S.] Firestar Engn LLC, Jet Prop Lab, M-S 301-445,4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Dreyer, Christopher] CSR, Colorado Sch Mines, Golden, CO 80401 USA. RP Mungas, GS (reprint author), Firestar Engn LLC, Jet Prop Lab, M-S 301-445,4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM greg.s.mungas@jpl.nasa.gov; cdreyer@mines.edu FU NASA ASTID [NNG04GN40G] FX This work is supported under NASA ASTID NNG04GN40G. NR 15 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 412 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583100039 ER PT S AU Tripathi, RK Wilson, JW Youngquist, RC AF Tripathi, Ram K. Wilson, John W. Youngquist, Robert C. GP IEEE TI Electrostatic Active Radiation Shielding - Revisited SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB For the success of NASA's new vision for space exploration to Moon, Mars and beyond, exposures from the hazards of severe space radiation in deep space long duration missions is 'a must solve' problem The payload penalty demands a very stringent requirement on the design of the spacecrafts for human deep space missions. Langley has developed state-of-the-art radiation protection and shielding technology for space missions. The exploration beyond low Earth orbit (LEO) to enable routine access to space will require protection from the hazards of the accumulated exposures of space radiation, Galactic Cosmic Rays (GCR) and Solar Particle Events (SPE), and minimizing the production of secondary radiation is a great advantage. There is a need to look to new horizons for newer technologies. The present investigation revisits electrostatic active radiation shielding and explores the feasibility of using the electrostatic shielding in concert with the innovative materials shielding and protection technologies. The full space radiation environment has been used for the investigation. The goal is to repel enough positive charge ions so that they miss the spacecraft without attracting thermal electrons. Conclusions are drawn, should the electrostatic shielding be successful, for the future directions of space radiation protection. C1 [Tripathi, Ram K.; Wilson, John W.] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Youngquist, Robert C.] NASA, Kennedy Space Ctr, FL 32899 USA. RP Tripathi, RK (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM ram.k.tripathi@larc.nasa.gov; Robert.C.Youngquist@nasa.gov NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 444 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583100042 ER PT S AU Kowbel, W Bruce, C Withers, JC AF Kowbel, W. Bruce, C. Withers, J. C. GP IEEE TI Boron Based Advanced Materials For Radiation Protection SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Future space systems developed under NASA Space Initiative need to address the issue of radiation protection in conjunction with multifunctional requirements. The state-of-the-art (SOTA) thermal protection systems are based upon low density carbon insulation and phenolic based ablatives. Such systems are not optimized for radiation resistance. A novel approach to thermal protection incorporating radiation protection was developed. This new system is based upon boron-foam with a specifically designed, functionally graded thermal protection system. C1 [Kowbel, W.; Bruce, C.; Withers, J. C.] MER Corp, 2650 Elvira Rd, Tucson, AZ 85706 USA. NASA, LaRC, Hampton, VA 23665 USA. RP Kowbel, W (reprint author), MER Corp, 2650 Elvira Rd, Tucson, AZ 85706 USA. EM kowbel@mercorp.com NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 458 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583100044 ER PT S AU Pinsky, LS Andersen, V Elkhayari, N Empl, A Lebourgeois, M Lee, K Mayes, B Smirnov, G Zapp, N Ferrari, A Roesler, S Vlachoudis, V Battistoni, G Campanella, M Cerutti, F Gadioli, E Garzelli, MV Muraro, S Rancati, T Sala, P Ballarini, F Ottolenghi, A Scannicchio, D Carboni, M Pelliccioni, M Wilson, T Ranft, J Fasso, A AF Pinsky, Lawrence S. Andersen, Victor Elkhayari, Najib Empl, Anton Lebourgeois, Matthew Lee, Kerry Mayes, Billy Smirnov, Georgi Zapp, Neal Ferrari, Alfredo Roesler, Stefan Vlachoudis, Vasilis Battistoni, Giuseppe Campanella, Mauro Cerutti, Francesco Gadioli, Ettore Garzelli, Maria-Vittoria Muraro, Silvia Rancati, Tiziana Sala, Paola Ballarini, Francesca Ottolenghi, Andrea Scannicchio, Domenico Carboni, Massimo Pelliccioni, Maurizio Wilson, Thomas Ranft, Johannes Fasso, Alberto GP IEEE TI FLUKA Status And Preliminary Results From the July-2005 AGS Run SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB As-12 reported in 2005 Aerospace Conference, the FLUKA Monte Carlo code is being modified as part of NASA's Space Radiation Shielding Program for use in simulating the Space Radiation environment in order to evaluate the properties of spacecraft and habitat shielding. Since the last workshop, several notable enhancements have been made to the FLUKA code itself and the ancillary support software. These include improvements to the GUI-based packages for analysis of the results as well as GUI-based tools to ease the setup and running of the programs. Examples of these will be presented. From the physics perspective, an accelerator run this July at the AGS was undertaken in collaboration with the groups from LBL and MSFC to measure the fragmentation, neutron and secondary charged particle spectra from Fe, Si and C beams at 3, 5 and 10 GeV/A on a variety of targets including C, Al, Fe, Cu and Polyethylene. This energy range is the crossover point in event generator technique and the data will help guide the evolution of the event generators in this crucial region. Preliminary results from this run will be presented for the angular distribution of the secondary charged particles from scattering angles of 3-45 degrees along with normalized comparisons to RQMD and DPMJET, the event generators that are currently employed within FLUKA. C1 [Pinsky, Lawrence S.; Andersen, Victor; Elkhayari, Najib; Empl, Anton; Lebourgeois, Matthew; Lee, Kerry; Mayes, Billy; Smirnov, Georgi] Univ Houston, Dept Phys, 4800 Calhoun Blvd, Houston, TX 77204 USA. [Zapp, Neal; Ferrari, Alfredo; Roesler, Stefan; Vlachoudis, Vasilis] CERN, Geneva, Switzerland. [Battistoni, Giuseppe; Campanella, Mauro; Cerutti, Francesco; Gadioli, Ettore; Garzelli, Maria-Vittoria; Muraro, Silvia; Rancati, Tiziana; Sala, Paola] Univ Milan, INFN, Milan 20133, Italy. [Ballarini, Francesca; Ottolenghi, Andrea; Scannicchio, Domenico] Univ Pavia, INFN, Pavia 27100, Italy. [Carboni, Massimo; Pelliccioni, Maurizio] INFN, Lab Nazl Frascati, Frascati 00044, Italy. [Wilson, Thomas] NASA, JSC, Houston, TX 77058 USA. [Ranft, Johannes] Univ Siegen, Dept Phys, D-57068 Siegen, Germany. [Fasso, Alberto] Stanford Linear Accelerator Ctr, Menlo Pk, CA 94025 USA. RP Pinsky, LS (reprint author), Univ Houston, Dept Phys, 4800 Calhoun Blvd, Houston, TX 77204 USA. EM pinsky@uh.edu NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 465 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583100045 ER PT S AU Turner, PR Herrell, LM AF Turner, Philip R. Herrell, Linda M. GP IEEE TI Formulation Refinement and Access to Space for the ST8 Mission SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB (12)-NASA's The New Millennium Program (NMP) approach to space flight validation of advanced technologies is to alternate between subsystem and system flight validations [1]. Candidates for each NMP project (subsystem or system) are competed through a NASA Research Announcement process, and proposal selection is determined by NASA Headquarters. Space Technology 8 (ST8) is the second NMP subsystem project. It will host four technology experiments selected from technology capability areas: The SAILMAST, a light-weight, deployable boom for potential solar sail structural applications The Next Generation Ultraflex (NGU), a lightweight, deployable solar panel The Environmentally Adaptive Fault Tolerant Computing (EAFTC) experiment, a Commercial-Off-The-Shelf (COTS) electronics package for validation of high speed computing in a radiation environment The Miniature Loop Heat Pipe (MLHP), a small spacecraft thermal control subsystem experiment The launch is planned for early 2009 on a Pegasus XL launch vehicle. Access to space for ST8 involves working with the technology experiment development activity to baseline a mission, procuring a spacecraft bus to host the experiments and procuring appropriate launch services through NASA Because of the competitive element of NMP, however, the mission concept and preliminary spacecraft bus requirements were developed in parallel with the independent development of the technology experiment proposals. This initial part of the mission formulation process and the interaction between the NMP project architects and the experiment selection process is described in an earlier paper [2]. The selection of the technology payloads is a key step towards developing the procurement of the spacecraft bus(3) and evaluating competing launch services approaches. An earlier "Space Technology Carrier", study confirmed the feasibility of obtaining a spacecraft bus from among available commercial design concepts. Additional steps used to proceed included: Confirmation of capabilities and cost projections. Development of top level requirements on the bus. Evaluating competing launch services options Developing materials to support a procurement activity This paper tells the story of these steps in the formulation refinement of the ST8 mission leading to its establishment as a formal flight project, with some insights and comments on the benefits and risks of the approach. C1 [Turner, Philip R.; Herrell, Linda M.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Turner, PR (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Philip.R.Turner@jpl.nasa.gov; Linda.M.Herrell@jpl.nasa.gov NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 486 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583100047 ER PT S AU Herrell, L Zhou, X AF Herrell, L. Zhou, X. GP IEEE TI Access to Space for Technology Validation Missions: Exploring Possibilities of Suborbital Flight SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID BALLOON AB Space technology experiments and validation missions share a common dilemma with the aerospace community in general: the high cost of access to space. Whether the experiment is a so-called university cubesat, a technology experiment, or a NASA New Millennium Program (NMP) technology validation mission, the access to space approach must be scaled appropriately: a cubesat might fly as one of a number of cubesats that negotiate a flight on an experimental vehicle; a technology experiment might do the same; a NASA flight validation might partner with another NASA or Air Force experimental mission.(1,2) But are there other options, and what are the benefits of one approach over another? What are the limitations of one approach over another? How can one assess the viability for a particular experiment? How does one go about acquiring such a space access? What experiments originally considered for space-flight might be validated instead in a suborbital environment? New vehicles, most notably unmanned aerial vehicles, are pushing existing capability to higher and higher altitudes and longer duration flights. Reliable suborbital flights and long-used balloon flights can now be applied to new, different payloads as the technology needs change over time. So what are the similarities and differences between the space and suborbital flights? Where are these programs managed, and with what capabilities both existing (proven) and new? This guide is written for the space experimenter seeking an understanding of the issues which will drive a large part of the design of a space experiment - the method of access to space. Since this is, indeed, rocket science, this guide can only serve as a starting point for the reader. The range of suborbital capabilities is so broad - flights cover an altitude range from 3 km to 1400 km, the payload weight from 1 to 3600 kg, the flight time from 5 min to more than 100 days, and the cost from few thousand to tens of millions of dollars - that farther research and data will be required. This paper can only point the way to the start of an assessment. With the range of flight possibilities so broad (a dilemma of too many parameters and too many unknowns), two constraints are established to provide a reference for discussion: 1) Earth science measurements are presented as an example of the range of space flight needs as they can apply to the suborbital regime. 2) A sample set of space technologies is considered in the suborbital regime. With these constraints in place, a framework is established to compare and contrast these different suborbital options. C1 [Herrell, L.; Zhou, X.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Herrell, L (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Linda.Herrell@jpl.nasa.gov; Xiaoyan.Zhou@jpl.nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 492 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583100048 ER PT S AU Franklin, S Ku, JT Spence, B McEachen, M White, S Samson, J Some, R Zsoldos, J AF Franklin, Stephen Ku, Jentung Spence, Brian McEachen, Mike White, Steve Samson, John Some, Rafael Zsoldos, Jennifer GP IEEE TI The Space Technology 8 Mission SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB The Space Technology 8 (ST8) mission is the latest in NASA's New Millennium Program technology demonstration missions. ST8 includes a spacecraft bus built by industry, flying four new technology payloads in low-Earth orbit. This paper will describe each payload, along with a brief description of the mission and spacecraft. The payloads include a miniature loop heat pipe intended to save mass and power on future small satellites, designed and built by NASA's Goddard Space Flight Center; a lightweight, 35g/m linear mass, 40-m deployable boom intended as a future solar sail mast built by ATK Space Systems; a deployable, lightweight Ultraflex solar array producing 175W/kg, also built by ATK Space Systems; and a high-speed, parallel-processing computer system built of state-of-the-art COTS processors, demonstrating SEU tolerance without the need for radiation-hardened electronics, and 100M operations per second per Watt processing throughput density. C1 [Franklin, Stephen] CALTECH, Jet Propuls Lab, Pasadena, CA 91125 USA. [Spence, Brian; McEachen, Mike; White, Steve] ATK Space Syst, Goleta, CA 93117 USA. [Ku, Jentung] NASA, Goddard Spaceflight CTR, Greenbelt, MD 20771 USA. RP Franklin, S (reprint author), CALTECH, Jet Propuls Lab, Pasadena, CA 91125 USA. NR 14 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 501 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583100049 ER PT S AU Carlisle, CC Le, G Slavin, JA VanSant, JT Webb, EH AF Carlisle, Candace C. Le, Guan Slavin, James A. VanSant, J. Timothy Webb, Evan H. GP IEEE TI Goddard Spaceflight Center SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB The Space Technology 5 (ST5) Project, part of NASA's New Millennium Program, will consist of a constellation of three micro-satellites. The validation objectives are to demonstrate the research-quality science capability of the ST5 spacecraft; to operate the three spacecraft as a constellation; and to design, develop, test and flight-validate three capable micro-satellites with new technologies. The project team has made significant progress in the past year in building and testing the ground system and flight hardware. Through component-level testing and spacecraft integration and test, many components have been demonstrated on the ground to begin achieving the validation objectives. We are on target for our February 28, 2006 launch date. A three-month flight demonstration phase is planned, during which we will complete the flight validation objectives. This paper describes the validation strategy for science capability, constellation operations, and spacecraft and component technologies, as well as progress made to date.(1,2) C1 [Carlisle, Candace C.; Le, Guan; Slavin, James A.; VanSant, J. Timothy; Webb, Evan H.] NASA, Goddard Space Flight Ctr, Space Technol 5 Project,Code 495, Greenbelt, MD 20771 USA. RP Carlisle, CC (reprint author), NASA, Goddard Space Flight Ctr, Space Technol 5 Project,Code 495, Greenbelt, MD 20771 USA. EM Candace.Carlisle@nasa.gov; Guan.Le@nasa.gov; James.A.Slavin@nasa.gov; John.T.VanSant@nasa.gov; Evan.H.Webb@nasa.gov RI Le, Guan/C-9524-2012; Slavin, James/H-3170-2012 OI Le, Guan/0000-0002-9504-5214; Slavin, James/0000-0002-9206-724X NR 1 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 517 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583100050 ER PT S AU Sherwood, R Chien, S Tran, D Cichy, B Castano, R Davies, A Rabideau, G AF Sherwood, Rob Chien, Steve Tran, Daniel Cichy, Benjamin Castano, Rebecca Davies, Ashley Rabideau, Gregg GP IEEE TI Autonomous Science Agents and Sensor Webs: EO-1 and Beyond SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB An Autonomous Science Agent, part of the New Millennium Space Technology 6 Project is currently flying onboard the Earth Observing One (EO-1) Spacecraft. This software enables the spacecraft to autonomously detect and respond to science events occurring on the Earth. The package includes software systems that perform science data analysis, deliberative planning, and run-time robust execution. This software has demonstrated the potential for space missions to use onboard decision-making to detect, analyze, and respond to science events, and to downlink only the highest value science data. As a result, ground-based mission planning and analysis functions have been greatly simplified, thus reducing operations cost. We will describe several technology infusions applications being developed. We will also describe how the software has been used in conjunction with other satellites and ground sensors to form an autonomous sensor-web.(1) C1 [Sherwood, Rob; Chien, Steve; Tran, Daniel; Cichy, Benjamin; Castano, Rebecca; Davies, Ashley; Rabideau, Gregg] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Sherwood, R (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Rob.Sherwood@jpl.nasa.gov NR 17 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 527 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583100051 ER PT S AU Carmain, A Dunn, C Folkner, W Hruby, V Spence, D Demmons, N Roy, T McCormick, R Gasdaska, C Young, J Connolly, W O'Donnell, J Markley, F Maghami, P Hsu, O AF Carmain, A. Dunn, C. Folkner, W. Hruby, V. Spence, D. Demmons, N. Roy, T. McCormick, R. Gasdaska, C. Young, J. Connolly, W. O'Donnell, J. Markley, F. Maghami, P. Hsu, O. GP IEEE TI Space technology 7 Disturbance Reduction System - Precision control flight validation SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB (1,2)-The NASA New Millennium Program Space Technology 7 (ST7) project will validate technology for precision spacecraft control. The Disturbance Reduction System (DRS) will be part of the European Space Agency's LISA Pathfinder project. The DRS will control the position of the spacecraft relative to a reference to an accuracy of one nanometer over time scales of several thousand seconds. To perform the control, the spacecraft will use a new colloid thruster technology. The thrusters will operate over the range of 5 to 30 micro-Newtons with precision of 0.1 micro-Newton. The thrust will be generated by using a high electric field to extract charged droplets of a conducting colloid fluid and accelerating them with a precisely adjustable voltage. The control reference will be provided by the European LISA Technology Package, which will include two nearly free-floating test masses. The test mass positions and orientations will be measured using a capacitance bridge. The test mass position and attitude will be adjustable using electrostatically applied forces and torques. The DRS will control the spacecraft position with respect to one test mass while minimizing disturbances on the second test mass. The dynamic control system will cover eighteen degrees of fteedom: six for each of the test masses and six for the spacecraft. After launch in late 2009 to a low Earth orbit, the LISA Pathfinder spacecraft will be maneuvered to a halo orbit about the Earth-Sun L1 Lagrange point for operations. C1 [Carmain, A.; Dunn, C.; Folkner, W.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Hruby, V.; Spence, D.; Demmons, N.; Roy, T.; McCormick, R.; Gasdaska, C.; Young, J.; Connolly, W.] Busek Co Inc, Natick, MA 07160 USA. [O'Donnell, J.; Markley, F.; Maghami, P.; Hsu, O.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Carmain, A (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM andrew.carmain@jpl.nasa.gov; vhraby@busek.com; james.r.odonnell@gsfc.nasa.gov FU National Aeronautics and Space Administration FX The research described in this paper was, in part, carried out by the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 537 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583100052 ER PT S AU Lee, S Lee, CH Kerridge, S Edwards, CD Cheung, KM AF Lee, Seungwon Lee, Charles H. Kerridge, Stuart Edwards, Charles D. Cheung, Kar-Ming GP IEEE TI Orbit design and optimization based on global telecommunication performance metrics SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB The orbit selection of telecommunications orbiters is one of the critical design processes and should be guided by mission-specific performance metrics and constraints. In order to aid the orbit selection process, we have coupled the Telecom Orbit Analysis and Simulation Tool (TOAST) with genetic optimization algorithms. As a demonstration, we have applied the developed tool to find the optimal orbit for Mars orbiters with the constraint of traveling on a frozen orbit and the optimization goal of minimizing the telecommunication gap time. For the measurement of the gap time, several relevant metrics are constructed: 1) area-weighted average gap time, 2) global maximum of local maximum gap time, 3) global maximum of local minimum gap time. Optimal solutions are found for each type of metrics. Common features and differences between the optimal solutions as well as the advantages and disadvantages of each metric are presented. The optimal solutions are compared with several candidate orbits that were considered during the development of the Mars Telecommunications Orbiter mission. C1 [Lee, Seungwon; Lee, Charles H.; Kerridge, Stuart; Edwards, Charles D.; Cheung, Kar-Ming] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Lee, S (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Seungwon.Lee@jpl.nasa.gov FU National Aeronautics and Space Administration; JPLs Research and Technology Development program FX This work was carried out at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. The research was supported by JPLs Research and Technology Development program. NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 556 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583100054 ER PT S AU Kuhn, W Lay, N Grigorian, E AF Kuhn, William Lay, Norman Grigorian, Edwin GP IEEE TI A UHF proximity micro-transceiver for Mars exploration SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB A UHF half-duplex micro-transceiver for future Mars exploration missions is described. The transceiver target specifications include a volume of less than 1 cm(3), mass of less than 10 grams, and power consumption of < 40 mW on receive and 50mW, 300mW, or 3W on transmit. It is compatible with a subset of Prox-1 protocols and supports transmission rates from 1 to 4096 ksps, depending on RF link parameters, in BPSK or QPSK format. Command and control instructions can be received at 1 or 8 ksps. In addition to its low mass/power features, temperature compensation to -100 C and radiation tolerance to 100 krad allow operation outside of large, thermally controlled, shielded enclosures, further reducing the mass and complexity of exploration vehicles. Although designed around Mars missions and environmental constraints, the transceiver is expected to be useful as well in other proximity links where a small/low-power radio compatible with Prox-1 protocols is desired. C1 [Kuhn, William] Kansas State Univ, Manhattan, KS 66506 USA. [Lay, Norman; Grigorian, Edwin] CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Kuhn, W (reprint author), Kansas State Univ, Manhattan, KS 66506 USA. EM wkuhn@ksu.edu; norman.e.lay@jpl.nasa.gov; edwin.r.grigorian@jpl.nasa.gov FU Mars Technology Program of the Jet Propulsion Laboratory; California Institute of Technology; National Aeronautics and Space Administration FX This work was supported by the Mars Technology Program of the Jet Propulsion Laboratory, California Institute of Technology under a contract with the National Aeronautics and Space Administration. The authors also gratefully acknowledge the work of the following individuals who have assisted in the design, layout, and testing process: Dan Nobbe, Yogesh Tugnawat, Igor Kuperman, Xin He, Mark Hartter, Kai Wong, Jeongmin Jeon. Evan Cullens, and Keith Kovala 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 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 628 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101007 ER PT S AU Schenker, PS AF Schenker, Paul S. GP IEEE TI Advances in rover technology for space exploration SO 2006 IEEE Aerospace Conference, Vols 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID MARS-EXPLORATION; MULTIROBOT SYSTEMS; LOCALIZATION; MISSION AB As NASA's two Mars Exploration Rovers (MER) continue their second year of operation at the red planet, the importance of surface mobility to space science is ever more apparent. In this paper we discuss some key problems in advancing performance of autonomous planetary rovers for future missions. Among the topics covered are the safe and accurate traverse of rough, science rich terrain, accurate localization and navigation of large terrain expanses, time-efficient and precise placement science instruments on targets of interest, on-board science data processing, and development of higher-level on-board "decision" skills. We also briefly discuss the development of a class of multi-robot systems that move beyond objectives of planetary science toward eventual emplacement and maintenance of planetary outposts for human-robotic exploration as articulated in the recent Vision for Space Exploration by George W. Bush. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Schenker, PS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 180-603, Pasadena, CA 91109 USA. NR 46 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 643 EP 665 PG 23 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101009 ER PT S AU Li, R Di, KC Agarwal, S Wang, J Matthies, L AF Li, Ron Di, Kaichang Agarwal, Sanchit Wang, Jue Matthies, Larry GP IEEE TI Object modeling and matching from multi-view ground images for automated Mars rover localization SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID EXPLORATION; NAVIGATION; MISSION AB This paper presents an innovative method for object modeling and matching from multi-view ground images for automated Mars rover localization. In this method, rocks are first extracted from a selection of 3D ground points that are generated from dense matching. The extracted rocks are then modeled using analytical surfaces such as ellipsoids, hemispheres, cones, and tetrahedrons. The extracted rocks of two rover stations are matched through a robust algorithm that matches the geometric configuration patterns of the rocks from the two stations using an improved Hough transform technique, followed by a heuristic refinement. Finally, peaks of the matched rocks serve as cross-site tie points in bundle adjustment of the rover image network. Experiments conducted using Navcam images acquired from the 2003 Mars Exploration Rover mission have demonstrated that the proposed method is capable of selecting cross-site tie points for two rover stations that are 26 m apart. The issues of integration of visual odometry with bundle-adjustment is also briefly discussed. C1 [Li, Ron; Di, Kaichang; Agarwal, Sanchit; Wang, Jue] Ohio State Univ, CEEGS, Mapping & GIS Lab, 470 Hitchcock Hall,2070 Neil Ave, Columbus, OH 43210 USA. [Matthies, Larry] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Li, R (reprint author), Ohio State Univ, CEEGS, Mapping & GIS Lab, 470 Hitchcock Hall,2070 Neil Ave, Columbus, OH 43210 USA. EM li.282@osu.edu; di.2@osu.edu; agarwal.59@osu.edu; wang.813@osu.edu; lhm@helios.jpl.nasa.gov OI di, kai chang/0000-0001-6581-6615 FU NASA/JPL through the Mars Technology Program FX This work is partially performed at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. The work has been supported by NASA/JPL through the Mars Technology Program. Collaborations with Drs. Reg Willson and Andrew Howard of the Jet Propulsion Laboratory are appreciated. NR 15 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 666 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101010 ER PT S AU Mukherjee, S Bartlett, P Glass, B Guerrero, J Stanley, S AF Mukherjee, Suparna Bartlett, Paul Glass, Brian Guerrero, Jose Stanley, Scott GP IEEE TI Technologies for exploring the Martian subsurface SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB The Mars Technology Program has invested in a number of development efforts with the collective goal of providing robust access to the Martian subsurface for future landed missions. Currently funded technologies include a sampling system that will be able to penetrate hard rock to 20 in in a highly autonomous manner and at flight-like power levels; shallow (0.5 m) regolith samplers appropriate for low-force platforms such as a rover-mounted robotic arm; a light-weight, low-force hard rock sampler that collects 1 cc powdered samples; and an advanced automation task for permafrost drilling. A summary of capabilities and current status of each of these technologies is presented here. In addition, the program supports the development and integrated testing of a number of science instruments for exploring the subsurface directly, including downhole IR, neutron and x-ray fluorescence spectrometers. Given the increased uncertainties associated with operating such systems, the program's goal is to bring these technologies to high Technology Readiness Levels (TRLs) so that they may be readily utilized by future missions. Recent efforts to facilitate the necessary field and laboratory testing to achieve this high level of maturity will also be discussed.(1,2). C1 [Mukherjee, Suparna] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Bartlett, Paul] SUNY Fashion Inst Technol, Honeybee Robot, New York, NY 10001 USA. [Guerrero, Jose] Ames Res Ctr, Moffett Field, CA 94035 USA. [Stanley, Scott] Swales Aerosp, Pasadena, CA 91107 USA. [Stanley, Scott] Alliance Spacesyst Inc, Pasadena, CA 91103 USA. RP Mukherjee, S (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Suparna.Mukherjee@jpl.nasa.gov; Bartlett@honeybeerobotics.com; brian.glass@nasa.gov; jguerrero@swales.com; sstanley@asi-space.com NR 8 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 674 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101011 ER PT S AU Chu, CCC AF Chu, Cheng-Chih (Chesters) GP IEEE TI Development of advanced entry, descent, and landing technologies for future Mars missions SO 2006 IEEE Aerospace Conference, Vols 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Future Mars missions may need the capability to land much closer to a desired target and/or advanced methods of detecting, avoiding, or tolerating landing hazards. Therefore, technologies that enable "pinpoint landing" (within tens of meters to I km of a target site) will be crucial to meet future mission requirements. As part of NASA Research Announcement, NRA 03-OSS-01, NASA solicited proposals for technology development needs of missions to be launched to Mars during or after the 2009 launch opportunity. Six technology areas were identified as of high priority including advanced entry, descent, and landing (EDL) technologies. In May 2004, 11 proposals with PIs from universities, industries, and NASA centers, were awarded in the area of advanced EDL by NASA for further study and development. This paper presents an overview of these developing technologies. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Chu, CCC (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 6 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 685 EP 692 PG 8 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101012 ER PT S AU Tudryn, CD Blalock, B Burke, G Chen, Y Cozy, S Ghaffarian, R Hunter, D Johnson, M Kolawa, E Mojarradi, M Schatzel, D Shapiro, A AF Tudryn, Carissa D. Blalock, Benjamin Burke, Gary Chen, Yuan Cozy, Scott Ghaffarian, Reza Hunter, Don Johnson, Michael Kolawa, Elizabeth Mojarradi, Mohammad Schatzel, Don Shapiro, Andrew GP IEEE TI Low temperature thermal cycle survivability and reliability study for brushless motor drive electronics SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB (1,2)This paper presents a survivability and reliability investigation for integrated actuator and brushless motor drive electronics packaging and components under an extreme low temperature and high thermal cycle environment. A universal brushless motor drive electronics assembly has been designed, built, and thermal cycle tested for use in Mars, moon, and asteroid type cold environments without the need for any active thermal control. The assembly uses electronic part types and chip-on-board electronic packaging technology that allow operation at temperatures down to -180 degrees C. The thermal cycle capability of the assembly has been demonstrated to be in excess of 2010 cycles from -120 degrees C to 85 degrees C, over a 210 degrees C total temperature swing. Future space missions will require electronic and actuator systems on a planet, asteroid or moon surface to function beyond the established reliability limits of currently used components and materials systems. In support of this target application, the Jet Propulsion Laboratory (JPL) has performed a series of experiments to test the reliability of actuators, sensors, electronic components, and electronic packaging designs to provide input to the detailed flight design of a universal brushless motor drive electronics and integrated actuator assembly. These experiments started with the use of a chip-on-board electronic packaging strategy due to its inherent advantage of improved high functionality with minimal circuit board area compared with standard packaged electronic components. Initial electronic packaging experiments were comprised of various sized chip devices with gold wire bonds. The second phase of electronic packaging experiments conducted at JPL consisted of power devices with large diameter wire bonds as well as various surface mount resistor devices. Full factorial experiments were designed to find the most reliable combinations of substrate type, component attach method and encapsulation. The surviving material combinations after a minimum of 1500 thermal cycles were utilized to form the basis of the packaging and electronic component detailed design approach used in the universal brushless motor drive electronics design. Electrical failures were defined as open circuits. A failure analysis procedure was applied by defining the failure mechanism and applying a risk mitigation. After 1500 cycles, the packaged assembles were cycled to exceed 2010 cycles and additional material considerations were made. In addition, selected components were functionally tested over the temperature range of +100 degrees C to -180 degrees C and cold soaked at -150 degrees C for 1000 hours for reliability. A design for reliability method was also developed at the component and circuit level for electronics operating at extreme low temperatures. C1 [Tudryn, Carissa D.; Burke, Gary; Chen, Yuan; Cozy, Scott; Ghaffarian, Reza; Hunter, Don; Johnson, Michael; Kolawa, Elizabeth; Mojarradi, Mohammad; Schatzel, Don; Shapiro, Andrew] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Blalock, Benjamin] Univ Tennessee, Dept Elect & Comp Engn, Knoxville, TN USA. RP Tudryn, CD (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Carissa.D.Tudryn@jpl.nasa.gov FU Mars Focus Technology Program, NASA FX This work was sponsored by the Mars Focus Technology Program, NASA. The authors would like to especially thank Samad Hayati and Suraphol (Gabriel) Udomkesmalee for their support. NR 10 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 693 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101013 ER PT S AU Kim, SS Hayati, S Lavery, D McBride, KS AF Kim, Soon Sam Hayati, Samad Lavery, David McBride, Karen S. GP IEEE TI Mars miniature science instruments SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID SURFACE AB For robotic Mars in-situ missions, all the science information is gathered through on-board miniature instruments(1,2) that have been developed through many years of R&D. Compared to laboratory counterparts, the rover instruments require miniaturization, such as low mass (1-2 kg), low power (less than 10 W) and compact (1-2 liters), yet with comparable sensitivity. Since early 1990s, NASA recognized the need for the miniature instruments and launched several instrument R&D programs, e.g., PIDDP (Planetary Instrument Definition and Development). However, until 1998, most of the instrument R&D programs supported only up to a breadboard level (TRL 3, 4) and there was a need to carry such instruments to flight qualifiable status (TRL 5, 6) to respond to flight AOs (Announcement of Opportunity). Most flight AOs have only limited time and financial resources, and cannot afford such instrument development processes. To bridge the gap between instrument R&D programs and the flight instrument needs, NASA's Mars Technology Program (MTP) created an advanced instrumentation program called Mars Instrument Development Project (MIDP). MIDP candidate instruments are selected through NASA Research Announcement (NRA) process [1]. For example, MIDP I (1998-2000) selected and developed 10 instruments, MIDP II (2003-2005) 16 instruments, and MIDP III (2004-2006) 11 instruments. Working with PIs, JPL has been managing the MIDP tasks since September 1998. All the instruments being developed under MIDP have been selected through a highly competitive NRA process, and employ state-of-the-art technology. So far, four MIDP funded instruments have been selected by two Mars missions (these instruments have been discussed in this paper). C1 [Kim, Soon Sam; Hayati, Samad] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Lavery, David; McBride, Karen S.] NASA Headquarters, Sci Miss Directorate, Washington, DC 20546 USA. RP Kim, SS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Soonsam.Kim@jpl.nasa.gov; Samad.A.Hayati@jpl.nasa.gov; dave.lavery@hq.nasa.gov; karen.s.mcbride@nasa.gov NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 730 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101014 ER PT S AU Lin, Y AF Lin, Ying GP IEEE TI Mars technology program Planetary Protection technology development SO 2006 IEEE Aerospace Conference, Vols 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID BACTERIA AB The objectives of the NASA Planetary Protection program are to preserve biological and organic conditions of solar-system bodies for future scientific exploration and to protect the Earth from potential hazardous extraterrestrial contamination. As the exploration of solar system continues, NASA remains committed to the implementation of planetary protection policy and regulations. To fulfill this commitment, the Mars Technology Program (MTP) has invested in a portfolio of tasks for developing necessary technologies to meet planetary protection requirements for the next decade missions.(1,2) The MTP planetary protection technology development program comprises seven tasks: 1. Cleaning to achieve sterility 2. Rapid single spore enumeration assay 3. Light weight biobarrier technology 4. Spore adhesion for contamination transport model 5. Near field and integrated particle transport model 6. Mars orbital debris analysis toot 7. Contained sample handling and analysis In this paper, we will give an overview of the task objectives, current technical progress, and future directions. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Lin, Y (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 22 TC 1 Z9 1 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 741 EP 750 PG 10 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101015 ER PT S AU Yung, PT Kempf, MJ Ponce, A AF Yung, Pun To Kempf, Michael J. Ponce, Adrian GP IEEE TI A Rapid Single Spore Enumeration Assay SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID DIPICOLINIC ACID CONTENT; ANTHRAX SMOKE DETECTOR; BACTERIAL-SPORES; SUBTILIS SPORES; HEAT RESISTANCE; BACILLUS SPORES; GERMINATION; ENDOSPORES; SPACECRAFT; IDENTIFICATION AB The Rapid Single Spore Enumeration Assay (RapidSSEA) is being developed for the Mars Technology Program to aid planetary protection personnel in their efforts to validate bioburden reduction on spacecraft surfaces prior to launch. RapidSSEA is based on imaging and counting individual bacterial spores in a microscope field-of-view, where the contrast is generated by a highly luminescent complex that forms when dipicolinic acid (DPA) is released from spores during germination and binds to terbium (Tb3+) ions in the surrounding medium. Under pulsed UV excitation, the long-lived (tau similar to 1 ms) DPA-triggered Tb luminescence is imaged by a lifetime-gated camera, essentially eliminating fluorescent interferents from the image, which enables counting of bacterial spores swabbed from environmental samples. in practice, the RapidSSEA analytical procedure entails swabbing bacterial spores from the surface to be analyzed with cotton applicators, and resuspending them from the applicators into water, which up to this point is identical to the NASA standard assay. Filtration of the resuspended sample concentrates and immobilizes the bacterial spores onto a membrane filter. Spores are then transferred onto Tb3+- and L-alanine-doped agarose by streaking the membrane filter across the agarose surface. Finally, individual spores, or more specifically the resultant Tb-DPA luminescence halos surrounding the germinated spore bodies, are imaged and counted using a lifetime-gated microscope. Here we report results from the first side-by-side comparison of RapidSSEA and the NASA standard assay. Both assays were used to assess the spore population on 2.25"x2.25" (5.7 cm x 5.7 cm or 32.5 cm(2)) stainless steel coupons inoculated with 1.3x 10(5), 5.0 x 10(4) and 7.0 x 10(3) Bacillus atrophaeus spores. Using RapidSSEA, 38.0% +/- 5.8% of the total inoculated spore population was recovered and counted within 30 minutes. The NASA standard assay recovered and counted 7.4% +/- 2.7% of the inoculated spores, but required 3 days before results became available. In addition, we report a concentration dependence experiment, which demonstrated a 5000 spores/coupon detection limit for RapidSSEA due to background luminescence, contamination and difficulties in counting. Finally, we discuss future work that is envisioned to improve the detection limit to less than 10 spores/coupon. C1 [Yung, Pun To; Kempf, Michael J.; Ponce, Adrian] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Yung, PT (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Adrian.Ponce@jpl.nasa.gov NR 48 TC 2 Z9 2 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 751 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101016 ER PT S AU Wyatt, EJ Elya, TA Klimesh, MA Krupiarz, CJ AF Wyatt, E. Jay Elya, Todd. A. Klimesh, Matthew A. Krupiarz, Christopher J. GP IEEE TI Telecommunications IT and navigation for future Mars exploration missions SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID STEREO IMAGE COMPRESSION; 2-D FILTERING SCHEME AB There are three primary drivers behind current investments in telecommunications information technology and navigation for Mars exploration. One is finding ways to maximize the volume of science data return since instrument data generation often exceeds communication bandwidth. Another is to provide the necessary technology to enable networked spacecraft. The third is to enable more precise landing so in-situ vehicles can be placed in more scientifically interesting regions. This paper describes current NASA investments in these areas funded through the Mars Technology Program (competed via NASA Research Announcements). Current investments are in stereo image compression, next generation Mars relay protocols, and a capability for autonomous approach navigation using in-situ Mars orbiter(1) assets. C1 [Wyatt, E. Jay; Elya, Todd. A.; Klimesh, Matthew A.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Krupiarz, Christopher J.] Johns Hopkins Univ, Appl Phys Lab, Laurel, MD 20723 USA. RP Wyatt, EJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM e.j.wyatt@jpl.nasa.gov NR 22 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 764 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101017 ER PT S AU Braun, RD Manning, RM AF Braun, Robert D. Manning, Robert M. GP IEEE TI Mars exploration entry, descent and landing challenges SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB The United States has successfully landed five robotic systems on the surface of Mars. These systems all had landed mass below 0.6 metric tons (t), had landed footprints on the order of hundreds of km and landed at sites below -1 km MOLA elevation due the need to perform entry, descent and landing operations in an environment with sufficient atmospheric density. Current plans for human exploration of Mars call for the landing of 40-80 t surface elements at scientifically interesting locations within close proximity (10's of m) of pre-positioned robotic assets. This paper summarizes past successful entry, descent and landing systems and approaches being developed by the robotic Mars exploration program to increased landed performance (mass, accuracy and surface elevation). In addition, the entry, descent and landing sequence for a human exploration system will be reviewed, highlighting the technology and systems advances required. C1 [Braun, Robert D.] Georgia Inst Technol, Atlanta, GA 30332 USA. [Manning, Robert M.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Braun, RD (reprint author), Georgia Inst Technol, Atlanta, GA 30332 USA. EM robert.braun@ae.gatech.edu; rmmannim@jpl.nasa.gov NR 27 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 776 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101018 ER PT S AU Wright, MJ Edquist, KT Hollis, BR Olejniczak, J Venkatapathy, E AF Wright, Michael J. Edquist, Karl T. Hollis, Brian R. Olejniczak, Joseph Venkatapathy, Ethiraj GP IEEE TI Status of aerothermal modeling for current and future Mars exploration missions SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID PATHFINDER ENTRY; HEATSHIELD; DIFFUSION; VISCOSITY; MIXTURES; ABLATION; VEHICLE; EROSION; EARTH; FLOW AB The status of aerothermal analysis for Mars entry missions is reviewed. The aeroheating environment of all Mars missions to date has been dominated by convective heating. Two primary uncertainties in our ability to predict forebody convective heating are turbulence on a blunt lifting cone and surface catalysis in a CO2 environment. Future missions, particularly crewed vehicles, will encounter additional heating from shock-layer radiation due to a combination of larger size and faster entry velocity. Uncertainties inherent in the physical models employed to predict these phenomena are explored. Capabilities of ground test facilities to support aeroheating validation are also summarized. Engineering flight data from the Viking and Pathfinder missions, which may be useful for aerothermal model validation, are discussed. Examples are taken from past, present, and future Mars entry missions, including the twin Mars Exploration Rovers and the Mars Science Laboratory, scheduled for launch in 2009.(12). C1 [Wright, Michael J.; Olejniczak, Joseph; Venkatapathy, Ethiraj] NASA, Ames Res Ctr, MS 230-2, Moffett Field, CA 94035 USA. [Edquist, Karl T.; Hollis, Brian R.] NASA, Langley Res Ctr, Hampton, VA USA. RP Wright, MJ (reprint author), NASA, Ames Res Ctr, MS 230-2, Moffett Field, CA 94035 USA. EM Michael.J.Wright@nasa.gov; Karl.T.Edquist@nasa.gov; Brian.R.Hollis@nasa.gov; Joseph.Olejniczak@nasa.gov; Ethiraj.Venkatapathy@nasa.gov NR 71 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 794 EP + PG 5 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101019 ER PT S AU Wolf, AA Tooley, J Ploen, S Ivanov, M Acikmese, B Gromov, K AF Wolf, Aron A. Tooley, Jeff Ploen, Scott Ivanov, Mark Acikmese, Behcet Gromov, Konstantin GP IEEE TI Performance trades for Mars pinpoint landing SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Previous Mars landers(1,2) have been able to land only within tens to hundreds of km of a target site. Principal sources of uncertainty are approach navigation, atmospheric modeling, and vehicle aerodynamics; additional (lesser) uncertainty sources are map-tie error and wind drift. The Mars Science Laboratory mission scheduled for 2009 launch will use guidance during hypersonic entry to improve this to similar to 10 km. To achieve "pinpoint landing" (within 100m) for future missions, ways of addressing the remaining error sources (approach navigation, wind drift and map-tie error) must be found. This work defines a "reference system design" for guidance, navigation, and control in future pinpoint landing missions, and assesses uncertainties and performance penalties associated with pinpoint landing using this reference system design. C1 [Wolf, Aron A.; Tooley, Jeff; Ploen, Scott; Ivanov, Mark; Acikmese, Behcet; Gromov, Konstantin] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Wolf, AA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Aron.A.Wolf@jpl.nasa.gov; Jeffrey.Tooley@jpl.nasa.gov; Scott.R.Ploen@jpl.nasa.gov; Mark.C.Ivanov@jpl.nasa.gov; Ahmet.B.Acikmese@jpl.nasa.sgov; Konstantin.G.Gromov@jpl.nasa.gov FU Jet Propulsion Laboratory FX The authors would like to express their appreciation to Frank Jordan, Samad Hayati, and Lanny Miller of the Jet Propulsion Laboratory who funded and advised on the work described in this paper, and to acknowledge the contributions of Wyatt Johnson, Andrew Johnson, and Ben Leong. This research was carried out at the Jet Propulsion Laboratory, California Ins titute of Technology, under a contract with the National Aeronautics and Space Administration. Reference herein to any specific commercial product, process, or service by trade name, trademark, manufacturer, or otherwise, does not constitute or imply its endorsement by the United States Government or the Jet Propulsion Laborator y, California Institute of Technology. NR 12 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 817 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101021 ER PT S AU Huertas, A Cheng, Y Madison, R AF Huertas, Andres Cheng, Yang Madison, Richard GP IEEE TI Passive imaging based multi-cue hazard detection for spacecraft safe landing SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Accurate assessment of potentially damaging ground hazards during the spacecraft EDL (Entry, Descent, and Landing) phase is crucial to insure a high probability of safe landing. A lander that encounters a large rock, falls off a cliff, or tips over on a steep slope can sustain mission-ending damage. Guided entry is expected to shrink landing ellipses from 100-300 kin to similar to 10 kin radius for the second-generation landers as early as 2009. Regardless of size and location, however, landing ellipses will almost always contain hazards such as craters, discontinuities, steep slopes, and large rocks. It is estimated that an MSL (Mars Science Laboratory)-sized lander should detect and avoid 16-150m diameter craters, vertical drops similar to the edges of 16m or 3.75m diameter crater, for high and low altitude HDA (Hazard Detection and Avoidance) respectively. It should also be able to detect slopes 20 degrees or steeper, and rocks 0.75m or taller. In this paper(1) we will present a passive imaging based, multi-cue hazard detection and avoidance (HDA) system suitable for Martian and other lander missions. This is the first passively imaged HDA system that seamlessly integrates multiple algorithins-crater detection, slope estimation, rock detection and texture analysis, and multicues-crater morphology, rock distribution, to detect these hazards in real time. C1 [Huertas, Andres; Cheng, Yang; Madison, Richard] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Huertas, A (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Andres.Huertas@jpl.nasa.gov; Yang.Cheng@jpl.nasa.gov; Richard.W.Madison@jpl.nasa.gov FU Mars Program under NASA Mars Exploration Program Advanced Technologies [NRA OSS-03-01] FX The research described in this paper was carried out at the Jet Propulsion Laboratory, California Institute of Technology, funded by Mars Program under NASA Mars Exploration Program Advanced Technologies NRA OSS-03-01. NR 28 TC 0 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 833 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101022 ER PT S AU Serrano, N Bajracharya, M Howard, A Seraji, H AF Serrano, Navid Bajracharya, Max Howard, Ayanna Seraji, Homayoun GP IEEE TI A novel tiered sensor fusion approach for terrain characterization and safe landing assessment SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB This paper presents a novel, tiered sensor fusion methodology for real-time terrain safety assessment. A combination of active and passive sensors, specifically, radar, lidar, and camera, operate in three tiers according to their inherent ranges of operation. Low-level terrain features (e.g. slope, roughness) and high-level terrain features (e.g. hills, craters) are integrated using principles of reasoning under uncertainty. Three methodologies are used to infer landing safety: Fuzzy Reasoning, Probabilistic Reasoning, and Evidential Reasoning. The safe landing predictions from the three fusion engines are consolidated in a subsequent decision fusion stage aimed at combining the strengths of each fusion methodology. Results from simulated spacecraft descents are presented and discussed.(1,2). C1 [Serrano, Navid; Bajracharya, Max; Seraji, Homayoun] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Howard, Ayanna] Georgia Inst Technol, Sch Elect & Comp Engn, Human Automat Syst HumAnS Lab, Atlanta, GA 30332 USA. RP Serrano, N (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM navid.serrano@jpl.nasa.gov; max.bajracharya@jpl.nasa.gov; ayanna.howard@ece.gatech.edu; homayoun.seraji@nasa.gov FU Mars Technology Program, NASA Science Mission Directorate FX The research described in this publication was carried out at the Jet Propulsion Laboratory, California Institute of Technology under contract from the National Aeronautics and Space Administration (NASA), with funding from the Mars Technology Program, NASA Science Mission Directorate. NR 12 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 847 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101023 ER PT S AU Steltzner, A Kipp, D Chen, A Burkhart, D Guernsey, C Mendeck, G Mitcheltree, R Powell, R Rivellini, T San Martin, M Way, D AF Steltzner, Adam Kipp, Devin Chen, Allen Burkhart, Dan Guernsey, Carl Mendeck, Gavin Mitcheltree, Robert Powell, Richard Rivellini, Tommaso San Martin, Miguel Way, David GP IEEE TI Mars Science Laboratory entry, descent, and landing system SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB In 2010, the Mars Science Laboratory (MSL) mission will pioneer the next generation of robotic Entry, Descent, and Landing (EDL) systems by delivering the largest and most capable rover to date to the surface of Mars. In addition to landing more mass than prior missions to Mars, MSL will offer access to regions of Mars that have been previously unreachable. By providing an EDL system capable of landing at altitudes as high as 2 km above the reference areoid, as defined by the Mars Orbiting Laser Altimeter (MOLA) program, MSL will demonstrate sufficient performance to land on a large fraction of the Martian surface. By contrast, the highest altitude landing to date on Mars has been the Mars Exploration Rover (MER) MER-B at 1.44 kin below the areoid. The coupling of this improved altitude performance with latitude limits as large as 60 degrees off of the equator and a precise delivery to within 10 km of a surface target will allow the science community to select the MSL landing site from thousands of scientifically interesting possibilities. In meeting these requirements, MSL is extending the limits of the EDL technologies qualified by the Mars Viking, Mars Pathfinder, and MER missions. This paper discusses the MSL EDL architecture, system, and subsystem design and discusses some of the challenges faced in delivering such an unprecedented rover payload to the surface of Mars.(1,2). C1 [Steltzner, Adam; Kipp, Devin; Chen, Allen; Burkhart, Dan; Guernsey, Carl; Mitcheltree, Robert; Rivellini, Tommaso; San Martin, Miguel] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Mendeck, Gavin] NASA, Johnson Space Flight Ctr, Houston, TX USA. [Powell, Richard; Way, David] NASA, Langley Res Ctr, Hampton, VA USA. RP Steltzner, A (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Adam.D.Steltzner@jpl.nasa.gov NR 4 TC 0 Z9 0 U1 1 U2 6 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 857 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101024 ER PT S AU Cianciolo, AD Powell, R Lockwood, MK AF Cianciolo, Alicia Dwyer Powell, Richard Lockwood, Mary Kae GP IEEE TI Mars Science Laboratory launch-arrival space study: A pork chop plot analysis SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Launch-Arrival, or "pork chop", plot analysis can provide mission designers with valuable information and insight into a specific launch and arrival space selected for a mission. The study begins with the array of entry states for each pair of selected Earth launch and Mars arrival dates, and nominal entry, descent and landing trajectories are simulated for each pair. Parameters of interest, such as maximum heat rate, are plotted in launch-arrival space. The plots help to quickly identify launch and arrival regions that are not feasible under current constraints or technology and also provide information as to what technologies may need to be developed to reach a desired region. This paper provides a discussion of the development, application, and results of a pork chop plot analysis to the Mars Science Laboratory mission. This technique is easily applicable to other missions at Mars and other destinations.(1,2). C1 [Cianciolo, Alicia Dwyer; Powell, Richard] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Lockwood, Mary Kae] Johns Hopkins Univ, Appl Phys Lab, Laurel, MD 20723 USA. RP Cianciolo, AD (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM Alicia.M.Dwyer@ianciolo.nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 872 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101025 ER PT S AU Way, DW Powell, RW Chen, A Steltzner, AD AF Way, David W. Powell, Richard W. Chen, Allen Steltzner, Adam D. GP IEEE TI Asymptotic parachute performance sensitivity SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB In 2010, the Mars Science Laboratory mission will pioneer the next generation of robotic Entry, Descent, and Landing systems by delivering the largest and most capable rover to date to the surface of Mars. In addition to landing more mass than any other mission to Mars, Mars Science Laboratory will also provide scientists with unprecedented access to regions of Mars that have been previously unreachable. By providing an Entry, Descent, and Landing system capable of landing at altitudes as high as 2 kin above the reference gravitational equipotential surface, or areoid, as defined by the Mars Orbiting Laser Altimeter program, Mars Science Laboratory will demonstrate sufficient performance to land on 83% of the planet's surface. By contrast, the highest altitude landing to date on Mars has been the Mars Exploration Rover at 1.3 kin below the areoid. The coupling of this improved altitude performance with latitude limits as large as 60 degrees off of the equator and a precise delivery to within 10 kin of a surface target, will allow the science community to select the Mars Science Laboratory landing site from thousands of scientifically interesting possibilities. In meeting these requirements, Mars Science Laboratory is extending the limits of the Entry, Descent, and Landing technologies qualified by the Mars Viking, Mars Pathfinder, and Mars Exploration Rover missions. Specifically, the drag deceleration provided by a Viking-heritage 16.15 in supersonic Disk-Gap-Band parachute in the thin atmosphere of Mars is insufficient, at the altitudes and ballistic coefficients under consideration by the Mars Science Laboratory project, to maintain necessary altitude performance and timeline margin. This paper defines and discusses the asymptotic parachute performance observed in Monte Carlo simulation and performance analysis and its effect on the Mars Science Laboratory Entry, Descent, and Landing architecture.(1,2). C1 [Way, David W.; Powell, Richard W.] NASA, Langley Res Ctr, 1 North Dryden St,Mail Stop 489, Hampton, VA 23681 USA. [Chen, Allen; Steltzner, Adam D.] Jet Prop Lab, Pasadena, CA USA. RP Way, DW (reprint author), NASA, Langley Res Ctr, 1 North Dryden St,Mail Stop 489, Hampton, VA 23681 USA. EM David.W.Way@nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 882 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101026 ER PT S AU Mitcheltree, R Steltzner, A Chen, A SanMartin, M Rivellini, T AF Mitcheltree, Robert Steltzner, Adam Chen, Allen SanMartin, Miguel Rivellini, Tomasso GP IEEE TI Mars Science Laboratory entry descent and landing system verification and validation program SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB The Mars Science Laboratory (MSL)(1) mission will land the next generation of robotic Entry, Descent, and Landing (EDL) systems on Mars in 2010. Relative to previous missions, the MSL EDL architecture will deliver a significantly larger mass to a significantly higher altitude while maintaining a significantly tighter delivery ellipse. MSL is pushing the limits of EDL technologies qualified previously by the Mars Viking, Mars Pathfinder, and Mars Exploration Rover missions as well as introducing new elements into the architecture. Given the difficulties of conducting a meaningful end-to-end flight test on Earth, this combination introduces numerous challenges for the EDL Verification and Validation program. This paper discusses how system Validation challenges influenced the design of the EDL architecture and highlights how some of the remaining challenges will be addressed to assure a successful landing of this unprecedented rover on Mars. C1 [Mitcheltree, Robert; Steltzner, Adam; Chen, Allen; SanMartin, Miguel; Rivellini, Tomasso] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Mitcheltree, R (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Robert.A.Mitcheltree@jpl.nasa.gov NR 2 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 891 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101027 ER PT S AU Brat, G Denney, E Farrell, K Giannakopoulou, D Jonsson, A Frank, J Boddy, M Carpenter, T Estlin, T Pivtoraiko, M AF Brat, Guillaume Denney, Ewen Farrell, Kimberley Giannakopoulou, Dimitra Jonsson, Ari Frank, Jeremy Boddy, Mark Carpenter, Todd Estlin, Tara Pivtoraiko, Mihail GP IEEE TI A robust compositional architecture for autonomous systems SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID PROGRAMS AB (12)Space exploration applications can benefit greatly from autonomous systems. Great distances, limited communications and high costs make direct operations impossible while mandating operations reliability and efficiency beyond what traditional commanding can provide. Autonomous systems can improve reliability and enhance spacecraft capability significantly. However, there is reluctance to utilizing autonomous systems. In part, this is due to general hesitation about new technologies, but a more tangible concern is the reliability and predictability of autonomous software. C1 [Brat, Guillaume; Denney, Ewen; Farrell, Kimberley; Giannakopoulou, Dimitra; Jonsson, Ari] NASA, Ames Res Ctr, Adv Comp Sci Res Inst, Mailstop 269-2, Moffett Field, CA 94035 USA. [Frank, Jeremy] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Boddy, Mark; Carpenter, Todd] Adventium Enterprises, Minneapolis, MN 55401 USA. [Estlin, Tara; Pivtoraiko, Mihail] Jet Propuls Lab, Pasadena, CA USA. RP Brat, G (reprint author), NASA, Ames Res Ctr, Adv Comp Sci Res Inst, Mailstop 269-2, Moffett Field, CA 94035 USA. EM brat@email.arc.nasa.gov; edenney@email.arc.nasa.gov; kfarrell@email.arc.nasa.gov; dimitra@email.arc.nasa.gov; jonsson@email.arc.nasa.gov; frank@email.arc.nasa.gov; mark.boddy@adventiumenterprises.com; todd.carpenter@adventiumenterprises.com; tara.estlin@jpl.nasa.gov; mihail.n.pivtoraiko@jpl.nasa.gov NR 20 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 923 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101030 ER PT S AU Tumer, K Agogino, A AF Tumer, Kagan Agogino, Adrian GP IEEE TI Robust coordination for large sets of simple rovers SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID ROBOTS AB The ability to coordinate sets of rovers in an unknown environment is critical to the long-term success of many of NASAs exploration missions. Such coordination policies must have the ability to adapt in unmodeled or partially modeled domains and must be robust against environmental noise and rover failures. In addition such coordination policies must accommodate a large number of rovers, without excessive and burdensome hand-tuning. In this paper we present a distributed coordination method that addresses these issues in the domain of controlling a set of simple rovers. The application of these methods allows reliable and efficient robotic exploration in dangerous, dynamic, and previously unexplored domains. C1 [Tumer, Kagan; Agogino, Adrian] NASA, Ames Res Ctr, Mailstop 269-3, Moffett Field, CA 94035 USA. RP Tumer, K (reprint author), NASA, Ames Res Ctr, Mailstop 269-3, Moffett Field, CA 94035 USA. EM ktumer@mail.arc.nasa.gov; adrian@email.arc.nasa.gov NR 19 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 939 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101032 ER PT S AU Chamberlain, N Zawadzki, M Sadowy, G Oakes, E Brown, K Hodges, R AF Chamberlain, Neil Zawadzki, Mark Sadowy, Greg Oakes, Eric Brown, Kyle Hodges, Richard GP IEEE TI The UAVSAR phased array aperture SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB The development of a microstrip patch antenna array for an L-band repeat-pass interferometric synthetic aperture radar (InSAR) is discussed in this paper. The instrument will be flown on an unmanned aerial vehicle (UAV) and will provide accurate topographic maps for Earth science by 2007. The antenna operates at a center frequency of 1.2575 GHz and with a bandwidth of 80 MHz, consistent with a number of radar instruments that JPL has previously flown. The antenna is designed to radiate orthogonal linear polarizations for fully-polarimetric measurements. Beam-pointing requirements for repeat-pass SAR interferometry necessitate electronic scanning in azimuth over a range of +/- 20degrees in order to compensate for aircraft yaw. Beam-steering is accomplished by transmit receive (T/R) modules and a beamforming network implemented in a stripline circuit board. C1 [Chamberlain, Neil; Zawadzki, Mark; Sadowy, Greg; Oakes, Eric; Brown, Kyle; Hodges, Richard] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Chamberlain, N (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Neil.F.Chamberlain@jpl.nasa.gov; Mark.S.Zawadzki@jpl.nasa.gov; Gregory.A.Sadowy@jpl.nasa.gov; Eric.Oakes@jpl.nasa.gov; Kyle.M.Brown@jpl.nasa.gov; Richard.E.Hodges@jpl.nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 978 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101036 ER PT S AU Imbriale, WA Gama, E Smith, KS Shultz, R AF Imbriale, William A. Gama, Eric Smith, Kenneth S. Shultz, Roger GP IEEE TI Thermal considerations for hydroformed reflectors SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB One antenna design under consideration(1,2) for both the next generation Deep Space Network (DSN) array and the Square Kilometer Array (SKA) project is a hydroformed symmetrically shaped dual reflector system. Hydroforming is the process of forming aluminum to a rigid and precise mold by using a fluid or gas under pressure. Three 6-meter hydroformed reflectors with rms less than 8 mils (0.2 mm) have been delivered to JPL. C1 [Imbriale, William A.; Gama, Eric] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Smith, Kenneth S.] Alliance Spacesyst Inc, Pasadena, CA 91103 USA. [Shultz, Roger] Schultz Associates, Alamo, CA 94507 USA. RP Imbriale, WA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM William.A.Imbriale@jpl.nasa.gov; Eric.Gama@jpl.nasa.gov; ksmith@asi-space.com; schultz_assoc@pipeline.com NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 991 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101037 ER PT S AU Jones, DL AF Jones, Dayton L. GP IEEE TI Lower-cost architectures for large arrays of small antennas SO 2006 IEEE Aerospace Conference, Vols 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID ALLEN-TELESCOPE ARRAY AB Future, plans for NASA's Deep Space Network (DSN) call for the construction of arrays of small antennas to compliment and eventually replace the existing network of large single antennas. The motivation for this transformation is the need to support much higher downlink data rates in the future, along with the. realization that the most cost-effective way to do this is though a large increase in total collecting area on the ground. As currently designed, the DSN arrays will consist of approximately four hundred 12-m diameter antennas at each of three longitudes, operating at X and Ka bands (8 and 32 GHz). A possible near-term option is the construction of large arrays operating at X-band only. Such an array could be built more rapidly and less expensively than an X/Ka hand array, and would be able to support the majority of space missions planned for the next 20 years, which will not require bandwidths wider than the 50 MHz X-band allocation. Cost-saving advantages of an X-band only array include the use of COTS antennas much smaller than 12 In in diameter, uncooled receivers, and direct optical transfer of signals from antennas to a central signal processing area. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Jones, DL (reprint author), CALTECH, Jet Prop Lab, Mail Code 138-308,4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 22 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1005 EP 1013 PG 9 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101038 ER PT S AU Jamnejad, V Peng, T AF Jamnejad, Vahraz Peng, Ted GP IEEE TI Mathematical gain models of large-aperture earth station antennas for Space Research Service SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Compatibility studies between Space Research Service (SRS) earth stations and high-density fixed systems are being conducted in the 31.8-32.3 GHz and 37-38 GHz bands. One of the key parameters in determining the level of interference that may occur at SRS earth stations is the antenna pattern to be used in the calculations. There are a number of antenna pattern models proposed in the literature and in various International Telecommunication Union (ITU) recommendations. In this paper we propose and present a new gain model representing a peak envelope of the class of large aperture antennas currently in use at the SRS earth stations. This model takes into account the effect of surface tolerance on gain distribution in the main beam and at side-lobes. It includes aperture efficiency in a way affecting both the peak and the side-lobe regions. It is demonstrated to have properties superior to the existing models in many respects. We also propose the use of the integrated average gain value as a validity check in evaluating the general accuracy of any model compared to an actual antenna pattern. An "average gain" model is also proposed to allow more accurate estimation of aggregate interference of a large number of distributed interfering sources. Many examples and plots are provided to clarify the concepts and compare and validate the proposed models. C1 [Jamnejad, Vahraz; Peng, Ted] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Jamnejad, V (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM vahraz.jamnejad@jpl.nasa.gov NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1014 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101039 ER PT S AU Tanner, AB Brown, ST Dinardo, SJ Gaier, TM Kangaslahti, PP Lambrigtsen, BH Wilson, WJ Piepmeier, JR Ruf, CS Gross, SM Lim, BH Musko, S Rogacki, S AF Tanner, A. B. Brown, S. T. Dinardo, S. J. Gaier, T. M. Kangaslahti, P. P. Lambrigtsen, B. H. Wilson, W. J. Piepmeier, J. R. Ruf, C. S. Gross, S. M. Lim, B. H. Musko, S. Rogacki, S. GP IEEE TI Initial results of the GeoSTAR prototype - (Geosynchronous Synthetic Thinned Array Radiometer) SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB A prototype(12) of the Geostationary Synthetic Thinned Array Radiometer (GeoSTAR) will be presented. GeoSTAR is a concept for a Y-array of correlation interferometers operating in bands from 50 GHz to 180 GHz which will for the first time provide high spatial resolution, continuous soundings of the earths atmosphere from geosynchronous orbit. This paper presents preliminary data from a small (24-element) 50-55 GHz prototype system which has been built under NASA's Instrument Incubator Program to demonstrate the basic technology and calibration techniques needed for the larger (300 element) spacebome system. Images are synthesized by Fourier Transform of interferometric data, and it is essential that the spatial response of each antenna in the array be well characterized. This has been achieved using a novel variant of a Potter horn antenna which minimizes embedding effects in a closely packed array. The array electronics consists of low-power MMIC receivers, built by JPL, and a high speed digital correlator, built by the University of Michigan. Calibration circuits include a phase-switched correlated noise reference which is injected behind the antenna array; circuitry to modulate the receiver noise temperature and gain; and local oscillator phase shifters which are used to negate correlator offsets and quadrature imbalances. An outline of the data processing will be presented, along with the first images from this system. C1 [Tanner, A. B.; Brown, S. T.; Dinardo, S. J.; Gaier, T. M.; Kangaslahti, P. P.; Lambrigtsen, B. H.; Wilson, W. J.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. [Piepmeier, J. R.] Goddard Space Flight Ctr, Greenbelt, MD USA. [Ruf, C. S.; Gross, S. M.; Lim, B. H.; Musko, S.; Rogacki, S.] Univ Michigan, Ann Arbor, MI USA. RP Tanner, AB (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. EM alan.b.tanner@jpl.nasa.gov RI Ruf, Christopher/I-9463-2012 NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1039 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101042 ER PT S AU Chuang, E Hensley, S Wheeler, K AF Chuang, Ernie Hensley, Scott Wheeler, Kevin GP IEEE TI A highly capable Arbitrary Waveform Generator for next generation radar systems SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB We are developing an Arbitrary Waveform Generator (AWG) to provide enhanced capability for radar applications. The current design will accommodate two waveform generators on a single unit for dual frequency operation. The basic architecture of this unit employs a Field Programmable Gate Array (FPGA) and a high speed and high precision Digital to Analog Converter (DAC) for direct digital synthesis. This AWG will be capable of up to 450 MHz bandwidth with ability for frequency notching. Phase fidelity of better than 1.2 degrees deviation RMS is also achievable. This AWG operates with lower power consumption as compared with other waveform generators, which is advantageous for future spaceborne applications. This will enable radars to return higher precision data, to be reduced in complexity, and to operate in any band without interfering with dedicated bandwidths. C1 [Chuang, Ernie; Hensley, Scott; Wheeler, Kevin] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Chuang, E (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Ernie.Chuang@jpl.nasa.gov NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1061 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583101045 ER PT S AU Pogorzelski, RJ AF Pogorzelski, Ronald J. GP IEEE TI Coupled oscillator based agile beam transmitters and receivers: A review of work at JPL SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID PHASED-ARRAYS; DYNAMICS; DESIGN AB This is a review of the work done at Caltech's Jet Propulsion Laboratory during the past decade on development of the coupled oscillator technology in phased array applications to spacecraft telecommunications. 1,2 First, some historical background is provided to set the work in context. However, this is by no means intended to be a comprehensive review of all work in this area. Rather, the focus is on the JPL contribution with some mention of other work which provided either insight or motivation. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Pogorzelski, RJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM pogo@jpl.nasa.gov NR 33 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1164 EP 1177 PG 14 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583102004 ER PT S AU Amoozegar, F AF Amoozegar, Farid GP IEEE TI Applications and operation concepts of large transmit phased array of parabolic reflectors SO 2006 IEEE Aerospace Conference, Vols 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB The primary motive(1,2) for large transmit array of parabolic reflectors, also known as Uplink Array, was to explore alternate methods in order to replace the large 70m antennas of Deep Space Network (DSN) such that the core capability for emergency support to a troubled spacecraft in deep space is preserved. Given that the Uplink Array is a new technology, the focus has always been on its feasibility and phase calibration techniques, which by itself is quite a challenge. It would be interesting to examine, however, what else could be accomplished by the Uplink Array capability other than the emergency support to a troubled spacecraft in deep space. Although the Uplink Array calibration and demonstration for proof of concept is still underway at Jet Propulsion Laboratory (JPL), knowledge of various potential meaningful application scenarios as well as operation concepts of Uplink Array is equally important to better understand and fine tune the high level architectural requirements of this big evolving system of systems. Therefore, the objective of this paper is to discuss a few application scenarios and the corresponding operation concepts, such as lunar positioning system, high EIRP uplink and the synergies with solar system radar, and high power RF beams. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Amoozegar, F (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 29 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1233 EP 1252 PG 20 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583102010 ER PT S AU Hurd, WJ Moe, RV Cheng, ES Fairbrother, DA AF Hurd, William J. Moe, Rud V. Cheng, Edward S. Fairbrother, Debora A. GP IEEE TI Exo-atmospheric telescopes for deep space optical communications SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB For deep space optical communications, optical telescopes located above the Earth's atmosphere would have significant performance advantages over telescopes mounted on the Earth's surface. Link outages due to cloud cover would be eliminated, atmospheric attenuation would be eliminated, and signal degradation due to stray light would be reduced. A study has been conducted to compare various exo-atmospheric platforms for the Earth end of the optical link. The three most promising platforms among many initially considered were selected for detailed study: satellites, free-flying airships and tethered airships. System configurations were compared that would have data rate capability comparable to a 6-m to 10-m diameter ground-mounted telescope, 100 percent line-of-sight coverage to a deep space spacecraft in the ecliptic, and at least 80 percent coverage in the event of failure of one Earth terminal. Based upon technical feasibility and readiness, life-cycle cost, performance and risk, a satellite platform is recommended. However, it is noted that airship technology may be advanced in the next decade or so to a level where airships should be reconsidered. Finally, this study provides a basis for a future study to compare systems using Earth-mounted and exo-atmospheric telescopes.(1,2). C1 [Hurd, William J.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Moe, Rud V.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Cheng, Edward S.] LLC, Conceptual Anal, Glenn Dale, MD 20769 USA. [Fairbrother, Debora A.] NASA, Goddard Space Flight Ctr, WFF, Wallops Isl, VA 23337 USA. RP Hurd, WJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM William.J.Hurd@jpl.nasa.gov; Rud.V.Moe@nasa.gov; ec@conceptual-analytics.com; Debora.A.Fairbrother@nasa.gov FU NASA Goddard Space Flight Center; Space Operations Mission Directorate; Science Mission Directorate of NASA Headquarters FX The main study from which this report is derived was managed by the NASA Goddard Space Flight Center under the co-sponsorship of the Space Operations Mission Directorate and the Science Mission Directorate of NASA Headquarters. NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1253 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583102011 ER PT S AU Breidenthal, JC Edwards, CD Greenberg, E Kazz, GJ Noreen, GK AF Breidenthal, Julian C. Edwards, Charles D. Greenberg, Edward Kazz, Greg J. Noreen, Gary K. GP IEEE TI End-to-end information system concept for the Mars Telecommunications Orbiterk SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB The Mars Telecommunications Orbiter (MTO) was intended to provide high-performance deep space relay links to landers, orbiters, sample-return missions, and approaching spacecraft in the vicinity of Mars, to demonstrate interplanetary laser communications, to demonstrate autonomous navigation, and to carry out its own science investigations. These goals led to a need for an array of end-to-end information system (EEIS) capabilities unprecedented for a deep space mission. We describe here the EEIS concept for provision of six major types of services by the MTO: relay, open-loop recording, Marscraft tracking, timing, payload data transport, and Earthlink data transport. We also discuss the key design drivers and strategies employed in the EEIS design, and possible extensions of the MTO EEIS concept to accommodate scenarios beyond the original MTO mission requirements. C1 [Breidenthal, Julian C.; Edwards, Charles D.; Greenberg, Edward; Kazz, Greg J.; Noreen, Gary K.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Breidenthal, JC (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM jbreid@ipl.nasa.gov NR 0 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1265 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583102012 ER PT S AU Sun, J Gao, J Shambayati, S Modiano, E AF Sun, Jun Gao, Jay Shambayati, Shervin Modiano, Eytan GP IEEE TI Ka-band link optimization with rate adaptation SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB On-going development of Ka-band capability for the Deep Space Networks (DSN) will radically increase the bandwidth available to support advanced mission concepts envisioned for future robotic as well as human exploration of Mars and beyond. While Ka-band links can operate at much higher data rate than X-band, they are much more susceptible to fluctuating weather conditions and manifest a significant trade-off between throughput and availability. If the operating point is fixed, the maximum average throughput for deep space Ka-band link is achieved at about 80 percent availability, i.e., weather-related outages will occur about 20 percent of the time. Low availability increases the complexity of space mission operation, while higher availability would require additional link margins that lowers the overall throughput. To improve this fundamental throughput-availability tradeoff, data rate adaptation based on real-time observation of the channel condition is necessary. In this paper, we model the ka-band channel using a Markov process to capture the impact of the temporal correlation in weather conditions. We then develop a rate adaptation algorithm to optimize the data rate based on real time feedback on the measured channel conditions. Our algorithm achieves both higher throughput and link availability as compared to the constant rate scheme presently in use. C1 [Sun, Jun; Modiano, Eytan] MIT, Informat & Decis Syst Lab, 77 Massachusetts Ave, Cambridge, MA 02139 USA. [Gao, Jay; Shambayati, Shervin] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Sun, J (reprint author), MIT, Informat & Decis Syst Lab, 77 Massachusetts Ave, Cambridge, MA 02139 USA. EM junsun@mit.edu; Jay.L.Gao@jpl.nasa.gov; Shervin.Shambayati@jpl.nasa.gov; modiano@mit.edu NR 4 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1278 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583102013 ER PT S AU Riha, AP Okino, C AF Riha, Andrew P. Okino, Clayton GP IEEE TI An Advanced Orbiting Systems approach to quality of service in space-based intelligent communication networks SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB As humans and robotic technologies are deployed in future constellation systems, differing traffic services will arise, e.g., realtime and non-realtime. In order to provide a quality of service framework that would allow humans and robotic technologies to interoperate over a wide and dynamic range of interactions, a method of classifying data as realtime or non-realtime is needed. In this paper, we present an approach that leverages the Consultative Committee for Space Data Systems (CCSDS) Advanced Orbiting Systems (AOS) data link protocol. Specifically, we redefine the AOS Transfer Frame Replay Flag in order to provide an automated store-and-forward approach on a per service basis for use in the next-generation Interplanetary Internet. In addition to addressing the problem of intermittent connectivity and associated services, we propose a follow-on methodology for prioritizing data through further modification of the AOS Transfer Frame. C1 [Riha, Andrew P.; Okino, Clayton] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 238-343, Pasadena, CA 91109 USA. RP Riha, AP (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 238-343, Pasadena, CA 91109 USA. EM riha@iastate.edu; clayton.okino@jpl.nasa.gov FU National Aeronautics and Space Administration FX The research described in this paper was carried out at the Jet Propulsion Laboratory, California Institute of Technology and was sponsored by the National Aeronautics and Space Administration. NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1285 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583102014 ER PT S AU Rieser, J Berry, K Clare, L Slywczak, R AF Rieser, Jack Berry, Kirk Clare, Loren Slywczak, Richard GP IEEE TI The NASA Space Communications Testbed (SCT) SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB A robust and continuously available space communications network will play a key role in the planning and execution of safe and successful manned and robotic missions to the Moon, Mars and beyond. As future space missions become increasingly complex, it is essential that NASA develop a low cost method for validating, optimizing and verifying communications architectures, technologies and operational procedures for the evolving elements of the Space Exploration program. To this end, the Space Communications Testbed (SCT) is being developed by Comsat Laboratories, Glenn Research Center, Jet Propulsion Laboratory, Goddard Space Flight Center, and Langley Research Center. The SCT will be geographically distributed and seamlessly integrated between Comsat Laboratories and the various NASA Centers with each providing support in their relevant areas of expertise. The SCT will focus on the detailed testing of advanced space and ground communications networks, technologies and client applications essential for future exploration missions. C1 [Rieser, Jack; Berry, Kirk] Comsat Labs, Div ViaSat, 20511 Seneca Meadows Pkwy, Germantown, MD 20876 USA. [Clare, Loren] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. [Slywczak, Richard] Glenn Res Ctr, Cleveland, OH 44135 USA. RP Rieser, J (reprint author), Comsat Labs, Div ViaSat, 20511 Seneca Meadows Pkwy, Germantown, MD 20876 USA. EM jack.rieser@viasat.com; kirk.berry@viasat.com; Loren.P.Clare@jpl.nasa.gov; Richard.A.Slywczak@nasa.gov NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1305 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583102016 ER PT S AU Tarello, A Gao, J Modiano, E AF Tarello, Alessandro Gao, Jay Modiano, Eytan GP IEEE TI Energy efficient transmission scheduling over Mars proximity links SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB We consider the scheduling of transmissions from an energy limited Mars lander to a Mars orbiter. Typically, the channel quality of the Mars proximity links is time-varying due to orbital dynamics, multi-path effects and the antenna positioning on the lander. Since the channel state determines the throughput obtained per unit of energy transmitted, it is desirable to select when, and at what data rate, to transmit based on channel conditions. In this paper we consider the dual problem of maximizing the throughput of a lander that has a limited amount of energy to be used for transmission; and minimizing the energy consumption used for transmission of data subject to delay constraints. In [1], [3] it was shown, using techniques from Dynamic Programming, that energy efficiency can be signiticantly improved through an adaptive rate and power allocation scheme. We apply the policies developed in [1] and [3] to the Mars proximity link and compare them with scheduling algorithms presently in use for proximity links. Our simulations, using channel measurement data obtained from NASA's 2001 Mars Odyssey orbiter and the Mars Exploration Rover (MER) project, show over an order of magnitude increase in throughput and decrease in energy consumption through the use of the Dynamic Programming based rate and power adaptation scheme. C1 [Tarello, Alessandro] Politecn Torino, Dept Elect Engn, Telecommun Networks Grp, Cso Duca Abruzzi 24, I-10129 Turin, Italy. [Gao, Jay] Commun Network Grp, Jet Prop Lab, Pasadena, CA 91109 USA. [Modiano, Eytan] MIT, Lab Informat & Decis Syst, Cambridge, MA 02139 USA. RP Tarello, A (reprint author), Politecn Torino, Dept Elect Engn, Telecommun Networks Grp, Cso Duca Abruzzi 24, I-10129 Turin, Italy. EM tarello@mail.tlc.polito.it; jay.l.gao@jpl.nasa.gov; modiano@mit.edu NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1324 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583102018 ER PT S AU Toung, J Gilstrap, R Freeman, K AF Toung, Jerry Gilstrap, Raymond Freeman, Kenneth GP IEEE TI A split implementation of the dynamic source routing protocol for lunar/planetary surface communications SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Future NASA exploration missions will involve teams of humans and robots working together to achieve science objectives on lunar and planetary surfaces. Members of these teams must be able to communicate with each other interactively as they work together in close proximity. However, current operational procedures and technologies are based on the assumption that surface elements operate in isolation and communicate solely with the Earth, either directly or through orbiting relays. The use of direct wireless communications among local surface elements will be necessary to achieve optimal communications efficiency. However, the surface elements are mobile and may lose communication with one another, due to traveling either out of range or behind an obstruction. This problem can be addressed through the use of a mobile ad hoc network routing protocol, allowing nodes unable to communicate directly to remain in contact by relaying data through one or more intermediate nodes. To test this method of dynamic surface-to-surface communications, we have implemented the Dynamic Source Routing (DSR) protocol in a UNIX-based test environment. DSR is an efficient routing protocol that allows independent wireless nodes to self-organize into an ad hoc network. To enhance performance, forwarding and routing functions are split between kernel and user space, respectively. We have conducted field testing to determine the performance and effectiveness of DSR in maintaining connectivity among mobile nodes in the presence of communications outages caused by distance or obstructions. The results suggest that mobile ad hoc routing is a promising basis for communications among surface elements.(12). C1 [Toung, Jerry] NASA, Ames Res Ctr, Adv Management Technol Inc, M-S 258-6, Moffett Field, CA 94035 USA. [Gilstrap, Raymond; Freeman, Kenneth] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Toung, J (reprint author), NASA, Ames Res Ctr, Adv Management Technol Inc, M-S 258-6, Moffett Field, CA 94035 USA. EM jtoung@nren.nasa.gov; ray.gilstrap@nasa.gov; kenneth.freeman-1@nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1334 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583102019 ER PT S AU Stadter, PA Sharer, PJ Guzman, JJ Engelbrecht, CS Eng, DA Finnegan, EJ Bussey, DB Spudis, PD Reed, CLB Nozette, S AF Stadter, P. A. Sharer, P. J. Guzman, J. J. Engelbrecht, C. S. Eng, D. A. Finnegan, E. J. Bussey, D. B. Spudis, P. D. Reed, C. L. B. Nozette, S. GP IEEE TI Evolvable navigation and communication infrastructure for lunar exploration SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB The NASA Exploration Initiative provides a defining vision for the U.S. space program and an implementation of U.S. policy that will include a series of human and robotic missions to the Moon with a goal to thereby enabling ultimate exploration of Mars and other destinations. The success of this initiative will rest on the foundation of the initial lunar missions and the ability to develop the means for a sustained human presence on the moon.. These missions can be aided and enabled by a navigation and communication infrastructure that can evolve in capability to support lunar operations and data collection. This paper describes a system concept for evolving a lunar navigation/communication infrastructure (LNCI). The described approach uses small spacecraft that are capable of launch as auxiliary payloads. The mission concept is detailed, including spacecraft design, payload concepts and performance estimates for navigation precision and communications coverage. A complete lunar infrastructure would provide global, persistent high-precision navigation and full communications connectivity among lunar elements and the Earth. Detailed herein is an approach for implementation of a prototype LNCI system that would provide navigation and communication services to near-term RLEP missions (e.g., RLEP2 through RLEP4) and demonstrate the LNCI concept such that sustainment of the capability could be transitioned to NASA operational elements and/or industry. The system consists of four small, cost-effective spacecraft that provide radio frequency (RF)-based navigation and communication services from polar orbits. The system concept is designed to evolve by providing improved navigation accuracy and increased communication coverage and bandwidth as additional spacecraft supplement the infrastructure. C1 [Stadter, P. A.; Sharer, P. J.; Guzman, J. J.; Engelbrecht, C. S.; Eng, D. A.; Finnegan, E. J.; Bussey, D. B.; Spudis, P. D.; Reed, C. L. B.] Johns Hopkins Univ, Appl Phys Lab, 11100 Johns Hopkins Rd, Laurel, MD 20723 USA. [Nozette, S.] NASA, Space Miss Operat Directorate, Washington, DC 20546 USA. RP Stadter, PA (reprint author), Johns Hopkins Univ, Appl Phys Lab, 11100 Johns Hopkins Rd, Laurel, MD 20723 USA. RI Bussey, Ben/D-7892-2016 NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1381 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583102024 ER PT S AU Biswas, A Khatri, F Boroson, D AF Biswas, A. Khatri, F. Boroson, D. GP IEEE TI Near-Sun free-space optical communications from space SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT DE free-space; laser communication; Sun-Earth Probe (SEP) angle; Sun-Probe-Earth (SPE) angle ID RECEIVER; SYSTEM AB Free-space optical communications offers expanded data return capacity, from probes distributed throughout the solar system and beyond. Space-borne and Earth-based optical transceivers used for communicating optically, will periodically encounter near-Sun pointing. This will result in an increase in the scattered background-light flux, often contributing to degraded link performance. The varying duration of near-Sun pointing link operations relative to the location of space-probes, is discussed in this paper. The impact of near-Sun pointing on link performance for a direct detection photon-counting communications system is analyzed for both ground- and space-based Earth receivers. Finally, the impact of near-Sun pointing on space-borne optical transceivers is discussed. C1 [Biswas, A.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Khatri, F.; Boroson, D.] MIT, Lincoln Lab, Lexington, MA 02420 USA. RP Biswas, A (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM abiswas@jpl.nasa.gov NR 16 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1395 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583102026 ER PT S AU Eftekhar, AA Hashmi, AJ Adibi, A Amoozegar, F AF Eftekhar, Ali Asghar Hashmi, Ali Javad Adibi, Ali Amoozegar, Farid GP IEEE TI The effect of synchronization errors on the performance of telescope arrays for optical deep space communications SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB (12)Evolving optical deep space communication network architecture requires incremental growth in the total aperture. On the other hand, the cost of a large aperture telescope grows exponentially as a function of its diameter, therefore telescope array architecture could provide a cost effective scalable growth for an evolving optical deep space network. However, the total aperture size and the corresponding breakdown into smaller individual telescope segments poses some system architecture impact in terms of site selection of the entire network, and the number of telescopes that fall within the footprint from the space-to-earth at various distances, e.g., Moon, Mars, etc. In this paper, the effect of synchronization on the performance of the telescope arrays is analyzed. An adaptive method based on Kalman filtering is developed and used to synchronize different telescope signals in a telescope array with PPM modulation and direct detection. It is shown that the degradation in combined signal due to synchronization error can be reduced to a small value so that it places only a minor limitation on the number of telescopes in a telescope array. C1 [Eftekhar, Ali Asghar; Hashmi, Ali Javad; Adibi, Ali] Georgia Inst Technol, Atlanta, GA 30332 USA. [Amoozegar, Farid] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Eftekhar, AA (reprint author), Georgia Inst Technol, Atlanta, GA 30332 USA. EM eftekhar@ece.gatech.edu; Farid.Amoozegar@jpl.nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1404 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583102027 ER PT S AU Shambayati, S AF Shambayati, Shervin GP IEEE TI Weather related continuity and completeness on deep space Ka-band links: Statistics and forecasting SO 2006 IEEE Aerospace Conference, Vols 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Due to lack of spectrum at 8.41 GHz (X-band) future NASA deep space missions will be using 32 GHz Ka-band. Since combating adverse weather events require gins at Ka-band, link design methods prohibitively large margins based on maximizing the average data return over the link subject to a minimum link availability have been proposed. Furthermore, weather forecasting has also been suggested as means of combating the weather effects on the link. While the performance of these methods in term of data return has been well-understood, questions have remained about the completeness and continuity performance of the link. In this paper the concept of link "stability" as means of measuring the continuity of the link is introduced and through it, along with the distributions of "good" periods and "bad" periods, the performance of the proposed Ka-band link design method using both forecasting and long-term statistics has been analyzed. The results indicate that the proposed link design method has relatively good continuity and completeness characteristics even when only long-term statistics are used and that the continuity performance further improves when forecasting is employed. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Shambayati, S (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 IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1456 EP 1463 PG 8 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583102033 ER PT S AU Kerczewski, RJ AF Kerczewski, Robert J. GP IEEE TI Emerging definition of next-generation of aeronautical communications SO 2006 IEEE Aerospace Conference, Vols 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Aviation continues to experience rapid growth. In regions such as the United States and Europe air traffic congestion is constraining operations, leading to major new efforts to develop methodologies and infrastructures to enable continued aviation growth through transformational air traffic management systems. Such a transformation requires better communications linking airborne and ground-based elements. Technologies for next-generation communications, the required capacities, frequency spectrum of operation, network interconnectivity, and global interoperability are now receiving increased attention. A number of major planning and development efforts have taken place or are in process now to define the transformed airspace of the future. These activities include government and industry led efforts in the United States and Europe, and by international organizations. This paper will review the features, approaches, and activities of several representative planning and development efforts, and identify the emerging global consensus on requirements of next generation aeronautical communications systems for air traffic control. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Kerczewski, RJ (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 2 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1690 EP 1696 PG 7 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583103002 ER PT S AU Ivancic, WD AF Ivancic, William D. GP IEEE TI Modular, cost-effective, extensible avionics architecture for secure, mobile communications SO 2006 IEEE Aerospace Conference, Vols 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Current onboard communication architectures are based upon an all-in-one communications management unit. This unit and associated radio systems has regularly been designed as a one-off, proprietary system. As such, it lacks flexibility and cannot adapt easily to new technology, new communication protocols, and new communication links. This paper describes the current avionics communication architecture and provides a historical perspective of the evolution of this system. A new onboard architecture is proposed that allows full use of commercial-off-the-shelf technologies to be integrated in a modular approach thereby enabling a flexible, cost-effective and fully deployable design that can take advantage of ongoing advances in the computer, cryptography, and telecommunications industries. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Ivancic, WD (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 13 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1737 EP 1745 PG 9 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583103007 ER PT S AU Carek, J AF Carek, Jerry GP IEEE TI Space Power Facility for testing large space optical systems SO 2006 IEEE Aerospace Conference, Vols 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB The Space Power Facility is located at NASA's Glenn Research Center Plum Brook Station in Sandusky, Ohio. It is the world's largest space simulation test facility with a test chamber that is 30.5m (100ft) in diameter by 37.2m (122ft) high. It has been used to test a variety of large space flight hardware and space systems for NASA, other government agencies, and the private sector over the last 20 years. Most of the design features of the facility provide unique characteristics that are ideally suited to meet the requirements of large space optical system thermal/vacuum testing. This paper(1.2) describes the Space Power Facility's unique characteristics and systems and how they meet these requirements. Future large space optical systems will require a facility that can handle large, delicate hardware in a clean environment. Large high bay clean rooms will be needed for pre-test build-up and checkout activities. A large test chamber with easy access will be needed near the build-up area to minimize the risk of transporting the hardware into the chamber for thermal/vacuum testing. The Space Power Facility's unique architecture with large high bays on each side of the test chamber is ideal for handling and processing large hardware and systems. Large space optical system testing will also require a test environment that is as quiet as possible from a vibration standpoint. By nature of the construction of the Space Power Facility, the vibration environment has been found to be extremely stable. Additionally, large space optical system testing must be performed at high-vacuum (< 1x10-5 Torr) conditions and many future systems require testing at cryogenic temperatures. The facility's high-vacuum system for pumping the test chamber has recently been upgraded with cryopumps and high-vacuum isolation valves to provide a contaminant-free, clean testing environment. To ensure that the facility upgrades will meet the demands of future test programs, an integrated systems test was performed to assess the operation and performance of the chamber and the new vacuum pumping system. C1 NASA, Glenn Res Ctr, Plum Brook Stn, Sandusky, OH 44089 USA. RP Carek, J (reprint author), NASA, Glenn Res Ctr, Plum Brook Stn, 6100 Columbus Ave, Sandusky, OH 44089 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 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1798 EP 1806 PG 9 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583103013 ER PT S AU Liebe, CC Padgett, C Chapsky, J Wilson, D Brown, K Jerebets, S Goldberg, H Schroeder, J AF Liebe, Carl Christian Padgett, Curtis Chapsky, Jacob Wilson, Daniel Brown, Kenneth Jerebets, Sergei Goldberg, Hannah Schroeder, Jeffrey GP IEEE TI Spacecraft hazard avoidance utilizing structured light SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB At JPL, a < 5 kg free-flying micro-inspector spacecraft is being designed for host-vehicle inspection. The spacecraft includes a hazard avoidance sensor to navigate relative to the vehicle being inspected. Structured light was selected for hazard avoidance because of its low mass and cost. Structured light is a method of remote sensing 3-dimensional structure of the proximity utilizing a laser, a grating, and a single regular APS camera. The laser beam is split into 400 different beams by a grating to form a regular spaced grid of laser beams that are projected into the field of view of an APS camera. The laser source and the APS camera are separated forming the base of a triangle. The distance to all beam intersections of the host are calculated based on triangulation. C1 [Liebe, Carl Christian; Padgett, Curtis; Chapsky, Jacob; Wilson, Daniel; Brown, Kenneth; Jerebets, Sergei; Goldberg, Hannah; Schroeder, Jeffrey] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Liebe, CC (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM carl.c.liebe@jpl.nasa.gov FU National Aeronautics and Space Administration FX The research described in this paper was carried out at the Jet Propulsion Laboratory, California Institute of Technology and was sponsored by the National Aeronautics and Space Administration. References herein to any specific commercial product, process or service by trademark, manufacturer, or otherwise, does not constitute or imply its endorsement by the United States Government or the Jet Propulsion Laboratory, California Institute of Technology. NR 12 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1879 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583103021 ER PT S AU Peng, GS de la Torre-Juarez, M Farley, RW Wessel, JE AF Peng, Grace S. de la Torre-Juarez, Manuel Farley, Robert W. Wessel, John E. GP IEEE TI Impacts of upper tropospheric clouds on GPS radio refractivity SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID WATER-VAPOR AB Global Positioning System radio occultations (GPS RO) are active limb soundings in which a receiver aboard a low earth orbiting satellite tracks the coherent signal broadcast by the GPS satellites as they occult behind the Earth's atmosphere(1,2). The GPS signal delay introduced by the atmosphere along the entire signal path can be inverted to yield high vertical resolution radio-refractivity profiles as a function of height from the lower-troposphere to the stratosphere. Using various retrieval techniques, the neutral atmosphere refractivity can yield vertical profiles of temperature and water vapor. Recently, GPS RO has been used to identify thin moist atmospheric layers and to globally map boundary layer and tropopause heights as well as tropopause sharpness with high vertical sensitivity. The expected thermodynamic cloud boundary signatures and how they would appear in GPS refractivity are discussed; numerical algorithms for detecting cloud boundaries are proposed. The algorithms are validated using nearly coincident radio occultations from the CHAMP satellite and lidar and radiosonde data over a four-night period near Hawaii. The validation shows that the algorithms correctly determine cloud boundaries whenever lidar detected clouds, even when clouds are thin or layered. C1 [Peng, Grace S.; Farley, Robert W.; Wessel, John E.] Aerosp Corp, POB 92957,M1-102, Los Angeles, CA 90009 USA. [de la Torre-Juarez, Manuel] CALTECH, Jet Prop Lab, MS 138308, Pasadena, CA 91109 USA. RP Peng, GS (reprint author), Aerosp Corp, POB 92957,M1-102, Los Angeles, CA 90009 USA. EM Grace.S.Peng@aero.org; mtj@jpl.nasa.gov; Robert.W.Farley@aero.org; John.E.Wessel@aero.org FU National Aeronautics and Space Administration; The Aerospace Corporation (all others) under The Aerospace Corporation's Independent Research and Development Program; Defense Meteorological Satellite Program; U.S. Air Force Space and Missile Systems Center [FA8802-04-C-0001] FX The authors would like to thank C. Ao for the RO retrievals and J. Hecht and A. J. Manucci for many helpful comments. This research was carried out at the Jet Propulsion Laboratory/California Institute of Technology (MTJ), under a contract with the National Aeronautics and Space Administration and at The Aerospace Corporation (all others) under The Aerospace Corporation's Independent Research and Development Program and the Defense Meteorological Satellite Program, funded by the U.S. Air Force Space and Missile Systems Center under Contract No. FA8802-04-C-0001. NR 17 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1889 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583103022 ER PT S AU Coyle, DB Stysley, PR AF Coyle, D. Barry Stysley, Paul R. GP IEEE TI The High Output Maximum Efficiency Resonator (HOMER) developed for long life, space-based altimetry SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID ND-YAG LASER AB We report on the status of the High Output Maximum Efficiency Resonator (HOMER), a prototype space-flight Nd:YAG, diode pumped, unstable resonator. HOMER, the 3(rd) generation of this design based on the High Efficiency Laser Transmitter, is a stand-alone oscillator that has achieved similar to 2 billion 10 ns q-switched pulses at 17-15 mJ. In this configuration HOMER achieves an excellent optical efficiency of similar to 16%. It is currently the lead candidate for the Biomass Monitoring Mission (BioMM); a global vegetation instrument currently under design and preproposal at NASA-GSFC. C1 [Coyle, D. Barry] NASA, Goddard Space Flight Ctr, Code 690-1, Greenbelt, MD 20771 USA. [Stysley, Paul R.] Amer Univ, Dept Phys, Washington, DC 20016 USA. RP Coyle, DB (reprint author), NASA, Goddard Space Flight Ctr, Code 690-1, Greenbelt, MD 20771 USA. EM barry@cornfed.gsfc.nasa.gov; paul@cornfed.gsfc.nasa.gov NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 1895 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583103023 ER PT S AU Martin, S AF Martin, Stefan GP IEEE TI Progress in four-beam nulling: results from the Terrestrial Planet Finder Planet Detection Testbed SO 2006 IEEE Aerospace Conference, Vols 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB The Terrestrial Planet Finder Interferometer (TPF-I) is a large space telescope consisting of four 4 meter diameter telescopes flying in formation in space together with a fifth beam combiner spacecraft. The Planet Detection Testbed has been developed to study the combination of the four beams of light from the telescopes in a twin nulling beam combiner which emulates the functionality of the TPF-I beam combiner. Recent results from the testbed include nulling of 4 input beams simultaneously at null depths of 250,000 to one and planet detection at a contrast ratio of one 2 millionth of the intensity of the star. For successful detection of exoplanets, the space interferometer will need to reach null depths of one million to one and demonstrate high stability during long observing periods. Testbed program goals include the same one million to one null depths and stability of the null comparable to the levels required in space (2 10(-7)). (1,2) C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Martin, S (reprint author), CALTECH, Jet Prop Lab, MS 306-388,Oak Grove Dr, Pasadena, CA 91109 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2256 EP 2263 PG 8 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583104003 ER PT S AU Serabyn, E Mennesson, B AF Serabyn, E. Mennesson, B. GP IEEE TI Testing the TPF interferometry approach before launch SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID NULLING INTERFEROMETER; COMBINER; PLANETS AB One way 1,2 to directly detect nearby extra-solar planets is via their thermal infrared emission, and with this goal in mind, both NASA and ESA are investigating cryogenic infrared interferometers. Common to both agencies' approaches to faint off-axis source detection near bright stars is the use of a rotating nulling interferometer, such as the Terrestrial Planet Finder interferometer (TPF-I), or Darwin. In this approach, the central star is nulled, while the emission from off-axis sources is transmitted and modulated by the rotation of the off-axis fringes. Because of the high contrasts involved, and the novelty of the measurement technique, it is essential to gain experience with this technique before launch. Here we describe a simple ground-based experiment that can test the essential aspects of the TPF signal measurement and image reconstruction approaches by generating a rotating interferometric baseline within the pupil of a large single-aperture telescope. This approach can mimic potential space-based interferometric configurations, and allow the extraction of signals from off-axis sources using the same algorithms proposed for the space-based missions. This approach should thus allow for testing of the applicability of proposed signal extraction algorithms for the detection of single and multiple near-neighbor companions. Here the optical approach and the expected performance of the experiment are described. Interestingly, because of the small inner working distance possible with this approach, such a "nulling coronagraph" may be able to outperform classical coronagraphs in certain respects. C1 [Serabyn, E.; Mennesson, B.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 171-113, Pasadena, CA 91109 USA. RP Serabyn, E (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 171-113, Pasadena, CA 91109 USA. EM gene.serabyn@jpl.nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2264 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583104004 ER PT S AU Lindensmith, CA Briggs, HC Beregovski, Y Feria, VA Goullioud, R Gursel, Y Hahn, I Kinsella, G Orzewalla, M Phillips, C AF Lindensmith, Chris A. Briggs, H. Clark Beregovski, Yuri Feria, V. Alfonso Goullioud, Renaud Gursel, Yekta Hahn, Inseob Kinsella, Gary Orzewalla, Matthew Phillips, Charles GP IEEE TI Development and validation of high precision models for SIM Planetquest SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB SIM Planetquest (SIM) is a large optical interferometer for making microarcsecond measurements of the positions of stars, and to detect Earth-sized planets around nearby stars. To achieve this precision, SIM requires stability of optical components to tens of picometers per hour. The combination of SIM's large size (9 meter baseline) and the high stability requirement makes it difficult and costly to measure all aspects of system performance on the ground. To reduce risks, costs and to allow for a design with fewer intermediate testing stages, the SIM project is developing an integrated thermal, mechanical and optical modeling process that will allow predictions of the system performance to be made at the required high precision. This modeling process uses commercial, off-the-shelf tools and has been validated against experimental results at the precision of the SIM performance requirements. This paper(1,2) presents the description of the model development, some of the models, and their validation in the Thermo-Opto-Mechanical (TOM3) testbed which includes full scale brassboard optical components and the metrology to test them at the SIM performance requirement levels. C1 [Lindensmith, Chris A.; Briggs, H. Clark; Beregovski, Yuri; Feria, V. Alfonso; Goullioud, Renaud; Gursel, Yekta; Hahn, Inseob; Kinsella, Gary; Orzewalla, Matthew; Phillips, Charles] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Lindensmith, CA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM lindensm@mail.jpl.nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2273 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583104005 ER PT S AU Goullioud, R Lindensmith, CA Hahn, I AF Goullioud, R. Lindensmith, C. A. Hahn, I. GP IEEE TI Results from the TOM3 testbed: Thermal deformation of optics at the picometer level. SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Future space-based optical interferometers, such as the Space Interferometer Mission (SIM), require thermal stability of the optical wavefront to the level of picometers in order to produce astrometric data at the micro-arc-second level. In SIM, the internal path of the interferometer will be measured with a small metrology beam whereas the starlight fringe position is estimated from a large concentric annular beam. To achieve the micro-arc-second observation goal for SIM, it is necessary to maintain the optical path difference between the central and the outer annulus portions of the wavefront of the front-end telescope optics to a few tens of picometers for an hour. The Thermo-Opto-Mechanical testbed (TOM3) was developed at the Jet Propulsion Laboratory to measure thermally induced optical deformations of a full-size flight-like beam compressor and siderostat, the two largest optics on SIM, in flight-like thermal environments. A Common Path Heterodyne Interferometer (COPHI) developed at JPL was used for the fine optical path difference measurement as the metrology sensor. The system was integrated inside a large vacuum chamber in order to mitigate the atmospheric and thermal disturbances. The Siderostat was installed in a temperature-controlled thermal shroud inside the vacuum chamber, creating a flight-like thermal environment. Detailed thermal and structural models of the test articles (siderostat and compressor) were also developed for model prediction and correlation of the thermal deformations. Experimental data shows SIM required thermal stability of the test articles and good agreement with the model predictions. C1 [Goullioud, R.; Lindensmith, C. A.; Hahn, I.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 171-113, Pasadena, CA 91109 USA. RP Goullioud, R (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 171-113, Pasadena, CA 91109 USA. EM renaud@jpl.nasa.gov FU Jet Propulsion Laboratory of the California Institute of Technology; National Aeronautics and Space Administration FX The research described in this publication was performed at the Jet Propulsion Laboratory of the California Institute of Technology, under contract with the National Aeronautics and Space Administration. The authors would like to thank Edouard Schmidlin, Jim Moore, Shonte Wright, Yuanming Liu and the TOM3 team for th eir contribution to the success of the experiments. NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2289 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583104006 ER PT S AU Evans, JP AF Evans, Jordan P. GP IEEE TI Engineering the LISA project: Systems engineering challenges SO 2006 IEEE Aerospace Conference, Vols 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB The Laser Interferometer Space Antenna (LISA) is a joint NASA/ESA mission to detect and measure gravitational waves with periods from 1 s to 10000 s. The systems engineering challenges of developing a giant interferometer, 5 million kilometers on a side, are numerous. Some of the key challenges are presented in this paper(1,2). The organizational challenges imposed by sharing the engineering function between three centers (ESA ESTEC, NASA GSFC, and JPL) across nine time zones are addressed. The issues and approaches to allocation of the acceleration noise and measurement sensitivity budget terms across a traditionally decomposed system are discussed. Additionally, using LISA to detect gravitational waves for the first time presents significant data analysis challenges, many of which drive the project system design. The approach to understanding the implications of science data analysis on the system is also addressed. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Evans, JP (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 301-490, Pasadena, CA 91109 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2300 EP 2307 PG 8 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583104007 ER PT S AU Turyshev, SG AF Turyshev, Slava G. GP IEEE TI The science, technology and mission design for the Laser Astrometric Test of Relativity SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID POST-NEWTONIAN FORMALISM; ANGULAR POWER SPECTRUM; TENSOR-SCALAR THEORIES; GRAVITATIONAL DEFLECTION; GENERAL-RELATIVITY; 2ND-ORDER CONTRIBUTIONS; COSMOLOGICAL CONSTANT; GRAVITY; LIGHT; SUPERNOVAE AB The Laser Astrometric Test of Relativity (LATOR) is a Michelson-Morley-type experiment designed to test the Einstein's general theory of relativity in the most intense gravitational environment available in the solar system - the close proximity to the Sun. By using independent time-series of highly accurate measurements of the Shapiro time-delay (laser ranging accurate to 1 cm) and interferometric astrometry (accurate to 0.1 picoradian), LATOR will measure gravitational deflection of light by the solar gravity with accuracy of 1 part in a billion, a factor similar to 30,000 better than currently available. LATOR will perform series of highly-accurate tests of gravitation and cosmology in its search for cosmological remnants of scalar field in the solar system. We present science, technology and mission design for the LATOR mission. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Turyshev, SG (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM turyshev@jpl.nasa.gov NR 46 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2308 EP 2323 PG 16 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583104008 ER PT S AU Okino, C Mukai, R Schoolcraft, J Gray, A AF Okino, Clayton Mukai, Ryan Schoolcraft, Joshua Gray, Andrew GP IEEE TI Reconfigurable protocol sensing for space-based applications SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB In this paper, we present sensing performance using an architecture for a reconfigurable protocol chip for space-based applications(12). We examine three common framing standards and present the sensing performance of these standards and their decorrelation statistics. We also examine the impact over lossy links. Finally, we describe a process flow for development of this sensor mechanism. C1 [Okino, Clayton; Mukai, Ryan; Schoolcraft, Joshua; Gray, Andrew] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 238-343, Pasadena, CA 91109 USA. RP Okino, C (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 238-343, Pasadena, CA 91109 USA. EM clayton.okino@jpl.nasa.gov; ryan.mukai@jpl.nasa.gov; joshua.schoolcraft@jpl.nasa.gov; andrew.gray@jpl.nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2324 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583104009 ER PT S AU Rakow, G Schnurr, R Parkes, S AF Rakow, Glenn Schnurr, Richard Parkes, Steve GP IEEE TI SpaceWire protocol ID: What does it means to you? SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB (1,2)t-SpaceWire is becoming a popular solution for satellite high-speed data buses, because it is a simple standard that provides great flexibility for a wide range of system requirements. It is simple in packet format and protocol, allowing users to easily tailor their implementation for their specific application. Some of the attractive aspects of SpaceWire that make it easy to implement also make it hard for future reuse. Protocol reuse is difficult because SpaceWire does not have a defined mechanism to communicate with the higher layers of the protocol stack. This has forced users of SpaceWire to define unique packet formats and define how these packets are to be processed. SpaceWire also has two different packet formats that may be presented to the end user, one with a Destination Address and one without. This further complicates the system design, as both options cannot be supported. Each particular mission writes it's own Interface Control Document (ICD) and tailors SpaceWire for it's specific requirements making reuse difficult. Part of the reason for this habit may be because engineers typically optimize designs for their own requirements in the absence of a standard. This is an inefficient use of project resources and costs more to develop missions. C1 [Rakow, Glenn; Schnurr, Richard] NASA, Goddard Space Flight Ctr, Code 561, Greenbelt, MD 20771 USA. [Parkes, Steve] Univ Dundee, Space Technol Ctr, Dundee DD1 4HN, Scotland. RP Rakow, G (reprint author), NASA, Goddard Space Flight Ctr, Code 561, Greenbelt, MD 20771 USA. EM Glenn.P.Rakow@nasa.gov; Richard.G.Schnurr@nasa.gov; sparkes@computing.dundee.ac.uk NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2387 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583104016 ER PT S AU Strauss, K Black, BW Joshi, V Ohno, M Ida, J Nagatomo, Y AF Strauss, Karl Black, Bruce W. Joshi, Vikram Ohno, Morifumo Ida, Jiro Nagatomo, Yoshiki GP IEEE TI The effect of integration of Strontium-Bismuth-Tantalate capacitors onto SOI wafers. SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB We report for the first time the successful integration of Strontium-Bismuth-Tantalate (SBT) ferroelectric capacitors on an SOI Substrate. We have verified that the unique processing requirements of SBT capacitors does not affect the properties of the surrounding Fully Depleted Silicon On Insulator (FD-SOI) transistors, and, conversely, we have verified that the SOI processing does not affect the quality of the SBT capacitors. Further, we present total ionization radiation test results on the base, Oki FD-SOI material. We present that processing of the SBT material has no effect on the radiation performance of the FD-SOI transistors. C1 [Strauss, Karl] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. [Black, Bruce W.] Raytheon, Sudbury, ON, Canada. [Joshi, Vikram] IC Intelligence, Palo Alto, CA USA. [Ohno, Morifumo; Ida, Jiro; Nagatomo, Yoshiki] Oki Elect Ind Co Ltd, Hachioji, Tokyo, Japan. RP Strauss, K (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. EM karl.f.strauss@jpl.nasa.gov FU California Institute of Technology Jet Propulsion Laboratory, Pasadena, California, US; NASA [7107141]; NASA Prometheus Program FX This development funded, in part, by California Institute of Technology Jet Propulsion Laboratory, Pasadena, California, US, in support of NASA Task Order 7107141 and the NASA Prometheus Program NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2434 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583104021 ER PT S AU Ramos, J Samson, J Lupia, D Troxel, I Subramaniyan, R Jacobs, A Greco, J Cieslewski, G Curreri, J Fischer, M Grobelny, E George, A Aggarwal, V Patel, M Some, R AF Ramos, Jeremy Samson, John Lupia, David Troxel, Ian Subramaniyan, Rajagopal Jacobs, Adam Greco, James Cieslewski, Grzegorz Curreri, John Fischer, Michael Grobelny, Eric George, Alan Aggarwal, Vikas Patel, Minesh Some, Raphael GP IEEE TI High-performance, Dependable Multiprocessor SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB (123)With the ever-increasing demand for higher bandwidth and processing capacity of today's space exploration, space science, and defense missions, the ability to efficiently apply commercial-off-the-shelf (COTS) processors for on-board computing is now a critical need. In response to this need, NASA's New Millennium Program office has commissioned the development of Dependable Multiprocessor (DM) technology for use in payload and robotic missions. The Dependable Multiprocessor technology is a COTS-based, power-efficient, high-performance, highly dependable, fault-tolerant cluster computer. To date, Honeywell has successfully demonstrated a TRL4 prototype of the Dependable Multiprocessor [1], and is now working on the development of a TRL5 prototype. For the present effort Honeywell has teamed up with the University of Florida via its High-performance Computing and Simulation (HCS) Research Laboratory, and together the team has demonstrated major elements of the Dependable Multiprocessor TRL5 system. This paper provides a detailed description of the basic Dependable Multiprocessor technology, and the TRL5 technology prototype currently under development. C1 [Ramos, Jeremy; Samson, John; Lupia, David] Honeywell Aerosp, Def & Space, 13350 US Highway 19 N, Clearwater, FL 33764 USA. [George, Alan] Univ Florida, Gainesville, FL 32611 USA. [Aggarwal, Vikas; Patel, Minesh] Tandel Syst, Oldsmar, FL USA. [Some, Raphael] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Ramos, J (reprint author), Honeywell Aerosp, Def & Space, 13350 US Highway 19 N, Clearwater, FL 33764 USA. EM jeremy.ramos@honeywell.com; john.r.samson@honywell.com; george@hcs.ufl.edu; mpatel@tandelsys.com; rsome@jpl.nasa.gov FU NASA NMP ST-8 [NMO-710209]; National Aeronautics and Space Administration. FX The research described in this paper was carried out under the auspices of the Jet Propulsion Laboratory, California Institute of Technology, under contract with the National Aeronautics and Space Administration. The Dependable Multiprocessor effort is funded under NASA NMP ST-8 contract NMO-710209. NR 16 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2466 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583104025 ER PT S AU Gerke, RD Ator, D AF Gerke, R. David Ator, Danielle GP IEEE TI Embedded resistors and capacitors in organic and inorganic substrates SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Embedded resistors and capacitors were purchased from two technologies;(1,2) organic PWB and inorganic low temperature co-fired ceramic (LTCC). Small groups of each substrate were exposed to four environmental tests and several characterization tests to evaluate their performance and reliability. Even though all passive components maintained electrical performance throughout environmental testing, differences between the two technologies were observed. Environmental testing was taken beyond manufacturers' reported testing, but generally not taken to failure. When possible, data was quantitatively compared to manufacturer's data. Both technologies performed favorably with some nuances noted for each material set. The resistors were not embedded deep into the substrate structures but were placed on the surface and coated. This served two purposes: the first was that resistors could later be trimmed if they reside on the surface and the second was that it represented worst case for protection of the resistive elements for the reliability testing, mainly moisture exposure. Typically, the PC board solder resist is sufficient to protect the resistors in the PWB resistors. Should there be a pin-hole or damaged area, the environmental protection could be compromised. During the moisture environmental testing, a resistor in the PWB technology failed due to corrosion. The level of concern for this failure mechanism is elevated only for laser trimmed resistors where the coating would be opened and an additional coating is applied following the adjustment. The failed resistor in this study failed at the 1000 hour readpoint of 85%RH/85 degrees C and the failure was not an open but an increase in resistance. The capacitors exhibited a size relationship to reliability where small capacitors varied in capacitance more than large capacitor sizes selected in this study. The best physical size for the capacitors was found to be between 1 and 2 cm on a side. C1 [Gerke, R. David] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Ator, Danielle] Univ Idaho, Moscow, ID 83844 USA. RP Gerke, RD (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM david.gerke@jpl.nasa.gov; ator8374@uidaho.edu NR 11 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2527 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583104032 ER PT S AU Baloch, S Arslan, T Stoica, A AF Baloch, S. Arslan, T. Stoica, A. GP IEEE TI Design of a novel soft error mitigation technique for reconfigurable architectures SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Commercially off the shelf (COTS) available reconfigurable architectures are becoming popular for applications where high dependability, performance and low costs are mandatory constraints such as space applications. We present a unique SEE (single Event Effect) mitigation technique based upon Temporal Data Sampling and Weighted Voting for synchronous circuits and configuration bit storage for reconfigurable Architectures. The design technique addresses both conventional static SEUs (Single Event Upsets) and SETs (Single Event Transients) induced errors which result in data loss for reconfigurable architectures in space. The design technique not only eliminates all the single event upsets and single event transients but eliminates all double event upset as well. C1 [Baloch, S.] Univ Edinburgh, Sch Elect & Engn, Mayfield Rd,Kings Bldg, Edinburgh EH9 3JL, Midlothian, Scotland. [Arslan, T.] Alba Ctr, Inst Syst Level Integrat, Livingston, Scotland. [Stoica, A.] NASA, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Baloch, S (reprint author), Univ Edinburgh, Sch Elect & Engn, Mayfield Rd,Kings Bldg, Edinburgh EH9 3JL, Midlothian, Scotland. EM Sajid.Baloch@sli-institute.ac.uk; Tughrul.Arslan@ee.ed.ac.uk; Adrian.stoica@jpl.nasa.gov NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2588 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583104036 ER PT S AU Zebulum, RS Rejeshuni, R Keymeulen, D Daud, T Neff, J Stoica, A AF Zebulum, Ricardo S. Rejeshuni, Ramesham Keymeulen, Didier Daud, Taher Neff, Joseph Stoica, Adrian GP IEEE TI Extreme temperature electronics using a reconfigurable analog array SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Temperature(1 2) and radiation tolerant electronics, as well as long life survivability are key capabilities required for future NASA missions. Current approaches to electronics for extreme environments focus on component level robustness and hardening. Compensation techniques such as bias cancellation circuitry have also been employed. However, current technology can only ensure very limited lifetime in extreme environments. Previous work presented a novel approach, based on evolvable hardware technology, which allows adaptive in-situ circuit redesign/reconfiguration during operation in extreme environments. This technology would complement material/device advancements and increase the mission capability to survive harsh environments. This work describes a new reconfigurable analog chip developed by JPL and SPAWAR that is targeted for extreme temperature and evolutionary hardware experiments. Being based on Gm-C technology, this chip can have its functionality tuned and adapted to extreme temperatures through voltage bias adjustment. This tuning process will be controlled by Evolutionary Algorithms. This paper presents details of the reconfigurable analog chip as well as a system level overview. Some early experiments are also described. C1 [Zebulum, Ricardo S.; Rejeshuni, Ramesham; Keymeulen, Didier; Daud, Taher; Stoica, Adrian] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Neff, Joseph] SPAWAR, San Diego, CA USA. RP Zebulum, RS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM ricardo@brain.jpl.nasa.gov; didier.keymeulen@jpl.nasa.gov; adrian.stoica@jpl.nasa.gov FU National Aeronautics and Space Administration FX The work described in this paper was performed at the Jet Propulsion Laboratory, California Institute of Technology and was sponsored by the National Aeronautics and Space Administration. NR 15 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2597 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583104037 ER PT S AU Ramesham, R Keymeulen, D Kumar, N Zebulum, RS Mao, J Stoica, A AF Ramesham, Rajeshuni Keymeulen, Didier Kumar, Nikil Zebulum, Ricardo S. Mao, James Stoica, Adrian GP IEEE TI Data converters performance at extreme temperatures SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Space missions often require radiation and extreme-temperature hardened electronics to survive the harsh environments beyond earth's atmosphere. Traditional approaches to preserve electronics incorporate shielding, insulation and redundancy at the expense of power and weight. However, a novel way of bypassing these problems is the concept of evolutionary hardware. A reconfigurable device, consisting of several switches interconnected with analog/digital parts, is controlled by an evolutionary processor (EP). When the EP detects degradation in the circuit it sends signals to reconfigure the switches, thus forming a new circuit with the desired output. This concept has been developed since the mid-90s, but one problem remains - the EP cannot degrade substantially. For this reason, extensive testing at extreme temperatures (- 180 degrees to 120 degrees C) has been done on devices found on FPGA boards (taking the role of the EP) such as the Analog to Digital and the Digital to Analog Converter. Analysis of the results has shown that FPGA boards implementing EP with some compensation may be a practical solution to evolving circuits. This paper describes results on the tests of data converters at extreme temperatures. C1 [Ramesham, Rajeshuni; Keymeulen, Didier; Kumar, Nikil; Zebulum, Ricardo S.; Mao, James; Stoica, Adrian] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Ramesham, R (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Rajeshuni.Ramesham@jpl.nasa.gov; didier.keymeulen@jpl.nasa.gov; ricardo.zebulum@jpl.nasa.gov; adrian.stoica@jpl.nasa.gov FU National Aeronautics and Space Administration FX The work described in this paper was performed at the Jet Propulsion Laboratory, Californi a Institute of Technology and was sponsored by the National Aeronautics and Space Administration. NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2605 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583104038 ER PT S AU Keymeulen, D Ferguson, MI Breuer, L Peay, C Oks, B Yen-Cheng Kim, D MacDonald, E Foor, D Terrile, R Yee, K AF Keymeulen, Didier Ferguson, Michael I. Breuer, Luke Peay, Chris Oks, Boris Yen-Cheng Kim, Dennis MacDonald, Eric Foor, David Terrile, Richard Yee, Karl GP IEEE TI Tuning of MEMS gyroscope using evolutionary algorithm and "switched drive-angle" method. SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB We (12) propose a tuning method for Micro-Electro-Mechanical Systems (MEMS) gyroscopes based on evolutionary computation that has the capacity to efficiently increase the sensitivity of MEMS gyroscopes through tuning and, furthermore, to find the optimally tuned configuration for this state of increased sensitivity. We present the results of an experiment to determine the speed and efficiency of an evolutionary algorithm applied to electrostatic tuning of MEMS micro gyros. The MEMS gyro used in this experiment is a pyrex post resonator gyro (PRG) in a closed-loop control system. A measure of the quality of tuning is given by the difference in resonant frequencies, or frequency split, for the two orthogonal rocking axes. The current implementation of the closed-loop platform is able to measure and attain a relative stability in the sub-millihertz range, leading to a reduction of the frequency split to less than 100 mHz. C1 [Keymeulen, Didier] Jet Prop Lab, 4800 Oak Grove Dr,MS 303-300, Pasadena, CA 91109 USA. [Yen-Cheng; Kim, Dennis] Univ Calif Los Angeles, Mech & Aerosp Engn Dept, Los Angeles, CA 90095 USA. [MacDonald, Eric] Univ Texas El Paso, El Paso, TX 79968 USA. [Foor, David] Texas A&M Univ Kingsville, Kingsville, TX 78363 USA. RP Keymeulen, D (reprint author), Jet Prop Lab, 4800 Oak Grove Dr,MS 303-300, Pasadena, CA 91109 USA. EM didier.keymeulen@jpl.nasa.gov FU Research and Technology Development Evolutionary Computation Technologies for Space Systems FX The work described in this publication was carried out at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronatics and Space Administration. Special thanks to Tom Prince, who has supported this research through the Research and Technology Development grant entitled "Evolutionary Computation Technologies for Space Systems". NR 14 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2617 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583104039 ER PT S AU Chen, Y Johnson, T Mojaradi, M Cozy, S Kolawa, E Westergard, L Billman, C AF Chen, Yuan Johnson, Travis Mojaradi, Mohammad Cozy, Scott Kolawa, Elizabeth Westergard, Lynett Billman, Curtis GP IEEE TI Design for A/D converter reliability for low temperature applications SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB In this paper(1,2), we present a design for reliability approach on Analog to Digital (A/D) converters for low temperature applications. Parametric degradation, including drain saturation and linear currents, threshold voltage, transconductance and drain conductance, have been characterized to translate the hot carrier aging impact on A/D circuits under low temperatures. Both substrate current profile and operating temperature profile have been taken into consideration to determine the most applicable transistor size to be used in the A/D converter and to ensure the required A/D converter reliability for low temperature applications. C1 [Chen, Yuan; Johnson, Travis; Mojaradi, Mohammad; Cozy, Scott; Kolawa, Elizabeth] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,Mail Stop 303-230, Pasadena, CA 91109 USA. [Westergard, Lynett; Billman, Curtis] AMI Semicond, Pocatello, ID 83201 USA. RP Chen, Y (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,Mail Stop 303-230, Pasadena, CA 91109 USA. EM yuan.chen@jpl.nasa.gov FU California Institute of Technology; National Aeronautics and Space Administration FX This work was carried out at Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2625 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583104040 ER PT S AU Tudryn, CD AF Tudryn, Carissa D. GP IEEE TI Solder joint fatigue study under low temperature Martian conditions SO 2006 IEEE Aerospace Conference, Vols 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB (1,2) Electronics, without requiring heater power or enclosure in a centralized "warm electronics box," will need to survive mean surface temperatures of -120 degrees C to +20 degrees C for an extended (> 2 years) Martian mission and an operational temperature up to 85 degrees C. These surface temperatures range over one Martian day or typical cycle. Since the electronics will need to survive extended thermal cycles (3x life of 2010 cycles) under these conditions, thermally induced fatigue is a significant concern. The solder joint reliability of connectors with Sn60Pb40 finish and In80Pb15Ag5 solder on a printed wiring board was investigated. Between 638 to 1431 cycles from -120 degrees C to +85 degrees C, a small number of leads failed on a printed wiring board with a silicone conformal coating. Scanning Electronic Microscopy analysis revealed crack initiation at the lead finish and In80Pb15Ag5 solder interface in at least one case with martensitic phase transformation of tin/lead solder and the loss of ductility in the tin phase at low temperatures as the failure modes. Another failure region was composed of several intermetallic compounds with intermetallic embrittlement as a failure mode. This fatigue study determines the corresponding failure modes of the thermally stressed components at each failed interface. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Tudryn, CD (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 9 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2632 EP 2640 PG 9 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583104041 ER PT S AU Jerebets, S AF Jerebets, Sergei GP IEEE TI Star tracker focal plane evaluation for the JIMO mission SO 2006 IEEE Aerospace Conference, Vols 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID CHARGE-COUPLED-DEVICES; DAMAGE; FLUCTUATIONS; PERFORMANCE; IMAGERS AB The Jupiter Icy Moon Orbiter (JIMO) mission(1) was planned as the first implementation of Prometheus, an ambitious space exploration project proposed by NASA. The mission would provide a rigorous scientific investigation of Jupiter and three of its moons Callisto, Ganymede, and Europa. To safely and efficiently power and maneuver the spacecraft in deep space, novel technologies would be incorporated. Though launch is currently indefinitely postponed, this mission, as conceived, already presents a significant technical challenge for a robust Attitude Control System (ACS) design due to severe radiation environment of the Jovian system, and because navigation sensors must survive and function properly throughout the mission. It is particularly relevant to a spacecraft's ACS that relies on star trackers for an accurate attitude determination. A star tracker focal plane is very susceptible to impinging charged particles and cosmic gamma rays. The radiation will degrade the device performance through false signal appearance and increased noise. At Jet Propulsion Laboratory, California Institute of Technology an extensive study has been initiated to understand available visible imager technologies such as charge coupled device (CCD), charge injection device (CID), active pixel sensor (APS) in applications for radiation-tolerant star trackers. More specifically, this paper includes the results of a detailed technical study and presents relevant parameters and performance characteristics (e.g., read noise, dynamic range, dark current, hot pixel rates, quantum efficiency, linearity) that must be considered in a challenging star tracker design. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Jerebets, S (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 25 TC 0 Z9 0 U1 2 U2 5 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2641 EP 2646 PG 6 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583104042 ER PT S AU Keim, JA Acikmese, AB Shields, JF AF Keim, Jason A. Acikmese, A. Behcet Shields, Joel F. GP IEEE TI Spacecraft inertia estimation via constrained least squares SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB This paper presents a new formulation for spacecraft inertia estimation from flight data. Specifically, the inertia estimation problem is formulated as a constrained least squares minimization problem with explicit bounds on the inertia matrix incorporated as LMIs (linear matrix inequalities). The resulting minimization problem is a semidefinite optimization problem that can be solved efficiently with guaranteed convergence to the global optimum by readily available algorithms. This method is applied to test data collected from a robotic testbed consisting of a free rotating body. The results show that the constrained least squares approach produces more accurate estimates of the inertia matrix than standard unconstrained least squares estimation methods. C1 [Keim, Jason A.; Acikmese, A. Behcet; Shields, Joel F.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,M-S 198-326, Pasadena, CA 91109 USA. RP Keim, JA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,M-S 198-326, Pasadena, CA 91109 USA. EM Jason.A.Keim@jpl.nasa.gov NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2817 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583105006 ER PT S AU Smith, RS Hadaegh, FY AF Smith, Roy S. Hadaegh, Fred Y. GP IEEE TI Parallel estimation and control architectures for deep-space formation flying spacecraft SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID INTERFEROMETER; INFORMATION AB The formation flying of precisely controlled spacecraft in deep space can be used to implement optical instruments capable of imaging planets in other solar systems. The distance of the formation from Earth necessitates a significant level of autonomy and each spacecraft must base its actions on its estimates of the location and velocity of the other spacecraft. Precise coordination and control is the key requirement in such missions and the flow of information between spacecraft must be carefully designed. Doing this in an efficient and optimal manner requires novel techniques for the design of the on-board estimators. The use of standard Kalman filter-based designs can lead to unanticipated dynamics-which we refer to as disagreement dynamics-in the estimators" errors. We show how communication amongst the spacecraft can be designed in order to control all of the dynamics within the formation. We present several results relating the topology of the communication network to the resulting closed-loop control dynamics of the formation. The consequences for the design of the control, communication and coordination are discussed. C1 [Hadaegh, Fred Y.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Smith, Roy S.] Univ Calif Santa Barbara, Dept Elect & Comp Engn, Santa Barbara, CA 93106 USA. RP Hadaegh, FY (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM roy@ece.ucsb.edu; Fred.Y.Hadaegh@jpl.nasa.gov RI Smith, Roy/C-7340-2009 OI Smith, Roy/0000-0002-8139-4683 NR 41 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2823 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583105007 ER PT S AU Wilcox, B AF Wilcox, Brian GP IEEE TI Low-cost propellant launch to earth orbit from a tethered balloon SO 2006 IEEE Aerospace Conference, Vols 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Propellant will be more than 85% of the mass that needs to be lofted into Low Earth Orbit (LEO) in the planned program of Exploration of the Moon, Mars, and beyond. This paper 1,2 describes a possible means for launching thousands of tons of propellant per year into LEO at a cost 15 to 30 times less than the current launch cost per kilogram. The basic idea is to mass-produce very simple, small and relatively low-performance rockets at a cost per kilogram comparable to automobiles, instead of the similar to > 25X greater cost that is customary for current launch vehicles that are produced in small quantities and which are manufactured with performance near the limits of what is possible. These small, simple rockets can reach orbit because they are launched above > 95% of the atmosphere, where the drag losses even on a small rocket are acceptable, and because they can be launched nearly horizontally with very simple guidance based largely on spin-stabilization. Launching above most of the atmosphere is accomplished by winching the rocket up a tether to a balloon. A fuel depot in equatorial orbit passes over the launch site on every orbit (approximately every 90 minutes). One or more rockets can be launched each time the fuel depot passes overhead, so the launch rate can be any multiple of similar to 6000 small rockets per year, a number that is sufficient to reap the benefits of mass production. This approach might allow NASA to have a "propellant rich" exploration architecture that makes it possible to reduce the performance requirements on all space hardware launched into LEO, since there will be abundant propellant to move that hardware out to the moon, to Mars, or beyond. This heavier, lower-performance hardware can be much less expensive and much more reusable than would be possible if so much propellant were not available. As a result, this approach might reduce the overall cost of exploration by an order of magnitude. Think of the tethered balloon as a "flagpole" (Figure 1). The balloon supports a pulley that has the tether looped over it, and winches on the ground can lift the rocket launcher up to the stationary balloon, much as a flag is hoisted up a flagpole. A reloaded launcher goes up to the balloon from one winch as an empty launcher is lowered from the balloon to the other winch. By physically separating the two winches on the ground, the tether lines will not get tangled and the rocket can be dropped freely between the two tether lines for a few seconds before firing so that neither the balloon nor the tether are put at risk of being incinerated by the rocket. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Wilcox, B (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 8 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2863 EP 2879 PG 17 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583105011 ER PT S AU Abelson, RD Spilker, TR Shirley, JH Green, JR Smythe, WD AF Abelson, Robert D. Spilker, Thomas R. Shirley, James H. Green, Jacklyn R. Smythe, William D. GP IEEE TI Exploring Europa with an RPS-powered orbiter spacecraft SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB The National Research Council's Solar System Exploration Decadal Survey identified Jupiter's moon Europa as its highest-priority destination for near-term exploration. Voyager and Galileo missions to the Jupiter system provided evidence consistent with a subsurface ocean on Europa, which is of great interest as a potential abode for extraterrestrial life. This paper describes a conceptual flagship-class Europa orbiter concept that was assumed to launch as early as 2012, arriving at Europa approximately 8 years later using inner solar system gravity assists to reach Jupiter. Jupiter's intense radiation environment limits the mission duration at Europa to 30 days for this study, though the duration is a result of multiple trades and is by no means fixed. The Europa Subgroup of the Outer Planets Assessment Group identified six primary science objectives for this concept. An similar to 150-kg instrument suite selected for the study addresses those objectives. Large heliocentric distances, high power levels required, and especially the harsh Jovian radiation environment drove the selection of radioisotope thermoelectric generators (RTGs) for all onboard electrical power, with the excess heat aiding spacecraft thermal control. Mass and architecture trades were performed using different spacecraft trajectories, launch vehicle types, radioisotope power systems, and mission durations. The study shows that new mission constraints allow a scientifically compelling Europa orbiter mission that might also deliver a Europa lander(1,2). C1 [Abelson, Robert D.; Spilker, Thomas R.; Shirley, James H.; Green, Jacklyn R.; Smythe, William D.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,Mail Stop 301-445W, Pasadena, CA 91109 USA. RP Abelson, RD (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,Mail Stop 301-445W, Pasadena, CA 91109 USA. EM Robert.D.Abelson@jpl.nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2925 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583105016 ER PT S AU Fleurial, JP Johnson, K Mondt, J Sakamoto, J Snyder, J Huang, CK Blair, R Stapfer, G Caillat, T Frye, P Determan, W Heshmatpour, B Brooks, M Tuttle, K AF Fleurial, Jean-Pierre Johnson, Kenneth Mondt, Jack Sakamoto, Jeff Snyder, Jeff Huang, Chen-Kuo Blair, Richard Stapfer, Gerhard Caillat, Thierry Frye, Patrick Determan, William Heshmatpour, Ben Brooks, Michael Tuttle, Karen GP IEEE TI Development of segmented thermoelectric multicouple converter technology SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT DE energy conversion; thermoelectric; nuclear power; electric propulsion AB The Jet Propulsion Laboratory (JPL), Pratt & Whitney Rocketdyne, and Teledyne Energy Systems, Inc., have teamed together under JPL leadership to develop the next generation of advanced thermoelectric space reactor power conversion systems. The program goals are to develop the technologies needed to achieve a space nuclear power system specific mass goal of less than 30 kg/kW at the 100 kW power level with a greater than 15 year lifetime. The technologies required for such a power system include liquid metal cooled reactors with outlet temperatures ranging from 1125 K up to 1325 K, segmented thermoelectric multicouple converter (STMC) arrays which can achieve greater than 8 percent system efficiency and carbon-carbon heat pipe radiator panels to reduce the radiator subsystem areal density to a goal of 5 k g/m(2). The STMC Program's development efforts focused on a highly compact conductively coupled modular thermoelectric converter assembly (TCA) design. STMC design efforts were based on a multicouple design similar to the SP-100 Program's design but using segmented thermoelectric (TE) legs rather than the single alloy silicon-germanium legs. Efforts have addressed in parallel the selection and optimization of the most promising high temperature thermoelectric materials, the development of the various STMC components and sub-assemblies, design, analysis fabrication and assembly of subscale STMC devices as weli as scale-up plans to the 100 kW-class power level. The performance of the selected high temperature TE materials and initial thermal, electrical and mechanical test results on several STMC demonstration devices are reported.(1,2) C1 [Fleurial, Jean-Pierre; Johnson, Kenneth; Mondt, Jack; Sakamoto, Jeff; Snyder, Jeff; Huang, Chen-Kuo; Blair, Richard; Stapfer, Gerhard; Caillat, Thierry] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Frye, Patrick; Determan, William] Pratt & Whitney Rocketdyne Inc, Canoga Pk, CA 91309 USA. [Heshmatpour, Ben; Brooks, Michael] Teledyne Energy Syst Inc, Hunt Valley, MD 21031 USA. [Tuttle, Karen] NASA, Glenn Res Ctr, Cleveland, OH USA. RP Fleurial, JP (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM jean-pierre.fleurial@jpl.nasa.gov RI Snyder, G. Jeffrey/E-4453-2011 OI Snyder, G. Jeffrey/0000-0003-1414-8682 FU National Aeronautics and Space Administration (NASA) [ROSS-2002] FX The work described in this paper was performed at the Jet Propulsion Laboratory, California Institute of Technology under contract with the National Aeronautics and Space Administration (NASA ROSS-2002 NRA, In-Space Propulsion Technologies). The authors would like to acknowledge the thermoelectric materials university research group leads that contri buted to this effort: Profs. Terry Tritt (Clemson), George Nolas (South Florida), Ctirad Uher (Michigan), Mercouri Kanatzidis (Michigan State), Rudiger Dieckmann and Francis DiSalvo (Cornell), Robert Cava (Princeton) and Susan Kauzlarich (Davis). The authors would also like to thank Drs. Andrew Kindler and Elizabeth Yen for development of the polymeric egg-crate concept, Drs. Steve Jones and Jay Pak for aerogel packaging of the modules and Eric Stewart and his team at NASA/MSFC for support in developing the PCA and TCA designs. NR 10 TC 0 Z9 0 U1 0 U2 4 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2936 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583105017 ER PT S AU Baloch, S Arslan, T Stoica, A AF Baloch, S. Arslan, T. Stoica, A. GP IEEE TI Probability based partial triple modular redundancy technique for reconfigurable architectures SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB This paper represents a design technique for hardening combinational circuits mapped onto any reconfigurable architecture. An effective and simple algorithm for signal probabilities has been used to detect SEU sensitive gates for a given combinational circuit. The circuit can be hardened against radiation effects by applying triple modular redundancy (TMR) technique to only these sensitive gates. PTMR is tested against different circuits to prove its efficacy. With a small loss of SEU immunity, the proposed PTMR scheme can greatly reduce the area overhead as compare to TMR technique. PTMR scheme along with reconfiguration feature of FPGAs can result into a very effective SEU mitigation technique. C1 [Baloch, S.; Arslan, T.; Stoica, A.] Univ Edinburgh, Sch Elect & Engn, Mayfield Rd,Kings Bldg, Edinburgh EH9 3JL, Midlothian, Scotland. [Arslan, T.] Inst Syst Level Integrat, Alba Ctr, Livingston EH54 7EG, Scotland. [Stoica, A.] NASA, Jet Prop Lab, Pasadena, CA 91109 USA. RP Baloch, S (reprint author), Univ Edinburgh, Sch Elect & Engn, Mayfield Rd,Kings Bldg, Edinburgh EH9 3JL, Midlothian, Scotland. EM Sajid.Baloch@sli-institute.ac.uk; Tughrul.Arslan@ee.ed.ac.uk; Adrian.stoica@jpl.nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2946 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583105018 ER PT S AU Bornstein, B Castano, R Gilmore, MS Merrill, M Greenwood, JP AF Bornstein, Benjamin Castano, Rebecca Gilmore, Martha S. Merrill, Matthew Greenwood, James P. GP IEEE TI Onboard detection of jarosite minerals with applications to Mars SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID SPECTRA AB We have developed a highly accurate Support Vector Machine (SVM) based detector capable of identifying jarosite (K, Na, H3O)Fe-3(SO4)(2)(OH)(6)) in the visibleNIR (350-2500 nm) spectra of both laboratory specimens and rocks in Mars analogue field environments. To keep the computational complexity of the detector to a minimum, we restricted our design to an SVM with a linear kernel and a small number of support vectors. We used our generative model to create linear mixtures of end-member library spectra to train the SVM. We validated the detector on museum quality laboratory samples (97% accuracy) and field rock samples measured in both the laboratory and the field (both 88% accuracy). In the interest of technology infusion, the detector has been integrated into the CLARAty autonomous mobile robotics software architecture(1,2). C1 [Bornstein, Benjamin; Castano, Rebecca] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Gilmore, Martha S.; Merrill, Matthew; Greenwood, James P.] Wesleyan Univ, Dept Earth & Environm Sci, Middletown, CT 06459 USA. RP Bornstein, B (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM ben.bornstein@jpl.nasa.gov; rebecca.castano@jpl.nasa.gov; mgilmore@wesleyan.edu; nimerrill@wesleyan.edu; greenwood@wesleyan.edu RI Gilmore, Martha/G-5856-2011 FU NASA Applied Information Systems Research Program FX This research is supported by the NASA Applied Information Systems Research Program. XRD and SEM- EDS analyses were conducted at Yale University. Field assistance by J. Andrew Gilmore is appreciated. Special thanks to the Sulphur Springs Park in St. Lucia managed by the Soufriere Foundation. Richard Maclin contributed to the development of the code used for the creation of the training data. In part, this work was carried out at the Jet Propulsion Laboratory, California Institute of Technology, under contract with the National Aeronautics and Space Administration. NR 23 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2967 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583105021 ER PT S AU Castano, R Estlin, T Gaines, D Castano, A Chouinard, C Bornstein, B Anderson, RC Chien, S Fukunaga, A Judd, M AF Castano, Rebecca Estlin, Tara Gaines, Daniel Castano, Andres Chouinard, Caroline Bornstein, Ben Anderson, Robert C. Chien, Steve Fukunaga, Alex Judd, Michele GP IEEE TI Opportunistic rover science: Finding and reacting to rocks, clouds and dust devils SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB The goal of the Onboard Autonomous Science Investigation System (OASIS) project at NASA's Jet Propulsion Laboratory (JPL) is to evaluate, and autonomously act upon, science data gathered by in-situ spacecraft, such as planetary landers and rovers. (1,2) Using the FIDO rover in the Mars Yard at JPL, we have successfully demonstrated a closed loop system test of the rover acquiring image data, finding rocks in the image, analyzing rock properties and identifying rocks that merit further investigation. When the system on the rover alerts the rover to take additional measurements of interesting rocks, the planning and scheduling component determines if there are enough resources to meet this additional science data request. The rover is then instructed to either turn toward the rock, or to actually move closer to the rock to take an additional, close up, picture. In addition to these hardware integration successes, the OASIS team has also continued its autonomous science research by collaboratively working with other scientists and technologists to identify and react to other scientific phenomena - such as clouds and dust devils. Prototype dust devil and cloud detection algorithms were delivered to an infusion task which has refined the algorithms specifically for Mars Exploration Rovers (MER) and is integrating the code into the next release of MER flight software. C1 [Castano, Rebecca; Estlin, Tara; Gaines, Daniel; Castano, Andres; Chouinard, Caroline; Bornstein, Ben; Anderson, Robert C.; Chien, Steve; Fukunaga, Alex; Judd, Michele] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Castano, R (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM rebecca.castano@jpl.nasa.gov; tara.estlin@jpl.nasa.gov; daniel.gaines@jpl.nasa.gov; andres.castano@jpl.nasa.gov; caroline.chouinard@jpl.nasa.gov; ben.bornstein@jpl.nasa.gov; robert.anderson@jpl.nasa.gov; steve.chien@jpl.nasa.gov; alex.fukunaga@jpl.nasa.gov; michele.judd@jpl.nasa.gov FU Intelligent Systems Program; Mars Technology Program; DSMS Technology Program. FX The research described in this paper was carried out at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. Specific funding for this work provided by the Intelligent Systems Program, the Mars Technology Program and the DSMS Technology Program. Finally, our work this year could not proceed without the support and advice of scientists outside of the team, in particular: Albert Haldemann (JPL) and Matt Golombek (JPL). NR 18 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2974 EP + PG 5 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583105022 ER PT S AU Sen, DK Banks, JC Maggio, G Railsback, J AF Sen, Dev K. Banks, Justin C. Maggio, Gaspare Railsback, Jan GP IEEE TI Rapid development of an event tree modeling tool using COTS software SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB This paper introduces a simple and powerful event tree modeling tool called EC Tree, which was developed using Microsoft Excel and Visual Basic. The tool enables the rapid construction of event trees of any complexity through easy-to-use templates, menu items, and shortcut keys. EC Tree was developed to facilitate the rapid generation of event trees for application to event based risk analyses, specifically for use in NASA's IM&S (Integrated Modeling and Simulation) Team. In contrast to many other event tree modeling tools, EC Tree does not require the purchase or installation of any specialized software, other than Microsoft Office, and is simple enough for a risk analyst to use immediately, without training. Further, EC Tree was created as a generic event tree modeling tool and is thus not restricted to specific systems, domains of relevance, or scope. This paper describes EC Tree, its functionality, and the development process employed. Specific focus is given to the process of rapid prototyping, programming, testing and software release used during the development of EC Tree, and on lessons learned. The general approach of using COTS software as a basis for rapid software development is also discussed along with the limitations of this approach. Some potential applications of EC Tree to model event based processes in the aerospace field are also discussed. C1 [Sen, Dev K.; Banks, Justin C.; Maggio, Gaspare] Sci Applicat Int Corp, 350 Broadway,8th Floor, New York, NY 10013 USA. [Railsback, Jan] Natl Aeronaut & Space Adm, Lyndon B Johnson Space Ctr, Houston, TX USA. RP Sen, DK (reprint author), Sci Applicat Int Corp, 350 Broadway,8th Floor, New York, NY 10013 USA. EM dev.k.sen@saic.com NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 2998 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583105024 ER PT S AU Pressburger, T Di Vito, B Feather, MS Hinchey, M Markosian, L Trevino, LC AF Pressburger, Thomas Di Vito, Ben Feather, Martin S. Hinchey, Michael Markosian, Lawrence Trevino, Luis C. GP IEEE TI Infusing software assurance research techniques into use SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Research in the software engineering community continues to lead to new development techniques that encompass processes, methods and tools. However, a number of obstacles impede their infusion into software development practices. These are the recurring obstacles common to many forms of research. Practitioners cannot readily identify the emerging techniques that may benefit them, and cannot afford to risk time and effort evaluating and trying one out while there remains uncertainty about whether it will work for them. Researchers cannot readily identify the practitioners whose problems would be amenable to their techniques, and, lacking feedback from practical applications, are hard-pressed to gauge the where and in what ways to evolve their techniques to make them more likely to be successful. This paper describes an ongoing effort conducted by a software engineering research infusion team established by NASA's Software Engineering Initiative to overcome these obstacles. (1.2.3) C1 [Pressburger, Thomas] NASA, Ames Res Ctr, Moffett Field, CA 94303 USA. [Di Vito, Ben] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Feather, Martin S.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. [Hinchey, Michael] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Markosian, Lawrence] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Trevino, Luis C.] 2L Res Corp, Huntsville, AL USA. RP Pressburger, T (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94303 USA. EM Tom.Pressburger@nasa.gov; B.DiVito@nasa.gov; Martin.S.Feather@jpl.nasa.gov; Michael.G.Hinchey@nasa.gov; lzmarkosian@email.arc.nasa.gov; Trevino@hiwaay.net FU NASA Software Engineering Initiative FX We wish to acknowledge the contributions of the following individuals and institutions. John Kelly, in the NASA Office of the Chief Engineer, leads the NASA intercenter Software Working Group and has provided support for the research infusion effort as part of the NASA Software Engineering Initiative. This Initiative was the basis for a software engineering research infusion effort. Pat Schuler of NASA Langley suggested our basic approach. Martha Wetherholt, in the NASA Office of Mission Assurance, is head of the NASA Software Assurance Research Program, which is administered by Kenneth McGill at the NASA IV&V Facility. Both have helped our infusion effort by providing collaboration funding, direction, and advice. Tim Menzies, formerly of West Virginia University and the IV&V Facility, now at Portland State University, was an early member of the team and helped give us our start. Wes Deadrick of the IV&V facility has also advised us and has been a reviewer of collaboration proposals. The Research Infusion team also wishes to acknowledge the many researchers who have lent their support and the software developers who have submitted collaboration proposals. NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 3006 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583105025 ER PT S AU Shapiro, AA Cornford, SL Feather, MS Price, G Gawdiak, YO Ricks, WR AF Shapiro, Andrew A. Cornford, Steven L. Feather, Martin S. Price, George Gawdiak, Yuri O. Ricks, Wendell R. GP IEEE TI Planning a large-scale progression of R&D - a pilot study in the aerospace domain SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB A prior case study reported in "Programmatic Risk Balancing" [D.M. Tralli, IEEE Aerospace Conference 2003] established the suitability of adopting a lifecycle risk management decision-support tool to the planning of application projects across NASA's Earth Science Enterprise. Here we report on a pilot study to gauge the suitability of this same approach for large-scale planning of a progression of research and development efforts in the Aerospace domain. The purpose of the study was to assess feasibility and utility, and to prototype adaptations to the approach as and when such adaptations were found to be needed. The novel challenges posed by this domain included: scale - the overall goal is to plan and monitor $1.513 worth of R&D spread over several years; scope - information spans task-level, project-level and program-level concerns; distributed expertise - the information on which to base decisions requires combining inputs from multiple geographically dispersed, busy people (i.e., they won't be available to all meet concurrently, even via a teleconference); and novel problem domain aspects - for example the world continues to evolve as the multi-year R&D efforts take place, so that what might be desirable solutions to aim for this year may be rendered obsolete and unnecessary a few years hence as other capabilities mature, or alternately, may continue to be necessary but less sufficient as demands increase. The net result was promising: the approach worked, and a number of interesting observations could indeed be drawn from the accumulated information. Overall it also pointed to several possible avenues to scale-up the approach, together with some remaining key problems. (1,2) C1 [Shapiro, Andrew A.; Cornford, Steven L.; Feather, Martin S.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91009 USA. [Price, George; Gawdiak, Yuri O.] NASA, Washington, DC 20546 USA. [Ricks, Wendell R.] NASA, Langley Res Ctr, Hampton, VA 23687 USA. RP Shapiro, AA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91009 USA. EM Andrew.A.Shapiro@jpl.nasa.gov; Steven.L.Cornford@jpl.nasa.gov; Martin.S.Feather@jpl.nasa.gov; george.price@nasa.gov; yuri.o.gawdiak@nasa.gov; Wendell.R.Ricks@nasa.gov FU NASA Aeronautics Research Mission Directorate FX Much of the research described in this paper was carried out at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. We wish to thank our sponsors at the NASA Aeronautics Research Mission Directorate for making this work possible. NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 3016 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583105026 ER PT S AU Schumann, J Visser, W AF Schumann, Johann Visser, Willem GP IEEE TI Autonomy software: V&V challenges and characteristics SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB The successful operation of unmanned air vehicles requires software with a high degree of autonomy. Only if high level functions can be carried out without human control and intervention can complex missions, in a changing and potentially unknown environment, be carried out successfully. Autonomy software is highly mission and safety critical: failures, caused by flaws in the software cannot only jeopardize the mission, but could also endanger human life (e.g., a crash of an UAV in a densely populated area). Due to its large size, complex architecture, and use of specialized algorithms (planners, constraint-solvers, etc.), autonomy software poses specific challenges for its verification, validation, and certification. We have carried out a survey among researchers and scientists at NASA to study these issues. In this paper, we will present major results of this study, discussing the broad spectrum of notions and characteristics of autonomy software and its challenges for design and development. A main focus of this survey was to evaluate verification and validation (V&V) issues and challenges, compared to the development of "traditional" safety-critical software. We will discuss important issues in V&V of autonomous software and advanced V&V tools which can help to mitigate software risks. Results of this survey will help to identify and understand safety concerns in autonomy software and will lead to improved strategies for mitigation of these risks. C1 [Schumann, Johann; Visser, Willem] NASA, Ames Res Ctr, RIACS, Moffett Field, CA 94035 USA. RP Schumann, J (reprint author), NASA, Ames Res Ctr, RIACS, Moffett Field, CA 94035 USA. EM schumann@email.arc.nasa.gov; wvisser@email.arc.nasa.gov FU NASA HRT FX This work is in part sponsored by a NASA H&RT project. We would like to thank the participants of the survey for they time and effort to answer our questionnaire. NR 8 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 3107 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583105034 ER PT S AU Brat, G Denney, E Giannakopoulou, D Frank, J Jonsson, A AF Brat, G. Denney, E. Giannakopoulou, D. Frank, J. Jonsson, A. GP IEEE TI Verification of autonomous systems for space applications SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Autonomous' 2 software, especially if it is based on model, can play an important role in future space applications. For example, it can help streamline ground operations, or, assist in autonomous rendezvous and docking operations, or even, help recover from problems (e.g., planners can be used to explore the space of recovery actions for a power subsystem and implement a solution without (or with minimal) human intervention). In general, the exploration capabilities of model-based systems give them great flexibility. Unfortunately, it also makes them unpredictable to our human eyes, both in terms of their execution and their verification. The traditional verification techniques are inadequate for these systems since they are mostly based on testing, which implies a very limited exploration of their behavioral space. In our work, we explore how advanced V&V techniques, such as static analysis, model checking, and compositional verification, can be used to gain trust in model-based systems. We also describe how synthesis can be used in the context of system reconfiguration and in the context of verification. C1 [Brat, G.; Denney, E.; Giannakopoulou, D.; Jonsson, A.] USRA RIACS, Ames Res Ctr, MS 269-2, Moffett Field, CA 94035 USA. [Frank, J.] NASA, Moffett Field, CA 94035 USA. RP Brat, G (reprint author), USRA RIACS, Ames Res Ctr, MS 269-2, Moffett Field, CA 94035 USA. EM brat@email.arc.nasa.gov; edenney@email.arc.nasa.gov; dimitra@email.arc.nasa.gov; frank@email.arc.nasa.gov; jonsson@email.arc.nasa.gov NR 17 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 3155 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583105040 ER PT S AU Richardson, J Wilson, E AF Richardson, Julian Wilson, Edward GP IEEE TI Flexible generation of Kalman filter code SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Domain-specific program synthesis can automatically generate high quality code in complex domains from succinct specifications, but the range of programs which can be generated by a given synthesis system is typically narrow. Obtaining code which falls outside this narrow scope necessitates either 1) extension of the code generator, which is usually very expensive, or 2) manual modification of the generated code, which is often difficult and which must be redone whenever changes are made to the program specification. In this paper, we describe adaptations and extensions of the AUTOFILTER Kalman filter synthesis system which greatly extend the range of programs which can be generated. Users augment the input specification with a specification of code fragments and how those fragments should interleave with or replace parts of the synthesized filter. This allows users to generate a much wider range of programs without their needing to modify the synthesis system or edit generated code. We demonstrate the usefulness of the approach by applying it to the synthesis of a complex state estimator which combines code from several Kalman filters with user-specified code. The work described in this paper allows the complex design decisions necessary for real-world applicatons to be reflected in the synthesized code. When executed on simulated input data, the generated state estimator was found to produce comparable estimates to those produced by a handcoded estimator. C1 [Richardson, Julian] NASA, Ames Res Ctr, RIACS, Ames, IA 50010 USA. [Wilson, Edward] Intellizat, Redwood City, CA 94065 USA. RP Richardson, J (reprint author), NASA, Ames Res Ctr, RIACS, Ames, IA 50010 USA. EM julianr@riacs.edu; ed.wilson@intellization.com NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 3166 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583105041 ER PT S AU Truszkowski, WF Odubiyi, JB AF Truszkowski, Walt F. Odubiyi, Jide B. GP IEEE TI AEGONE - Agent-enabled, grid-oriented, and just-in-time network of experts SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Consider a model developed by a multidisciplinary team of scientists. This model will be used by researchers to support some scientific investigation. However, this investigation might be hampered if the researcher needs to interface (on the fly) with the members of the inter-disciplinary team responsible for the development of the model. The situation becomes more complicated if the following occurs: (a) multiple distributed models are needed for the researcher's scientific endeavor and (b) a similar need for interaction with the model-development teams arises. (As an example, consider a weather researcher who needs access to multiple weather models from different localities and each model reflects the contributions of several experts in air currents, air pressure, temperature, etc.) This paper presents an innovative integrated solution to the two problems identified above (i.e., access to multidisciplinary team members responsible for model development and access to multiple distributed models and other data/information resources in a user-friendly transparent way) with the introduction of Agent-Enabled, Grid-Oriented Network of Expert agents (AEGONE). AEGONE is a system under development to give researchers just-in-time access to expert domain knowledge. This system will enable them to conduct scientific investigations and transparent access to distributed models and other resources without the immediate need to interface with human experts or knowledge of the complexity of the underlying grid-oriented and agent-mediated infrastructures.(12) AEGONE extends the capabilities of current grid-oriented computing systems and DARPA's Coalition Agents eXperiments (CoAX). C1 [Truszkowski, Walt F.] NASA, Goddard Space Flight Ctr, Adv Architectures & Automat Branch, Code 588, Greenbelt, MD 20771 USA. [Odubiyi, Jide B.] Bowie State Univ, Dept Comp Sci, Bowie, MD 20905 USA. RP Truszkowski, WF (reprint author), NASA, Goddard Space Flight Ctr, Adv Architectures & Automat Branch, Code 588, Greenbelt, MD 20771 USA. EM Walt.Truszkowski@nasa.gov; jodubiyi@segma.com NR 15 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 3189 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583105044 ER PT S AU Sebens, C Truszkowski, W AF Sebens, Charles Truszkowski, Walt GP IEEE TI An agent-based tetrahedral walker SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB ANTS (Autonomous Nano Technology Swarm) SMART (Super Miniaturized Addressable Reconfigurable Technology) architectures were initiated at the Goddard Space Flight Center (GSFC) to develop new kinds of robotic structures capable of goal-oriented motion, changing its form to optimize its function, adapting to new environmental demands, and/or repairing itself. To begin to explore the possibilities of these concepts and the possible application of multi-agent control, a series of increasingly complex roving shapes leading up to the tetrahedron were considered. The goal is to have the structure move from an initial location to a specified goal location. The tetrahedron has six struts that can be reversibly deployed or stowed. More complex structures will be formed by interconnectig these reconfigurable tetrahedra, making structures that are scalable and massively parallel systems. The full functionality of such a complex system requires fully autonomous operations. [1] As illustrated in Figure 1, the tetrahedron (tet) has four nodes and six expandable struts. It "walks" by extending certain struts, changing its center of gravity and "falling" in the desired direction. Currently, the basic structure, the tetrahedron, is being modeled as a cooperating/collaborating 4-agent system with an agent located on each node of the tet. (An agent, in this context, is an intelligent autonomous process capable of deliberative and reactive behaviors as well as social and introspective behaviors.) The desired result is the realization of a truly autonomous tetrahedron structure. This paper will address this innovative use of multi-agent system technology that is being used to achieve the desired autonomous behaviors as well as the increasingly complex staged approach in the development of the multi-agent tet. C1 [Sebens, Charles] MIT, 4306 Woodberry St, Hyattsville, MD 20782 USA. [Truszkowski, Walt] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Sebens, C (reprint author), MIT, 4306 Woodberry St, Hyattsville, MD 20782 USA. EM csebens@mit.edu; walt.truszkowski@nasa.gov NR 1 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 3206 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583105046 ER PT S AU Lee, S Russell, RP Fink, W Terrile, RJ Petropoulos, AE von Allmen, P AF Lee, Seungwon Russell, Ryan P. Fink, Wolfgang Terrile, Richard J. Petropoulos, Anastassios E. von Allmen, Paul GP IEEE TI Low-thrust mission trade studies with parallel, evolutionary computing SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID OPTIMIZATION AB New mission concepts are increasingly considering the use of ion propulsion for fuel-efficient navigation in deep space. The development of new low-thrust mission concepts requires efficient methods to rapidly determine feasibility and thoroughly explore trade spaces. This paper presents parallel, evolutionary computing methods to assess a trade-off between delivered payload mass and required flight time. The developed methods utilize a distributed computing environment in order to speed up computation, and use evolutionary algorithms to approximate optimal solutions. The methods are coupled with the Primer Vector theory, where a thrust control problem is transformed into a co-state control problem and the initial values of the co-state vector are optimized. The developed methods are applied to two mission scenarios: i) an orbit transfer around Earth and ii) a transfer between two distant retrograde orbits around Europa. The solutions found with the present methods are comparable to those obtained by other state-of-the-art trajectory optimizers. The required computational time can be up to several orders of magnitude shorter than that of other optimizers thanks to the utilization of the distributed computing environment, the significant reduction of the search space dimension with the Primer Vector theory, and the efficient and synergistic exploration of the remaining search space with evolutionary computing. C1 [Lee, Seungwon; Russell, Ryan P.; Fink, Wolfgang; Terrile, Richard J.; Petropoulos, Anastassios E.; von Allmen, Paul] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Lee, S (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Seungwon.Lee@jpl.nasa.gov FU JPL's Research and Technology Development program FX We thank Christoph Adami for useful discussions about performance analysis for genetic algorithms, and we also thank Robert Tisdale for his support on the parallelization of the simulated annealing. This work was carried out at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. The research was supported by JPLs Research and Technology Development program. NR 27 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 3242 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583105049 ER PT S AU Maluf, DA Schipper, JF AF Maluf, David A. Schipper, John F. GP IEEE TI Sensing super-position: Visual instrument Sensor Replacement SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID BLIND AB The coming decade of fast, cheap and miniaturized electronics and sensory devices opens new pathways for the development of sophisticated equipment to overcome limitations of the human senses. This project addresses the technical feasibility of augmenting human vision through Sensing Super-position using a Visual Instrument Sensory Organ Replacement (VISOR). The current implementation of the VISOR device translates visual and other passive or active sensory instruments into sounds, which become relevant when the visual resolution is insufficient for very difficult and particular sensing tasks. A successful Sensing Super-position meets many human and pilot vehicle system requirements. The system can be further developed into cheap, portable, and low power taking into account the limited capabilities of the human user as well as the typical characteristics of his dynamic environment. The system operates in real time, giving the desired information for the particular augmented sensing tasks. The Sensing Super-position device increases the image resolution perception and is obtained via an auditory representation as well as the visual representation. Auditory mapping is performed to distribute an image in time. The three-dimensional spatial brightness and multi-spectral maps of a sensed image are processed using real-time image processing techniques (e.g. histogram normalization) and transformed into a two-dimensional map of an audio signal as a function of frequency and time. This paper details the approach of developing Sensing Super-position systems as a way to augment the human vision system by exploiting the capabilities of the human hearing system as an additional neural input. The human hearing system is capable of learning to process and interpret extremely complicated and rapidly changing auditory patterns. The known capabilities of the human hearing system to learn and understand complicated auditory patterns provided the basic motivation for developing an image-to-sound mapping system. The human brain is far superior to most existing computer systems in rapidly extracting relevant information from blurred, noisy, and redundant images. From a theoretical viewpoint, this means that the available bandwidth is not exploited in an optimal way. While image-processing techniques can manipulate, condense and focus the information (e.g., Fourier Transforms), keeping the mapping as direct and simple as possible might also reduce the risk of accidentally filtering out important clues. After all, especially a perfect non-redundant sound representation is prone to loss of relevant information in the non-perfect human hearing system. Also, a complicated non-redundant image-to-sound mapping may well be far more difficult to learn and comprehend than a straightforward mapping, while the mapping system would increase in complexity and cost. This work will demonstrate some basic information processing for optimal information capture for head-mounted systems. C1 [Maluf, David A.; Schipper, John F.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Maluf, DA (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM David.A.Maluf@nasa.gov; John.F.Schipper@nasa.gov NR 22 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 3286 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583105054 ER PT S AU McDermott, WJ Robinson, P Duncavage, DP Maluf, DA Gurram, M Bass, K Alena, R AF McDermott, William J. Robinson, Peter Duncavage, Daniel P. Maluf, David A. Gurram, Mohana Bass, Kevin Alena, Rick GP IEEE TI Knowledge mining application in ISHM testbed SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB The scope of Integrated System Health Management (ISHM) is the end-to-end autonomous management of subsystems, systems and systems of systems. Among ISHM's components is management of data, information, and knowledge to detect and diagnose anomalies, and propose mitigation procedures for crew implementation. Complex systems such as the International Space Station (ISS) generate a large amount of data, over 160,000 documents that are distributed across disparate systems. But this data is fragmented and applications are unable to interoperate. In addition, the lack of a seamless mechanism for ensuring use of latest, best information hinders development of much needed modeling, simulation and visualization systems that could increase the operating safety of a complex system. To reduce development time for ISHM systems, builders of advanced diagnostic systems require rapid retrieval of precise information from various sources spread across multiple, distributed, heterogeneous databases.(1) To meet this challenge, a technological leap that goes beyond the bounds of today's understanding of documents is needed. Software developed by NASA Ames researchers in the Advanced Knowledge Exploration Networks (AKEN) Lab that enables diagnostic systems and distributed information sources to be linked into an Information Grid is one such technology. Funded through the Integrated Testbed Prototypes (ITP) Project, in 2005 AKEN installed Netmark's Context Based Retrieval system at Johnson Space Center to incorporate this technology into advanced diagnostic systems. For the ITP Project this technology was given the name Knowledge Mining Application (KMA). KMA was responsible for integrating documents from a range of information sources so that an advanced caution and warning diagnostic system could retrieve precise information on ISS events in question. C1 [McDermott, William J.; Maluf, David A.; Alena, Rick] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Robinson, Peter] NASA, Ames Res Ctr, SAIC, Moffett Field, CA 94035 USA. [Duncavage, Daniel P.] NASA, Johnson Space Ctr, Houston, TX 77058 USA. [Gurram, Mohana] Univ Space Res Associat, NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Bass, Kevin] NASA, Johnson Space Ctr, QSS Grp, Houston, TX 77058 USA. RP McDermott, WJ (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM B.McDermott@nasa.gov; robinson@mail.arc.nasa.gov; DanielP.Duncavage@nasa.gov; maluf@email.arc.nasa.gov; mgurram@email.arc.nasa.gov; kbass@mail.arc.nasa.gov; ralena@mail.arc.nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 3296 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583105055 ER PT S AU Akkawi, F Cottenier, T Alena, RL Fletcher, DP Duncavage, DP Elrad, T AF Akkawi, Faisal Cottenier, Thomas Alena, Richard L. Fletcher, Daryl P. Duncavage, Daniel P. Elrad, Tzilla GP IEEE TI An executable choreography framework for dynamic service-oriented architectures SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Interoperability and loose coupling requirements are pushing the next generation of distributed applications towards more decentralized and more dynamic interaction schemes, which the classic request/response communication paradigm can hardly accommodate. Hence, sound foundations and mechanisms for the establishment of unanticipated peer-to-peer interactions across organizational boundaries are of significant importance to upcoming middleware platforms. The Executable Choreography Framework (ECF) is a middleware-level framework that targets dynamic and decentralized service compositions. The ECF combines transparent context propagation with aspect-oriented software composition techniques to dynamically refine the default control and data flow of service invocations. The framework provides a ground for experimentation with dynamic and distributed workflows, and a base to assess their safety and applicability when deployed across organizational boundaries. C1 [Akkawi, Faisal] Northwestern Univ, Chicago, IL 60616 USA. [Fletcher, Daryl P.] NASA, Ames Res Ctr, SAIC, Moffett Field, CA 94035 USA. [Cottenier, Thomas; Elrad, Tzilla] IIT, Chicago, IL 60616 USA. [Duncavage, Daniel P.] NASA, Johnson Space Ctr, Houston, TX 77058 USA. [Alena, Richard L.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Akkawi, F (reprint author), Northwestern Univ, Chicago, IL 60616 USA. EM f-akkawi@northwestem.edu; cotttho@iit.edu; Richard.L.Alena@nasa.gov; dpfletcher@mail.arc.nasa.gov; Daniel.P.Duncavage@nasa.gov; elrad@iit.edu NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 3463 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583106014 ER PT S AU Lee, C Ossenfort, J Alena, RL Walker, E Stone, T Notario, H AF Lee, Charles Ossenfort, John Alena, Richard L. Walker, Ed Stone, Thom Notario, Hugo GP IEEE TI Software architecture of sensor data distribution in planetary exploration SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Data from mobile and stationary sensors(1,2) Will be vital in planetary surface exploration. The distribution and collection of sensor data in an ad-hoc wireless network presents unique challenges. Some of the conditions encountered in the field include: irregular terrain, mobile nodes, routing loops from clients associating with the wrong access point or repeater, network routing reconfigurations caused by moving repeaters, signal fade, and hardware failures. These conditions present the following problems: data errors, out of sequence packets, duplicate packets, and drop out periods (when the node is not connected). To mitigate the effects of these impairments, robust and reliable software architecture tolerant of communications outages must be implemented. This paper describes such a robust and reliable software infrastructure that meets the challenges of a distributed ad hoc network in a difficult environment and presents the results of actual field experiments testing the principles and exploring the underlying technology. C1 [Lee, Charles; Ossenfort, John] NASA, Ames Res Ctr, SAIC, Moffett Field, CA 94035 USA. [Stone, Thom] NASA, Ames Res Ctr, Comp Sci Corp, Moffett Field, CA 94035 USA. [Alena, Richard L.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Walker, Ed] NASA, Ames Res Ctr, MCT, Moffett Field, CA 94035 USA. [Notario, Hugo] NASA, Ames Res Ctr, Foothill DeAnza Coll, Moffett Field, CA 94035 USA. RP Lee, C (reprint author), NASA, Ames Res Ctr, SAIC, Moffett Field, CA 94035 USA. EM clee@mail.arc.nasa.gov; jossenfort@mail.arc.nasa.gov; Richard.L.Alena@nasa.gov; ctmwalker@mail.arc.nasa.gov; tstone@arc.nasa.gov; hnotario@mail.arc.nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 3476 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583106015 ER PT S AU Kizhner, S Blank, K Flatley, T Huang, NE Petrick, D Hestnes, P AF Kizhner, Semion Blank, Karin Flatley, Thomas Huang, Norden E. Petrick, David Hestnes, Phyllis GP IEEE TI On certain theoretical developments underlying the Hilbert-Huang Transform SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID SYSTEM-IDENTIFICATION; SPECTRAL-ANALYSIS; MODES AB One of the main traditional tools used in scientific and engineering data spectral analysis is the Fourier Integral Transform and its high performance digital equivalent - the Fast Fourier Transform (FFT). Both carry strong a-priori assumptions about the source data, such as being linear and stationary, and of satisfying the Dirichlet conditions. A recent development at the National Aeronautics and Space Administration (NASA) Goddard Space Flight Center (GSFC), known as the Hilbert-Huang Transform (HHT), proposes a novel approach to the solution for the nonlinear class of spectral analysis problems. Using a-posteriori data processing based on the Empirical Mode Decomposition (EMD) sifting process (algorithm), followed by the normalized Hilbert Transform of the decomposed data, the HHT allows spectral analysis of nonlinear and nonstationary data. The EMD sifting process results in a non-constrained decomposition of a source numerical data vector into a finite set of Intrinsic Mode Functions (IMF). These functions form a nearly orthogonal, derived from the data basis (adaptive basis). The IMFs can be further analyzed for spectrum content by using the classical Hilbert Transform. A new engineering spectral analysis tool using HHT has been developed at NASA GSFC, the HHT Data Processing System (HHT-DPS). As the HHT-DPS has been successfully used and commercialized, new applications pose additional questions about the theoretical basis behind the HHT EMD algorithm. Why is the fastest changing component of a composite signal being sifted out first in the EMD sifting process? Why does the EMD sifting process seemingly converge and why does it converge rapidly? Does an IMF have a distinctive structure? Why are the IMFs nearly orthogonal? We address these questions and develop the initial theoretical background for the HHT. This will contribute to the development of new HHT processing options, such as real-time and 2-D processing using Field Programmable Gate Array (FPGA) computational resources, enhanced HHT synthesis, and will broaden the scope of HHT applications for signal processing. C1 [Kizhner, Semion; Blank, Karin; Flatley, Thomas; Huang, Norden E.; Petrick, David; Hestnes, Phyllis] NASA, Goddard Space Flight Ctr, NASA, Greenbeld Rd, Greenbelt, MD 20771 USA. RP Kizhner, S (reprint author), NASA, Goddard Space Flight Ctr, NASA, Greenbeld Rd, Greenbelt, MD 20771 USA. EM Semion.Kizhner-1@nasa.gov NR 17 TC 0 Z9 0 U1 0 U2 5 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 3485 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583106016 ER PT S AU Cockrell, J Wysocki, P Hodgson, R Bailin, S AF Cockrell, Jim Wysocki, Phil Hodgson, Ralph Bailin, Sidney GP IEEE TI Wire integrity management using sensors on-board manned aero-spacecraft SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Is there a business case(1),(2) for on-board wire integrity sensors for aero-spacecraft? Wire integrity management using on-board sensors seems a natural fit for future Integrated System Health Management (ISHM). Government and private enterprises are presently developing in-situ wire integrity sensors. Is there a value proposition for wire integrity management in manned aero-spacecraft? How would risk be reduced, or other benefits gained, from isolating failure to wiring, or a particular wire? In this paper we assume that in-situ wire sensors will be incorporated into ISHM systems. We focus on the business case for the inclusion of Wire Integrity Management in future vehicle design. We explore ground processing scenarios, rather than in-flight. Our expectations are that the greatest value of in-situ wire integrity management will be in savings of cost, scheduling, invasiveness, and risks. Ground processing includes: vehicle recovery, fault diagnosis, access, closeout and safing, tooling, repairs, spares provisioning, testing and validation, and preflight/postflight preparations. C1 [Cockrell, Jim; Wysocki, Phil] NASA, Ames Res Ctr, MS 213-15, Moffett Field, CA 94035 USA. [Hodgson, Ralph; Bailin, Sidney] Top Quadrant Inc, Beaver Falls, PA 15010 USA. RP Cockrell, J (reprint author), NASA, Ames Res Ctr, MS 213-15, Moffett Field, CA 94035 USA. EM James.J.Cockrell@nasa.gov; pwysocki@mail.arc.nasa.gov; rhodgson@topquadrant.com; sbailin@kevol.com NR 4 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 3611 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583106028 ER PT S AU Dempsey, PJ Kreider, G Fichter, T AF Dempsey, Paula J. Kreider, Gary Fichter, Thomas GP IEEE TI Investigation of tapered roller bearing damage detection using oil debris analysis SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB A diagnostic tool was developed for detecting fatigue damage to tapered roller bearings. Tapered roller bearings are used in helicopter transmissions and have potential for use in high bypass advanced gas turbine aircraft engines. This diagnostic tool was developed and evaluated experimentally by collecting oil debris data from failure progression tests performed by The Timken Company in their Tapered Roller Bearing Health Monitoring Test Rig. Failure progression tests were performed under simulated engine load conditions. Tests were performed on one healthy bearing and three predamaged bearings. During each test, data from an on-line, in-line, inductance type oil debris sensor was monitored and recorded for the occurrence of debris generated during failure of the bearing. The bearing was removed periodically for inspection throughout the failure progression tests. Results indicate the accumulated oil debris mass is a good predictor of damage on tapered roller bearings. The use of a fuzzy logic model to enable an easily interpreted diagnostic metric was proposed and demonstrated. C1 [Dempsey, Paula J.] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. [Kreider, Gary; Fichter, Thomas] Timken Co, North Canton, OH 44720 USA. RP Dempsey, PJ (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. EM paula.j.dempsey@nasa.gov; gary.kreider@timken.com; tom.fichter@timken.com FU Dennis Shaughnessy of Pratt; Whitney Advanced Engine Systems FX The authors acknowledge the contributions of Dennis Shaughnessy of Pratt & Whitney Advanced Engine Systems for his leadership in project management and engineering support. The authors also thank Mary J. Long Davis and Isaac Lopez of the NASA Glenn Vehicle Systems Project Office for their dedicated support in program management of this research effort. NR 14 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 3694 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583106037 ER PT S AU Budalakoti, S Srivastava, AN Akella, R AF Budalakoti, Suratna Srivastava, Ashok N. Akella, Ram GP IEEE TI Discovering atypical flights in sequences of discrete flight parameters SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB This paper describes the results of a novel research and development effort conducted at the NASA Ames Research Center for discovering anomalies in discrete parameter sequences recorded from flight data(1,2) Many of the discrete parameters that are recorded during the flight of a commercial airliner correspond to binary switches inside the cockpit. The inputs to our system are records from thousands of flights for a given class of aircraft and destination. The system delivers a list of potentially anomalous flights as well as reasons why the flight was tagged as anomalous. This output can be analyzed by safety experts to determine whether or not the anomalies are indicative of a problem that could be addressed with a human factors intervention. The final goal of the system is to help safety experts discover significant human factors issues such as pilot mode confusion, i.e., a flight in which a pilot has lost situational awareness as reflected in atypicality of the sequence of switches that he or she throws during descent compared to a population of similar flights. We view this work as an extension of Integrated System Health Management (ISHM) where the goal is to understand and evaluate the combined health of a class of aircraft at a Piven destination. C1 [Budalakoti, Suratna; Akella, Ram] Univ Calif Santa Cruz, Santa Cruz, CA 95064 USA. [Srivastava, Ashok N.] NASA, Ames Res Ctr, Washington, DC 20546 USA. RP Budalakoti, S (reprint author), Univ Calif Santa Cruz, Santa Cruz, CA 95064 USA. EM suratna@soe.ucsc.edu; Ashok.N.Srivastava@nasa.gov; akella@soe.ucsc.edu FU NASA FX This work was supported by the NASA Aviation Safety Program, Aviation Systems Monitoring and Modeling element. NR 8 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 3972 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583107010 ER PT S AU Gutleber, J Brogan, J Gambino, RJ Sampath, S Longtin, J Zhu, DM AF Gutleber, Jonathan Brogan, Jeffrey Gambino, Richard J. Sampath, Sanjay Longtin, Jon Zhu, Dongming GP IEEE TI Embedded temperature and heat flux sensors for advanced health monitoring of turbine engine components SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB MesoScribe Technologies has developed a process for producing embedded, conformal, thick film sensors based on Direct Write technology. Thermocouple and heat flux sensors can be fabricated directly onto engineering components and embedded into functional coatings. This provides for a variety of vital advantages: reliability, robustness and survivability in extremely harsh environments, cost effective implementation, and fabrication onto surfaces that are large, conformal (non-flat) and flexible. Embedded thermocouples and heat flux sensors were deposited onto superalloy substrates and subjected to a number of high temperature tests including isothermal furnace heating, cyclic burner rig testing, and continuous flame impingement. Initial testing yields Seebeck coefficients within 3% of commercial thermocouples. Results also demonstrate that embedded Type K thermocouples survive over 200 thirty minute burner rig cycles with surface temperatures exceeding 1150 degrees C. Embedding thermocouples at different depths within the TBC allows for simultaneous temperature measurements within the temperature gradient. In addition, over 20 hours of continuous flame impingement have been recorded with stable output. Embedded thermocouples were also tested at NASA GRC using a 3.5 kW CO2 high heat flux laser which also allows extraction of thermal conductivity. The test comprised of 75 thirty minute cycles with a surface temperature of 1150 degrees C and metal interface temperature of 930 degrees C for a total duration of 41 hours. This very first test showed the capability of the embedded TC in terms of performance and durability. This paper will summarize the harsh environment test results as well as provide an overview of the capabilities of Direct Write technology to instrument propulsion and space structures.(1,2) C1 [Gutleber, Jonathan; Brogan, Jeffrey; Gambino, Richard J.] MesoScribe Technol Inc, 25 Hlth Sci Dr, Stony Brook, NY 11790 USA. [Sampath, Sanjay; Longtin, Jon] SUNY Stony Brook, Cent Thermal Spray Res, Stony Brook, NY 11794 USA. [Zhu, Dongming] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Gutleber, J (reprint author), MesoScribe Technol Inc, 25 Hlth Sci Dr, Stony Brook, NY 11790 USA. FU NIST-ATP [70NANB4H3042]; Naval Air Warfare Center [N00421-04-P-0516]; UTC [04-S508-009-03-C1]; Air Force [F33615-03-D-5204]; US Department of Energy [DE FG02-02ER83497] FX The authors gratefully acknowledge the support for this work under the following contracts or grants: NIST-ATP (Award No.70NANB4H3042), Naval Air Warfare Center, (Contract No. N00421-04-P-0516), UTC Subcontract No. 04-S508-009-03-C1 in support of Air Force Contract No F33615-03-D-5204 and US Department of Energy (Grant No. DE FG02-02ER83497) NR 4 TC 1 Z9 1 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4046 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583107018 ER PT S AU Fijany, A Vatan, F AF Fijany, Amir Vatan, Farrokh GP IEEE TI A new efficient algorithm for analyzing and optimizing the system of sensors SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID CONFLICTS; DIAGNOSIS AB In this paper, we propose a new algorithmic approach for design of a sensor system that maximizes the diagnosability of the system and minimizes the cost of the sensor placement. This approach also allows us to analyze extend of the coverage of the sensor system and to determining its diagnosability degree. The quality and efficiency of a diagnosis system depends on the availability and relevance of the information it can retrieve from the diagnosed plant. The quality of the measurements is expressed by the diagnosability degree, i.e., given a set of sensors, which faults can be discriminated? There is no straightforward relation between the number of sensors and diagnosability of the systems; increasing the number of sensors alone does not guarantee a higher level of diagnosability. The relevance of information provided by an additional sensor and its correlation with information provided by other sensors must also be taken into account. Besides the issue of diagnosability, we also consider economics issues. We must provide a sensor system that achieves a desired degree of diagnosability at the lowest possible cost. Our new algorithmic approach allows us to find efficient solutions for these two important problems regarding the system of sensors. The first problem is to analyze and certify the sensor system. Here the main problem is to determine the Diagnosability Degree of the system, i.e., characterize the set of the faults that can be discriminated. Our method also determines an optimal set of new sensors that needs to be added to the system to enhance its diagnosability. T he second issue is the optimization problem of sensor placement. In this regard, the main questions are as follows. (1) Minimal Sensor Set: Finding a minimal additional sensor set that guarantees a specific degree of diagnosability. (2) Minimal Cost Sensors: In the case that different sensors are assigned with different costs, finding the minimal cost additional sensors which achieve a specific degree of diagnosability. The primary application of this method is at the design level where the number and position of sensors are not known. Our new approach for solving these problems is motivated by our successful method for solving the diagnosis problem. For sensor placement, we start by observing that it can be mapped onto a 0-1 IP Problem. The objective function, in the most general case, is not linear, but the constraints are linear and defined by a 0-1 matrix. For the sensor placement problem, we start with the structural model of the system. The structure analysis of the system and the potential information carried by each sensor provide a set of relations usually called the Analytical Redundant Relations (ARRs). We can also consider the additional sensors (the potential sensors that will provide the desired degree of diagnosability) and their corresponding ARRs. The information of all these ARRs can be summarized in a signature matrix. Then the above sensor optimization problems can be formulated as combinatorial problem regarding the signature matrix, or as integer programming problem involving this matrix. The existing methods for solving these combinatorial problems usually boil down to exhaustive search methods. For solving the diagnosis problem, we have found a new branch-and-bound technique which has achieved order of magnitude speedup over the standard algorithms. Combination of this new algorithm and the ARR approach would provide a powerful efficient technique for solving the difficult problem of sensor placement optimization. We have developed a Mathematica code for validating and benchmarking this algorithm. C1 [Fijany, Amir; Vatan, Farrokh] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Fijany, A (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Amir.Fijany@jpl.nasa.gov; Farrokh.Vatan@jpl.nasa.gov NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4063 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583107020 ER PT S AU Oostdyk, RL Mata, CT Perotti, JM AF Oostdyk, Rebecca L. Mata, Carlos T. Perotti, Jose M. GP IEEE TI A Kennedy space center implementation of IEEE 1451 networked smart sensors and lessons learned SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB To meet(1,2) the need for more specific and reliable information from ground support instrumentation systems and future spacecraft sensors and to support Intelligent Health Management Systems (IHMS), NASA's Instrumentation Branch and ASRC's Advanced Electronics and Technology Development Laboratory at Kennedy Space Center (KSC) have consulted the IEEE 1451 family of smart-sensor standards to develop smart network elements (SNEs). SNEs provide reliable signal conditioning to raw sensors, complex data processing, and communication capabilities with a light implementation of the IEEE 1451 family of standards. They are capable of assessing the health of the raw sensors and the electronics and the reliability and tolerance of the measurement, and they relay this information to higher-level systems. The KSC SNEs employ a scaled-down version of the IEEE 1451.1 object model for smart sensors. The sensors are capable of publish-subscribe and client-server cominunication over an Ethernet network using a custom on-the-wire transmission format that is bandwidth-conservative. KSC, together with NASA Stennis Space Center, has also implemented a user-defined transducer electronic data sheet (TEDS) to store health information about the sensor, defined as the health electronic data sheet (HEDS). The KSC SNEs expand upon the IEEE 1451 family of standards to include a well-defined communication protocol for high-level sensor-to-sensor interaction and a HEDS structure for passing relevant health data over the network. C1 [Oostdyk, Rebecca L.; Mata, Carlos T.] ASRC Aerosp, MS ASRC-25, Kennedy Space Ctr, FL 32899 USA. [Perotti, Jose M.] NASA, Kennedy Space Ctr, FL 32899 USA. RP Oostdyk, RL (reprint author), ASRC Aerosp, MS ASRC-25, Kennedy Space Ctr, FL 32899 USA. EM Rebecca.Oostdyk-1@ksc.nasa.gov; Carlos.Mata-1@ksc.nasa.gov; Jose.M.Perotti@nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4071 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583107021 ER PT S AU Feather, MS Markosian, LZ AF Feather, Martin S. Markosian, Lawrence Z. GP IEEE TI Emerging technologies for V&V of ISHM software for space exploration SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID SPECIFICATIONS; VERIFICATION; CHECKING; SYSTEMS AB Systems(1,2) required to exhibit high operational reliability often rely on some form of fault protection to recognize and respond to faults, preventing faults' escalation to catastrophic failures. Integrated System Health Management (ISHM) extends the functionality of fault protection to both scale to more complex systems (and systems of systems), and to maintain capability rather than just avert catastrophe. Forms of ISHM have been utilized to good effect in the maintenance phase of systems' total lifecycles (often referred to as "condition-based maintenance"), but less so in a "fault protection" role during actual operations. One of the impediments to such use lies in the challenges of verification, validation and certification of ISHM systems themselves. This paper makes the case that state-of-the-practice V&V and certification techniques will not suffice for emerging forms of ISHM systems; however, a number of maturing software engineering assurance technologies show particular promise for addressing these ISHM V&V challenges. C1 [Feather, Martin S.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Markosian, Lawrence Z.] NASA, Ames Res Ctr, QSS Grp Inc, Moffett Field, CA 94035 USA. RP Feather, MS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Martin.S.Feather@jpl.nasa.gov; lzmarkosian@email.arc.nasa.gov FU National Aeronautics and Space Administration; Jet Propulsion Laboratory's internal Research and Technology Development program FX The research described in this paper was carried out at NASA Ames Research Center and at the Jet Propulsion Laboratory, California Institute of Technology, and was funded by both the National Aeronautics and Space Administration and by the Jet Propulsion Laboratory's internal Research and Technology Development program. Reference herein to any specific commercial product, process, or service by trade name, trademark, manufacturer, or otherwise, does not constitute or imply its endorsement by the United States Government or the Jet Propulsion Laboratory, California Institute of Technology. NR 76 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4204 EP + PG 7 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583107034 ER PT S AU Garcia-Galan, C Duncavage, D Olofinboba, O AF Garcia-Galan, Carlos Duncavage, Daniel Olofinboba, Olu GP IEEE TI ISS as a testbed for advanced health management and automation technologies SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Achieving(1,2) a sustainable Exploration Program requires development of a foundation of knowledge, validated technologies, and tools that will support safe/reliable, affordable, effective, and flexible systems. Furthermore, the Exploration Program will require new paradigms in program execution and mission operations to meet both technical and budgetary challenges of Space Exploration missions. New technologies in a wide spectrum of applications must be developed, matured and implemented in spacecraft and mission operations, from vehicle subsystem components to health management and automation applications. In many of these areas, the performance of new technology can be examined and validated in laboratory settings, other ground facilities or un-manned space platforms. However, to develop, mature, and validate new technologies that will enable new Systems and Mission Management capabilities necessary to support long duration manned missions beyond LEO, highly relevant operational environments and data for manned spaceflight applications are necessary. Extensive interaction between state-of-the-art technology developers and the operations community is crucial for the successful evolution of relevant technology from development labs to on-board future space systems. New or existing platforms where relevant environments and data are available for this purpose, and where the developer-operator collaboration can occur, need to be identified and made available. The International Space Station (ISS) is one of the few platforms where abundant data of complex human-rated systems is available, both on-board the spacecraft and on the ground. Additionally, the extended-duration mission profile of ISS provides opportunities for the operations community, including on-board crew and Flight Control Team (FCT), to evaluate and gain familiarity with new technologies and capabilities to execute mission operations, thus reducing the risk of implementation and maximizing the relevancy of the new applications. The ISS provides a unique, long-term on-orbit operations environment to mature and validate technologies that will directly impact on-board vehicle/crew autonomy and mission operations. This paper provides an evaluation of using ISS as a platform to mature and validate new technologies in Health Management and Automation, which will directly impact future spacecraft Systems and Mission Management. The evaluation includes a review of the following: -Current ISS on-board architecture and data, as well as ground facilities, such as Mission Control Center, training facilities and existing testbeds, to enable the platform functions -Candidate technologies in Health Management and Automation to be evaluated, in the areas of Integrated System Health Management, Automated Mission Planning, Automated Command and Procedure Execution, and Human Computer Interface. C1 [Garcia-Galan, Carlos] Honeywell Def & Space Elect Syst, 1980 N Atlant Blvd,Suite 1030, Cocoa Beach, FL 32931 USA. [Duncavage, Daniel] NASA, Johnson Space Ctr, Houston, TX 77058 USA. [Olofinboba, Olu] Honeywell Lab, Minneapolis, MN 55418 USA. RP Garcia-Galan, C (reprint author), Honeywell Def & Space Elect Syst, 1980 N Atlant Blvd,Suite 1030, Cocoa Beach, FL 32931 USA. EM carlos.garcia-galan@honeywell.com; daniel.p.duncavage@nasa.gov; olu.a.olofinboba@honeywell.com NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4219 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583107035 ER PT S AU Agogino, A Tumer, K AF Agogino, Adrian Tumer, Kagan GP IEEE TI Entropy based anomaly detection applied to Space Shuttle Main Engines SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Automated model-free anomaly and fault detection using large collections of sensor suites is vital to increasing safety and reducing maintenance costs of complex aerospace systems, such as the Space Shuttle Main Engine. Current anomaly and fault detection methods are deficient in that they either require a huge amounts of laborious expert analysis or rely on models that fail to capture unmodelled anomalies. To overcome these deficiencies, model-free statistical approaches to this analysis are needed that do not require significant user input. This paper presents two general automated analysis methods that detect anomalies in sensor data taken from large sets of sensors. The first approach uses entropy analysis over the entire set of sensors at once to detect anomalies that have broad system-wide impact. The global nature of this approach reduces its sensitivity to faulty sensors. The second approach uses automated clustering of sensors combined with intracluster entropy analysis to detect anomalies and faults that have more local impact. Results derived from the application of these approaches to sensor data recorded from test-stand runs of the Space Shuttle Main Engine show that they can be effective in finding faults and anomalies. With test-stand data consisting time-series derived from 147 sensors, the system-wide approach was able to reveal an anomalous mixture ratio programmed by the test-engineers, but not revealed to the authors. Using similar data from a different engine test, the localized clustering approach revealed a fault in the high pressure fuel turbo-pump early in the test-run and subsequent cascaded faults later in the test run. In addition the clustering approach was able to separate sensors that contained little analytic value from more important sensors, potentially reducing the burden of subsequent expert analysis. C1 [Agogino, Adrian; Tumer, Kagan] NASA, Ames Res Ctr, Mailstop 269-3, Moffett Field, CA 94035 USA. RP Agogino, A (reprint author), NASA, Ames Res Ctr, Mailstop 269-3, Moffett Field, CA 94035 USA. EM adrian@email.arc.nasa.gov; ktumer@mail.arc.nasa.gov NR 14 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4236 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583107036 ER PT S AU Srivastava, AN Akella, R Diev, V Kumaresan, SP McIntosh, DM Pontikakis, ED Xu, ZB Zhang, Y AF Srivastava, Ashok N. Akella, Ram Diev, Vesselin Kumaresan, Sakthi Preethi McIntosh, Dawn M. Pontikakis, Emmanuel D. Xu, Zuobing Zhang, Yi GP IEEE TI Enabling the discovery of recurring anomalies in aerospace problem reports using high-dimensional clustering techniques SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB This paper describes the results of a significant research and development effort conducted at NASA Ames Research Center to develop new text mining algorithms to discover anomalies in free-text reports regarding system health and safety of two aerospace systems. We discuss two problems of significant import in the aviation industry. The first problem is that of automatic anomaly discovery concerning an aerospace system through the analysis of tens of thousands of free-text problem reports that are written about the system. The second problem that we address is that of automatic discovery of recurring anomalies, i.e., anomalies that may be described in different ways by different authors, at varying times and under varying conditions, but that are truly about the same part of the system. The intent of recurring anomaly identification is to determine project or system weakness or high-risk issues. The discovery of recurring anomalies is a key goal in building safe, reliable, and cost-effective aerospace systems. We address the anomaly discovery problem on thousands of free-text reports using two strategies: (1) as an unsupervised learning problem where an algorithm takes free-text reports as input and automatically groups them into different bins, where each bin corresponds to a different unknown anomaly category; and (2) as a supervised learning problem where the algorithm classifies the free-text reports into one of a number of known anomaly categories. We then discuss the application of these methods to the problem of discovering recurring anomalies. In fact, because recurring anomalies tend to have very small cluster sizes, we explore new methods and measures to enhance the original approach for anomaly detection. We present our results on the identification of recurring anomalies in problem reports concerning two aerospace systems as well as benchmark data sets that are widely used in the field of text mining. The first system is the Aviation Safety Reporting System (ASRS) database, which contains several hundred-thou sand free text reports filed by commercial pilots concerning safety issues on commercial airlines. The second aerospace system we analyze is the NASA Space Shuttle problem reports as represented in the CARS data set, which consists of 7440 NASA Shuttle problem reports. We show significant classification accuracies on both of these systems as well as compare our results with reports classified into anomaly categories by field experts. C1 [Srivastava, Ashok N.; McIntosh, Dawn M.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Akella, Ram; Diev, Vesselin; Kumaresan, Sakthi Preethi; Pontikakis, Emmanuel D.; Xu, Zuobing; Zhang, Yi] Univ Calif Santa Cruz, Santa Cruz, CA USA. RP Srivastava, AN (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM Ashok.N.Srivastava@nasa.gov; akella@soe.ucsc.edu; vdiev@soe.ucsc.edu; shakthi@soe.ucsc.edu; Dawn.M.McIntosh@nasa.gov; manos@stanford.edu; zbxu@soe.ucsc.edu; yiz@cmu.edu NR 17 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4243 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583107037 ER PT S AU Gal-Edd, J Fatig, CC AF Gal-Edd, Jonathan Fatig, Curtis C. GP IEEE TI James Webb Space Telescope XML database: From the beginning to today SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB The James Webb Space Telescope (JWST) Project has been defining, developing, and exercising the use of a common eXtensible Markup Language (XML) for the command and telemetry (C&T) database structure. JWST is the first large NASA space mission to use XML for databases. The JWST Project started developing the concepts for the C&T database in 2002. The database will need to last at least 20 years since it will be used beginning with flight software development, continuing through Observatory integration and test (I&T) and through operations. Also, a database tool kit has been provided to the 18 various flight software development laboratories located in the United States, Europe, and Canada that allows the local users to create their own databases. Recently the JWST Project has been working with the Jet Propulsion Laboratory (JPL) and Object Management Group (OMG) XML Telemetry and Command Exchange (XTCE) personnel to provide all the information needed by JWST and JPL for exchanging database information using a XML standard structure. The lack of standardization requires custom ingest scripts for each ground system segment, increasing the cost of the total system. Providing a non-proprietary standard of the telemetry and command database definition format will allow dissimilar systems to communicate without the need for expensive mission specific database tools and testing of the systems after the database translation. The various ground system components that would benefit from a standardized database are the telemetry and command systems, archives, simulators, and trending tools. JWST has exchanged the XML database with the Eclipse (R), EPOCH (R), ASIST (R) ground systems, Portable spacecraft simulator (PSS), a front-end system, and Integrated Trending and Plotting Systeme (ITPS) successfully. This paper will discuss how JWST decided to use XML, the barriers to a new concept, experiences utilizing the XML structure, exchanging databases with other users, and issues that have been experienced in creating databases for the C&T system. C1 [Gal-Edd, Jonathan] NASA, Goddard Space Flight Ctr, Code 661, Greenbelt, MD 20771 USA. [Fatig, Curtis C.] NASA, Goddard Space Flight Ctr, SAIC, Code 661, Greenbelt, MD 20771 USA. RP Gal-Edd, J (reprint author), NASA, Goddard Space Flight Ctr, Code 661, Greenbelt, MD 20771 USA. EM jonathan.s.galedd@nasa.gov; curtis.fatig@gsfc.nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4275 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583107040 ER PT S AU Madden, M Cary, E Esposito, T Parker, J Bradley, D AF Madden, Maureen Cary, Everett, Jr. Esposito, Timothy Parker, Jeffrey Bradley, David GP IEEE TI Lessons learned from engineering a multi-mission satellite operations center SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB NASA's Small Explorers (SMEX)(1,2) satellites have surpassed their designed science-lifetimes and their flight operations teams are now facing the challenge of continuing operations with reduced funding. At present, these missions are being reengineered into a fleet-oriented ground system at Goddard Space Flight Center (GSFC). When completed, this ground system will provide command and control of four SMEX missions and will demonstrate fleet automation and control concepts. As a path-finder for future mission consolidation efforts, this ground system will also demonstrate new ground-based technologies that show promise of supporting longer mission lifecycles and simplifying component integration. One of the core technologies being demonstrated in the SMEX Mission Operations Center is the GSFC Mission Services Evolution Center (GMSEC) architecture. The GMSEC architecture uses commercial Message Oriented Middleware with a common messaging standard to realize a higher level of component interoperability, allowing for interchangeable components in ground systems. Moreover, automation technologies utilizing the GMSEC architecture are being evaluated and implemented to provide extended lights-out operations. This mode of operation will provide routine monitoring and control of the heterogeneous spacecraft fleet. The operational concepts being developed will reduce the need for staffed contacts and is seen as a necessity for fleet management. This paper will describe the experiences of the integration team throughout the reengineering effort of the SMEX ground system. Additionally, lessons learned will be presented based on the team's experiences with integrating multiple missions into a fleet-based automated ground system. C1 [Madden, Maureen] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Cary, Everett, Jr.; Esposito, Timothy] Emergent Space Technol Inc, Greenbelt, MD 20770 USA. [Parker, Jeffrey; Bradley, David] Honeywell Technol Solut Inc, Lanham, MD 20706 USA. RP Madden, M (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM maureen.p.madden@nasa.gov; everett.cary@emergentspace.com; timothy.esposito@emergentspace.com; jsparker@pop400.gsfc.nasa.gov; dbradley@pop500.gsfc.nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4317 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583107044 ER PT S AU Pingree, PJ AF Pingree, Paula J. GP IEEE TI The deep impact test benches - Two spacecraft, twice the fun SO 2006 IEEE Aerospace Conference, Vols 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB The Jet Propulsion Laboratory's Deep Impact (DI) Project was a smashing success with its successful Impact and Flyby Encounter on July 4, 2005 (UTC). Deep Impact launched the flight system, consisting of two spacecraft, on January 12, 2005 for an Encounter with comet Tempel 1 just 6 months later. The two spacecraft, known as the Flyby and the Impactor, were separated 24 hours prior to Encounter, whereby the Impactor targeted itself to a collision course with Tempel 1 and the Flyby captured the event as it flew by the comet. Ball Aerospace and Technologies Corporation (BATC) located in Boulder, CO. was the system contractor for the Deep Impact spacecraft. BATC also developed the DI Test Benches. Test benches are developed by a flight project to provide an effective platform for developing flight software and mission sequences, to offload the flight system for prelaunch validation and verification efforts, and to reliably represent the flight system for development and anomaly resolution post-launch. The success of Deep Impact was heavily reliant on these valuable project resources. Developing and operating two spacecraft simultaneously required a unique test bench architecture that could support the various configurations of the DI mission. This paper presents an overview of the Deep Impact Test Bench architecture. The process and challenges of operating the test benches, specifically in testing Impactor sequences, are described. Lessons learned from the test bench experience on Deep Impact are shared. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Pingree, PJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,M-S 197-326, Pasadena, CA 91109 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4402 EP 4410 PG 9 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583107053 ER PT S AU Hammer, FJ Kahr, JR AF Hammer, Fred J. Kahr, Joseph R. GP IEEE TI Achieving operability via the mission system paradigm SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Based on a combined 40 years of experience developing mission operations systems at JPL, the authors have concluded that special attention to "operability" via integrated flight-ground development can significantly reduce lifecycle cost and mission risk.(1,2) In the past, flight and ground systems have been developed largely-independently, with the flight system taking the lead, and dominating the development process. Operability issues have been addressed poorly in planning, requirements, design, I&T, and system-contracting activities. In many cases, as documented in lessons-learned, this has resulted in significant avoidable increases in cost and risk. With complex missions and systems, operability is being recognized as an important end-to-end design issue. Never-the-less, lessons-learned and operability concepts remain, in many cases, poorly understood and sporadically applied. A key to effective application of operability concepts is adopting a "Mission System" paradigm. In this paradigm, flight and ground systems are treated, from an engineering and management perspective, as inter-related elements of a larger mission system. The mission system consists of flight hardware, flight software, telecom services, ground data system, testbeds, flight teams, science teams, flight operations processes, procedures, and facilities. The system is designed in functional layers, which span flight and ground. It is designed in response to project-level requirements, mission design and an operations concept, and is developed incrementally, with early and frequent integration of flight and ground components. Processes and tools used successfully at JPL include: Operations Concepts and Design Reference Missions, Mission System Implementation (and V&V) Plans, End-to-end data management and accountability, Integrated Flight-Ground schedules & deliveries Integrated, controlled dictionaries and databases, Hierarchical Flight-Ground interface requirements, Flight Ops - Science Ops interface requirements, Operations-development testbeds, "Test as you fly / fly as you test", Objective-oriented test planning, Multi-mission standards, tools and services. C1 [Hammer, Fred J.; Kahr, Joseph R.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Hammer, FJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM fred.j.hammer@jpl.nasa.gov; jkahr@sirtfweb.jpl.nasa.gov NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4426 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583108002 ER PT S AU Thronesbery, C Malin, JT Holden, K Smith, DP AF Thronesbery, Carroll Malin, Jane T. Holden, Kritina Smith, Danielle Paige GP IEEE TI Tools to support human factors and systems engineering interactions during early analysis SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB We describe(1,2) an approach and existing software tool support for effective interactions between human factors engineers and systems engineers in early analysis activities during system acquisition. We examine the tasks performed during this stage, emphasizing those tasks where system engineers and human engineers interact. The Concept of Operations (ConOps) document is an important product during this phase, and particular attention is paid to its influences on subsequent acquisition activities. Understanding this influence helps ConOps authors describe a complete system concept that guides subsequent acquisition activities. We identify commonly used system engineering and human engineering tools and examine how they can support the specific tasks associated with system definition. We identify possible gaps in the support of these tasks, the largest of which appears to be creating the ConOps document itself. Finally, we outline the goals of our future empirical investigations of tools to support system concept definition. C1 [Thronesbery, Carroll] S&K Technol Inc, 201 Flint Ridge Plaza,Ste 102, Webster, TX 77598 USA. [Malin, Jane T.] NASA, Johnson Space Ctr, Houston, TX 77058 USA. [Holden, Kritina; Smith, Danielle Paige] Lockheed Martin, Houston, TX 77058 USA. RP Thronesbery, C (reprint author), S&K Technol Inc, 201 Flint Ridge Plaza,Ste 102, Webster, TX 77598 USA. EM c.thronesbery@jsc.nasa.gov; jane.t.malin@nasa.gov; kritina.l.holden1@jsc.nasa.gov; danielle.paige-smith1@jsc.nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4466 EP + PG 4 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583108005 ER PT S AU Morse, E Leavens, T Cohanim, B Harmon, C Mahr, E Lewis, B AF Morse, Elisabeth Leavens, Tracy Cohanim, Babak Harmon, Corey Mahr, Eric Lewis, Brian GP IEEE TI Next-generation concurrent engineering: Developing models to complement point designs SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Concurrent Engineering Design (CED) teams have made routine the rapid development of point designs for space missions. The Jet Propulsion Laboratory's Team X is now evolving into a "next-generation" CED; in addition to a point design, the Team develops a model of the local trade space. The process is a balance between the power of model-developing tools and the creativity of human experts, enabling the development of a variety of trade models for any space mission. This paper reviews the modeling method and its practical implementation in the CED environment. Example results illustrate the benefits of the approach. C1 [Morse, Elisabeth; Leavens, Tracy; Cohanim, Babak; Harmon, Corey] NASA, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Mahr, Eric; Lewis, Brian] Aerosp Corp, El Segundo, CA 90009 USA. RP Morse, E (reprint author), NASA, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM elisabeth.morse@jpl.nasa.go; tracy.j.leavens@jpl.nasa.go; babak.e.cohanim@jpl.nasa.go; corey.harmon@jpl.nasa.go; eric.mahr@aero.org; brian.lewis@aero.org NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4485 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583108007 ER PT S AU Cheung, KM Lee, CH Ho, J AF Cheung, Kar-Ming Lee, Charles H. Ho, Jeannie GP IEEE TI Problem formulation for optimal array modeling and planning SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB To support NASA's vision to increase the Deep Space Network (DSN) communications capability by at least 100 times the current capability of the 70m antennas, the option of large arrays of thousands of 12m antennas is being studied at the Jet Propulsion Laboratory (JPL), and an operational prototype is planned for the 2010 timeframe. The flexibility of dynamically subdividing a large antenna array into smaller array clusters of various sizes to support different concurrent missions and the ability to add or remove antenna elements from an array cluster without interrupting the signal tracking definitely enable new network operation concepts. Yet there are unique challenges to the modeling and planning of the large array. Current DSN antenna planning and scheduling is done based on network support requests from individual missions that perform their own communication link analysis and inview period analysis. The largely manual 'horse-trading' among missions is done, by and large, based on antenna tracking-time metrics and does not take into account antenna network performance and reliability. Recognizing the iterative nature of negotiations for resources, missions tend to grossly overestimate their required coverage time, thus reducing the overall network efficiency. The above manual approach will break down in the operation of a large array of thousands of antennas. To efficiently utilize the large array, the modeling and planning process needs to 1) be highly automated, 2) take into account link capability and antenna element reliability, and 3) support long-term, short-term, and instantaneous planning. In this paper we describe an optimal modeling and planning framework for the future large array of DSN antennas. This framework takes into account the array link performance models, reliability models, constraint models, and objective functions, and determines the optimal sub-array clusters configuration that will support the maximum number of concurrent missions based on mission link properties, antenna element reliabilities, mission requests, and array operation constraints. Array cluster size can vary dynamically during the support of a mission. Larger numbers of small antennas may be needed during the acquisition/calibration phase. Some of these antennas may be released for other uses during the tracking phase. Thus, resources will be efficiently allocated to achieve full utilization. C1 [Cheung, Kar-Ming; Lee, Charles H.; Ho, Jeannie] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Cheung, KM (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Kar-Ming.Cheung@jpl.nasa.gov FU National Aeronautics and Space Administration; California State University Fullerton (CSUF); CSUF Faculty Development Center Grant and Funds FX This research was carried out jointly by the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration, and by the California State University Fullerton (CSUF), with funding from the CSUF Faculty Development Center Grant and Funds. NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4509 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583108009 ER PT S AU Lehman, DH Clark, KB Cook, BA Gavit, SA Kayali, SA McKinney, JC Milkovich, DA Reh, KR Taylor, RL Casani, JR Griebel, T AF Lehman, David H. Clark, Karla B. Cook, Beverly A. Gavit, Sarah A. Kayali, Sammy A. McKinney, John C. Milkovich, David A. Reh, Kim R. Taylor, Randall L. Casani, John R. Griebel, Therese GP IEEE TI Experiences in managing the Prometheus project SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Congress authorized NASA's Prometheus Project in February 2003, with the first Prometheus mission slated to explore the icy moons of Jupiter. The Project had two major objectives: (1) to develop a nuclear reactor that would provide unprecedented levels of power and show that it could be processed safely and operated reliably in space for long-duration, deep-space exploration and (2) to explore the three icy moons of Jupiter - Callisto, Ganymede, and Europa - and return science data that would meet the scientific goals as set forth in the Decadal Survey Report of the National Academy of Sciences. Early in Project planning, it was determined that the development of the Prometheus nuclear powered Spaceship would be complex and require the intellectual knowledge residing at numerous organizations across the country. In addition, because of the complex nature of the Project and the multiple partners, approaches beyond those successfully used to manage a typical JPL project would be needed. This paper(1,2) describes the key experiences in managing Prometheus which should prove useful for future projects of similar scope and magnitude. C1 [Lehman, David H.; Clark, Karla B.; Cook, Beverly A.; Gavit, Sarah A.; Kayali, Sammy A.; McKinney, John C.; Milkovich, David A.; Reh, Kim R.; Taylor, Randall L.; Casani, John R.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Griebel, Therese] Glenn Res Ctr, Cleveland, OH 44135 USA. RP Lehman, DH (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Therese.M.Griebel@grc.nasa.gov NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4517 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583108010 ER PT S AU Taylor, RL AF Taylor, Randall L. GP IEEE TI Acquisition strategy and source selection for co-designing a new-development spacecraft SO 2006 IEEE Aerospace Conference, Vols 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB NASA's Prometheus Project (12)was authorized to develop a revolutionary solar system exploration capability - a nuclear electric propulsion spacecraft - that would, during its initial flight, orbit three icy moons of Jupiter. An innovative acquisition strategy - including competitive industry studies, parallel Government studies, customized rules of engagement, research, and benchmarking - was employed for Project Formulation. This strategy produced a new paradigm for space system development: co-design. The co-design paradigm was infused into a unique Request for Proposal process and a streamlined Source Evaluation Board process, resulting in a timely and effective contractor selection. Following contractor selection, the mechanics of co-design were baselined, then modified through experience. The Project co-design team successfully completed the Project conceptual design and life cycle cost estimate on schedule, meeting or exceeding all requirements. This paper describes the study contract and down-select phases, provides a definition and description of co-design, and recommends future application of the paradigm for major systems developments [1]. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Taylor, RL (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 IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4529 EP 4541 PG 13 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583108011 ER PT S AU Baroff, LE AF Baroff, Lynn E. GP IEEE TI Project-line interaction: JPL's matrix SO 2006 IEEE Aerospace Conference, Vols 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB Matrix structures are common in highly technical organizations. The matrix structure is most defined by this characteristic: that most people in the enterprise have two bosses. One resides in the programmatic organizations that make direct contact with the enterprise's customers, and organize and manage work to meet customer expectations. The other boss lives in the line organizations, functional and service organizations that provide the enterprise with capability to accomplish the work. The JPL enterprise is organized as a matrix because that structure can optimize retention and development of knowledge, aswell as flexibility in applying that knowledge to the programs and projects JPL conducts. A matrix is usually considered most effective for accomplishing current project and technology development work while maintaining and developing institutional capability for the future. Can programmatic and line organizations really work interdependently, to accomplish their work as a community? Does the matrix produce a culture in which individuals take personal responsibility for both immediate mission success and long-term growth? What is the secret to making a matrix enterprise actually work? This paper will consider those questions, and propose that developing an effective project-line partnership demands primary attention to personal interactions among people. Many potential problems can be addressed by careful definition of roles, responsibilities, and work processes for both parts of the matrix - and by deliberate and clear communication between project and line organizations and individuals.(12). C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Baroff, LE (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 IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4551 EP 4557 PG 7 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583108013 ER PT S AU Bell, DG Maluf, DA Gawdiak, Y Putz, P Swanson, K AF Bell, David G. Maluf, David A. Gawdiak, Yuri Putz, Peter Swanson, Keith GP IEEE TI The NASA Program Management Tool: A new vision in business intelligence SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB This paper(1) describes a novel approach to business intelligence and program management for large technology enterprises like the U.S. National Aeronautics and Space Administration (NASA). Two key distinctions of the approach are that 1) standard business documents are the user interface, and 2) a "schema-less" XML2 database enables flexible integration of technology information for use by both humans and machines in a highly dynamic environment. The implementation utilizes patent-pending NASA software called the NASA Program Management Tool (PMT) and its underlying "schema-less" XML database called Netmark. Initial benefits of PMT include elimination of discrepancies between business documents that use the same information and "paperwork reduction" for program and project management in the form of reducing the effort required to understand standard reporting requirements and to comply with those reporting requirements. We project that the underlying approach to business intelligence will enable significant benefits in the timeliness, integrity and depth of business information available to decision makers on all organizational levels. C1 [Bell, David G.; Putz, Peter] NASA, Ames Res Ctr, Univ Space Res Assoc, Moffett Field, CA 94035 USA. [Maluf, David A.; Swanson, Keith] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Gawdiak, Yuri] NASA, Washington, DC 20546 USA. RP Bell, DG (reprint author), NASA, Ames Res Ctr, Univ Space Res Assoc, Moffett Field, CA 94035 USA. EM dbell@riacs.edu; david.a.maluf@nasa.gov; yuri.o.gawdiak@nasa.gov; pputz@riacs.edu; kswanson@mail.arc.nasa.gov NR 1 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4582 EP + PG 2 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583108016 ER PT S AU Gawdiak, Y Gurram, M Bell, D Maluf, D AF Gawdiak, Yuri Gurram, Mohana Bell, David Maluf, David GP IEEE TI Context based configuration management SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB (12) The commercial state-of-the-art tools for configuration managements (CM) systems are very mature for asset, hardware and software development systems. These tools are very good for tactical management for daily issues. However, strategic management and decisions also have a requirement for configuration management but unfortunately the traditional Commercial Off The Shelf (COTS) tools are not adequate for those requirements. They come up short in 5 major ways: 1) User interface: engineering/tactical CM systems have minimum interface support and are usually focused to only select groups of technical users, vs. the broader strategic planning communities: budget, policy, legal, and administrative users. 2) COTS CM tools provide minimum support for the context of the change environment. The implications of implementing or not implementing a change is well documented, but the broader forces at play, the environment, and other important contextual facets are not well supported. Those parameters are not usually critical for the tactical engineering management, but they are potentially key lessons learned, and corporate knowledge components that are very important to capture at the strategic planning levels; 3) Items that need to be tracked at the strategic planning levels often don't fit well within COTS CM systems. They include unofficial or implicit changes that on the surface aren't considered baselines, but in reality have very large impacts into the operations of an organization. In particular organization parameters such as: beliefs, agreements, goals, priorities, values, disconnects, etc. to name a few. 4) Agility - formal CM processes and systems require significant discipline and direct human involvement. Change boards and auditing processes require significant time and attention. Strategic planning must have a tracking system that is fast and agile with preloaded components that make inputs very efficient and provide the context that is key to improving the overall process. 5) Change Management affects entire organizations and enterprises, but the nature of human processing and time limits the amount of participation members can have on a particular component Change Request (CR) with traditional tools. Using those shortcomings as requirements drivers our team has developed a hybrid tool-suite that directly supports the dynamic, distributed strategic planning and decision making environments. The Context Based Configuration Management (CBCM) system marries Decision Map technology with COTS configuration management work flow (Xerox Docushare), embedded component models (events models, configuration item models, and feedback models) all on top of a web based online collaboration technology (NASA/Xerox Netmark [3] middleware engine). This paper will document the rapid prototype that has been developed to meet those requirements using this design and highlight the initial pilot results at NASA Headquarters with the Aeronautics Research Mission Directorate. C1 [Gawdiak, Yuri] NASA, ARMD, 300 E St SW, Washington, DC 20546 USA. [Gurram, Mohana; Bell, David; Maluf, David] NASA, ARC, RIACS, Moffett Field, CA 94035 USA. RP Gawdiak, Y (reprint author), NASA, ARMD, 300 E St SW, Washington, DC 20546 USA. EM yuri.o.gawdiak@nasa.gov; Mohana.m.gurram@nasa.gov; dbell@arc.nasa.gov; david.a.maluf@nasa.gov FU LMI Government Consulting FX Although much of the conceptual work and initial software for this pilot was done as part of the ECS program, the initial pilot testing was done under a contract with LMI Government Consulting with a subcontract to NXAR LLC. We wish to thank Shahab Hasan, Denise Duncan and Joanna Gribko from LMI for the concept pilot task management as well as state-of-the-art research on current configuration management systems and requirements analysis for the ARMD organization. We would also like to thank Randy Nickel from NXAR for the current pilot software upgrades and test support. NR 4 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4589 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583108017 ER PT S AU Jansma, PAT Jones, RM AF Jansma, P. A. Trisha Jones, Ross M. GP IEEE TI Advancing the practice of systems engineering at JPL SO 2006 IEEE Aerospace Conference, Vols 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB In FY 2004, JPL launched an initiative to improve the way it practices systems engineering. The Lab's senior management formed the Systems Engineering Advancement (SEA) Project in order to "significantly advance the practice and organizational capabilities of systems engineering at JPL on flight projects and ground support tasks." The scope of the SEA Project includes the systems engineering work performed in all three dimensions of a program, project, or task: 1. the full life-cycle, i.e., concept through end of operations 2. the full depth, i.e., Program, Project, System, Subsystem, Element (SE Levels 1 to 5) 3. the full technical scope, e.g., the flight, ground and launch systems, avionics, power, propulsion, telecommunications, thermal, etc. The initial focus of their efforts defined the following basic systems engineering functions at JPL: systems architecture, requirements management, interface definition, technical resource management, system design and analysis, system verification and validation, risk management, technical peer reviews, design process management and systems engineering task management. They also developed a list of highly valued personal behaviors of systems engineers, and are working to inculcate those behaviors into members of their systems engineering community. The SEA Project is developing products, services, and training to support managers and practitioners throughout the entire system life-cycle. As these are developed, each one needs to be systematically deployed. Hence, the SEA Project developed a deployment process that includes four aspects: infrastructure and operations, communication and outreach, education and training, and consulting support. In addition, the SEA Project has taken a proactive approach to organizational change management and customer relationship management - both concepts and approaches not usually invoked in an engineering environment. This paper(1,2) describes JPL's approach to advancing the practice of systems engineering at the Lab. It describes the general approach used and how they addressed the three key aspects of change: people, process and technology. It highlights a list of highly valued personal behaviors of systems engineers, discusses the various products, services and training that were developed, describes the deployment approach used, and concludes with several lessons learned. C1 CALTECH, Jet Prop Lab, SEA Project, Pasadena, CA 91109 USA. RP CALTECH, Jet Prop Lab, SEA Project, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 38 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4597 EP 4615 PG 19 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583108018 ER PT S AU Mendoza, DR Johnson, R AF Mendoza, Donald R. Johnson, Ronald GP IEEE TI Using a Lessons Learned process to develop and maintain institutional memory and intelligence SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB The process of collecting, disseminating, and applying Lessons Learned (LL) is critical to the development and maintenance of any organization's institutional memory and intelligence, perhaps its most important resource. This is especially true for the NASA Ames Research Center (ARC), a research and development organization that develops systems meant to operate in high risk environments. However, the ARC environment being extremely diversified posed several challenges for implementing this process. These included; limited resources, employee turn over, many diverse communities of practice using unique sets of nomenclature, and employee anxiety over identifying problems or criticizing their organization. Thus, the Center developed a LL process based on interviews that successfully addressed these challenges and increased its LL submittal rate from two to thirty per year. In particular, it was found that the key to a successful LL program was the process of decomposition and re-integration of tacit (as represented by the anecdotal and contextual) with explicit information throughout the collection and dissemination steps. Furthermore, it was found that interviewers possessing corporate and technical experience/knowledge/access and excellent writing abilities were necessary for success. This combination of skills enabled the interviewer to accurately capture the LL explicit information while maintaining as much of the tacit as possible. In addition, by choosing interviewers that were involved in Center wide activities, the propagation of the tacit information was ensured. These findings in addition to the tools used to manage both the process and the LL will be described in his paper. C1 [Mendoza, Donald R.; Johnson, Ronald] NASA, Ames Res Ctr, M-S 244-14, Moffett Field, CA 94035 USA. RP Mendoza, DR (reprint author), NASA, Ames Res Ctr, M-S 244-14, Moffett Field, CA 94035 USA. EM Donald.R.Mendoza@nasa.gov; Ronald.D.Johnson@nasa.gov NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4616 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583108019 ER PT S AU Malin, JT Fleming, L AF Malin, Jane T. Fleming, Land GP IEEE TI Vulnerabilities, influences and interaction paths: Failure data for integrated system risk analysis SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID PLANTS AB We describe analysis methods for identifying and analyzing cross-subsystem interaction risks from subsystem connectivity information. These methods identify entities that can pose a hazard to a function if they can be propagated from the hazard source to the vulnerable function. The analysis method can assess combined impacts of multiple disabling influences on a vulnerable function. The analysis method also uses numerical estimates of hazard strength to calculate cumulative measures of impact severity. These methods can support design of more dependable and diagnosable systems and promote better communication among subsystem designers about risk. Identification of cross-subsystem hazard-vulnerability pairs and propagation paths will increase coverage of risk analysis and can help identify risk control and protection strategies. C1 [Malin, Jane T.] NASA, Johnson Space Ctr, 2101 NASA Rd 1, Houston, TX 77058 USA. [Fleming, Land] MEI Technol Inc, Houston, TX 77058 USA. RP Malin, JT (reprint author), NASA, Johnson Space Ctr, 2101 NASA Rd 1, Houston, TX 77058 USA. EM jane.t.malin@nasa.gov; land.d.fleming@jsc.nasa.gov FU NASA Exploration Systems Mission Directorate; NASA Engineering for Complex Systems FX This work has been funded by the NASA Exploration Systems Mission Directorate, a legacy project from the NASA Engineering for Complex Systems program. Thanks to David Throop, Luis Flores, Dennis Lawler and Carroll Thronesbery for working with us to develop the overall concept and context for this analysis work. NR 20 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4625 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583108020 ER PT S AU Dillon, RL Rogers, EW Tinsley, CH AF Dillon, Robin L. Rogers, Edward W. Tinsley, Catherine H. GP IEEE TI The near-miss bias in decision making SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB The Columbia Accident Investigation Board(1,2) (CAIB) report states that NASA needs to develop an organizational culture that reflects the best characteristics of a learning organization and that NASA historically has not demonstrated such characteristics [1]. When there is a technical failure, most organizations are good at identifying the technical cause and learning not to repeat that same mistake. However, it is more difficult to learn from near-misses and lucky successes (i.e., situations where a technical failure does not occur but nearly did) [2]. This research shows that managers whose decisions ended in a failure were perceived as significantly less competent, as having made poorer decisions, and as less deserving of promotions than managers that made the same decisions but whose project outcomes were either a success or a near miss. Moreover, there were no significant differences in the perceptions of a manager's competence or promotability when that manager's decisions resulted in a near-miss or a complete success. Therefore, even when a problem occurs that is linked to prior managerial decisions, if the project outcome is successful, that manager may not be held as accountable for any faulty decision making compared to managers of projects that fail. These results indicate a potential mechanism to explain why organizations fail to learn from their successes. C1 [Dillon, Robin L.; Tinsley, Catherine H.] Georgetown Univ, McDonough Sch Business, Washington, DC 20057 USA. [Rogers, Edward W.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Dillon, RL (reprint author), Georgetown Univ, McDonough Sch Business, Washington, DC 20057 USA. EM rld9@georgetown.edu; edward.w.rogers@nasa.gov; tinsleyc@georgetown.edu NR 6 TC 0 Z9 0 U1 0 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4637 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583108021 ER PT S AU Chao, LP Tumer, I AF Chao, Lawrence P. Tumer, Irem GP IEEE TI Risk assessment practices at NASA: Studies of design and review methods SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT DE design; review; risk; management; assess; NASA ID MANAGEMENT AB This report(1) describes a number of design and review activities observed at NASA for risk identification, assessment, and management. The NASA life-cycle is centered around the experience of its scientists, engineers, and managers, and the checks-and-balances are primarily instituted through a number of programmatic and technical reviews but also workshops and design tools. This paper explores the project development on both a full mission level as well as an accelerated design project to better demonstrate the range of methods used to identify and manage risk in NASA missions. With better understanding of not only the execution but motivation for the current development life-cycle practices, organizations, including but not limited to NASA, can better improve and error-proof their design process through risk management. C1 [Chao, Lawrence P.] Intel Corp, 2200 Mission Coll Blvd,RNB 504, Santa Clara, CA 95054 USA. [Tumer, Irem] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Chao, LP (reprint author), Intel Corp, 2200 Mission Coll Blvd,RNB 504, Santa Clara, CA 95054 USA. EM chao12@asme.org; itumer@email.arc.nasa.gov NR 17 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4650 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583108023 ER PT S AU Rioux, N AF Rioux, Norman GP IEEE TI ANSI/AIAA guide for estimating spacecraft systems contingencies applied to the NASA GLAST Mission SO 2006 IEEE Aerospace Conference, Vols 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB An assessment 12 is conducted of the mass and power contingency trends experienced by NASA's Gamma Ray Large Area Telescope (GLAST) Mission from the Bid to CDR Program design stages with respect to the ANSI/AIAA Guide for Estimating and Budgeting Weight and Power Contingencies for Spacecraft Systems G-020-1992. The GLAST spacecraft is a gamma ray telescope observatory that is scheduled to be launched into low Earth orbit in late 2007. The GLAST observatory consists of a spacecraft bus that supports two instruments - the Large Area Telescope (LAT) and the GLAST Burst Monitor (GBM). Mass and power contingencies for each of these three observatory elements have been allocated and managed based on application of the ANSI/AIAA Guide. The correlation of the GLAST experience with the Guide is analyzed and suggestions are offered to potential users of the Guide for increasing the effectiveness of their application of it on other missions. The results of this paper contribute to the constructive evolution of this important aspect of systems engineering design practice. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Rioux, N (reprint author), NASA, Goddard Space Flight Ctr, Code 661, Greenbelt, MD 20771 USA. NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4689 EP 4705 PG 17 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583108027 ER PT S AU Terrile, RJ Kordon, M Mandutianu, D Salcedo, J Wood, E Hashemi, M AF Terrile, Richard J. Kordon, Mark Mandutianu, Dan Salcedo, Jose Wood, Eric Hashemi, Mona GP IEEE TI Automated design of spacecraft power subsystems SO 2006 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT AB This paper(1,2) discusses the application of evolutionary computing to a dynamic space vehicle power subsystem resource and performance simulation in a parallel processing environment. Our objective is to demonstrate the feasibility, application and advantage of using evolutionary computation techniques for the early design search and optimization of space systems. With this approach, engineers specify several sets of conditional subsystem performance criteria to trade off subsystem goals of mass, cost, performance and risk. Once specified, the integrated evolutionary/simulation software will then automatically generate a design option for each criteria, selecting and sizing power elements based on the space system's anticipated performance in the simulated environment. Initial Activity plans from two actual JPL missions, Mars Exploration Rovers (MER) and Deep Impact (DI) are used to test the software. Our results have shown human-competitive advantages by generating credible design concepts much faster than humans are able to and without the need for expert initial designs. C1 [Terrile, Richard J.; Kordon, Mark; Mandutianu, Dan; Salcedo, Jose; Wood, Eric; Hashemi, Mona] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Terrile, RJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM rich.terrile@jpl.nasa.gov FU California Institute of Technology; National Aeronautics and Space Administration FX The work described in this publication was carried out at the Jet Propulsion Laboratory, California Institute of Technology under a contract with the National Aeronautics and Space Administration. NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4706 EP + PG 3 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583108028 ER PT S AU Duren, RM AF Duren, Riley M. GP IEEE TI Validation (not just verification) of deep space missions SO 2006 IEEE Aerospace Conference, Vols 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2006 IEEE Aerospace Conference CY MAR 04-11, 2006 CL Big Sky, MT ID MODEL AB Verification & Validation (V&V) is a widely recognized and critical systems engineering function. However, the often used definition "Verification proves the design is right; validation proves it is the right design" is rather vague. And while Verification is a reasonably well standardized systems engineering process, Validation is a far more abstract concept and the rigor and scope applied to it varies widely between organizations and individuals. This is reflected in the findings in recent Mishap Reports for several NASA missions, in which shortfalls in Validation (not just Verification) were cited as root- or contributing-factors in catastrophic mission loss. Furthermore, although there is strong agreement in the community that Test is the preferred method for V&V, many people equate "V&V" with "Test", such that Analysis and Modeling aren't given comparable attention. Another strong motivator is, a realization that the rapid growth in complexity of deep-space missions (particularly Planetary Landers and Space Observatories given their inherent unknowns) is placing greater demands on systems engineers to "get it right" with Validation. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Duren, RM (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 14 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 0-7803-9545-X J9 AEROSP CONF PROC PY 2006 BP 4720 EP 4732 PG 13 WC Engineering, Aerospace SC Engineering GA BFF34 UT WOS:000241583108029 ER PT S AU Callantine, TJ Palmer, EA Homola, J Mercer, J Prevot, T AF Callantine, Todd J. Palmer, Everett A. Homola, Jeff Mercer, Joey Prevot, Thomas GP IEEE TI Agent-based assessment of trajectory-oriented operations with limited delegation SO 2006 IEEE/AIAA 25TH DIGITAL AVIONICS SYSTEMS CONFERENCE, VOLS 1- 3 SE IEEE-AIAA Digital Avionics Systems Conference LA English DT Proceedings Paper CT IEEE/AIAA 25th Digital Avionics Systerms Conference CY OCT 15-18, 2006 CL Portsmouth, OR SP IEEE, AIAA AB An evolutionary concept called "trajectory-oriented operations with limited delegation" is the subject of a preliminary assessment conducted using fast-time simulations with computational agents that represent air traffic controllers. The concept integrates technologies relevant to the Next Generation Air Transportation System (NGATS) and holds promise for efficiency gains by enabling aircraft to fly Continuous Descent Approaches (CDAs). The assessment focuses on how controller strategies and automation tools impact CDA operations. The results indicate the concept represents an advance toward higher-efficiency NGATS operations, and emphasize the importance of shared. information and air traffic controller decision support tools. C1 [Callantine, Todd J.; Palmer, Everett A.; Mercer, Joey; Prevot, Thomas] San Jose State Univ, NASA, Ames Res Ctr, San Jose, CA 95192 USA. [Homola, Jeff] San Jose State Univ, NASA, Ames Res Ctr, Moffett Field, CA USA. RP Callantine, TJ (reprint author), San Jose State Univ, NASA, Ames Res Ctr, San Jose, CA 95192 USA. FU NASA Airspace Systems Program FX Funding support for this research is provided by the NASA Airspace Systems Program. NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2155-7195 BN 978-1-4244-0377-6 J9 IEEEAAIA DIGIT AVION PY 2006 BP 185 EP + PG 2 WC Automation & Control Systems; Engineering, Aerospace; Computer Science, Artificial Intelligence; Telecommunications SC Automation & Control Systems; Engineering; Computer Science; Telecommunications GA BGB18 UT WOS:000245889700019 ER PT B AU Barmore, B AF Barmore, Bryan GP IEEE TI Airborne precision spacing: A trajectory-based aprroach to improve terminal area operations SO 2006 IEEE/AIAA 25TH DIGITAL AVIONICS SYSTEMS CONFERENCE, VOLS 1- 3 SE Digital Avionics Systems Conference LA English DT Proceedings Paper CT IEEE/AIAA 25th Digital Avionics Systerms Conference CY OCT 15-18, 2006 CL Portsmouth, OR SP IEEE, AIAA AB Airborne Precision Spacing has been developed by the National Aeronautics and Space Administration (NASA) over the past seven years as an attempt to benefit from the capabilities of the flight deck to precisely space their aircraft relative to another aircraft. This development has leveraged decades of work on improving terminal area operations, especially the arrival phase. With APS operations, the air traffic controller instructs the participating aircraft to achieve an assigned inter-arrival spacing interval at the runway threshold, relative to another aircraft. The flight crew then uses airborne automation to manage the aircraft's speed to achieve the goal. The spacing tool is designed to keep the speed within acceptable operational limits, promote system-wide stability, and meet the assigned goal. This reallocation of tasks with the controller issuing strategic goals and the flight crew managing the tactical achievement of those goals has been shown to be feasible through simulation and flight test. A precision of +/- 2-3 seconds is generally achievable. Simulations of long strings of arriving traffic show no signs of instabilities or compression waves. Subject pilots have rated the workload to be similar to current-day operations and eye-tracking data substantiate this result. This paper will present a high-level review of research results over the past seven years from a variety of tests and experiments. The results will focus on the precision and accuracy achievable, flow stability and some major sources of uncertainty. The paper also includes a summary of the flight crew's procedures and interface and a brief concept overview. C1 NASA, Langley Res Ctr, Hampton, VA 23665 USA. RP Barmore, B (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. NR 26 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0377-6 J9 DIGIT AVION SYST CON PY 2006 BP 296 EP 307 PG 12 WC Automation & Control Systems; Engineering, Aerospace; Computer Science, Artificial Intelligence; Telecommunications SC Automation & Control Systems; Engineering; Computer Science; Telecommunications GA BGB18 UT WOS:000245889700030 ER PT B AU Jafri, M Vahala, L Ely, J AF Jafri, Madiha Vahala, Linda Ely, Jay GP IEEE TI Classification and prediction of RF coupling inside A-320 and A-319 airplanes using feed forward neural networks SO 2006 IEEE/AIAA 25TH DIGITAL AVIONICS SYSTEMS CONFERENCE, VOLS 1- 3 SE Digital Avionics Systems Conference LA English DT Proceedings Paper CT IEEE/AIAA 25th Digital Avionics Systerms Conference CY OCT 15-18, 2006 CL Portsmouth, OR SP IEEE, AIAA AB Neural Network Modeling is introduced in this paper to classify and predict Interference Path Loss measurements on Airbus 319 and 320 airplanes. Interference patterns inside the aircraft are classified and predicted based on the locations of the doors, windows, aircraft structures and the communication/navigation system-of-concern. Modeled results are compared with measured data and a plan is proposed to enhance the modeling for better prediction of electromagnetic coupling problems inside aircraft. C1 Old Dominion Univ, Norfolk, VA 23529 USA. NASA, Langley Res Ctr, Hampton, VA 23665 USA. RP Jafri, M (reprint author), Old Dominion Univ, Norfolk, VA 23529 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0377-6 J9 DIGIT AVION SYST CON PY 2006 BP 578 EP 586 PG 9 WC Automation & Control Systems; Engineering, Aerospace; Computer Science, Artificial Intelligence; Telecommunications SC Automation & Control Systems; Engineering; Computer Science; Telecommunications GA BGB18 UT WOS:000245889700058 ER PT S AU Jones, BA Prinzel, LJ AF Jones, Benise A. Prinzel, Lawrence J., III GP IEEE TI Runway incursion prevention for general aviation operations SO 2006 IEEE/AIAA 25TH DIGITAL AVIONICS SYSTEMS CONFERENCE, VOLS 1- 3 SE IEEE-AIAA Digital Avionics Systems Conference LA English DT Proceedings Paper CT IEEE/AIAA 25th Digital Avionics Systerms Conference CY OCT 15-18, 2006 CL Portsmouth, OR SP IEEE, AIAA AB A Runway Incursion Prevention System (RIPS) and additional incursion detection algorithm were adapted for general aviation operations and evaluated in a simulation study at the National Aeronautics and Space Administration (NASA) Langley Research Center (LaRC) in the fall of 2005. RIPS has been designed to enhance surface situation awareness and provide cockpit alerts of potential runway conflicts in order to prevent runway incidents while also improving operational capability. The purpose of the study was to evaluate the airborne incursion detection algorithms and associated alerting and airport surface display concepts for general aviation operations. This paper gives an overview of the system, simulation study, and test results. C1 [Jones, Benise A.; Prinzel, Lawrence J., III] Natl Aeronaut & Space Adm, Hampton, VA USA. RP Jones, BA (reprint author), Natl Aeronaut & Space Adm, Hampton, VA USA. NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2155-7195 BN 978-1-4244-0377-6 J9 IEEEAAIA DIGIT AVION PY 2006 BP 587 EP + PG 2 WC Automation & Control Systems; Engineering, Aerospace; Computer Science, Artificial Intelligence; Telecommunications SC Automation & Control Systems; Engineering; Computer Science; Telecommunications GA BGB18 UT WOS:000245889700059 ER PT B AU Glaab, LJ Hughes, MF Parrish, RV Takallu, MA AF Glaab, Louis J. Hughes, Monica F. Parrish, Russell V. Takallu, Mohammad A. GP IEEE TI Effectively transforming IMC flight into VMC flight: An SVS casestudy SO 2006 IEEE/AIAA 25TH DIGITAL AVIONICS SYSTEMS CONFERENCE, VOLS 1- 3 SE Digital Avionics Systems Conference LA English DT Proceedings Paper CT IEEE/AIAA 25th Digital Avionics Systerms Conference CY OCT 15-18, 2006 CL Portsmouth, OR SP IEEE, AIAA AB A flight-test experiment was conducted using the NASA LaRC Cessna 206 aircraft. Four primary flight and navigation display concepts, including baseline and Synthetic Vision System (SVS) concepts, were evaluated in the local area of Roanoke Virginia Airport, flying visual and instrument approach procedures. A total of 19 pilots, from 3 pilot groups reflecting the diverse piloting skills of the GA population, served as evaluation pilots. Multi-variable Discriminant Analysis was applied to three carefully selected and markedly different operating conditions with conventional instrumentation to provide an extension of traditional analysis methods as well as provide an assessment of the effectiveness of SVS displays to effectively transform IMC flight into VMC flight. C1 NASA, Langley Res Ctr, Hampton, VA 23665 USA. Raytheon, Hampton, VA USA. Lockheed Martin, Hampton, VA USA. RP Glaab, LJ (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. NR 19 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0377-6 J9 DIGIT AVION SYST CON PY 2006 BP 714 EP 727 PG 14 WC Automation & Control Systems; Engineering, Aerospace; Computer Science, Artificial Intelligence; Telecommunications SC Automation & Control Systems; Engineering; Computer Science; Telecommunications GA BGB18 UT WOS:000245889700072 ER PT B AU Hayhurst, KJ Maddalon, JM Miner, PS DeWalt, MP McCormick, GF AF Hayhurst, Kelly J. Maddalon, Jeffrey M. Miner, Paul S. DeWalt, Michad P. McCormick, G. Frank GP IEEE TI Unmanned aircraft hazards and their implications for regulation SO 2006 IEEE/AIAA 25TH DIGITAL AVIONICS SYSTEMS CONFERENCE, VOLS 1- 3 SE Digital Avionics Systems Conference LA English DT Proceedings Paper CT IEEE/AIAA 25th Digital Avionics Systerms Conference CY OCT 15-18, 2006 CL Portsmouth, OR SP IEEE, AIAA AB Use of unmanned aircraft systems (UASs) has been characterized as the next great step forward in the evolution of civil aviation. Indeed, UASs are in limited civil use in the United States today, and many believe that the time is rapidly approaching when they will move into the commercial marketplace, too, To make this a reality, a number of challenges must be overcome to develop the necessary regulatory framework for assuring safe operation of this special class of aircraft. This paper discusses some of what must be done to establish that framework. In particular, we examine hazards specific to the design, operation, and flight crew of UASs, and discuss implications of these hazards for existing policy and guidance. Understanding unique characteristics of UASs that pose new hazards is essential to developing a cogent argument, and the corresponding regulatory framework, for safely integrating these aircraft into civil airspace. C1 NASA, Langley Res Ctr, Hampton, VA 23665 USA. Certificat Serv Inc, Eastsound, WA USA. RP Hayhurst, KJ (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. NR 18 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0377-6 J9 DIGIT AVION SYST CON PY 2006 BP 847 EP 858 PG 12 WC Automation & Control Systems; Engineering, Aerospace; Computer Science, Artificial Intelligence; Telecommunications SC Automation & Control Systems; Engineering; Computer Science; Telecommunications GA BGB18 UT WOS:000245889700086 ER PT S AU Hwu, SU Loh, YC Sham, CC AF Hwu, Shian U. Loh, Yin-Chung Sham, Catherine C. GP IEEE TI Space station wireless local area network signal characteristics modeling and measurements SO 2006 IEEE/AIAA 25TH DIGITAL AVIONICS SYSTEMS CONFERENCE, VOLS 1- 3 SE IEEE-AIAA Digital Avionics Systems Conference LA English DT Proceedings Paper CT IEEE/AIAA 25th Digital Avionics Systerms Conference CY OCT 15-18, 2006 CL Portsmouth, OR SP IEEE, AIAA ID PROPAGATION AB This paper presents the signal characteristic analysis of the International Space Station 2.4 GHz Wireless Local Area Networks (WLANs). The test data indicate the Space Station RF environment is quite different from typical indoor environment. The empty Space Station modules may be regarded as oversized waveguides with very little propagation loss. The furnished Space Station modules are imperfect waveguides with many lossy materials presented. The propagation loss in both unfurnished and furnished module is less than in free space. It is observed that the propagation characteristics are significantly affected by the presence of the equipment and furniture inside the Space Station modules. The obtained results indicate the module geometry and interior furniture materials are the two important factors determining the propagation characteristics of the Space Station WLAN system. The analysis results from this paper are essential for Space Station WLAN access point placement and RF coverage performance determination. C1 Jacobs Engn, Houston, TX USA. NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Hwu, SU (reprint author), Jacobs Engn, Houston, TX USA. NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2155-7195 BN 978-1-4244-0377-6 J9 IEEEAAIA DIGIT AVION PY 2006 BP 950 EP 957 PG 8 WC Automation & Control Systems; Engineering, Aerospace; Computer Science, Artificial Intelligence; Telecommunications SC Automation & Control Systems; Engineering; Computer Science; Telecommunications GA BGB18 UT WOS:000245889700097 ER PT S AU Goodrich, KH Schutte, PC Flemisch, FO Williams, RA AF Goodrich, Kenneth H. Schutte, Paul C. Flemisch, Frank O. Williams, Ralph A. GP IEEE TI Application of the H-mode, a design and interaction concept for highly automated vehicles, to aircraft SO 2006 IEEE/AIAA 25TH DIGITAL AVIONICS SYSTEMS CONFERENCE, VOLS 1- 3 SE IEEE-AIAA Digital Avionics Systems Conference LA English DT Proceedings Paper CT IEEE/AIAA 25th Digital Avionics Systerms Conference CY OCT 15-18, 2006 CL Portsmouth, OR SP IEEE, AIAA AB Driven by increased safety, efficiency, and airspace capacity, automation is playing an increasing role in aircraft operations. As aircraft become increasingly able to autonomously respond to a range of situations with performance surpassing human operators, we are compelled to look for new methods that help us understand their use and guide their design using new forms of automation and interaction. We propose a novel design metaphor to aid the conceptualization, design, and operation of highly-automated aircraft. Design metaphors transfer meaning from common experiences to less familiar applications or functions. A notable example is the "Desktop metaphor" for manipulating files on a computer. This paper describes a metaphor for highly automated vehicles known as the H-metaphor and a specific embodiment of the metaphor known as the H-mode as applied to aircraft. The fundamentals of the H-metaphor are reviewed followed by an overview of an exploratory usability study investigating human-automation interaction issues for a simple H-mode implementation. The envisioned application of the H-mode concept to aircraft is then described as are two planned evaluations. C1 [Goodrich, Kenneth H.; Schutte, Paul C.] NASA, Langley Res Ctr, Hampton, VA 23665 USA. [Flemisch, Frank O.] DLR, Inst Transport Syst, Braunschweig, Germany. [Williams, Ralph A.] Analyt Mech Assoc, Hampton, VA 23666 USA. RP Goodrich, KH (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. NR 20 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2155-7195 BN 978-1-4244-0377-6 J9 IEEEAAIA DIGIT AVION PY 2006 BP 1018 EP + PG 3 WC Automation & Control Systems; Engineering, Aerospace; Computer Science, Artificial Intelligence; Telecommunications SC Automation & Control Systems; Engineering; Computer Science; Telecommunications GA BGB18 UT WOS:000245889700104 ER PT S AU Tso, KS Tai, AT Deng, YM Backes, PG AF Tso, Kam S. Tai, Ann T. Deng, Yong M. Backes, Paul G. GP IEEE TI Multiuser collaboration with networked mobile devices SO 2006 IEEE/AIAA 25TH DIGITAL AVIONICS SYSTEMS CONFERENCE, VOLS 1- 3 SE IEEE-AIAA Digital Avionics Systems Conference LA English DT Proceedings Paper CT IEEE/AIAA 25th Digital Avionics Systerms Conference CY OCT 15-18, 2006 CL Portsmouth, OR SP IEEE, AIAA AB This paper describes a multiuser collaboration infrastructure that enables multiple mission scientists to remotely and collaboratively interact with the visualization and planning software, using wireless networked personal digital assistants and other mobile devices. The infrastructure includes (1) human-computer interaction components to provide natural, fast, and accurate inputs, (2) a communications protocol to ensure reliable and efficient coordination of the input devices and host computers, (3) an application-independent middleware that maintains the states, sessions, and interactions of individual users of the software applications, and (4) an application programming interface to enable tight integration of applications and the middleware. The resulting technologies not only are applicable to NASA mission operations, but also useful in other situations such as design reviews, brainstorming sessions, and business meetings, as they can benefit from having the participants concurrently interact with the software applications (e.g., presentation applications and CAD design tools) to illustrate their ideas and provide inputs. C1 IA Tech Inc, Los Angeles, CA USA. Jet Propuls Lab, Pasadena, CA USA. RP Tso, KS (reprint author), IA Tech Inc, Los Angeles, CA USA. NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2155-7195 BN 978-1-4244-0377-6 J9 IEEEAAIA DIGIT AVION PY 2006 BP 1198 EP 1208 PG 11 WC Automation & Control Systems; Engineering, Aerospace; Computer Science, Artificial Intelligence; Telecommunications SC Automation & Control Systems; Engineering; Computer Science; Telecommunications GA BGB18 UT WOS:000245889700120 ER PT B AU Garrett, A Carnahan, B Muhdi, R Davis, J Dozier, G SanSoucie, MP Hull, PV Tinker, ML AF Garrett, Aaron Carnahan, Brian Muhdi, Rani Davis, Jerry Dozier, Gerry SanSoucie, Michael P. Hull, Patrick V. Tinker, Michael L. GP IEEE TI Evacuation planning via evolutionary computation SO 2006 IEEE CONGRESS ON EVOLUTIONARY COMPUTATION, VOLS 1-6 SE IEEE Congress on Evolutionary Computation LA English DT Proceedings Paper CT IEEE Congress on Evolutionary Computation CY JUL 16-21, 2006 CL Vancouver, CANADA SP IEEE AB According to the Life Safety Code (R), the geometry of a building, the location of exits, and the number of exits dictate the means of egress for all people occupying a building. In this paper we show how evolutionary computations in the form of Genetic Algorithms and Estimation of Distribution Algorithms are used to evolve the placement of exits in order to optimize overall evacuation time. In particular, a generational GA, a steady-state GA, and an elitist EDA are used to evolve the placement of exits for two practical design problems. The algorithms are evaluated in terms of success rate, number of function evaluations, and best fitness. For both problems, the steady-state GA outperformed the other algorithms in all evaluation categories. C1 [Garrett, Aaron; Dozier, Gerry] Auburn Univ, ACI Lab, Dept Comp Sci & Software Engn, Auburn, AL 36849 USA. [Carnahan, Brian; Muhdi, Rani; Davis, Jerry] Auburn Univ, Dept Ind & Syst Engn, Auburn, AL USA. [SanSoucie, Michael P.; Hull, Patrick V.; Tinker, Michael L.] NASA, Marshall Space Flight Ctr, Huntsville, AL USA. RP Garrett, A (reprint author), Auburn Univ, ACI Lab, Dept Comp Sci & Software Engn, Auburn, AL 36849 USA. NR 17 TC 3 Z9 3 U1 2 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-0-7803-9487-2 J9 IEEE C EVOL COMPUTAT PY 2006 BP 157 EP + DI 10.1109/CEC.2006.1688303 PG 2 WC Computer Science, Artificial Intelligence; Computer Science, Theory & Methods SC Computer Science GA BFY14 UT WOS:000245414200021 ER PT B AU Dozier, G Britt, W SanSoucie, MP Hull, PV Tinker, ML Unger, R Bancroft, S Moeller, T Rooney, D AF Dozier, Gerry Britt, Win SanSoucie, Michael P. Hull, Patrick V. Tinker, Michael L. Unger, Ron Bancroft, Steve Moeller, Trevor Rooney, Dan GP IEEE TI Evolving high-performance evolutionary computations for space vehicle design SO 2006 IEEE CONGRESS ON EVOLUTIONARY COMPUTATION, VOLS 1-6 SE IEEE Congress on Evolutionary Computation LA English DT Proceedings Paper CT IEEE Congress on Evolutionary Computation CY JUL 16-21, 2006 CL Vancouver, CANADA SP IEEE AB The Nuclear Electric Vehicle Optimization Toolset (NEVOT) optimizes the design of all major nuclear electric propulsion (NEP) vehicle subsystems for a defined mission within constraints and optimization parameters chosen by a user. The tool currently uses a number of evolutionary computations (ECs) for designing NEP vehicles. Since evaluating candidate vehicle designs is computationally expensive, it is important that a set of robust control parameters be discovered. In order to accomplish this, a metagenetic algorithm (meta-GA) was developed to discover control parameters for generational, steady-state, and steady-generational GAs as well as for particle swarm optimizers (PSOs) with ring, star, and random topologies. Our results show that the high-performance GAs are more efficient than the high-performance PSOs on a NASA Asteroid Mission problem. C1 [Dozier, Gerry; Britt, Win; Unger, Ron] Auburn Univ, Appl Comp Intelligence Lab, Auburn, AL 36849 USA. [SanSoucie, Michael P.; Hull, Patrick V.; Tinker, Michael L.] NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. [Bancroft, Steve] Arnold Engn Dev Ctr, Arnold, TN 37389 USA. [Moeller, Trevor; Rooney, Dan] Univ Tennessee, Inst Space, Tullahoma, TN 37388 USA. RP Dozier, G (reprint author), Auburn Univ, Appl Comp Intelligence Lab, Auburn, AL 36849 USA. EM gvdozier@eng.auburn.edu FU NASA-MSFC [NNMO4AA7OG]; NASA FX This research was partially funded a NASA-MSFC grant (NNMO4AA7OG). The authors would like to thank NASA for their support. NR 21 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-0-7803-9487-2 J9 IEEE C EVOL COMPUTAT PY 2006 BP 2186 EP + PG 3 WC Computer Science, Artificial Intelligence; Computer Science, Theory & Methods SC Computer Science GA BFY14 UT WOS:000245414203071 ER PT S AU Angrisani, L D'Arco, M Greenhall, C Lo Moriello, RS AF Angrisani, Leopoldo D'Arco, Mauro Greenhall, Charles Lo Moriello, Rosario Schiano GP IEEE TI Real-time phase noise meter based on a digital signal processor SO 2006 IEEE INSTRUMENTATION AND MEASUREMENT TECHNOLOGY CONFERENCE PROCEEDINGS, VOLS 1-5 SE IEEE Instrumentation and Measurement Technology Conference LA English DT Proceedings Paper CT 23rd IEEE Instrumentation and Measurement Technology Conference CY APR 24-27, 2006 CL Sorrento, ITALY SP IEEE Instrumentat & Measurement Soc DE phase noise measurement; digital signal processor; data acquisition board; power spectrum evaluation; quadrature demodulation AB A digital signal-processing meter for phase noise measurement on sinusoidal signal s is dealt with. It enlists a special hardware architecture, made up of a core digital signal processor connected to a data acquisition board, and takes advantage of a quadrature demodulation-based measurement scheme, already proposed by the authors. Thanks to an efficient measurement process and an optimied implementation of its fundamental stages, the proposed meter succeeds in exploiting all hardware resources in such an effective way as to gain high performance and real-time operation. For input frequencies up to some hundreds of kilohertz the meter is capable both of updating phase noise power spectrum while seamlessly capturing the analyed signal into its memory, and granting as good frequency resolution as few units of hertz After a brief outline of the aforementioned measurement scheme, key features of the adopted digital signal processor are highlighted. Hardware architecture, measurement process, and software strategies peculiar to the proposed meter are then described in detail. At the end, some results of experimental tests, carried out on sinusoidal signals provided by function generators and arbitrary waveform generators, give evidence of the meters reliability and efficacy. C1 [Angrisani, Leopoldo] Univ Naples Federico II, Dipartimento Informat & Sistemist, Via Claudio 21, I-80125 Naples, Italy. [D'Arco, Mauro; Lo Moriello, Rosario Schiano] Univ Naples Federico II, Dipartimento Ingn Elettr, I-80125 Naples, Italy. [Greenhall, Charles] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Angrisani, L (reprint author), Univ Naples Federico II, Dipartimento Informat & Sistemist, Via Claudio 21, I-80125 Naples, Italy. EM angrisan@unina.it; darco@unina.it; cgreenhall@jpl.nasa.gov; rschiano@unina.it OI D'Arco, Mauro/0000-0003-1641-8359 NR 12 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1091-5281 BN 978-0-7803-9359-2 J9 IEEE IMTC P PY 2006 BP 1850 EP + DI 10.1109/IMTC.2006.328279 PG 2 WC Instruments & Instrumentation SC Instruments & Instrumentation GA BFS10 UT WOS:000244176703075 ER PT S AU Case, JT Hepburn, FL Zoughi, R AF Case, J. T. Hepburn, F. L. Zoughi, R. GP IEEE TI Inspection of spray on foam insulation (SOFI) using microwave and millimeter wave synthetic aperture focusing and holography SO 2006 IEEE INSTRUMENTATION AND MEASUREMENT TECHNOLOGY CONFERENCE PROCEEDINGS, VOLS 1-5 SE IEEE Instrumentation and Measurement Technology Conference LA English DT Proceedings Paper CT 23rd IEEE Instrumentation and Measurement Technology Conference CY APR 24-27, 2006 CL Sorrento, ITALY SP IEEE Instrumentat & Measurement Soc DE microwave; millimeter wave; nondestructive testing; foam; SOFI AB The Space Shuttle Columbia's catastrophic failure is thought to have been caused by a dislodged piece of external tank spray on foam insulation (SOFI) striking and significantly! damaging the left wing of the orbiter, which may have been due to a flawed section of SOFI. Microwave and millimeter wave nondestructive evaluation (NDE) methods have shown great potential detecting anomalies in SOFI such as small air voids using a horn and lens in a (real)focused configuration. Synthetic focusing methods may also be used to detect air voids in SOFI and may additionally offer the ability to locate the defect in three dimensions. To this end, two different methods were investigated; namely, frequency, domain synthetic aperture focusing technique (FD-SAFT) and wide-band microwave holography. To illustrate the performance of these methods they were applied to two different SOFI samples. The results of these investigations demonstrate the capabilities of these methods for SOFI inspection. C1 [Case, J. T.; Zoughi, R.] Univ Missouri, AMNTL, Dept Elect & Comp Engn, Rolla, MO 65409 USA. [Hepburn, F. L.] NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Case, JT (reprint author), Univ Missouri, AMNTL, Dept Elect & Comp Engn, Rolla, MO 65409 USA. EM zoughir@umr.edu FU [NASA Marshall Space Flight Center through Cooperative Agreement] FX Funding for this work was provided by the NASA Marshall Space Flight Center through a Cooperative Agreement. NR 8 TC 7 Z9 7 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1091-5281 BN 978-0-7803-9359-2 J9 IEEE IMTC P PY 2006 BP 2148 EP + DI 10.1109/IMTC.2006.328527 PG 3 WC Instruments & Instrumentation SC Instruments & Instrumentation GA BFS10 UT WOS:000244176704041 ER PT S AU Le Moigne, J Cole-Rhodes, A Eastman, R Jain, P Joshua, A Meinarsadeghi, N Mount, D Netanyahu, N Morisette, J Uko-Ozoro, E AF Le Moigne, Jacqueline Cole-Rhodes, Arlene Eastman, Roger Jain, Peyush Joshua, Aimee Meinarsadeghi, Nargess Mount, David Netanyahu, Nathan Morisette, Jeffrey Uko-Ozoro, Ezinne GP IEEE TI Image registration and fusion studies for the integration of multiple remote sensing data SO 2006 IEEE INTERNATIONAL CONFERENCE ON ACOUSTICS, SPEECH, AND SIGNAL PROCESSING, VOL V, PROCEEDINGS: AUDIO AND ELECTROACOUSTICS, MULTIMEDIA SIGNAL PROCESSING, MACHINE LEARNING FOR SIGNAL PROCESSING SPECIAL SESSIONS SE International Conference on Acoustics Speech and Signal Processing ICASSP LA English DT Proceedings Paper CT 31st IEEE International Conference on Acoustics, Speech and Signal Processing CY MAY 14-19, 2006 CL Toulouse, FRANCE SP IEEE Signal Proc Soc ID FEATURES AB The future of remote sensing will see the development of spacecraft formations, and with this development will come a number of complex challenges such as maintaining precise relative position and specified attitudes. At the same time, there will be increasing needs to understand planetary system processes and build accurate prediction models. One essential technology to accomplish these goals is the integration of multiple source data. For this integration, image registration and fusion represent the first steps and need to be performed with very high accuracy. In this paper, we describe studies performed in both image registration and fusion, including a modular framework that was built to describe registration algorithms, a web-based image registration toolbox, and the comparison of several image fusion techniques using data from the EO-1/ALI and Hyperion sensors. C1 [Le Moigne, Jacqueline; Jain, Peyush; Joshua, Aimee; Meinarsadeghi, Nargess] NASA, Goddard Space Flight Ctr, Adv Architectures & Automat Branch, Code 588, Greenbelt, MD 20771 USA. [Cole-Rhodes, Arlene] Morgan State Univ, Baltimore, MD 21251 USA. [Eastman, Roger] Loyola Coll, Baltimore, MD 21210 USA. [Mount, David; Netanyahu, Nathan] Univ Maryland, College Pk, MD 20742 USA. [Netanyahu, Nathan] Bar Ilan Univ, IL-52900 Ramat Gan, Israel. [Morisette, Jeffrey; Uko-Ozoro, Ezinne] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Le Moigne, J (reprint author), NASA, Goddard Space Flight Ctr, Adv Architectures & Automat Branch, Code 588, Greenbelt, MD 20771 USA. EM Jacqueline.LeMoigne@nasa.gov NR 12 TC 2 Z9 2 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1520-6149 J9 INT CONF ACOUST SPEE PY 2006 BP 1189 EP + PG 2 WC Acoustics; Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic; Imaging Science & Photographic Technology SC Acoustics; Computer Science; Engineering; Imaging Science & Photographic Technology GA BFW40 UT WOS:000245100500298 ER PT S AU Hieronymus, J Aist, G Dowding, J AF Hieronymus, James Aist, Greg Dowding, John GP IEEE TI Open microphone speech understanding: Correct discrimination of in domain speech SO 2006 IEEE International Conference on Acoustics, Speech and Signal Processing, Vols 1-13 SE International Conference on Acoustics Speech and Signal Processing (ICASSP) LA English DT Proceedings Paper CT 31st IEEE International Conference on Acoustics, Speech and Signal Processing CY MAY 14-19, 2006 CL Toulouse, FRANCE SP IEEE Signal Proc Soc AB An ideal spoken dialogue system listens continually and determines which utterances were spoken to it, understands them and responds appropriately while ignoring the rest. This paper outlines a simple method for achieving this goal which involves trading a slightly higher false rejection rate of in domain utterances for a higher correct rejection rate of Out of Domain (OOD) utterances. The system recognizes semantic entities specified by a unification grammar which is specialized by Explanation Based Learning (EBL), so that it only uses rules which are seen in the training data. The resulting grammar has probabilities assigned to each construct so that overgeneralizations are not a problem. The resulting system only recognizes utterances which reduce to a valid logical form which has meaning for the system and rejects the rest. A class N-gram grammar has been trained on the same training data. This system gives good recognition performance and offers good out of domain discrimination when combined with the semantic analysis. The resulting systems were tested on a Space Station Robot Dialogue Speech Database and a subset of the OGI conversational speech database. Both systems run in real time on a PC laptop and the present performance allows continuous listening with an acceptably low false acceptance rate. This type of open microphone system has been used in the Clarissa procedure reading and navigation spoken dialogue system which is being tested on the International Space Station. C1 NASA, Ames Res Ctr, RIACS, Moffett Field, CA 94305 USA. RP Hieronymus, J (reprint author), NASA, Ames Res Ctr, RIACS, Code T1, Moffett Field, CA 94305 USA. NR 19 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1520-6149 BN 978-1-4244-0468-1 J9 INT CONF ACOUST SPEE PY 2006 BP 65 EP 68 PG 4 WC Acoustics; Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic; Imaging Science & Photographic Technology SC Acoustics; Computer Science; Engineering; Imaging Science & Photographic Technology GA BFZ22 UT WOS:000245559900017 ER PT S AU Scargle, JD Quweider, MK AF Scargle, Jeffrey D. Quweider, Mahmoud K. GP IEEE TI Edge detection using dynamic optimal partitioning SO 2006 IEEE International Conference on Acoustics, Speech and Signal Processing, Vols 1-13 SE International Conference on Acoustics Speech and Signal Processing (ICASSP) LA English DT Proceedings Paper CT 31st IEEE International Conference on Acoustics, Speech and Signal Processing CY MAY 14-19, 2006 CL Toulouse, FRANCE SP IEEE Signal Proc Soc AB In this paper, a new edge detector (boundary extractor) is proposed based on finding major change points in a local one-dimensional window of the image intensity values of the rows or columns. The approach amounts to separating the pixels in the window into sets or regions of constant intensities with the edge pixels providing transition points. The edge points are found based on partitioning the interval in an optimal way using dynamic programming with an appropriate cost function. Different cost functions are introduced for the algorithm with simulation results that show the detector's effectiveness even in the presence of noise. C1 NASA, Ames Res Ctr, Div Space Sci, Milpitas, CA 95035 USA. RP Scargle, JD (reprint author), NASA, Ames Res Ctr, Div Space Sci, Milpitas, CA 95035 USA. NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1520-6149 BN 978-1-4244-0468-1 J9 INT CONF ACOUST SPEE PY 2006 BP 1953 EP 1956 PG 4 WC Acoustics; Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic; Imaging Science & Photographic Technology SC Acoustics; Computer Science; Engineering; Imaging Science & Photographic Technology GA BFZ22 UT WOS:000245559902135 ER PT S AU Le Moigne, J Cole-Rhodes, A Eastman, R Jain, P Joshua, A Memarsadeghi, N Mount, D Netanyahu, N Morisette, J Uko-Ozoro, E AF Le Moigne, Jacqueline Cole-Rhodes, Arlene Eastman, Roger Jain, Peyush Joshua, Aimee Memarsadeghi, Nargess Mount, David Netanyahu, Nathan Morisette, Jeffrey Uko-Ozoro, Ezinne GP IEEE TI Image registration and fusion studies for the integration of multiple remote sensing data SO 2006 IEEE International Conference on Acoustics, Speech and Signal Processing, Vols 1-13 SE International Conference on Acoustics Speech and Signal Processing (ICASSP) LA English DT Proceedings Paper CT 31st IEEE International Conference on Acoustics, Speech and Signal Processing CY MAY 14-19, 2006 CL Toulouse, FRANCE SP IEEE Signal Proc Soc ID FEATURES AB The future of remote sensing will see the development of spacecraft formations, and with this development will come a number of complex challenges such as maintaining precise relative position and specified attitudes. At the same time, there will be increasing needs to understand planetary system processes and build accurate prediction models. One essential technology to accomplish these goals is the integration of multiple source data. For this integration, image registration and fusion represent the first steps and need to be performed with very high accuracy. In this paper, we describe studies performed in both image registration and fusion, including a modular framework that was built to describe registration algorithms, a web-based image registration toolbox, and the comparison of several image fusion techniques using data from the EO-1/ALI and Hyperion sensors. C1 NASA, Goddard Space Flight Ctr, Adv Architectures & Automat Branch, Greenbelt, MD 20771 USA. RP Le Moigne, J (reprint author), NASA, Goddard Space Flight Ctr, Adv Architectures & Automat Branch, Code 558, Greenbelt, MD 20771 USA. NR 12 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1520-6149 BN 978-1-4244-0468-1 J9 INT CONF ACOUST SPEE PY 2006 BP 6047 EP 6050 PG 4 WC Acoustics; Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic; Imaging Science & Photographic Technology SC Acoustics; Computer Science; Engineering; Imaging Science & Photographic Technology GA BFZ22 UT WOS:000245559906215 ER PT S AU Perrins, E Schober, R Rice, M Simon, M AF Perrins, Erik Schober, Robert Rice, Michael Simon, Marvin GP IEEE TI Shaped-Offset QPSK with Multiple-Bit Differential Detection SO 2006 IEEE INTERNATIONAL CONFERENCE ON COMMUNICATIONS, VOLS 1-12 SE IEEE International Conference on Communications LA English DT Proceedings Paper CT IEEE International Conference on Communications (ICC 2006) CY JUN 11-15, 2006 CL Istanbul, TURKEY SP IEEE AB We consider multiple-bit differential detection (MBDD) of differentially encoded shaped-offset quadrature phase-shift keying (SOQPSK), a highly bandwidth-efficient and popular constant-envelope modulation. We propose two MBDD schemes that are based on a recent continuous phase modulation (CPM) interpretation of SOQPSK. We show that the performance of these MBDD schemes approaches that of coherent detection as the multiple-bit observation window N increases. The first scheme uses a detection window that spans the full N-bit observation window (F-MBDD) and is shown to require very large values of N to approach the performance of coherent detection. This presents a practical problem since the complexity of MBDD grows exponentially with N. The second scheme is an improved version (I-MBDD) with a detection window that is shortened to N -2 bit intervals and requires more modest values of N for high performance. These performance characteristics are identified via a detailed performance analysis, which provides asymptotic formulas for the probability of bit error that are confirmed with computer simulations. C1 [Perrins, Erik] Univ Kansas, Dept Elect Engn & Comp Sci, Lawrence, KS 66045 USA. [Schober, Robert] Univ British Columbia, Dept Elect & Comp Engn, Vancouver, BC V5Z 1M9, Canada. [Rice, Michael] Brigham Young Univ, Dept Elect & Comp Engn, Provo, UT 84602 USA. [Simon, Marvin] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Perrins, E (reprint author), Univ Kansas, Dept Elect Engn & Comp Sci, Lawrence, KS 66045 USA. EM esp@ieee.org; rschober@ece.ubc.ca; mdr@ee.byu.edu; marvin.k.simon@jpl.nasa.gov NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1550-3607 BN 978-1-4244-0354-7 J9 IEEE ICC PY 2006 BP 1212 EP 1218 PG 7 WC Computer Science, Hardware & Architecture; Engineering, Electrical & Electronic; Telecommunications SC Computer Science; Engineering; Telecommunications GA BTI69 UT WOS:000287032701053 ER PT S AU Berenji, HR AF Berenji, Hamid R. GP IEEE TI Case-based reasoning for fault diagnosis and prognosis SO 2006 IEEE INTERNATIONAL CONFERENCE ON FUZZY SYSTEMS, VOLS 1-5 SE IEEE International Conference on Fuzzy Systems LA English DT Proceedings Paper CT IEEE International Conference on Fuzzy Systems CY JUL 16-21, 2006 CL Vancouver, CANADA SP IEEE AB Casi-Based Reasoning (CBR) is a mature technology used in help-desk customer services. To implement this technology to the diagnosis and prognosis of dynamic systems, many important factors must be considered. This paper reports on our development of a Matlab system for Multi-Agent Fault Diagnosis for Predictive Health Monitoring. In particular, we apply this technology to the SIMULINK simulation of a dynamic chiller system. Our system can detect single component faults and also multiple component faults in the system and advise on how to fix the problem using case based reasoning. C1 NASA, Intelligent Inference Syst Corp, Moffett Field, CA 94035 USA. RP Berenji, HR (reprint author), NASA, Intelligent Inference Syst Corp, Res Pk, Moffett Field, CA 94035 USA. EM berenji@iiscorp.com NR 7 TC 3 Z9 4 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1098-7584 BN 978-0-7803-9488-9 J9 IEEE INT CONF FUZZY PY 2006 BP 1316 EP 1321 DI 10.1109/FUZZY.2006.1681880 PG 6 WC Computer Science, Artificial Intelligence SC Computer Science GA BFR68 UT WOS:000244063602052 ER PT S AU Berenji, HR Wang, Y AF Berenji, Hamid R. Wang, Yan GP IEEE TI Wavelet neural networks for fault diagnosis and prognosis SO 2006 IEEE INTERNATIONAL CONFERENCE ON FUZZY SYSTEMS, VOLS 1-5 SE IEEE International Conference on Fuzzy Systems LA English DT Proceedings Paper CT IEEE International Conference on Fuzzy Systems CY JUL 16-21, 2006 CL Vancouver, CANADA SP IEEE AB Wavelet Neural Networks have been developed for fault diagnosis and prognosis with unique capabilities in addressing identification and classification problems. A fault diagnostic and prognostic system is presented by using Wavelet Neural Networks and Dynamic Wavelet Neural Networks. We used a Matlab Simulink model of a chiller system and applied the Wavelet Neural Network to detect and recover sensor errors. It has been shown that this method gains good performance in sensor fault diagnostics. C1 [Berenji, Hamid R.; Wang, Yan] NASA, Intelligent Inference Syst Corp, Res Pk, Moffett Field, CA 94035 USA. RP Berenji, HR (reprint author), NASA, Intelligent Inference Syst Corp, Res Pk, Moffett Field, CA 94035 USA. EM berenji@iiscorp.com; ywang@iiscorp.com FU NASA Ames Research Center [NNA05BE71C] FX This work is supported by the NASA Ames Research Center under Grant NNA05BE71C NR 17 TC 5 Z9 6 U1 0 U2 4 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1098-7584 BN 978-0-7803-9488-9 J9 IEEE INT CONF FUZZY PY 2006 BP 1334 EP + DI 10.1109/FUZZY.2006.1681883 PG 2 WC Computer Science, Artificial Intelligence SC Computer Science GA BFR68 UT WOS:000244063602055 ER PT S AU Castano, A Fukunaga, A Biesiadecki, J Neakrase, L Whelley, P Greeley, R Lemmon, M Castano, R Chien, S AF Castano, Andres Fukunaga, Alex Biesiadecki, Jeffrey Neakrase, Lynn Whelley, Patrick Greeley, Ronald Lemmon, Mark Castano, Rebecca Chien, Steve GP IEEE TI Autonomous detection of dust devils and clouds on mars SO 2006 IEEE INTERNATIONAL CONFERENCE ON IMAGE PROCESSING, ICIP 2006, PROCEEDINGS SE IEEE International Conference on Image Processing ICIP LA English DT Proceedings Paper CT IEEE International Conference on Image Processing (ICIP 2006) CY OCT 08-11, 2006 CL Atlanta, GA SP IEEE DE image analysis; object detection; extraterrestrial phenomena AB Acquisition of science in space applications is shifting from teleoperated gathering to an automated on-board analysis with improvements in the use of memory, CPU, bandwidth and data quality. In this paper, we describe algorithms to autonomously detect dust devils and clouds from a rover and summarize the results. The algorithms meet high hit-to-miss ratios and satisfy strict resouce constraints. Both detectors have been uploaded to the Mars Exploration Rovers (MER). These are the first autonomous science processes in the rovers. C1 [Castano, Andres; Fukunaga, Alex; Biesiadecki, Jeffrey; Castano, Rebecca; Chien, Steve] Jet Propuls Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Neakrase, Lynn; Whelley, Patrick; Greeley, Ronald; Lemmon, Mark] Arizona State Univ, Dept Geol Sci, Tempe, AZ 85287 USA. RP Castano, A (reprint author), Jet Propuls Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RI Whelley, Patrick/B-9560-2012; OI Whelley, Patrick/0000-0003-3266-9772; Lemmon, Mark/0000-0002-4504-5136 FU NASA; Software Intelligent Systems and Modeling (SISM) under the OASIS; Mars Technology program (MTP) under the MER On-board Science task; New Millennium Program (NMP) under the MER Infusion Studies task FX This work was supported by NASA as follows: algorithm prototyping and testing by the Software Intelligent systems and Modeling (SISM) program under the OASIS task,flight code integration by the Mars Technology program (MTP) under the MER On-board Science task and,MER testing and operation by the New Millennium Program (NMP) under the MER Infusion Studies task. NR 3 TC 1 Z9 1 U1 0 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-4880 BN 978-1-4244-0481-0 J9 IEEE IMAGE PROC PY 2006 BP 2765 EP + DI 10.1109/ICIP.2006.313120 PG 2 WC Computer Science, Artificial Intelligence; Computer Science, Information Systems; Computer Science, Software Engineering; Imaging Science & Photographic Technology; Radiology, Nuclear Medicine & Medical Imaging SC Computer Science; Imaging Science & Photographic Technology; Radiology, Nuclear Medicine & Medical Imaging GA BGA25 UT WOS:000245768501310 ER PT S AU Stein, AN Huertas, A Matthies, L AF Stein, Andrew N. Huertas, Andres Matthies, Larry GP IEEE TI Attenuating stereo pixel-locking via affine window adaptation SO 2006 IEEE INTERNATIONAL CONFERENCE ON ROBOTICS AND AUTOMATION (ICRA), VOLS 1-10 SE IEEE International Conference on Robotics and Automation ICRA LA English DT Proceedings Paper CT IEEE International Conference on Robotics and Automation (ICRA) CY MAY 15-19, 2006 CL Orlando, FL SP IEEE AB For real-time stereo vision systems, the standard method for estimating sub-pixel stereo disparity given an initial integer disparity map involves fitting parabolas to a matching cost function aggregated over rectangular windows. This results in a phenomenon known as pixel-locking, which produces artificially-peaked histograms of sub-pixel disparity. These peaks correspond to the introduction of erroneous ripples or waves in the 3D reconstruction of truly flat surfaces. Since stereo vision is a common input modality for autonomous vehicles, these inaccuracies can pose a problem for safe, reliable navigation. This paper proposes a new method for sub-pixel stereo disparity estimation, based on ideas from Lucas-Kanade tracking and optical flow, which substantially reduces the pixel-locking effect. In addition, it has the ability to correct much larger initial disparity errors than previous approaches and is more general as it applies not only to the ground plane. We demonstrate the method on synthetic imagery as well as real stereo data from an autonomous outdoor vehicle. C1 [Stein, Andrew N.] Carnegie Mellon Univ, Inst Robot, Pittsburgh, PA 15213 USA. [Huertas, Andres; Matthies, Larry] Jet Prop Lab, Comp Vis Grp, Pasadena, CA USA. RP Stein, AN (reprint author), Carnegie Mellon Univ, Inst Robot, Pittsburgh, PA 15213 USA. EM anstein@cmu.edu; Andres.Huertas@jpl.nasa.gov; Larry.Matthies@jpl.nasa.gov NR 20 TC 16 Z9 16 U1 0 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1050-4729 BN 0-7803-9505-0 J9 IEEE INT CONF ROBOT PY 2006 BP 914 EP 921 DI 10.1109/ROBOT.2006.1641826 PG 8 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Engineering, Mechanical; Robotics SC Automation & Control Systems; Computer Science; Engineering; Robotics GA BFB71 UT WOS:000240886902003 ER PT S AU Angelova, A Matthies, L Helmick, D Sibley, G Perona, P AF Angelova, Anelia Matthies, Larry Helmick, Daniel Sibley, Gabe Perona, Pietro GP IEEE TI Learning to predict slip for ground robots SO 2006 IEEE INTERNATIONAL CONFERENCE ON ROBOTICS AND AUTOMATION (ICRA), VOLS 1-10 SE IEEE International Conference on Robotics and Automation ICRA LA English DT Proceedings Paper CT IEEE International Conference on Robotics and Automation (ICRA) CY MAY 15-19, 2006 CL Orlando, FL SP IEEE AB In this paper we predict the amount of slip an exploration rover would experience using stereo imagery by learning from previous examples of traversing similar terrain. To do that, the information of terrain appearance and geometry regarding some location is correlated to the slip measured by the rover while this location is being traversed. This relationship is learned from previous experience, so slip can be predicted later at a distance from visual information only. The advantages of the approach are: 1) learning from examples allows the system to adapt to unknown terrains rather than using fixed heuristics or predefined rules; 2) the feedback about the observed slip is received from the vehicle's own sensors which can fully automate the process; 3) learning slip from previous experience can replace complex mechanical modeling of vehicle or terrain, which is time consuming and not necessarily feasible. Predicting slip is motivated by the need to assess the risk of getting trapped before entering a particular terrain. For example, a planning algorithm can utilize slip information by taking into consideration that a slippery terrain is costly or hazardous to traverse. A generic nonlinear regression framework is proposed in which the terrain type is determined from appearance and then a nonlinear model of slip is learned for a particular terrain type. In this paper we focus only on the latter problem and provide slip learning and prediction results for terrain types, such as soil, sand, gravel, and asphalt. The slip prediction error achieved is about 15% which is comparable to the measurement errors for slip itself. C1 [Angelova, Anelia] CALTECH, Dept Comp Sci, Pasadena, CA 91125 USA. [Matthies, Larry; Helmick, Daniel; Sibley, Gabe] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. [Perona, Pietro] CALTECH, Dept Elect Engn, Pasadena, CA 91125 USA. RP Angelova, A (reprint author), CALTECH, Dept Comp Sci, Pasadena, CA 91125 USA. EM anelia@vision.caltech.edu; lhm@jpl.nasa.gov; dhelmick@jpl.nasa.gov; gsibley@jpl.nasa.gov; perona@vision.caltech.edu FU NASA Mars Technology Program FX This research is funded by the NASA Mars Technology Program. Thanks also to the JPL LAGR team for giving us access to the LAGR vehicle, to Andrew Howard, Steve Goldberg, Lee Magnone, and Nathan Koenig for helping us with the data collection, to Max Bajracharya for reviewing the paper and providing helpful comments and to Randy Lindemann and Garett Sohl for discussions NR 23 TC 16 Z9 16 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1050-4729 BN 0-7803-9505-0 J9 IEEE INT CONF ROBOT PY 2006 BP 3324 EP + DI 10.1109/ROBOT.2006.1642209 PG 2 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Engineering, Mechanical; Robotics SC Automation & Control Systems; Computer Science; Engineering; Robotics GA BFB71 UT WOS:000240886907026 ER PT S AU Anderson, G Sheesley, C Tolson, J Wilson, E Tunstel, E AF Anderson, Gary Sheesley, Chris Tolson, Jay Wilson, Edmond Tunstel, Edward GP IEEE TI A mobile robot system for remote measurements of ammonia vapor in the atmosphere SO 2006 IEEE INTERNATIONAL CONFERENCE ON SYSTEMS, MAN, AND CYBERNETICS, VOLS 1-6, PROCEEDINGS SE IEEE International Conference on Systems Man and Cybernetics Conference Proceedings LA English DT Proceedings Paper CT IEEE International Conference on Systems, Man and Cybernetics CY OCT 08-11, 2006 CL Taipei, TAIWAN SP IEEE Syst, Man & Cybernet Soc, Minist Educ, Natl Sci Council, Natl Taipei Univ Technol, Natl Chiao Tung Univ ID MARS; SURFACE; SOIL AB In recent years there has been growing evidence that Mars once had a warm, wet environment that was capable of supporting life. This leads to questions as to whether life ever arose on the planet. Space agencies are actively supporting projects to answer this question. As part of that effort, this paper proposes a robotic system to rapidly scan large areas of the Martian surface for specific biogenic gases in the atmosphere. The long-term goal of the project is to develop a system that can locate local emissions of water vapor and biogases on Mars. The paper presents preliminary proof of concept experiments for a practical robotic measurement system to search for biogenic gases on Mars. In this work, an open path spectrometer to measure the biogenic gas ammonia was developed and deployed on a rover. Initial tests in an outdoor setting indicate that the system is effective in measuring ammonia. Difficulties in taking measurements outdoors include compensating for wind gusts and changes in ambient lighting. The paper proposes improvements in the current system that will compensate for current limitations and allow measurements to be taken over longer distances. C1 [Anderson, Gary] Univ Arkansas, Dept Appl Sci, Little Rock, AR 72204 USA. [Sheesley, Chris; Tolson, Jay] Univ Arkansas Little Rock, Appl Sci, Little Rock, AR 72204 USA. [Wilson, Edmond] Harding Univ, Dept Chem, Searcy, AR 72149 USA. [Tunstel, Edward] Jet Prop Lab, Pasadena, CA 91101 USA. RP Anderson, G (reprint author), Univ Arkansas, Dept Appl Sci, Little Rock, AR 72204 USA. EM granderson@ualr.edu; cpsheesley@ualr.edu; jxtolson@ualr.edu; wilson@harding.edu; tunstcl@robotics.jpl.nasa.gov NR 20 TC 4 Z9 4 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1062-922X BN 978-1-4244-0099-7 J9 IEEE SYS MAN CYBERN PY 2006 BP 241 EP + DI 10.1109/ICSMC.2006.384389 PG 3 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Computer Science, Cybernetics SC Automation & Control Systems; Computer Science GA BGK85 UT WOS:000248078500041 ER PT S AU Callantine, TJ AF Callantine, Todd J. GP IEEE TI Computational Modeling of dynamic planning in air traffic management SO 2006 IEEE INTERNATIONAL CONFERENCE ON SYSTEMS, MAN, AND CYBERNETICS, VOLS 1-6, PROCEEDINGS SE IEEE INTERNATIONAL CONFERENCE ON SYSTEMS, MAN, AND CYBERNETICS, CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT IEEE International Conference on Systems, Man and Cybernetics CY OCT 08-11, 2006 CL Taipei, TAIWAN SP IEEE Syst, Man & Cybernet Soc, Minist Educ, Natl Sci Council, Natl Taipei Univ Technol, Natl Chiao Tung Univ AB This paper describes a computational model of the air traffic management worksystem with current-day control techniques. The model simulates a dynamic planning process in which plans for issuing instructions to aircraft are adapted as improved information about the traffic situation becomes available. The paper presents a fast-time simulation evaluation with two air traffic controller agents controlling traffic in terminal-area arrival sectors. The results indicate that agents with dynamic planning capabilities exceed the performance of previously developed reactive agents. C1 San Jose State Univ, NASA, Ames Res Ctr, Human Syst Integrat Div, Moffett Field, CA 94035 USA. RP Callantine, TJ (reprint author), San Jose State Univ, NASA, Ames Res Ctr, Human Syst Integrat Div, Moffett Field, CA 94035 USA. EM tcallantine@mail.arc.nasa.gov NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1062-922X BN 978-1-4244-0099-7 J9 IEEE SYS MAN CYBERN PY 2006 BP 377 EP 382 DI 10.1109/ICSMC.2006.384411 PG 6 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Computer Science, Cybernetics SC Automation & Control Systems; Computer Science GA BGK85 UT WOS:000248078500063 ER PT S AU Feng, H AF Feng Hsu GP IEEE TI System importance measures using MCS with extended saphire applications SO 2006 IEEE INTERNATIONAL CONFERENCE ON SYSTEMS, MAN, AND CYBERNETICS, VOLS 1-6, PROCEEDINGS SE IEEE INTERNATIONAL CONFERENCE ON SYSTEMS, MAN, AND CYBERNETICS, CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT IEEE International Conference on Systems, Man and Cybernetics CY OCT 08-11, 2006 CL Taipei, TAIWAN SP IEEE Syst, Man & Cybernet Soc, Minist Educ, Natl Sci Council, Natl Taipei Univ Technol, Natl Chiao Tung Univ ID JOINT RELIABILITY-IMPORTANCE AB In order to address some technical challenges raised in the Space Shuttle PRA development, we introduce in this paper, a definition of Group level Importance Measure (GIM) to resolve the issue of risk ranking for mission phase, system (or element) within various level of the integrated shuttle PRA model. The GIM measures defined here are extensions of Fussel-Vesely (FV) type importances, and can also be extended to calculate other conventional type of importance measures, particularly at the Gate importance level within a coherent system fault tree model. Algorithms are also developed for extended SAPHIRE [1, C. Smith, T. Wood, 1996] implementations. Examples are given to show that the GIMs can be obtained for every level of contributors modeled in a PRA. Furthermore, these importances can be easily obtained and organized based on a top down hierarchy to show the safety significance of general contributors to specific category of mission risk profiles. Such measure can be easily used to produce PRA risk ranking at all level of details, such as by phase, element, sequence bins, failure type or any combinations of specific group of event type and failure mode. In the development of the underlying GIM importance measures, a complete set of extended mathematic functional relationships among the most commonly used importance measures are also derived and presented in the first section of this paper for the applications of PRA practitioners 12, F. Hsu et al., 2002]. RP Feng, H (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM Feng.Hsu@NASA.GOV NR 19 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1062-922X BN 978-1-4244-0099-7 J9 IEEE SYS MAN CYBERN PY 2006 BP 1884 EP 1890 PG 7 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Computer Science, Cybernetics SC Automation & Control Systems; Computer Science GA BGK85 UT WOS:000248078502017 ER PT S AU Fong, T Scholtz, J Shah, JA Fluckiger, L Kunz, C Lees, D Schreiner, J Siegel, M Hiatt, LM Nourbakhsh, I Simmons, R Ambrose, R Burridge, R Antonishek, B Bugajska, M Schultz, A Trafton, JG AF Fong, Terrence Scholtz, Jean Shah, Julie A. Flueckiger, Lorenzo Kunz, Clayton Lees, David Schreiner, John Siegel, Michael Hiatt, Laura M. Nourbakhsh, Illah Simmons, Reid Ambrose, Robert Burridge, Robert Antonishek, Brian Bugajska, Magda Schultz, Alan Trafton, J. Gregory GP IEEE TI A preliminary study of Peer-to-Peer Human-Robot Interaction SO 2006 IEEE INTERNATIONAL CONFERENCE ON SYSTEMS, MAN, AND CYBERNETICS, VOLS 1-6, PROCEEDINGS SE IEEE International Conference on Systems Man and Cybernetics Conference Proceedings LA English DT Proceedings Paper CT IEEE International Conference on Systems, Man and Cybernetics CY OCT 08-11, 2006 CL Taipei, TAIWAN SP IEEE Syst, Man & Cybernet Soc, Minist Educ, Natl Sci Council, Natl Taipei Univ Technol, Natl Chiao Tung Univ AB The Peer-to-Peer Human-Robot Interaction (P2P-HRI) project is developing techniques to improve task coordination and collaboration between human and robot partners. Our work is motivated by the need to develop effective human-robot teams for space mission operations. A central element of our approach is creating dialogue and interaction tools that enable humans and robots to flexibly support one another. In order to understand how this approach can influence task performance, we recently conducted a series of tests simulating a lunar construction task with a human-robot team. In this paper, we describe the tests performed, discuss our initial results, and analyze the effect of intervention on task performance. C1 [Fong, Terrence; Flueckiger, Lorenzo; Kunz, Clayton; Lees, David; Schreiner, John; Siegel, Michael] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Shah, Julie A.] MIT, Cambridge, MA 02139 USA. [Hiatt, Laura M.; Nourbakhsh, Illah; Simmons, Reid] Carnegie Mellon Univ, Inst Robot, Pittsburgh, PA 15213 USA. [Ambrose, Robert; Burridge, Robert] NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. [Scholtz, Jean; Antonishek, Brian] Natl Inst Stand & Technol, Gaithersburg, MD 20899 USA. [Bugajska, Magda; Schultz, Alan; Trafton, J. Gregory] Naval Res Lab, Washington, DC 20375 USA. RP Fong, T (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RI Scholtz, Jean/E-8955-2013 FU NASA Exploration Systems Mission Directorate [HRT-ICP-04-0000-0155] FX We would like to thank Bill Bluethmann, Dan Christian, Larry Edwards, John Hu, Pavithra Rajagopalan, Eli Young, the Ames Kl 0 team and the JSC Robonaut group for their tireless efforts and contributions to this project. This work was sponsored by a grant (HRT-ICP-04-0000-0155) from the NASA Exploration Systems Mission Directorate. NR 18 TC 2 Z9 3 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1062-922X BN 978-1-4244-0099-7 J9 IEEE SYS MAN CYBERN PY 2006 BP 3198 EP + DI 10.1109/ICSMC.2006.384609 PG 2 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Computer Science, Cybernetics SC Automation & Control Systems; Computer Science GA BGK85 UT WOS:000248078503086 ER PT S AU Glasgow, JM Thomas, G Pudenz, E Cabrol, N Wettergreen, D Coppin, P AF Glasgow, Justin M. Thomas, Geb Pudenz, Erin Cabrol, Nathalie Wettergreen, David Coppin, Peter GP IEEE TI Panoramic image information utility for mobile robot exploration SO 2006 IEEE INTERNATIONAL CONFERENCE ON SYSTEMS, MAN, AND CYBERNETICS, VOLS 1-6, PROCEEDINGS SE IEEE International Conference on Systems Man and Cybernetics Conference Proceedings LA English DT Proceedings Paper CT IEEE International Conference on Systems, Man and Cybernetics CY OCT 08-11, 2006 CL Taipei, TAIWAN SP IEEE Syst, Man & Cybernet Soc, Minist Educ, Natl Sci Council, Natl Taipei Univ Technol, Natl Chiao Tung Univ AB When searching a remote environment with a robot, the fundamental constraint on the operator is the bandwidth available to the mission. This paper examines how a science team uses a high bandwidth panorama during a two-year astrobiology field test. Bandwidth directly controls the type and amount of information received by the operator. Given the significance of information and bandwidth to mission success, it is important for human robot interaction analyses to consider bandwidth usage during robotic operations. Insight gained from these analyses can help future missions efficiently use their bandwidth to collect the necessary information from the environment. The analysis first shows that the science team preferentially views certain areas of the panorama based on tile elevation but not based on azimuth. This finding led the analysis to look into what tasks the science team completes while using the panorama. In the context of an astrobiology mission, the most important role of the panorama is to determine the robot's position on orbital images. The secondary task is to determine the general geologic context of the environment. Based on the viewing patterns and associated tasks the analysis produces a list of targets important to mission success. Future research efforts will focus on methods for collecting the information contained in these targets from the environment at a reduced bandwidth cost. C1 [Glasgow, Justin M.; Thomas, Geb; Pudenz, Erin] Univ Iowa, Dept Mech & Ind Engn, Iowa City, IA 52242 USA. [Cabrol, Nathalie] NASA, Ames Res Ctr, SETI Inst, Moffett Field, CA 94035 USA. [Wettergreen, David; Coppin, Peter] Carnegie Mellon Univ, Pittsburgh, PA 15213 USA. RP Thomas, G (reprint author), Univ Iowa, Dept Mech & Ind Engn, Iowa City, IA 52242 USA. EM geb-thomas@uiowa.edu; ncabrol@mail.arc.nasa.gov FU NASA's Applied Information Systems Research Program under NASA [NAGW5-11981, NNGO5GA51G]; Astrobiology Science and Technology for Exploring Planets [NAG5-12890] FX Support for this work comes from NASA's Applied Information Systems Research Program under NASA grant NAGW5-11981 and NNGO5GA51G and the Astrobiology Science and Technology for Exploring Planets under grant NAG5-12890. NR 18 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1062-922X BN 978-1-4244-0099-7 J9 IEEE SYS MAN CYBERN PY 2006 BP 3216 EP + DI 10.1109/ICSMC.2006.384612 PG 2 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Computer Science, Cybernetics SC Automation & Control Systems; Computer Science GA BGK85 UT WOS:000248078503089 ER PT S AU Bolton, ML Bass, EJ Comstock, JR AF Bolton, Matthew L. Bass, Ellen J. Comstock, James R., Jr. GP IEEE TI Using videos derived from simulations to support the analysis of spatial awareness in synthetic vision displays SO 2006 IEEE INTERNATIONAL CONFERENCE ON SYSTEMS, MAN, AND CYBERNETICS, VOLS 1-6, PROCEEDINGS SE IEEE International Conference on Systems Man and Cybernetics Conference Proceedings LA English DT Proceedings Paper CT IEEE International Conference on Systems, Man and Cybernetics CY OCT 08-11, 2006 CL Taipei, TAIWAN SP IEEE Syst, Man & Cybernet Soc, Minist Educ, Natl Sci Council, Natl Taipei Univ Technol, Natl Chiao Tung Univ AB The evaluation of human-centered systems can be performed using a variety of different methodologies. This paper describes a human-centered systems' evaluation methodology where participants watch 5-second non-interactive videos of a system in operation before supplying judgments and subjective measures based on the information conveyed in the videos. This methodology was used to evaluate the ability of different textures and fields of view to convey spatial awareness in synthetic vision systems (SVS) displays. It produced significant results for both judgment based and subjective measures. This method is compared to other methods commonly used to evaluate SVS displays based on cost, the amount of experimental time required, experimental flexibility, and the type of data provided. C1 [Bolton, Matthew L.; Bass, Ellen J.] Univ Virginia, Dept Syst Engn, Charlottesville, VA 22904 USA. [Comstock, James R., Jr.] NASA, Langley Res Ctr, Crew Syst & Aviat Operat Branch, Hampton, VA 23681 USA. RP Bolton, ML (reprint author), Univ Virginia, Dept Syst Engn, Charlottesville, VA 22904 USA. EM mlb4b@virginia.edu; ejb4n@virginia.edu; J.R.Comstock@larc.nasa.gov FU Systems - Rising Star [UVA-03-01, 4817-UV]; NIA; NASA FX This work was supported in part by Synthetic Vision Systems - Rising Star Fellowship (M. Bolton), UVA-03-01, Sub-Award Number: 4817-UV.; This work was supported in part by the NIA and NASA. NR 17 TC 0 Z9 0 U1 0 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1062-922X BN 978-1-4244-0099-7 J9 IEEE SYS MAN CYBERN PY 2006 BP 5203 EP + DI 10.1109/ICSMC.2006.385134 PG 2 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Computer Science, Cybernetics SC Automation & Control Systems; Computer Science GA BGK85 UT WOS:000248078505132 ER PT S AU Kim, Y van Zyl, J AF Kim, Yunjin van Zyl, Jakob GP IEEE TI A Time Series Approach for Soil Moisture Estimation SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci AB Soil moisture is a key parameter in understanding the global water cycle and in predicting natural hazards. Polarimetric radar measurements have been used for estimating soil moisture of bare surfaces. In order to estimate soil moisture accurately, the surface roughness effect must be compensated properly. In addition, these algorithms will not produce accurate results for vegetated surfaces. It is difficult to retrieve soil moisture of a vegetated surface since the radar backscattering cross section is sensitive to the vegetation structure and environmental conditions such as the ground slope. Therefore, it is necessary to develop a method to estimate the effect of the surface roughness and vegetation reliably. One way to remove the roughness effect and the vegetation contamination is to take advantage of the temporal variation of soil moisture. In order to understand the global hydrologic cycle, it is desirable to measure soil moisture with one- to two-days revisit. Using these frequent measurements, a time series approach can be implemented to improve the soil moisture retrieval accuracy. C1 [Kim, Yunjin; van Zyl, Jakob] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Kim, Y (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM yunjin.kim@jpl.nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 60 EP 62 DI 10.1109/IGARSS.2006.20 PG 3 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989400016 ER PT S AU Im, E Durden, SL Tanelli, S Pak, K AF Im, Eastwood Durden, Stephen L. Tanelli, Simone Pak, Kyung GP IEEE TI Early Results on Cloud Profiling Radar Post-launch Calibration and Operations SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE cloud; CloudSat; A-train; radar; EIK ID SATELLITE; OCEAN AB The Cloud Profiling Radar (CPR), the primary science instrument of the CloudSat Mission, is a 94-GHz nadir-looking radar that measures the power backscattered by clouds as a function of distance from the radar. This instrument will acquire a global time series of vertical cloud structure at 500-m vertical resolution and 1.4-km horizontal resolution. CPR will operate in a short-pulse mode and will yield measurements at a minimum detectable sensitivity of -28 dBZ. C1 [Im, Eastwood; Durden, Stephen L.; Tanelli, Simone; Pak, Kyung] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Im, E (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. EM Eastwood.Im@jpl.nasa.gov NR 6 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 93 EP 96 DI 10.1109/IGARSS.2006.29 PG 4 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989400025 ER PT S AU Yang, CP Bambacus, M Cao, Y Kafatos, M AF Yang, Chaowei Phil Bambacus, Myra Cao, Ying Kafatos, Menas GP IEEE TI An Interoperable Transportation Framework Data Service SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE Interoperable; Transportation; Framework Data; National Spatial Data Infrastructure; Geospatial Web Portal AB Heterogeneous geospatial data systems have been developed in the past decades. National Spatial Data Infrastructure (NSDI) was proposed and utilized to share these heterogeneous systems through interoperable solutions. As one of the first set of data sharing approaches, Federal Geographic Data Committee (FGDC) identified seven sets of data themes as framework data and developed relevant content standard for sharing these datasets. Together with other NSDI initiatives, a transportation framework data service is described in this paper to share our experience gained through the building of transportation framework service at different aspects: 1) the datasets are described through FGDC compliant metadata and categorized in a data searching engine supporting Z39.50; 2) the datasets are served through Web Feature Service (WFS) and could be accessed through standardized service for content updating and accessing; and 3) the WFS was chained with an in-house development on mapping WFS as Web Mapping Service (WMS) to provide web mapping, therefore, leverage the vast amount of deployed WMS clients in the last years. C1 [Yang, Chaowei Phil; Cao, Ying; Kafatos, Menas] George Mason Univ, Ctr Earth Observing & Space Res & Earth Syst & Ge, 4400 Univ Dr, Fairfax, VA USA. [Yang, Chaowei Phil; Bambacus, Myra] NASA, GeoSci Interoperabil Off, Greenbelt, MD 20771 USA. RP Yang, CP (reprint author), George Mason Univ, Ctr Earth Observing & Space Res & Earth Syst & Ge, 4400 Univ Dr, Fairfax, VA USA. EM cyang3@gmu.edu RI Yang, Chaowei/A-9881-2017; OI Yang, Chaowei/0000-0001-7768-4066 FU 973 project [2006CB701306]; US FGDC CAP; NASA JIESIC FX Sponsored by a 973 project (2006CB701306), US FGDC 2005 CAP, and NASA JIESIC Grant NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 233 EP + DI 10.1109/IGARSS.2006.64 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989400060 ER PT S AU Regner, K Conover, H Graves, S Hawkins, L Goodman, HM AF Regner, Kathryn Conover, Helen Graves, Sara Hawkins, Lamar Goodman, H. Michael GP IEEE TI Product Delivery Record Server Data Transfer at the AMSR-E SIPS SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci AB Issues associated with failed data transfers can be complicated and inconvenient, not only for end users expecting timely products, but also for the data managers who are responsible for recovering from failures. Working in close collaboration with engineers at the University of Alabama in Huntsville's Information Technology and Systems Center, the AMSR-E SIPS has evolved a local implementation of the Product Delivery Record Server from a simple ECS-compliant data exchange system to a smart automated message handling system that also executes routine operational error recovery procedures. While automated data exchange mechanisms have been the norm for quite some time, the AMSR-E SIPS has deployed unique technologies in our local implementation of the PDRS by integrating it with and automating some routine data management functions, such as process scheduling, restaging of certain classes of failed data transfers, and statistics reporting. This paper discusses the evolution of the PDRS design and architecture, highlights the unique features of this flexible processing system that has contributed to reduced operating costs, and describes our plans to meet future requirements. C1 [Regner, Kathryn; Conover, Helen; Graves, Sara; Hawkins, Lamar] Univ Alabama, Informat Technol & Syst Ctr, Huntsville, AL 35899 USA. [Goodman, H. Michael] NASA, Marshall Space Flight Ctr, Huntsville, AL USA. RP Regner, K (reprint author), Univ Alabama, Informat Technol & Syst Ctr, Huntsville, AL 35899 USA. EM kregner@itsc.uah.edu FU National Aeronautics and Space Administration FX Sponsored by the National Aeronautics and Space Administration NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 245 EP + DI 10.1109/IGARSS.2006.67 PG 3 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989400063 ER PT S AU McDonald, K Enloe, Y Di, LP Holloway, D AF McDonald, Kenneth Enloe, Yonsook Di, Liping Holloway, Daniel GP IEEE TI A Gateway to Support Interoperability of OPeNDAP and OGC Protocols SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci AB Data access and analysis tools that are developed within specific disciplines and the protocols that they are built upon provide valuable services to their respective users but can actually be a barrier to the integration of data from a broad set of data sources. An example of this is data supported by OPeNDAP that is widely used in the ocean and atmospheric sciences, and data provided through the interface specifications of the Open Geospatial Consortium (OGC) that typically serves the land science community. This paper describes a project that is developing a gateway to bridge these two data system infrastructures, in response to a specific need expressed by CEOP, an international science program. C1 [McDonald, Kenneth] NASA, Goddard Space Flight Ctr, Code 423, Greenbelt, MD 20771 USA. [Enloe, Yonsook] SGT Inc, Greenbelt, MD 20771 USA. [Di, Liping] George Mason Univ, CSISS, Greenbelt, MD 20771 USA. [Holloway, Daniel] OPeNDAP Inc, Narragansett, RI 02882 USA. RP McDonald, K (reprint author), NASA, Goddard Space Flight Ctr, Code 423, Greenbelt, MD 20771 USA. FU NASA [05-ACCESS/05-28] FX This research is supported by NASA ROSES 2005 ACCESS program (05-ACCESS/05-28). NR 9 TC 2 Z9 2 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 301 EP + DI 10.1109/IGARSS.2006.82 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989400078 ER PT S AU Esfandiari, M Ramapriyan, H Behnke, J Sofinowski, E AF Esfandiari, M. Ramapriyan, H. Behnke, J. Sofinowski, E. GP IEEE TI Evolution of the Earth Observing System (EOS) Data and Information System (EOSDIS) SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci AB The Earth Observing System (EOS) Data and Information System (EOSDIS) has been serving a broad user community since 1994. Most of NASA's Earth science data are currently being archived, managed and distributed by EOSDIS. Also, EOSDIS commands and controls EOS spacecraft and instruments, captures data from the instruments and processes them into a set of standard products. As of March 2006, the archives of EOSDIS held over 4.3 petabytes of data from over 90 instruments and over 2000 distinct science products. The distribution of data to end users amounts to approximately 2 TR a day. The community receiving data from EOSDIS is on the order of 200,000 distinct users from a diverse set of organizations and scientific disciplines. While EOSDIS is effectively managing a large amount of data and successfully serving a broad user community, it is a system whose design and development originated more than 10 years ago during which many advances have occurred in information technology. Although there has been an on-going process of technology infusion, incremental improvements in processing and performance, and new functionality added in areas of user access, distribution, and archive management over the years, the underlying design has remained essentially the same. During this time frame, data volumes have grown dramatically and the science community has gained considerable experience in processing and analyzing their data. More recently, through examination of current operations and a series of lessons learned, there has been a desire to re-examine current operations for significant improvements in a variety of areas. The overall objectives of the EOSDIS evolution are to: increase end-to-end data system efficiency and autonomy while decreasing operations costs, increase data interoperability and usability by the science research, application, and modeling communities, improve data access and processing, and ensure safe stewardship. C1 [Esfandiari, M.; Ramapriyan, H.; Behnke, J.] NASA, Goddard Space Flight Ctr, Washington, DC 20546 USA. [Sofinowski, E.] SGT Inc, Greenbelt, MD USA. RP Esfandiari, M (reprint author), NASA, Goddard Space Flight Ctr, Washington, DC 20546 USA. FU NASA's Science Mission Directorate; NASA [NNG05CA99C]; SGT, Inc. [NNG05CA99C] FX This work was performed by the first four authors as part of their duties as U.S. Government employees. It was supported by the NASAs Science Mission Directorate. The fifth author worked as a contractor supporting this effort under contract NNG05CA99C between NASA and SGT, Inc. The opinions expressed are those of the authors and do not necessarily reflect the official position of NASA. NR 5 TC 4 Z9 4 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 309 EP + DI 10.1109/IGARSS.2006.84 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989400080 ER PT S AU Rank, RH McDonald, KR AF Rank, Robert H. McDonald, Kenneth R. GP IEEE TI Use of a Standard Process for Submission of Data for Archive and Preservation SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci AB The Comprehensive Large Array-data Stewardship System (CLASS) has adopted the Open Archival Information System (OAIS) reference model to provide a framework and general guidelines in conducting its interactions with its data providers. The benefit of using OAIS is that it provides a common set of functions, processes and documents that are required to accomplish the data transfers and a common terminology to establish the scope of the effort and the respective responsibilities of the data providers and the archive. To complete this task a workgroup was formed for the development of a data submission process using recommendations for Space Data System Standards front the Consultative Committee for Space Data Systems (CCSDS) reference model. The paper will present the early prototyping activities that are underway for enhancing CLASS to support archive and distribution of Earth Observing System (EOS) data. C1 [Rank, Robert H.] NOAA, NESDIS, OSD, CLASS, Suitland, MD 20746 USA. [McDonald, Kenneth R.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Rank, RH (reprint author), NOAA, NESDIS, OSD, CLASS, Suitland, MD 20746 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 325 EP + DI 10.1109/IGARSS.2006.88 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989400084 ER PT S AU Kefauver, SC Greenberg, J Ustin, S AF Kefauver, Shawn C. Greenberg, Jonathan Ustin, Susan GP IEEE TI Remote Sensing of Tropospheric Ozone Impacts on Bio-Indicator Species Using Imaging Spectroscopy SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE hyperspectral; bio-indicators; forest health; ozone; imaging spectroscopy; air pollution; Pinus ponderosa; Pinus jeffreyi ID PONDEROSA PINE; CALIFORNIA; PARAMETERS; ECOSYSTEM; EXPOSURE; CONIFERS; DROUGHT; FORESTS; CARBON; INDEX AB The Sierra Nevada Mountains of California are likely to experience changes in ecosystem dynamics in coming decades as a result of multiple anthropogenic and climatic stressors. Recent advancements in remote sensing, specifically in high spatial and spectral imagery, allow for detailed, site-specific investigations of ecosystem conditions that are scalable for a comprehensive, landscape view of forest dynamics. Further development of hyperspectral imaging techniques to map bio-indicator species distributions (Pinus ponderosa and Pinus jeffreyi) and physiological conditions (chlorophyll and water content) in Yosemite and Sequoia/Kings Canyon National Parks will help to further understand and predict changes in ecosystem dynamics under changing conditions. C1 [Kefauver, Shawn C.; Ustin, Susan] Univ Calif Davis, Dept Land Air & Water Resources, Davis, CA 95616 USA. [Greenberg, Jonathan] NASA, Ames Res Ctr, Moffett Field, CA USA. RP Kefauver, SC (reprint author), Univ Calif Davis, Dept Land Air & Water Resources, Davis, CA 95616 USA. EM sckefauver@ucdavis.edu; jgreenberg@arc.nasa.gov; slustin@ucdavis.edu OI Greenberg, Jonathan/0000-0001-8435-9077; Kefauver, Shawn/0000-0002-1687-1965 FU Jastro Shields Grant; Ecology Graduate Group Block Grant; California State University of Monterey Bay; AVIRIS flight and data acquisitions crew at NASA Jet Propulsion Laboratories; California Space Institute Center of Excellence; US National Park Service [76735] FX We are grateful to many people including field crews, volunteers, and especially Jeanne Panek, Vern Vanderbilt, Hugh Stimson, and Sara Mastrangelo for their invaluable help on the different stages of the formation of the project. This project was funded and/or aided through collaboration in part by all of the following: Jastro Shields Grant, Ecology Graduate Group Block Grant, California State University of Monterey Bay, AVIRIS flight and data acquisitions crew at NASA Jet Propulsion Laboratories, the California Space Institute Center of Excellence, and the US National Park Service (PMIS #76735). NR 16 TC 0 Z9 0 U1 0 U2 7 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 391 EP + DI 10.1109/IGARSS.2006.105 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989400101 ER PT S AU Stackhouse, PW Eckman, RS Zhang, T Mikovitz, JC Whitlock, CH Chandler, WS Hoell, JM Leng, GS Lilienthal, P AF Stackhouse, P. W. Eckman, R. S. Zhang, T. Mikovitz, J. C. Whitlock, C. H. Chandler, W. S. Hoell, J. M. Leng, G. S. Lilienthal, P. GP IEEE TI Supporting Energy-Related Societal Applications Using NASA's Satellite and Modeling Data SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE energy; solar energy; decision support systems AB Improvements to NASA Surface Meteorology and Solar Energy (SSE) web site are now being made through the Prediction of Worldwide Energy Resource (POWER) project under NASA Science Mission Directorate Applied Science Energy Management Program. The purpose of this project is to tailor NASA Science Mission results for energy sector applications and decision support systems. The current status of SSE and research towards upgrading estimates of total, direct and diffuse solar irradiance from NASA satellite measurements and analysis are discussed. Part of this work involves collaborating with partners such as the National Renewable Energy Laboratory (NREL) and the Natural Resources Canada (NRCan). Energy Management and POWER plans including historic, near-term and forecast datasets are also overviewed. C1 [Stackhouse, P. W.; Eckman, R. S.] NASA, Langley Res Ctr, Sci Miss Directorate, Hampton, VA 23681 USA. [Whitlock, C. H.; Chandler, W. S.; Hoell, J. M.] Sci Applicat Int Corp, Hampton, VA 23681 USA. [Zhang, T.; Mikovitz, J. C.] Analyt Serv & Mat Inc, Hampton, VA 23681 USA. [Leng, G. S.] Ctr Technol Ingn CANMET, CANMET Energy Technol Ctr, Varennes, PQ J3X 1S6, Canada. [Lilienthal, P.] Natl Renewable Energy Lab, Golden, CO 80402 USA. RP Stackhouse, PW (reprint author), NASA, Langley Res Ctr, Sci Miss Directorate, Hampton, VA 23681 USA. EM Paul.W.Stackhouse@NASA.gov FU NASA Applied Science FX Funding for this work is provided through the NASA Applied Science Program Energy Management Theme NR 16 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 425 EP + DI 10.1109/IGARSS.2006.113 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989400109 ER PT S AU O'Neill, P Owe, M Gouweleeuw, B Njoku, E Shi, JC Wood, E AF O'Neill, Peggy Owe, Manfred Gouweleeuw, Ben Njoku, Eni Shi, J. C. Wood, Eric GP IEEE TI Hydros Soil Moisture Retrieval Algorithms: Status and Relevance to Future Missions SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE soil moisture; Hydros; retrieval algorithms; microwave radiometry; error budget AB In 2002 the Hydrosphere State Mission (Hydros) was selected by NASA as the alternate mission for a flight opportunity under its Earth System Science Pathfinder program. The Hydros mission objective was to collect the first global scale measurements of the Earth's soil moisture and land surface freeze/thaw conditions, using a combined L band radiometer and radar system operating at 1.41 and 1.26 GHz, respectively. Although NASA cancelled the Hydros mission in December 2005 due to insufficient funding and its reversion back to alternate mission status, the development of accurate soil moisture retrieval algorithms and associated error analyses begun under the Hydros project are still relevant to SMOS and to other potential future soil moisture missions. C1 [O'Neill, Peggy; Owe, Manfred; Gouweleeuw, Ben] NASA, Goddard Space Flight Ctr, Hydrol Sci Branch, Code 614-3, Greenbelt, MD 20771 USA. [Njoku, Eni] NASA, Jet Prop Lab, Pasadena, CA 91109 USA. [Shi, J. C.] Univ Calif Santa Barbara, Santa Barbara, CA 93106 USA. [Wood, Eric] Princeton Univ, Dept Civil & Environm Engn, Princeton, NJ 08854 USA. RP O'Neill, P (reprint author), NASA, Goddard Space Flight Ctr, Hydrol Sci Branch, Code 614-3, Greenbelt, MD 20771 USA. EM Peggy.E.ONeill@nasa.gov; Eni.Njoku@jpl.nasa.gov; shi@icess.ucsb.edu; efwood@runoff.princeton.edu RI O'Neill, Peggy/D-2904-2013; Gouweleeuw, Ben/A-8200-2012 NR 9 TC 1 Z9 1 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 436 EP + DI 10.1109/IGARSS.2006.116 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989400112 ER PT S AU Shi, JC Njoku, EG Jackson, T O'Neill, P AF Shi, Jiancheng Njoku, E. G. Jackson, T. O'Neill, P. GP IEEE TI Evaluation of Potential Error Sources for Soil Moisture Retrieval from Satellite Microwave Radiometer SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci AB This study demonstrates the impacts of land water, dry snow cover, and terrain at sub-pixel scale on soil estimation through numerical simulations. We will demonstrate the quantity of the above different factors contributing to the errors on the soil moisture estimation. C1 [Shi, Jiancheng] Univ Calif Santa Barbara, Inst Computat Earth Syst Sci, Santa Barbara, CA 93106 USA. [Njoku, E. G.] NASA, Jet Prop Lab, Pasadena, CA USA. [Jackson, T.] USDA ARS, Beltsville, MD USA. [O'Neill, P.] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. RP Shi, JC (reprint author), Univ Calif Santa Barbara, Inst Computat Earth Syst Sci, Santa Barbara, CA 93106 USA. EM shi@icess.ucsb.edu RI O'Neill, Peggy/D-2904-2013 NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 444 EP + DI 10.1109/IGARSS.2006.118 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989400114 ER PT S AU Kobayashi, S Tanelli, S Im, E Ito, S Oguchi, T AF Kobayashi, Satoru Tanelli, Simone Im, Eastwood Ito, Shigeo Oguchi, Tomohiro GP IEEE TI Time-dependent second order scattering theory for a weather radar with a finite beam width SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci ID RAIN AB Multiple scattering effects from spherical water particles of uniform diameter are studied for a W-band pulsed radar. The Gaussian transverse beam-profile and the rectangular pulse-duration are used for calculation. An second-order analytical solution is derived for a single layer structure, based on a time-dependent radiative transfer theory. When the range resolution is fixed, increase in footprint radius leads to increase in the second order reflectivity that is defined as the ratio of the second order return to the first order one. This undesireable feature becomes more serious as the range increases. Since the spaceborne millimeter-wavelength radar has a large footprint radius that is competitive to the mean free path, the multiple scattering effect must be taken into account for analysis. C1 [Kobayashi, Satoru; Tanelli, Simone; Im, Eastwood] CALTECH, Jet Prop Lab, Pasadena, CA 91101 USA. [Ito, Shigeo] Toyo Univ, Kawagoe, Saitama, Japan. [Oguchi, Tomohiro] Kanto Gakuin Univ, Yokohama, Kanagawa, Japan. RP Kobayashi, S (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91101 USA. EM Satoru.Kobayashi@jpl.nsa.gov; ito@eng.toyo.ac.jp; r-oguchi@js.ejnet.ne.jp NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 515 EP 518 DI 10.1109/IGARSS.2006.137 PG 4 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989400133 ER PT S AU Omar, AH Won, JG AF Omar, Ali H. Won, Jae-Gwang GP IEEE TI Distributions of Aerosol Extinction to Backscatter Ratios Derived from Cluster Analysis of AERONET Data SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci ID LIDAR MEASUREMENTS; RAMAN LIDAR AB The extinction-to-backscatter ratio (S-a) values and phase functions were calculated from mean properties of aerosol models determined from a statistically significant number of AERONET measurements. Cluster analysis by partitioning was used to categorize the AERONET data set based on several optical and physical characteristics of the aerosol. Using the mean values of the optical and microphysical properties together with the geographic locations, we identified these categories as desert dust, biomass burning, urban industrial pollution, rural background, polluted marine, and dirty pollution C1 [Omar, Ali H.] NASA, Langley Res Ctr, Sci Directorate, MailStop 401 A, Hampton, VA 23681 USA. [Won, Jae-Gwang] Seoul Natl Univ, Dept Earth & Environm Sci, Seoul, South Korea. RP Omar, AH (reprint author), NASA, Langley Res Ctr, Sci Directorate, MailStop 401 A, Hampton, VA 23681 USA. RI Omar, Ali/D-7102-2017 OI Omar, Ali/0000-0003-1871-9235 NR 12 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 577 EP + DI 10.1109/IGARSS.2006.152 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989400148 ER PT S AU Crowley, MD Chen, W Sukalac, EJ Sun, XH Coronado, PL Zhang, GQ AF Crowley, Matthew David Chen, William Sukalac, Eric J. Sun, Xiuhong Coronado, Patrick L. Zhang, Guo-Qiang GP IEEE TI Visualization of Remote Hyperspectral Image Data Using Google Earth SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci AB One of the greatest obstacles posed in the field of airborne remote sensing is the lack of an expeditious, cross-platform method of viewing imaging data through a standardized web interface. After an ariel photography session, clients or agencies typically wait days or weeks to obtain their images. We have been developing a solution for this issue by creating a wireless network system that allows aircraft to transfer data in-flight to a grounded base station using modified, but commercially available, MIMO-based wireless networking hardware. The final goal of this project is to devise a combination of hardware and software systems to deliver images to clients in near-realtime. This paper addresses the web visualization and telemetry monitoring component of the system, the process behind its development, and its path to fruition. The system developed shows not only the feasibility of but also the realization of a software system for transferring and viewing aerial multi- and hyperspectral images during in-flight imaging sessions. C1 [Crowley, Matthew David; Sukalac, Eric J.; Zhang, Guo-Qiang] Case Western Reserve Univ, Dept Elect Engn & Comp Sci, Cleveland, OH 44106 USA. [Chen, William; Sun, Xiuhong] Flight Landata Inc, Lawrence, MA 01843 USA. [Coronado, Patrick L.] NASA, Goddard Space Flight Ctr, Appl Informat Sci, Greenbelt, MD 20771 USA. RP Crowley, MD (reprint author), Case Western Reserve Univ, Dept Elect Engn & Comp Sci, Cleveland, OH 44106 USA. FU NASA for STTR [NNG05CA91C] FX The authors would like to thank the support of NASA for STTR 2004 Phase I Award NNG05CA91C, under which this project was carried out. NR 4 TC 2 Z9 2 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 907 EP + DI 10.1109/IGARSS.2006.233 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989400228 ER PT S AU Gao, BC Xiong, XX Li, RR AF Gao, Bo-Cai Xiong, Xiaoxiong Li, Rong-Rong GP IEEE TI A Study of MODIS Fire Detecting Channel Centered at 3.95-mu m SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci ID IDENTIFICATION AB The 3.75-mu m anal 11-mu m NOAA AVHRR channels have saturation temperatures of approximately 325 K. Although these channels allowed limited successes in estimating the sub-pixel fire temperature and fractional area coverage, the saturation problem associated with the 3.75-mu m channel over hot surfaces greatly limited the ability for such estimates. In order to overcome this problem, the MODIS instruments on board the NASA Terra and Aqua spacecrafts have both been equipped with a special fire channel centered at 3.95 mu m with a specified saturation temperature of 500 K and a nadir spatial resolution of 1 km. We have analyzed more than 30 sets of Terra and Aqua MODIS fire data sets acquired over different geographical regions, and found that very few fire pixels had the 3.95-mu m fire channel brightness temperatures greater than 450 K. We suggest that the saturation temperature of fire channels near 4 mu m for future satellite instruments with pixel sizes of about 1 km should be specified at about 450 K or even slightly lower in order to make the channels more useful for quantitative remote sensing of fires. C1 [Gao, Bo-Cai; Li, Rong-Rong] USN, Res Lab, Remote Sensing Div, Washington, DC 20375 USA. [Xiong, Xiaoxiong] NASA Goddard Space Flight Ctr, Earth Sun Explorat Div, Greenbelt, MD USA. RP Gao, BC (reprint author), USN, Res Lab, Remote Sensing Div, Washington, DC 20375 USA. EM gao@nrl.navy.mil RI Xiong, Xiaoxiong (Jack)/J-9869-2012 NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 1100 EP + DI 10.1109/IGARSS.2006.284 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989400279 ER PT S AU Sun, XH Baker, JJ Coronado, PL Stetina, F AF Sun, Xiuhong Baker, James J. Coronado, Patrick L. Stetina, Fran GP IEEE TI Airborne VNIR and SWIR Imaging Spectrometer and its Multi-sensor Remote Sensing Applications SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE Airborne Remote Sensing; Hyperspectral; Multispectral; Stereo Pairs; Multi-sensing; Mapping; Georeference; Calibration; Pixel spectrum; Imaging Spectrometer; GPS; IMU; System Integration; PC Instrumentation ID WATER ENVIRONMENT AB An Airborne VNIR and SWIR Imaging Spectrometer (AVSIS) system is fully integrated with grating-based VNIR and SWIR imaging spectrographs, a customized CCD camera and an InGaAs camera, a precision GPS/IMU setup, a specially-configured instrument PC, and a dedicated AVSIS operation autonomous software package. AVSIS is a fast hyperspectral imaging system capable of imaging simultaneously 129 spectral bands across a 1,392-pixel swathwidth with 1-meter resolution in a 445-900nm spectral range, along with 228 additional synchronized SWIR bands in a 900-1700nm range with a 320 coarse pixel swath, which matches the maximum acrosstrack viewing angle that the VNIR part covers. All of these bands are digitized at 12bits each with the same pushbroom scanning rate upto 60 scanlines/sec. AVSIS is interoperational with a multispectral framing camera system for simultaneous stereo pairs. Its initial hyperspectral/multispectral/stereo synthetic remote sensing applications have been discussed; and mapping-quality data samples are presented. C1 [Sun, Xiuhong; Baker, James J.] Flight Landata Inc, Lawrence, MA 01843 USA. [Coronado, Patrick L.; Stetina, Fran] NASA, Goddard Space Flight Ctr, Appl Informat Sci, Greenbelt, MD 20771 USA. RP Sun, XH (reprint author), Flight Landata Inc, Lawrence, MA 01843 USA. FU NASA for supporting the AVSIS project through SBIR [NAS5-02113] FX We thank NASA for supporting the AVSIS project through SBIR 2001 Phase II Contract # NAS5-02113. NR 6 TC 1 Z9 1 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 1103 EP + DI 10.1109/IGARSS.2006.285 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989400280 ER PT S AU Xiong, X Salomonson, VV Barnes, WL Guenther, B Xie, X Sun, J AF Xiong, X. Salomonson, V. V. Barnes, W. L. Guenther, B. Xie, X. Sun, J. GP IEEE TI An Overview of Terra MODIS Reflective Solar Bands On-orbit Calibration SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci ID PERFORMANCE; ALGORITHM AB The first MODIS instrument was launched aboard NASA's EOS Terra spacecraft in December 1999. MODIS has 20 reflective solar bands (RSB) with wavelengths from 0.41 to 2.2 mu m and nadir spatial resolutions of 0.25km, 0.5km, and 1.0km. It also has 16 thermal emissive bands (TEB) with wavelengths from 3.7 to 14.4 mu m, all with 1.0km spatial resolution. MODIS RSB on-orbit calibration and characterization are performed periodically using a solar diffuser (SD) and a solar diffuser stability monitor (SDSM). Another on-board calibrator, a spectro-radiometric calibration assembly (SRCA), is used for the sensor's spatial and spectral characterization. In addition to the SD/SDSM system, regularly scheduled lunar observations via spacecraft maneuvers are added to monitor RSB radiometric calibration stability. This paper provides an overview of Terra MODIS RSB calibration methodologies, operational activities, and on-orbit performance from its observations over 6 years. On-orbit results show that the Terra MODIS RSB calibrators have been performing well in tracking changes of detectors' responses and producing useful data sets to maintain RSB calibration and associated data product quality. C1 [Xiong, X.; Salomonson, V. V.] NASA, Goddard Space Flight Ctr, Sci Explorat Directorate, Greenbelt, MD 20771 USA. [Barnes, W. L.; Guenther, B.] Univ Maryland, JCET, Baltimore, MD 21250 USA. [Xie, X.; Sun, J.] Sci Syst & Appl Inc, Lanham, MD 20706 USA. RP Xiong, X (reprint author), NASA, Goddard Space Flight Ctr, Sci Explorat Directorate, Greenbelt, MD 20771 USA. EM Xiaoxiong.Xiong-l@nasa.gov; Vincent.V.Salomonson@nasa.gov; wbarnes@neptune.gsfc.nasa.gov; guenther@ltpmail.gsfs.nasa.gov; Xiaobo_Xie@ssaihq.com; Junqiang.sun.l@gsfc.nasa.gov RI Xiong, Xiaoxiong (Jack)/J-9869-2012 NR 10 TC 0 Z9 0 U1 0 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 1111 EP + DI 10.1109/IGARSS.2006.287 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989400282 ER PT S AU Wolfe, RE Nishihama, M Kuyper, JR AF Wolfe, Robert E. Nishihama, Masahiro Kuyper, James R. GP IEEE TI Improving satellite moderate resolution instrument geolocation accuracy in rough terrain SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE Geolocation; moderate resolution; MODIS; NASA ID MODIS AB When Earth-locating (geolocating) modern moderate resolution instrument data, such as from NASA's Moderate Resolution Imaging Spectroradiometer (MODIS) on the Earth Observing System (EOS) Terra and Aqua satellites, corrections for Earth terrain effects are applied to enable accurate retrieval of global geophysical parameters. The current approach to terrain correction calculates the pierce point of the center of each observation with a digital terrain model. With the recent Shuttle Radar Terrain Mapping Mission (SRTM) terrain model data, which has a higher spatial resolution and better accuracy than previous global terrain models, there is an opportunity to improve geolocation accuracy in rough terrain by using more advanced techniques to compute geolocations that are more representative of the centroid of each observation. The authors evaluate whether calculating geolocation using an observation weighting approach is significantly better than calculating the pierce point geolocation and if so under what conditions. The relative additional computational cost of an approximate technique is weighed against the possible increase in geolocation accuracy. C1 [Wolfe, Robert E.] NASA, Goddard Space Flight Ctr, Code 614-5, Greenbelt, MD 20771 USA. [Nishihama, Masahiro] Raytheon, Marlborough, MD USA. [Kuyper, James R.] SAIC GSC, Seabrook, MD USA. RP Wolfe, RE (reprint author), NASA, Goddard Space Flight Ctr, Code 614-5, Greenbelt, MD 20771 USA. EM robert.e.wolfe@nasa.gov; mash@ltpmail.gsfc.nasa.gov; kuyper@saicmodis.com RI Wolfe, Robert/E-1485-2012 OI Wolfe, Robert/0000-0002-0915-1855 FU MODIS Science Team FX The authors thank the MODIS Science Team for their support. NR 3 TC 4 Z9 5 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 1123 EP + DI 10.1109/IGARSS.2006.290 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989400285 ER PT S AU Schweiss, RJ Ho, E Ullman, R Samadi, S AF Schweiss, Robert J. Ho, Evelyn Ullman, Richard Samadi, Shahin GP IEEE TI The NPOESS Preparatory Project Science Data Segment: Brief Overview SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE National Polar-orbiting Operational Environmental Satellite; System(NPOESS); NPOESS Preparatory Project (NPP) Science Data Segment; leverage off existing science systems; climate studies; environmental data records; quality assessment; NASA; NOAA; DoD AB The NPOESS Preparatory Project (NPP) provides remotely-sensed land, ocean, atmospheric, ozone, and sounder data that will serve the meteorological and global climate change scientific communities while also providing risk reduction for the National Polar-orbiting Operational Environmental Satellite System (NPOESS), the U.S. Government's future low-Earth orbiting satellite system monitoring global weather and environmental conditions. NPOESS is a joint mission of three federal agencies, NASA, NOAA, and DoD. NASA's primary science role in NPP is to independently assess the quality of the NPP science and environmental data records for climate research. Such assessment is critical for making NPOESS products the best that they can be for operational use and ultimately for climate studies. The Science Data Segment (SDS) supports science assessment by assuring the timely provision of NPP data to NASA's science teams organized by climate measurement themes. The SDS breaks down into nine major elements, an input element that receives data from the operational agencies and acts as a buffer, a calibration analysis element, five elements devoted to measurement based quality assessment, an element used to test algorithmic improvements, and an element that provides overall science direction. This paper will describe how the NPP SDS will leverage on NASA experience to provide a mission-reliable research capability for science assessment of NPP derived measurements. C1 [Schweiss, Robert J.; Ho, Evelyn; Ullman, Richard; Samadi, Shahin] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Schweiss, RJ (reprint author), NASA, Goddard Space Flight Ctr, Code 429, Greenbelt, MD 20771 USA. EM robert.j.schweiss@nasa.gov; evelyn.l.ho@nasa.gov; richard.e.ullman@nasa.gov; shahin.samadi@gsfc.nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 1284 EP 1287 DI 10.1109/IGARSS.2006.332 PG 4 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989400327 ER PT S AU Lagerloef, GSE Chao, Y Colomb, FR AF Lagerloef, G. S. E. Chao, Y. Colomb, F. Raul GP IEEE TI Aquarius/SAC-D Ocean Salinity Mission Science Overview SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci AB Scheduled for launch in 2009, the international Aquarius/SAC-D satellite will begin a mission to map the global sea surface salinity (SSS) field and its variability from space. The overarching scientific goal is to provide the essential data to study the interactions between the ocean circulation, global water cycle and climate. Key scientific issues to address are (1) mapping large expanses of the unexplored ocean, (2) understanding the seasonal and interannual SSS variations and the link to precipitation, evaporation and sea-ice patterns, (3) links between SSS and circulation variations in the North Atlantic overturning circulation, (4) air-sea coupling processes in the tropics that influence El Nino, and (4) closing the marine freshwater budget. The satellite will provide repeat global coverage every 7 days with a footprint resolution ranging from 90 to 150 km over a three-beam similar to 390 km wide swath. Monthly SSS means will have an average root mean square (rms) accuracy of 0.2 psu at a spatial resolution of 150 km. Accuracies will be somewhat better in the tropics than high latitudes. Coincident microwave measurements of rain, sea ice and surface wind speed will he made with a resolution of about 45 km. The mission duration is initially three years, with probable extensions of two or more years. C1 [Lagerloef, G. S. E.] Earth & Space Res, Seattle, WA 98121 USA. [Chao, Y.] NASA, Jet Prop Lab, Pasadena, CA 91109 USA. [Colomb, F. Raul] CONAE, Buenos Aires, DF, Argentina. RP Lagerloef, GSE (reprint author), Earth & Space Res, Seattle, WA 98121 USA. EM lager@esr.org NR 13 TC 1 Z9 1 U1 0 U2 5 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 1675 EP + DI 10.1109/IGARSS.2006.433 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401025 ER PT S AU Le Vine, DM Lagerloef, GSE Yueh, S Pellerano, F Dinnat, E Wentz, F AF Le Vine, D. M. Lagerloef, G. S. E. Yueh, S. Pellerano, F. Dinnat, E. Wentz, F. GP IEEE TI Aquarius Mission Technical Overview SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE Microwave Remote Sensing; Ocean Salinity ID SEA-SURFACE SALINITY; L-BAND AB Aquarius is an L-band microwave instrument being developed to map the surface salinity field of the oceans from space. It is part of the Aquarius/SAC-D mission, a partnership between the USA (NASA) and Argentina (CONAE) with launch scheduled for early in 2009. The primary science objective of this mission is to monitor the seasonal and interannual variation of the large scale features of the surface salinity field in the open ocean with a spatial resolution of 150 kin and a retrieval accuracy of 0.2 psu globally on a monthly basis. C1 [Le Vine, D. M.; Pellerano, F.; Dinnat, E.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Lagerloef, G. S. E.] Earth & Space Res, Seattle, WA 98121 USA. [Yueh, S.] Jet Prop Lab, Pasadena, CA 91109 USA. [Wentz, F.] Remote Sensing Syst, Santa Rosa, CA 95401 USA. RP Le Vine, DM (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM David.M.LeVine@nasa.gov RI Dinnat, Emmanuel/D-7064-2012 OI Dinnat, Emmanuel/0000-0001-9003-1182 NR 10 TC 4 Z9 4 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 1678 EP 1680 DI 10.1109/IGARSS.2006.434 PG 3 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401026 ER PT S AU Pellerano, FA Piepmeier, J Wilson, WJ Yueh, S Spencer, M McWatters, D Freedman, A Triesky, M Horgan, K Forgione, J Caldwell, J AF Pellerano, Fernando A. Piepmeier, Jeffrey Wilson, William J. Yueh, Simon Spencer, Michael McWatters, Dalia Freedman, Adam Triesky, Michael Horgan, Kevin Forgione, Joshua Caldwell, James GP IEEE TI The Aquarius ocean salinity mission high stability L-band radiometer SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE radiometer; L-band radiometry; salinity; stable radiometers AB The NASA Earth Science System Pathfinder (ESSP) mission Aquarius, will measure global ocean surface salinity with similar to 120 km spatial resolution every 7-days with an average monthly salinity accuracy of 0.2 psu (parts per thousand) [1]. This requires an L-band low-noise radiometer with the long-term calibration stability of <= 0.15 K over 7 days. The instrument utilizes a push-broom configuration which makes it impractical to use a traditional warm load and cold plate in front of the feedhorns. Therefore, to achieve the necessary performance Aquarius utilizes a Dicke radiometer with noise injection to perform a warm - hot calibration. The radiometer sequence between antenna, Dicke load, and noise diode has been optimized to maximize antenna observations and therefore minimize NEDT. This is possible due the ability to thermally control the radiometer electronics and front-end components to 0.1 degrees Crms over 7 days. C1 [Pellerano, Fernando A.; Piepmeier, Jeffrey; Triesky, Michael; Horgan, Kevin; Forgione, Joshua; Caldwell, James] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Wilson, William J.; Yueh, Simon; Spencer, Michael; McWatters, Dalia; Freedman, Adam] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Pellerano, FA (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM Fernando.A.Pellerano@nasa.gov NR 3 TC 8 Z9 9 U1 0 U2 4 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 1681 EP + DI 10.1109/IGARSS.2006.435 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401027 ER PT S AU Freedman, A McWatters, D Spencer, M AF Freedman, Adam McWatters, Dalia Spencer, Michael GP IEEE TI The Aquarius Scatterometer An Active System for Measuring Surface Roughness for Sea-Surface Brightness Temperature Correction SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE sea-surface salinity; radar scatterometer; ocean roughness AB The Aquarius scatterometer is a total-power L-band radar system for estimating ocean surface roughness. Its measurements will enable the removal of wind effects from the Aquarius radiometer ocean-surface brightness temperature measurements being used to retrieve ocean salinity. The Aquarius scatterometer is a relatively simple, low-spatial resolution power-detecting radar, without ranging capability. But to meet its science requirement, it must be very stable, with repeatability on the order of 0.1 dB over several days, and calibrated accuracy to this level over several months. Data from this instrument over land as well as ocean areas will be available for a variety of geophysical applications. C1 [Freedman, Adam; McWatters, Dalia; Spencer, Michael] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Freedman, A (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Adam.Freedman@jpl.nasa.gov NR 4 TC 6 Z9 6 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 1685 EP 1688 DI 10.1109/IGARSS.2006.436 PG 4 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401028 ER PT S AU Simard, M Zhang, K Ross, MS Rivera-Monroy, VH Castaneda-Moya, E Twilley, R AF Simard, Marc Zhang, Keqi Ross, Michael S. Rivera-Monroy, Victor H. Castaneda-Moya, Edward Twilley, Robert GP IEEE TI Using Shuttle Radar Topography Mission Elevation Data to Map Mangrove Forest Height in the Caribbean SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci AB In this paper we describe a methodology to map mangrove forests in 3D in the caribbean region. We used Shuttle Radar Topography Mission (SRTM) elevation, lidar and field data to estimate mangrove mean tree height at the landscape scale. This paper emphasizes two regions which are undergoing ecosystem restoration activities: The Everglades National Park, USA and Cienaga Grande de Santa Marta, Colombia. In these regions we used, respectively, airborne and spaceborne (ICEsat (Ice, Cloud,and land Elevation Satellite)) lidar data to calibrate SRTM data and estimate mean tree height. Our results show the method is accurate if mangrove forest canopy vertical structure is well characterized. C1 [Simard, Marc] CALTECH, Jet Prop Lab, Pasadena, CA 90068 USA. [Zhang, Keqi; Ross, Michael S.] Dept Environm Studies, Miami, FL USA. [Rivera-Monroy, Victor H.; Castaneda-Moya, Edward; Twilley, Robert] Louisiana State Univ, Wetland Biogeochem Inst, Baton Rouge, LA 70803 USA. RP Simard, M (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 90068 USA. EM marc.simard@jpl.nasa.gov; zhangk@fiu.edu; vhrivera@lsu.edu OI Simard, Marc/0000-0002-9442-4562 NR 7 TC 0 Z9 0 U1 0 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 1713 EP + DI 10.1109/IGARSS.2006.443 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401035 ER PT S AU Jin, KW Njoku, E Chan, S AF Jin, Kyoung-Wook Njoku, Eni Chan, Steven GP IEEE TI Impact of Rainfall on the Retrieval of Soil Moisture using AMSR-E data SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE precipitation; rainfall; soil moisture; remote sensing; microwave; AMSR-E AB Rainfall leads to errors and limitations on the soil moisture retrieval using satellite radiometry. To understand the impact of rainfall, we examined the temporal and spatial correlations between rainfall and soil moisture using AMSR-E (Advanced Microwave Scanning Radiometer-EOS) data. Scan by scan (swath basis) analyses were conducted to find the short time scale relationship between the two physical parameters. The retention of soil moisture after rainfall in different climatic regimes (e.g. humid and and regions) was also examined. C1 [Jin, Kyoung-Wook; Njoku, Eni; Chan, Steven] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Jin, KW (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM kwjin@jpl.nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 1740 EP 1743 DI 10.1109/IGARSS.2006.450 PG 4 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401042 ER PT S AU Minnis, P Heck, PW Sun-Mack, S Trepte, QZ Chen, Y Brown, RR Gibson, S Dong, XQ Xi, BK AF Minnis, Patrick Heck, Patrick W. Sun-Mack, Sunny Trepte, Qing Z. Chen, Yan Brown, Ricky R. Gibson, Sharon Dong, Xiquan Xi, Baike GP IEEE TI A Multi-Year Data Set of Cloud Properties Derived for CERES from Aqua, Terra, and TRMM SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE clouds; MODIS; radiation; Aqua; Terra ID REFLECTANCE; MODIS; WATER AB The Clouds and Earth's Radiant Energy System (CERES) Project is producing a suite of cloud properties from high-resolution imagers on several satellites and matching them precisely with broadband radiance data to study the influence of clouds and radiation on climate. The cloud properties generally compare well with independent validation sources. Distinct differences are found between the CERES cloud properties and those derived with other algorithms from the same imager data. CERES products will be updated beginning in late 2006. C1 [Minnis, Patrick] NASA, Langley Res Ctr, Hampton, VA 23665 USA. [Heck, Patrick W.] Univ Wisconsin Madison, CIMSS, Madison, WI USA. [Sun-Mack, Sunny; Trepte, Qing Z.; Chen, Yan; Brown, Ricky R.; Gibson, Sharon] SAIC, Hampton, VA USA. [Dong, Xiquan; Xi, Baike] Univ North Dakota, Dept Meteorol, Grand Forks, ND USA. RP Minnis, P (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. EM p.minnis@nasa.gov FU NASA Science Mission through the CERES Project FX NASA Science Mission through the CERES Project (sponsors) NR 17 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 1780 EP + DI 10.1109/IGARSS.2006.460 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401052 ER PT S AU Teillet, PM Fedosejevs, G Barker, JL Miskey, CL Bannari, A AF Teillet, P. M. Fedosejevs, G. Barker, J. L. Miskey, C. L. Bannari, A. GP IEEE TI Spectral Simulations of Vegetation Indices in the Context of Landsat Data Continuity SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE NDVI; GEMI; vegetation indices; spectral similarity; TM; ETM; HRG; LISS-III; HRCC; LDCM; Landsat data continuity AB Differences between the analogous spectral bands on Landsat-class sensors can have significant impacts on vegetation index comparisons. Vegetation indices based on satellite image data are widely used for change monitoring but, when derived from different satellite sensors, they will differ as a function of the uncorrectable differences between the analogous spectral bands used to generate the vegetation indices. This issue becomes important as available satellite sensors in the Landsat class are being considered in order to fill the anticipated gap in continuity of the Landsat TM and ETM+ data record. A follow-on mission is not expected any earlier than 2011. Among the current imagers examined in this study, which encompassed four vegetation targets and eight vegetation indices, either one of the IRS-P6 sensors or the SPOT-5 HRG is preferable to the CBERS-2 HRCC as a replacement sensor from the standpoint of agreement with Landsat-based vegetation indices. Among the vegetation indices considered, the Global Environmental Monitoring Index (GEMI) proved to be the least sensitive to spectral dissimilarities between sensors and hence GEMI is worth considering for quantitative monitoring of environmental change using images from multiple sensors to fill the Landsat data archive. C1 [Teillet, P. M.; Fedosejevs, G.] Nat Resources Canada, Canada Ctr Remote Sensing, 588 Booth St, Ottawa, ON K1A 0Y7, Canada. [Barker, J. L.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Miskey, C. L.] Sci Syst & Applicat Inc, Lanham, MD 20706 USA. [Teillet, P. M.; Bannari, A.] Univ Ottawa, Dept Geog, Ottawa, ON K1N 6N5, Canada. RP Teillet, PM (reprint author), Nat Resources Canada, Canada Ctr Remote Sensing, 588 Booth St, Ottawa, ON K1A 0Y7, Canada. NR 9 TC 1 Z9 1 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 1784 EP + DI 10.1109/IGARSS.2006.461 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401053 ER PT S AU Houle, PA Zhang, KQ Ross, MS Simard, M AF Houle, Patricia A. Zhang, Keqi Ross, Michael S. Simard, Marc GP IEEE TI Use of Airborne LIDAR for the Assessment of Landscape Structure in the Pine Forests of Everglades National Park SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE LIDAR; laser altimetry; vegetation; Everglades AB Remote sensing technologies have provided valuable data for landscape modeling, vegetation mapping and comprehensive studies of ecosystems. Airborne laser mapping or LIDAR (Light Detection and Ranging) can directly measure the three dimensional structure of plant canopies, as well as, provide accurate digital terrain models (DTM). While temperate and boreal pine forests have been studied using these methods, very limited work has been done in subtropical pine forests. In this study, airborne, LIDAR was used to characterize the three dimensional structure of the forest on Long Pine Key at Everglades National Park. Analysis of the vertical distribution of airborne LIDAR data points has shown that distinctive patterns can be described which are characteristic of the vegetation communities and transition zones for pine forests, hammocks and marshes. This information is a valuable resource for forest managers by providing landscape structural data over large areas. C1 [Houle, Patricia A.; Zhang, Keqi] Florida Int Univ, Int Hurricane Res Ctr, Miami, FL 33199 USA. [Houle, Patricia A.; Zhang, Keqi] Florida Int Univ, Dept Environm Studies, Miami, FL 33199 USA. [Simard, Marc] CALTECH, Jet Propuls Lab, Radar & Engn Sect, Pasadena, CA USA. RP Houle, PA (reprint author), Florida Int Univ, Int Hurricane Res Ctr, Miami, FL 33199 USA. OI Simard, Marc/0000-0002-9442-4562 FU Interdisciplinary Science Program of National Aeronautics and Space Administration (NASA) FX This research was partially sponsored by the Interdisciplinary Science Program of National Aeronautics and Space Administration (NASA). Field work was done under permit EVER-2005-SCI-0043 from Everglades National Park. NR 10 TC 2 Z9 2 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 1960 EP + DI 10.1109/IGARSS.2006.507 PG 3 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401099 ER PT S AU Boardman, JW Bichl, LL Clark, RN Kruse, FA Mazer, AS Torson, J Staenz, K AF Boardman, Joseph W. Bichl, Larry L. Clark, Roger N. Kruse, Fred A. Mazer, Alan S. Torson, James Staenz, Karl GP IEEE TI Development and Implementation of Software Systems for Imaging Spectroscopy SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE hyperspectral; imaging spectroscopy; software ID VISUALIZATION; EARTH AB Specialized software systems have played a crucial role throughout the twenty-five year course of the development of the new technology of imaging spectroscopy, or hyperspectral remote sensing. By their very nature, hyperspectral data place unique and demanding requirements on the computer software used to visualize, analyze, process and interpret them. Often described as a marriage of the two technologies of reflectance spectroscopy and airborne/spaceborne remote sensing, imaging spectroscopy, in fact, produces data sets with unique qualities, unlike previous remote sensing or spectrometer data. Because of these unique spatial and spectral properties hyperspectral data are not readily processed or exploited with legacy software systems inherited from either of the two parent fields of study. This paper provides brief reviews of seven important software systems developed specifically for imaging spectroscopy. C1 [Boardman, Joseph W.] Analyt Imaging & Geophys LLC, Boulder, CO 80301 USA. [Bichl, Larry L.] Purdue Univ, Informat Technol Purdue ITaP, W Lafayette, IN USA. [Clark, Roger N.] US Geol Survey, Denver Spectroscopy Lab, Denver, CO USA. [Kruse, Fred A.] LLC, Horizon GeoImaging, Frisco, CO USA. [Mazer, Alan S.] CALTECH, Jet Prop Lab, Pasadena, CA USA. [Torson, James] US Geol Survey, Astrogeol Res Program, Flagstaff, AZ USA. [Staenz, Karl] Nat Res Canada, Canada Ctr Remote Sensing, Ottawa, ON, Canada. RP Boardman, JW (reprint author), Analyt Imaging & Geophys LLC, Boulder, CO 80301 USA. EM boardman@aiglle.com; biehl@purdue.edu; relark@usgs.gov; kruse@hgimaging.com; alan@judv.jpl.nasa.gov; jim.torson@computer.org; Karl.Staenz@CCRS.NRCan.gc.ca FU NASA; Center of the Study of Earth from Space [NAGW1601, NAS5-30552]; CCRS; CSA; MDA FX SIPS was developed under NASA funding at the Center of the Study of Earth from Space (NAGW1601 and NAS5-30552). We acknowledge the support of Alex Goetz, CSES Director. Funding for the research leading to the development of MultiSpec was provided by NASA. The Globe Program provided the support for the initial Windows versions of MultiSpec.; The support of CCRS, CSA, and MDA in the development of ISDAS is gratefully acknowledged. NR 20 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 1969 EP + DI 10.1109/IGARSS.2006.510 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401102 ER PT S AU Plaza, A Benediktsson, JA Boardman, J Brazile, J Bruzzone, L Camps-Valls, G Chanussot, J Fauvel, Q Gamba, P Gualtieri, A Tilton, JC Trianni, G AF Plaza, A. Benediktsson, J. A. Boardman, J. Brazile, J. Bruzzone, L. Camps-Valls, G. Chanussot, J. Fauvel, Q. Gamba, P. Gualtieri, A. Tilton, J. C. Trianni, G. GP IEEE TI Advanced Processing of Hyperspectral Images SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci ID CLASSIFICATION AB Hyperspectral iniaging offers the possibility of characterizing materials and objects in the air, land and water on the basis of the unique reflectance patterns that result from the interaction of solar energy with the molecular structure of the material. In this paper, we provide a seminal view on recent advances in techniques for hyperspectral data processing. Our main focus is on the development of approaches able to naturally integrate the spatial and spectral information available from the data. Special attention is paid to techniques that circumvent the curse of dimensionality introduced by high-dimensional data spaces. Experimental results, focused in this work on a specific case-study of urban data analysis, demonstrate the success of the considered techniques. This paper represents a first step towards the development of a quantitative and comparative assessment of advances in hyperspectral data processing techniques. C1 [Plaza, A.] Univ Extremadura, Dept Comp Sci, Caceres, Spain. [Benediktsson, J. A.] Univ Iceland, Dept Elect & Comp Engn, Reykjavik, Iceland. [Boardman, J.] LLC Boulder, Analyt Imaging & Geophys, Colorado Springs, CO USA. [Brazile, J.] Univ Zurich, Dept Geography, Zurich, Switzerland. [Bruzzone, L.] Univ Trento, Dept Informat & Commun Technol, Trento, Italy. [Camps-Valls, G.] Univ Valencia, Dept Elect Engn, Valencia, Spain. [Chanussot, J.; Fauvel, Q.] LIS, INPG, Lab Images & Signaux, Saint Martin Heres, France. [Gamba, P.; Trianni, G.] Univ Pavia, Dept Elect, Pavia, Italy. [Gualtieri, A.; Tilton, J. C.] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. RP Plaza, A (reprint author), Univ Extremadura, Dept Comp Sci, Caceres, Spain. RI Camps-Valls, Gustavo/A-2532-2011; Benediktsson, Jon/F-2861-2010; Plaza, Antonio/C-4455-2008; OI Camps-Valls, Gustavo/0000-0003-1683-2138; Benediktsson, Jon/0000-0003-0621-9647; Plaza, Antonio/0000-0002-9613-1659; Bruzzone, Lorenzo/0000-0002-6036-459X NR 15 TC 6 Z9 7 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 1974 EP + DI 10.1109/IGARSS.2006.511 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401103 ER PT S AU Ustin, SL Asner, GP Gamon, JA Huemmrich, KF Jacquemoud, S Schaepman, M Zarco-Tejada, P AF Ustin, Susan L. Asner, Gregory P. Gamon, John A. Huemmrich, K. Fred Jacquemoud, Stephane Schaepman, Michael Zarco-Tejada, Pablo GP IEEE TI Retrieval of Quantitative and Qualitative Information about Plant Pigment Systems from High Resolution Spectroscopy SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE plant pigments; chlorophyll a, b; carotenes; xanthophyll; leutin; anthocyanin pigments; absorption features; spectral measures of pigments ID REFLECTANCE RED EDGE; CHLOROPHYLL FLUORESCENCE; SPECTRAL REFLECTANCE; CANOPY REFLECTANCE; OPTICAL-PROPERTIES; LEAF PIGMENT; LEAVES; PHOTOSYNTHESIS; TRANSPIRATION; ACCLIMATION AB Life on earth depends on photosynthesis. Photosynthetic systems evolved early in earth history and have been stable for 2.5 billion years, providing prima facie evidence for these significance of evolutionary functions. Pigments perform multiple plant functions from increasing the range of energy captured for photosynthesis to a range of protective functions. Given the importance of pigments to leaf functioning, greater effort is needed to determine whether individual pigments can be identified and quantified by high fidelity spectroscopy. New methods to identify overlapping pigment absorptions would provide a major advance for understanding plant functions, quantifying net carbon exchange, and identifying plant stresses. C1 [Ustin, Susan L.] Univ Calif Davis, Dept LAWR, Davis, CA 95616 USA. [Asner, Gregory P.] Carnegie Inst Sci, Stanford, CA USA. [Gamon, John A.] Calif State Univ, Los Angeles, CA USA. [Huemmrich, K. Fred] NASA, GSFC, Greenbelt, MA USA. [Jacquemoud, Stephane] Inst Phys Globe Paris, Paris, France. [Schaepman, Michael] Wageningen Univ, Wageningen, Netherlands. [Zarco-Tejada, Pablo] Consejo Super Invest Cientificas ES, Inst Agr Sostenible, Madrid, Spain. RP Ustin, SL (reprint author), Univ Calif Davis, Dept LAWR, Davis, CA 95616 USA. EM slustin@ucdavis.edu RI Asner, Gregory/G-9268-2013; Zarco-Tejada, Pablo J./A-6874-2012; Schaepman, Michael/B-9213-2009; Gamon, John/A-2641-2014 OI Asner, Gregory/0000-0001-7893-6421; Zarco-Tejada, Pablo J./0000-0003-1433-6165; Schaepman, Michael/0000-0002-9627-9565; Gamon, John/0000-0002-8269-7723 NR 37 TC 1 Z9 1 U1 3 U2 16 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 1996 EP + DI 10.1109/IGARSS.2006.517 PG 3 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401109 ER PT S AU Schaepman, ME Green, RO Ungar, SG Curtiss, B Boardman, J Plaza, AJ Gao, BC Ustin, S Kokaly, R Miller, JR Jacquemoud, S Ben-Dor, E Clark, R Davis, C Dozier, J Goodenough, DG Roberts, D Swayze, G Milton, EJ Goetz, AFH AF Schaepman, Michael E. Green, Robert O. Ungar, Stephen G. Curtiss, Brian Boardman, Joe Plaza, Antonio J. Gao, Bo-Cai Ustin, Susan Kokaly, Raymond Miller, John R. Jacquemoud, Stephane Ben-Dor, Eyal Clark, Roger Davis, Curtiss Dozier, Jeff Goodenough, David G. Roberts, Dar Swayze, Gregg Milton, Edward J. Goetz, Alex F. H. GP IEEE TI The Future of Imaging Spectroscopy - Prospective Technologies and Applications SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE imaging spectroscopy; imaging spectrometry; hyperspectral; applications; technology ID HYPERSPECTRAL IMAGERY; HIGH-RESOLUTION; SPECTROMETER; CLASSIFICATION; REFLECTANCE; EARTH; ORBIT; INFORMATION; SPECTRUM; LOOKING AB Spectroscopy has existed for more than three centuries now. Nonetheless, significant scientific advances have been achieved. We discuss the history of spectroscopy in relation to emerging technologies and applications. Advanced focal plane arrays, optical design, and intelligent on-board logic are prime prospective technologies. Scalable approaches in pre-processing of imaging spectrometer data will receive additional focus, Finally, we focus on new applications monitoring transitional ecological zones, where human impact and disturbance have highest impact as well as in monitoring changes in our natural resources and environment. We conclude that imaging spectroscopy enables mapping of biophysical and biochemical variables of the Earth's surface and atmospheric composition with unprecedented accuracy. C1 [Schaepman, Michael E.] Univ Wageningen & Res Ctr, Ctr Geoinformat, Droevendaalsesteeg 3, NL-6708 PB Wageningen, Netherlands. [Green, Robert O.] CALTECH, Jet Prop Lab, Pasadena, CA USA. [Ungar, Stephen G.] NASA, GSFC, Greenbelt, MA USA. [Curtiss, Brian] Analyt Spectrum Devices Inc, Boulder, CO USA. [Boardman, Joe] Analyt Imaging & Geophys LLC, Boulder, CO USA. [Plaza, Antonio J.] Univ Extremadura, Badajoz, Spain. [Gao, Bo-Cai] Naval Res Lab, Washington, DC USA. [Ustin, Susan] Univ Calif Davis, Davis, CA USA. [Kokaly, Raymond; Swayze, Gregg] USGS, Denver, CO USA. [Miller, John R.] York Univ, Toronto, ON, Canada. [Jacquemoud, Stephane] Univ Paris 07, Paris, France. [Ben-Dor, Eyal] Tel Aviv Univ, Tel Aviv, Israel. [Davis, Curtiss] Oregon State Univ, Corvallis, OR USA. [Goodenough, David G.; Roberts, Dar] Univ Calif, Santa Barbara, CA USA. [Goodenough, David G.] Nat Resources Canada, Victoria, BC, Canada. [Milton, Edward J.] Univ Southampton, Southampton, Hants, England. [Goetz, Alex F. H.] Univ Colorado, Boulder, CO USA. RP Schaepman, ME (reprint author), Univ Wageningen & Res Ctr, Ctr Geoinformat, Droevendaalsesteeg 3, NL-6708 PB Wageningen, Netherlands. EM michael.schaepman@wur.nl RI Plaza, Antonio/C-4455-2008; Schaepman, Michael/B-9213-2009; Kokaly, Raymond/A-6817-2017; OI Plaza, Antonio/0000-0002-9613-1659; Schaepman, Michael/0000-0002-9627-9565; Kokaly, Raymond/0000-0003-0276-7101; Dozier, Jeff/0000-0001-8542-431X FU IEEE Geoscience and Remote Sensing Society FX The authors would like to acknowledge the support of their employing institutions. We are also grateful for the support of the organizers of the IEEE Geoscience and Remote Sensing Societys IGARSS conferences. A portion of this work was carried out at the Jet Propulsion Laboratory, California Institute of Technology under a contract with the National Aeronautics and Space Administration. NR 72 TC 3 Z9 6 U1 1 U2 10 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 2005 EP + DI 10.1109/IGARSS.2006.519 PG 4 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401111 ER PT S AU Hayden, L Omar, AH AF Hayden, Linda Omar, Ali H. GP IEEE TI Collaborations Focused on Enhancing Undergraduate Involvement in Remote Sensing Applications to Atmospheric and Earth Science Research SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci AB This paper discusses the mentoring strategies used with groups of undergraduate physics, mathematics and atmospheric science majors to develop their ability to contribute to remote sensing investigations. The projects have been a joint effort of scientist and educator at NASA Langley Research Center, Hampton University in Virginia, Elizabeth City State University in North Carolina, Stennis Space Center, and The Office of Naval Research. Atmospheric Science investigations have included verification of Sounding of the Atmosphere using Broadband Emission Radiometry (SABER). The SABER instrument is one of the four instruments housed on the Thermosphere Ionosphere Mesosphere Energetics and Dynamics (TIMED) satellite. SABER explores the MLTI (Mesosphere Lithosphere Thermosphere Ionosphere) region of the earth's atmosphere using infrared limb emission to sound the atmosphere. Other Atmospheric Science investigations have included use of a single scatter lidar equation to investigate tropospheric and stratospheric aerosol and temperature measurements derived from the 355 and 532 nm channels and comparison of the SAGE III limb scattering data to other instruments measuring similar aerosol and gas profiles. Earth Science Investigations include investigating incidents of coastal upwelling during the summer of 2000 along the northeastern coast of North Carolina (from Cape Hatteras to the Virginia Commonwealth border) by comparing archived in-situ near and offshore wind and temperature measurements with sea surface temperatures deduced from observations by the Advanced Very High Resolution Radiometer (AVHRR) on board several of NOAA's Polar Orbiting Environmental Satellites (POES); Remote sensing investigation of turbidity and water clarity in the Atlantic Ocean with the use of SeaWifs Data during which the frequency and extent of turbidity events in the Atlantic Coast was studied and SeaWiFS Ocean Color data was utilized to generate secchi disk depth estimates and; determining the spatial and temporal variability of chlorophyll concentrations in the northwestern Gulf of Mexico during 2002. Techniques for developing the required collaborations, student selection and organization of research training activities are described in this paper. C1 [Hayden, Linda] Elizabeth City State Univ, Ctr Excellence Remote Sensing Educ & Res, Box 672 ECSU 1704 Weeksville Rd, Elizabeth City, NC 27909 USA. [Omar, Ali H.] NASA, Langley Res Ctr Atmospher Sci, Hampton, VA 23681 USA. RP Hayden, L (reprint author), Elizabeth City State Univ, Ctr Excellence Remote Sensing Educ & Res, Box 672 ECSU 1704 Weeksville Rd, Elizabeth City, NC 27909 USA. EM haydenl@rnindspring.com; ali.h.omar@nasa.gov RI Omar, Ali/D-7102-2017 OI Omar, Ali/0000-0003-1871-9235 NR 7 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 2010 EP + DI 10.1109/IGARSS.2006.520 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401112 ER PT S AU Treuhaft, RN Chapman, BD dos Santos, JR Dutra, LV Goncalves, FG Freitas, CD Mura, JC Graca, PMD Drake, JB AF Treuhaft, R. N. Chapman, B. D. dos Santos, J. R. Dutra, L. V. Goncalves, F. G. Freitas, C. da Costa Mura, J. C. de Alencastro Graca, P. M. Drake, J. B. GP IEEE TI Tropical-Forest Density Profiles from Multibaseline Interferometric SAR SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE tropical forest; vertical distribution; interferometric SAR; biomass ID RADAR; FUSION; LIDAR AB Vertical profiles of forest density potentially are robust indicators of forest biomass, fire susceptibility and ecosystem function. Tropical forests, which are among the most dense and complicated targets for remote sensing, contain about 45% of the world's biomass. Remote sensing of tropical forest structure is therefore an important component to global biomass and carbon monitoring. As in radio astronomy, which uses multibaseline radio interferometry to measure the structure of celestial objects, so multibaseline interferometric SAR (InSAR) can be used to estimate the vertical structure of forests. Vegetation density profiles, along with radar backscattering characteristics and attenuation, determine the radar brightness profile "seen" by InSAR. This paper will describe an experiment at La Selva Biological Station in Costa Rica (similar to 3m rainfall/year) in which we flew 18 effective fixed baselines over tropical forests at C-band (0.056 m wavelength) and L-band (0.25 m). Preliminary inversions for radar brightness profiles will be compared to extensive lidar profiles measured in the same area. They will also be compared to field-measured profiles. C1 [Treuhaft, R. N.; Chapman, B. D.] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. [dos Santos, J. R.; Dutra, L. V.; Goncalves, F. G.; Freitas, C. da Costa; Mura, J. C.] Inst Nacl Pesquisas Espaciais, Sao Jose Dos Campos, Brazil. [de Alencastro Graca, P. M.] Inst Nacl Pesquisas Espaciais, Manaus, Amazonas, Brazil. [Drake, J. B.] USDA Forest Serv, Tallahassee, FL USA. RP Treuhaft, RN (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RI Freitas, Corina/C-6569-2009; de Alencastro Graca, Paulo Mauricio/B-3375-2013; Dutra, Luciano/C-6582-2009 OI Dutra, Luciano/0000-0002-7757-039X FU FAPEMIG [CRA 0070/04]; CNPq [304274/2005-4] FX We thank Danilo Vargas Ramirez and Walter Cruz Cambronero of La Selva Biological Station for assistance with field measurements. LVD acknowledges the Grants FAPEMIG CRA 0070/04, CNPq 304274/2005-4. JRS acknowledges CNPq 300677/91-1, CCF acknowledges CNPq 300927/92-4, and RNT acknowledges NASA RTOP 622-94-18-40-7787. The research described in this paper was carried out in part at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. NR 10 TC 5 Z9 5 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 2205 EP + DI 10.1109/IGARSS.2006.570 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401162 ER PT S AU Li, RR Remer, L Kaufman, YJ Mattoo, S Gao, BC Vermote, E AF Li, Rong-Rong Remer, Lorraine Kaufman, Yoram J. Mattoo, Shana Gao, Bo-Cai Vermote, Eric GP IEEE TI Masking of Residual Snow and Ice Covered Surfaces for Improving Aerosol Retrievals From MODIS Data SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci ID WATER AB Aerosol particles in the atmosphere can affect climate directly by interacting with solar and terrestrial radiation and indirectly by their effect on cloud microphysics, albedo, and precipitation. The atmospheric aerosol products have been derived operationally from multi-channel imaging data collected with the MOderate Resolution Imaging SpectroRadiometers (MODIS) on board the NASA Terra and Aqua spacecrafts. Through analysis of several years' MODIS aerosol products (Collection 4), we have found that the aerosol products over land are slightly contaminated by snow and ice during the springtime snow-melting season. We have developed an empirical technique using MODIS channels centered near 0.66, 0.86 and 1.24 gm and a thermal emission channel near 11 gm to mask out these snow-contaminated pixels over land. Improved aerosol retrievals have been obtained. C1 [Li, Rong-Rong; Gao, Bo-Cai] USN, Res Lab, Remote Sensing Div, Washington, DC 20375 USA. [Remer, Lorraine; Kaufman, Yoram J.; Mattoo, Shana; Vermote, Eric] NASA, Goddard Space Flight Ctr, Earth Sun Explorat Div, Greenbelt, MD USA. RP Li, RR (reprint author), USN, Res Lab, Remote Sensing Div, Washington, DC 20375 USA. EM rong-rong.li@nrl.navy.mil RI Vermote, Eric/K-3733-2012 NR 5 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 2236 EP + DI 10.1109/IGARSS.2006.578 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401170 ER PT S AU Savtchenko, A Gopalan, A MacHarrie, P AF Savtchenko, A. Gopalan, A. MacHarrie, P. GP IEEE TI Statistical Examination of Atmospheric Aerosol Properties using MODIS Global Data Product SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE aerosols; optical depth; MODIS AB Aerosols are understood to have a complex relationship with the climate system vertical bar 1 vertical bar. Aerosol research is currently in a global quantitative phase due to a network of in situ, ground and space based sensors currently in use vertical bar 2 vertical bar. Data from the Moderate Resolution Imaging Spectroradiometer (MODIS) instrument provide a unique view on the temporal and spatial variability of aerosol properties vertical bar 3 vertical bar. Presently, the aerosol data can be analyzed on synoptic to global and daily to inter-annual time scales, and decadal time series are expected to be available by the end of the design life of both MODIS instruments. That long climatological data records require careful approach and good understanding of data content to ensure realistic estimates of the natural variability and radiative forcing. The present paper addresses various statistical issues in dealing with MODIS aerosol data, in an attempt to also give users an estimate of inaccuracies when using the GES DISC Interactive Online Visualization and Analysis Infrastructure (Giovanni). C1 [Savtchenko, A.; Gopalan, A.; MacHarrie, P.] NASA, Goddard Space Flight Ctr, Goddard Earth Sci Data & Informat Serv Ctr, Greenbelt, MD 20771 USA. RP Savtchenko, A (reprint author), NASA, Goddard Space Flight Ctr, Goddard Earth Sci Data & Informat Serv Ctr, Code 610-2,Greenbelt Rd, Greenbelt, MD 20771 USA. EM Andrey.Savtchenko@gsfc.nasa.gov NR 8 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 2239 EP 2242 DI 10.1109/IGARSS.2006.579 PG 4 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401171 ER PT S AU Corp, LA Middleton, EM Daughtry, CST Campbell, PKE AF Corp, L. A. Middleton, E. M. Daughtry, C. S. T. Campbell, P. K. Entcheva GP IEEE TI Solar Induced Fluorescence and Reflectance Sensing Techniques for Monitoring Nitrogen Utilization in Corn SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE Reflectance (R); Fluoresenece (F); Fraunhofer Line Depth (FLD); Physiological Reflectance Index (PRI) ID INDUCED CHLOROPHYLL FLUORESCENCE AB Remote sensing systems using either passive reflectance (R) or actively induced fluorescence (F) have long been explored as a means to monitor species composition and vegetative productivity. Passive F techniques using the Fraunhofer Line Depth (FLD) principle to isolate solar induced F (SIF) from the high resolution R continuum have also been suggested for the large-scale remote assessment of vegetation. The FLD principle was applied to both canopy R spectra and AISA multi-spectral imagery to discriminate the relatively weak in situ vegetation F in-fill of the telluric 02 bands located at 688 nm and 760 nm. The magnitudes of SIF retrieved from R ranged from 7 to 36 mW/m(2)/nm/sr and the ratio of the two spectral bands successfully discriminated the four N treatment levels. In addition, a number of R indices including but not limited to the physiological reflectance index (PRI), R-550/R-515 and R-750/R-800 were calculated from the AISA aircraft imagery and the high-resolution canopy R spectra. These indexes were then evaluated against geo-referenced ground measurements of leaf area index (LAI), pigment contents, grain yields, and light use efficiency (LUE). A number of significant relationships were evident in both R and SIT indices to the biophysical changes in corn induced by N application rates. From this investigation we conclude that valuable SIF information can be extracted from high-resolution canopy R data and indices calculated from both data types can supply useful information for modeling N use for carbon sequestration by vegetation. C1 [Corp, L. A.] Sci Syst & Applicat Inc, Lanham, MD USA. [Middleton, E. M.] NASA, Goddard Space Flight Ctr, Hydrospher & Biospher Sci Lab, Greenbelt, MD USA. [Daughtry, C. S. T.] USDA ARS, Hydrol & Remote Sensing Lab, Beltsville, MD USA. [Campbell, P. K. Entcheva] UMBC, Joint Ctr Earth Syst Technol, Baltimore, MD USA. RP Corp, LA (reprint author), Sci Syst & Applicat Inc, Lanham, MD USA. EM lcorp@hydrotab.arsusda.gov RI Campbell, Petya/G-4931-2013; Campbell, Petya/L-7486-2013 OI Campbell, Petya/0000-0002-0505-4951; Campbell, Petya/0000-0002-0505-4951 NR 11 TC 1 Z9 1 U1 0 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 2267 EP + DI 10.1109/IGARSS.2006.586 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401178 ER PT S AU Walthall, CL Daughtry, CST Pachepsky, L Erbe, EF Lydon, J Higgins, MK Vanderbilt, VC Bobbe, T AF Walthall, Charles L. Daughtry, Craig S. T. Pachepsky, Ludmila Erbe, Eric F. Lydon, John Higgins, Melinda K. Vanderbilt, Vern C. Bobbe, Thomas GP IEEE TI Detection of Illegal Cannabis Cultivation Using Remote Sensing SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE Cannabis; illegal cultivations; spectral signature; spatial signature; specular reflectance; image texture AB Detection of illegal Cannabis cultivation by law enforcement agencies currently relies on low flying aircraft manned by trained aerial spotters. This is physically tiring for the aircrew, inefficient for large or complex landscapes, and is often foiled by camouflaged grow sites. A solution for detecting illegal Cannabis cultivation using remote sensing would be of considerable assistance and may increase the probability of detection. If multiple plants are grown in large homogeneous plots and the location of at least one cultivation site is known, then detection can be considered a traditional spectral land cover/land use classification problem. Probability of success is principally dependent upon the degree to which the known grow site is representative of unknown sites, and the adequacy of the sensor system spatial resolution. However, most illegal cultivation sites in the U.S. are "distributed" with a few isolated plants interspersed with other plant species. For distributed cultivations, requirements for high spatial resolution imagery become paramount and an alternative signature approach may be warranted. Analysis of Cannabis diffuse, nadir spectral signatures using laboratory, field and airborne data show a lack of stable, unique absorption features to use as a universal reference signature. However, Cannabis leaves appear to have a specular reflectance feature that contributes to the "emerald green" appearance reported by aerial spotters. This specular signature may be worthy of exploitation for detection. The leaf shape and plant architecture of Cannabis also offer potential spatial signatures that can be quantified using image texture analysis. These spatial signatures also warrant further investigation C1 [Walthall, Charles L.; Daughtry, Craig S. T.; Pachepsky, Ludmila; Erbe, Eric F.; Lydon, John] USDA ARS, Beltsville, MD USA. [Higgins, Melinda K.] Georgia Tech Res Inst, Atlanta, GA USA. [Vanderbilt, Vern C.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Bobbe, Thomas] USDA FS, Salt Lake City, UT USA. RP Walthall, CL (reprint author), USDA ARS, Beltsville, MD USA. EM ewalthall@hydrolab.arsusda.gov FU ONDCP Interagency Agreement [1010A1265017] FX The authors thank Andrew Russ (USDA-ARS) and Monisha Kaul (now EPA) for assistance with data collection and image processing. Thanks also to Lt. Col. Billy Asbell (National Guard Bureau Executive Services), Major Mike Thomas (National Guard-Ret.), CW3 Sam Thomas (Maryland National Guard), Wayne Davenport (Army Space and Missile Command), John Kershenstein (Naval Research Laboratory), Jan Kalshoven (NASA), Sgt. Harry McDaniel (Maryland State Police) and Dave Broadway (Florida Department of Law Enforcement). This research was partially funded by ONDCP Interagency Agreement 1010A1265017. NR 8 TC 1 Z9 1 U1 0 U2 9 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 2281 EP + DI 10.1109/IGARSS.2006.590 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401182 ER PT S AU Piepmeier, JR Pellerano, FA AF Piepmeier, J. R. Pellerano, F. A. GP IEEE TI Mitigation of Terrestrial Radar Interference in L-Band Spaceborne Microwave Radiometers SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci ID SOIL-MOISTURE AB Terrestrial radars operating in the 1215-1400 MHz radio-location and navigation spectrum allocation are important for air traffic safety, homeland security, and national defense. For low-frequency observations of soil moisture and ocean salinity, Earth-observing microwave radiometers are allocated Earth-Exploration Satellite Service (EESS;) spectrum for operating at 1400-1427 MHz. The proximity of powerful long-range radars to the passive allocation makes observing a challenge. Three aspects of mitigation to RFI are discussed in this paper: survivability, operability, and excisability (SOE). Modeling and simulations of NASA's Hydros and Aquarius radiometers were performed to examine the impacts of radar interference. The results are applied to the three aspects of mitigation SOE and the affects on the radiometer requirements are! discussed. C1 [Piepmeier, J. R.; Pellerano, F. A.] NASA, Goddard Space Flight Ctr, Microwave Instrument Technol Branch, Greenbelt, MD 21146 USA. RP Piepmeier, JR (reprint author), NASA, Goddard Space Flight Ctr, Microwave Instrument Technol Branch, Greenbelt, MD 21146 USA. EM jeff.piepmeier@nasa.gov NR 18 TC 7 Z9 7 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 2292 EP 2296 DI 10.1109/IGARSS.2006.593 PG 5 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401185 ER PT S AU Hudson, DL Piepmeier, JR Long, DG AF Hudson, Derek L. Piepmeier, Jeffrey R. Long, David G. GP IEEE TI Polarization Rotation Correction in Radiometry: An Extended Error Analysis SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci AB Yueh [1] proposed a method of using the third Stokes parameter, T-U, to correct brightness temperatures, such as T-v and T-h for polarization rotation. This paper presents an extended error analysis of the retrieval of T-Q equivalent to T-v - T-h by Yueh's method. Analytical formulas are derived for the bias, standard deviation, and mean-squared error (MSE) of retrieved TQ, as functions of scene and radiometer parameters. These formulas are validated through independent calculation via Monte Carlo simulation. The formulas predict several interesting effects: (a) MSE is minimized by rotating the radiometer by 45 degrees with respect to the natural polarization basis defined by the Earth's surface, (b) T-U from planetary surface radiation (of the magnitude expected on Earth) has a negligible effect on correction for polarization rotation, and (c) three-channel polarimetric radiometry (with the radiometer rotated by 45 degrees) has lower MSE than conventional two-channel radiometry that suffers no polarization rotation. C1 [Hudson, Derek L.; Long, David G.] Brigham Young Univ, Provo, UT 84602 USA. [Piepmeier, Jeffrey R.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Hudson, DL (reprint author), Brigham Young Univ, Provo, UT 84602 USA. EM dlh8@et.byu.edu RI Long, David/K-4908-2015 OI Long, David/0000-0002-1852-3972 NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 2305 EP + DI 10.1109/IGARSS.2006.596 PG 3 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401188 ER PT S AU Pagano, TS Chahine, MT Aumann, HH Tian, BJ Lee, SY Olsen, E Lambrigtsen, B Fetzer, E Irion, FW Fu, XH McMillan, W Strow, L Barnet, C Goldberg, M Susskind, J Blaisdell, J AF Pagano, Thomas S. Chahine, Moustafa T. Aumann, Hartmut H. Tian, Baijun Lee, Sung-Yung Olsen, Ed Lambrigtsen, Bjorn Fetzer, Eric Irion, F. W. Fu, Xiouhua McMillan, Wallace Strow, Larrabee Barnet, Chris Goldberg, Mitch Susskind, Joel Blaisdell, John GP IEEE TI Remote Sensing of Atmospheric Climate Parameters from the Atmospheric Infrared Sounder SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE Atmosphere; Infrared; Weather Forecasting; Climate Models AB This paper presents the standard and research products from Atmospheric Infrared Sounder (AIRS) and their current accuracies as demonstrated through validation efforts. It also summarizes ongoing research using AIRS data for weather prediction and improving climate models. C1 [Pagano, Thomas S.; Chahine, Moustafa T.; Aumann, Hartmut H.; Tian, Baijun; Lee, Sung-Yung; Olsen, Ed; Lambrigtsen, Bjorn; Fetzer, Eric; Irion, F. W.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [McMillan, Wallace; Strow, Larrabee] Univ Maryland Baltimore Cty, Baltimore, MD 21228 USA. [Fu, Xiouhua] Univ Hawaii, IPRC, Honolulu, HI 96822 USA. [Susskind, Joel; Blaisdell, John] NASA Goddard Space Flight Ctr, Greenbelt, MD USA. [Barnet, Chris; Goldberg, Mitch] NOAA NESDIS Satellite Meteorolo & Climat, Baltimore, MD USA. RP Pagano, TS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 10 TC 5 Z9 5 U1 1 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 2386 EP + DI 10.1109/IGARSS.2006.618 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401210 ER PT S AU Pagano, TS Chahine, MT Aumann, HH O'Callaghan, FG Broberg, SE AF Pagano, Thomas S. Chahine, Moustafa T. Aumann, Hartmut H. O'Callaghan, Fred G. Broberg, Steve E. GP IEEE TI Advanced Remote-sensing Imaging Emission Spectrometer (ARIES): AIRS Spectral Resolution with MODIS Spatial Resolution SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE Remote Sensing; Spectrometer; MODIS; AIRS AB This paper describes a space based instrument concept that will provide scientists with data needed to support key ongoing and future Earth System Science investigations. The measurement approach builds on the observations made by AIRS and MODIS and exceeds their capability with improved spatial and spectral resolution. This paper describes the expected products and the instrument concept that can meet those requirements C1 [Pagano, Thomas S.; Chahine, Moustafa T.; Aumann, Hartmut H.; O'Callaghan, Fred G.; Broberg, Steve E.] 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. EM Thomas.S.Pagano@jpl.nasa.gov NR 6 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 2390 EP 2393 DI 10.1109/IGARSS.2006.619 PG 4 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401211 ER PT S AU Memarsadeghi, N Le Moigne, J Mount, DM AF Memarsadeghi, Nargess Le Moigne, Jacqueline Mount, David M. GP IEEE TI Image Fusion Using Cokriging SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci ID LANDSAT TM; MULTIRESOLUTION C1 [Memarsadeghi, Nargess; Le Moigne, Jacqueline] NASA, Goddard Space Flight Ctr, Code 588, Greenbelt, MD 20771 USA. [Mount, David M.] Univ Maryland, College Pk, MD 20742 USA. RP Memarsadeghi, N (reprint author), NASA, Goddard Space Flight Ctr, Code 588, Greenbelt, MD 20771 USA. EM nargess@cs.umd.edu; Jacqueline.LeMoigne@nasa.gov; mount@cs.umd.edu NR 14 TC 6 Z9 6 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 2518 EP + DI 10.1109/IGARSS.2006.651 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401243 ER PT S AU Tanner, AB Lambrigsten, BH Gaier, TM Torres, F AF Tanner, A. B. Lambrigsten, B. H. Gaier, T. M. Torres, F. GP IEEE TI Near field characterization of the GeoSTAR demonstrator SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE remote sensing; radiometer; interferometer; near field ID APERTURE SYNTHESIS AB The GeoSTAR proof of concept demonstrator can be characterized at close range by means of a simple near-to-far-field phase correction. This reduces the test set-up configuration to reasonable dimensions. In order to simulate the Earth as seen from GEO, the target consists of a disc of absorbent material at ambient temperature placed against the sky. This work presents the details of the near-to-far-field correction as well as sonic preliminary results that confirm its suitability to characterize the demonstrator. C1 [Tanner, A. B.; Lambrigsten, B. H.; Gaier, T. M.] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. [Torres, F.] Politech Univ Catalonia, Dept Signal Theory & Commun, Barcelona, Spain. RP Tanner, AB (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. EM alan.b.tanner@jpl.nasa.gov; xtorres@tsc.upc.edu RI Torres, Francesc/D-7587-2013 OI Torres, Francesc/0000-0003-1160-6350 NR 6 TC 8 Z9 10 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 2529 EP + DI 10.1109/IGARSS.2006.654 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401246 ER PT S AU Simard, M Rodriguez, E AF Simard, Marc Rodriguez, Ernesto GP IEEE TI Real-Time Processing Algorithm for Wide Swath Radar Interferometry of Ocean Surface SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci AB We describe a real-time radar processing algorithm for radar interferometry of Ocean surface with a Wide Swath Ocean Altimeter: a real aperture radar interferometer concept to measure Ocean surface topography on a 200km swath. The algorithm compresses the input data by a factor of over 7000 and improves interferometric correlation by approximating the viewing geometry. It takes into account continuous changes in the viewing geometry due to the Earth's Geoid modeled as a table of n(th) order polynomials called the viewing scenario table. Each polynomial models a segment of the orbit and approximates how the distance between the platform and the ground varies as a function of time. Various algorithm parameters are updated regularly to compensate for the changes in the viewing geometry. These updates are implemented as time shifts to coregister successive data rangelines and frequency shifts to correct effects related to geometric decorrelation. C1 [Simard, Marc; Rodriguez, Ernesto] CALTECH, Jet Prop Lab, Pasadena, CA 90068 USA. RP Simard, M (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 90068 USA. EM marc.simard@jpl.nasa.gov OI Simard, Marc/0000-0002-9442-4562 NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 2538 EP 2541 DI 10.1109/IGARSS.2006.656 PG 4 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401248 ER PT S AU Kenyi, L Dubayah, R Hofton, M Hyde, P Blair, JB AF Kenyi, Lado Dubayah, Ralph Hofton, Michelle Hyde, Peter Blair, J. Bryan GP IEEE TI Comparison of Forest Canopy Structures in SRTM to LIDAR Data SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci AB Forest canopy height derived from the SRTM 30m grid DEM were compared to LVIS and ICESAT footprint data of three US sites, namely Sierra Nevada in California, Coweeta in North Carolina and Hubbard Brook in New Hampshire. It was found that in dense forest, such as the Coweeta forest, the SRTM data better estimate forest canopy height. By modeling the SRTM estimated mean canopy heights, the RMSE was found to improve significantly. In comparison to LVIS, the RMSE was reduced from 12.25m to 8.92m, 12.57m to 7.61m and 9.21m to 4.85m, respectively for the Sierra, Coweeta and Hubbard Brook sites. For the ICESAT data of the Sierra site, the RMSE was reduced from 15.49m to 8.75m. C1 [Kenyi, Lado; Dubayah, Ralph; Hofton, Michelle; Hyde, Peter] Univ Maryland, Dept Geog, 2181 Lefrak Hall, College Pk, MD 20742 USA. [Kenyi, Lado] Inst Digital Image Proc, Joanneum Res, A-8010 Graz, Austria. [Blair, J. Bryan] NASA, Goddard Space Flight Ctr, Terr Phys Lab, Greenbelt, MD 20771 USA. RP Kenyi, L (reprint author), Univ Maryland, Dept Geog, 2181 Lefrak Hall, College Pk, MD 20742 USA. RI Khachadourian, Diana/C-8513-2012; Blair, James/D-3881-2013 FU EU Marie Curie Outgoing Research Fellowship FX Lado Kenyi is being supported by the EU Marie Curie Outgoing Research Fellowship. NR 6 TC 0 Z9 0 U1 0 U2 5 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 2670 EP + DI 10.1109/IGARSS.2006.689 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401281 ER PT S AU Marshall, JJ Gerard, R Samadi, S Wolfe, RE AF Marshall, James J. Gerard, Ryan Samadi, Shahin Wolfe, Robert E. GP IEEE TI A Study of Earth Science Software Reuse Enablement Systems SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE Software reuse; repository systems; Earth science; SEEDS; NASA AB The reuse of software assets can be critical to the development of large-scale software projects where budget and reliability are paramount. Yet many of the benefits of software reuse are either not recognized or overlooked. The majority of software assets are not made available to peers or a wider community. Therefore, a key activity in promoting software reuse is the initiative to increase the awareness of reuse enablement systems. An ideal Earth science reuse enablement system should ensure that reusable software assets are readily available to the software developers who want to use them to build new or enhance existing Earth science applications. This can be done by placing the assets into a software catalog or repository system. Many such systems exist, mostly outside of the Earth science domain, each designed for a particular purpose. Some are domain-specific, covering one particular subject area, while others are more general, covering a large variety of fields. Each is well-designed for its target audience. Many candidate systems that exist provide open-source software solutions. However, user goals, quality control, and overall usability determine the usefulness of a system to the community of Earth science software developers. The software used to create these systems also varies, ranging from standard HTML to full repository software packages like Repository in a Box (RIB), which uses the Basic Interoperability Data Model (BIDM), IEEE Standard 1420.1. The NASA Earth Science Data System (ESDS) Software Reuse Working Group has examined a variety of these systems, and focused on their applicability to the Earth science domain. Within a set of requirements designed for the Earth science community, this paper compares selected features of these systems, such as providing reviews for assets or the software used to design the site, and how the presence or absence of these features affects the system's ability to promote reuse. C1 [Marshall, James J.; Gerard, Ryan; Samadi, Shahin; Wolfe, Robert E.] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. RP Marshall, JJ (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. EM james.marshall@gsfc.nasa.gov; ryan.gerard@gsfc.nasa.gov; shahin.samadi@gsfc.nasa.gov; robert.e.wolfe@nasa.gov RI Wolfe, Robert/E-1485-2012; Marshall, James/A-9611-2009 OI Wolfe, Robert/0000-0002-0915-1855; Marshall, James/0000-0002-6867-5616 NR 4 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 2832 EP 2835 DI 10.1109/IGARSS.2006.728 PG 4 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401320 ER PT S AU Schaepman-Strub, G Schaepman, ME Martonchik, J Schaaf, C AF Schaepman-Strub, G. Schaepman, M. E. Martonchik, J. Schaaf, C. GP IEEE TI What's in a satellite albedo product? SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE Albedo; BHR; DHR; BRDF; Broadband Albedo ID BIDIRECTIONAL REFLECTANCE; SURFACE ALBEDO; BRDF MODELS; RETRIEVAL; SENSITIVITY; ALGORITHM; MODIS AB Land surface albedo is one of the key drivers of the Earth's terrestrial surface energy budget. Surface Albedo products derived from satellite observations are increasingly being used as input to climate modelling. The derivation of surface albedo is a multidimensional challenge, whereas the sensor-specific calculation relies not only on the configuration of the observation, but also on angular models for inter- and extrapolation of the reflectance quantities to illumination and view angles not sampled by the satellite observations, as well as spectral conversion algorithms. While either combining albedo data from different sources or comparing studies relying on different albedo products, the above factors contribute to a bias and consequently to additional uncertainties. It is thus important to provide all relevant information of the albedo product generation, helping users to reduce uncertainties and enabling to link the different types of albedo in a physically consistent way. We are presenting a standardized description, exemplified using a selection of operational satellite products (i.e., MODIS, MISR). This effort will be continued through adding surface albedo products from instruments such as MERIS, POLDER, VEGETATION, and geostationary satellites. C1 [Schaepman-Strub, G.; Schaepman, M. E.] Univ Wageningen & Res Ctr, Wageningen, Netherlands. [Martonchik, J.] Jet Prop Lab, Pasadena, CA USA. [Schaaf, C.] Boston Univ, Boston, MA 02215 USA. RP Schaepman-Strub, G (reprint author), Univ Wageningen & Res Ctr, Wageningen, Netherlands. EM gabriela.schaepman@wur.nl RI Schaepman-Strub, Gabriela/D-8785-2011; Schaepman, Michael/B-9213-2009 OI Schaepman, Michael/0000-0002-9627-9565 FU European Space Agency external fellowship FX G. Schaepman-Strubs work was carried out in the framework of a European Space Agency external fellowship. NR 18 TC 1 Z9 1 U1 1 U2 5 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 2848 EP + DI 10.1109/IGARSS.2006.732 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401324 ER PT S AU Marshall, JJ Olding, SW Wolfe, RE Delnore, VE AF Marshall, James J. Olding, Stephen W. Wolfe, Robert E. Delnore, Victor E. GP IEEE TI Software Reuse Within the Earth Science Community SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE Software reuse; Earth science; SEEDS; NASA AB Scientific missions in the Earth sciences frequently require cost-effective, highly reliable, and easy-to-use software, which can be a challenge for software developers to provide. The NASA Earth science community spends a significant amount of resources developing software components and other software development artifacts that may also be of value if reused in other projects requiring similar functionality. In general, software reuse is often defined as utilizing existing software artifacts. Software reuse can improve productivity and quality while decreasing the cost of software development, as documented by case studies in the literature. Since large software systems are often the results of the integration of many smaller and sometimes reusable components, ensuring reusability of such software components becomes a necessity. Indeed, designing software components with reusability as a requirement can increase the software reuse potential within a community such as the NASA Earth science community. The NASA Earth Science Data Systems (ESDS) Software Reuse Working Group is chartered to oversee the development of a process that will maximize the reuse potential of existing software components while recommending strategies for maximizing the reusability potential of yet-to-be-designed components. As part of this work, two surveys of the Earth science community were conducted. The first was performed in 2004 and distributed among government employees and contractors. A follow-up survey was performed in 2005 and distributed among a wider community, to include members of industry and academia. The surveys were designed to collect information on subjects such as the current software reuse practices of Earth science software developers, why they choose to reuse software, and what perceived barriers prevent them from reusing software. In this paper, we compare the results of these surveys and discuss the findings, including the difference between the components desired for reuse and those made available for reuse. The results are very similar, with the second, larger survey confirming the basic results of the first, smaller survey. The results suggest that reuse of Earth science software can drive down the cost and time of system development, increase flexibility and responsiveness of these systems to new technologies and requirements, and increase effective and accountable community participation. C1 [Marshall, James J.; Olding, Stephen W.; Wolfe, Robert E.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Delnore, Victor E.] NASA, Langley Res Ctr, Hampton, VA 23666 USA. RP Marshall, JJ (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM james.marshall@gsfc.nasa.gov; solding@everware.com; robert.e.wolfe@nasa.gov; v.e.delnore@nasa.gov RI Wolfe, Robert/E-1485-2012; Marshall, James/A-9611-2009 OI Wolfe, Robert/0000-0002-0915-1855; Marshall, James/0000-0002-6867-5616 NR 4 TC 2 Z9 2 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 2880 EP + DI 10.1109/IGARSS.2006.740 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401332 ER PT S AU Ito, S Kobayashi, S Oguchi, T AF Ito, Shigeo Kobayashi, Satoru Oguchi, Tomohiro GP IEEE TI A New Approach to Backscattering of Pulsed Beam Waves from Hydrometers SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci ID MULTIPLE-SCATTERING; RAIN AB This paper deals with the backscattering of millimeter pulsed beam waves from hydrometeors. A new approach is presented for a solution of the time-dependent three dimensional vector radiative transfer equation for the Stokes vectors to discuss the multiple scattering effects of beam waves on radar echoes. General solutions including multiple scattering for beam waves are then derived explicitly in an integral form without any approximation. Time dependent second-order solutions for the radar echoes of pulsed beam waves are obtained to predict the multiple scattering effects depending on the variation in an incident beam size. It is shown that the inhomogeneity of the radial direction of beam waves causes the mode coupling of waves between the azimuth directions in the scattering matrix and that the mode coupling depends on the ratio of the incident beam size to the mean free path length of the medium. C1 [Ito, Shigeo] Toyo Univ, Kawagoe, Saitama 3508585, Japan. [Kobayashi, Satoru] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. [Oguchi, Tomohiro] Kanto Gakuin Univ, Kanazawa, Ishikawa 236-8501, Japan. RP Ito, S (reprint author), Toyo Univ, Kawagoe, Saitama 3508585, Japan. EM ito@eng.toyo.ac.jp; satoru@radar-sci.jpl.nasa.gov NR 10 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 2935 EP + DI 10.1109/IGARSS.2006.754 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989401346 ER PT S AU Xiong, X Salomonson, VV Chiang, K Chen, N Xiong, S Barnes, WL Guenther, B AF Xiong, X. Salomonson, V. V. Chiang, K. Chen, N. Xiong, S. Barnes, W. L. Guenther, Bruce GP IEEE TI Summary of Terra MODIS Thermal Emissive Bands On-orbit Calibration SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci ID PERFORMANCE AB Terra MODIS has been in operation for more than 6 years since its launch in December 1999. It has been continuously making global observations for scientific studies of the Earth system and its environment and climate changes. MODIS has 20 reflective solar bands (RSB) and 16 thermal emissive bands (TEB). An on-board blackbody (BB) is used on a scan-by-scan basis for the TEB on-orbit calibration. Another on-board calibrator, a spectro-radiometric calibration assembly (SRCA), is operated periodically for the sensor's spatial and spectral characterization. This paper provides an overview of Terra MODIS TEB calibration algorithms, operational activities and strategies. Results presented include TEB detector noise characterization, functionality, and stability derived using on-orbit observations made from the beginning of the mission to present. Excluding a few noisy detectors, the Terra MODIS TEB performance meets the design requirements, thereby assuring calibration accuracy and science data product quality. C1 [Xiong, X.; Salomonson, V. V.] NASA, Goddard Space Flight Ctr, Sci Explorat Directorate, Greenbelt, MD 20771 USA. [Chiang, K.; Chen, N.; Xiong, S.] Sci Syst & Applicat Inc, Lanham, MD 20706 USA. [Barnes, W. L.; Guenther, Bruce] Univ Maryland, Baltimore, MD 21250 USA. RP Xiong, X (reprint author), NASA, Goddard Space Flight Ctr, Sci Explorat Directorate, Greenbelt, MD 20771 USA. EM Xiaoxiong.Xiong-1@nasa.gov; Vincent.V.Salmonson@nasa.gov; Kwo-Fu_Chaing@ssaihq.com; Na_Chen@ssaihq.com; Sanxiong_Xiong@ssaihq.com; wbarnes@neotune.gsfc.nasa.gov; guenther@ltpmail.gsfs.nasa.gov RI Xiong, Xiaoxiong (Jack)/J-9869-2012 NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 3228 EP + DI 10.1109/IGARSS.2006.829 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989402015 ER PT S AU Ullman, RE Enloe, Y AF Ullman, Richard E. Enloe, Yonsook GP IEEE TI Accelerating Technology Adoption Through Community Endorsement SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE best practices; standards AB The idea that cross-discipline data interuse is a necessity for Earth systems science studies is now widely accepted, but data interoperability has been an elusive goal. The remote sensing community has a talented cohort of innovative developers of data and information technologies. However, despite the high level of innovation, progress on wide scale practical interuse has not been as rapid as expected. The usefulness of data interuse technologies requires adoption of these same visionary technologies on a wide scale. Thus adoption of technologies to enable wider interdisciplinary investigation faces similar challenges as adoption of technology products in the commercial marketplace. Bringing a new technology from innovative use by visionary practitioners to popular use by more pragmatically oriented users has come to be called "crossing the chasm". NASA's Earth Science Data Systems Working Group has been applying communications methodologies to bridge this adoption chasm within the agency. We have developed a process inspired by the successful model of the Internet "Request for Comments". The central idea of the RFC is notification to the wider community of specific detailed ideas that potentially affect interoperation of data and services though the Internet. Sharing ideas through the RFC mechanism has spurred adoption of Internet technologies and fostered collaboration in the development of Internet standards. NASA's Standards Process Group (SPG) seeks the same result in the domain of Earth science data systems. C1 [Ullman, Richard E.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20546 USA. [Enloe, Yonsook] SGT Inc, Greenbelt, MD USA. RP Ullman, RE (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20546 USA. EM richard.e.ullman@nasa.gov; yonsook@mindspring.com NR 5 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 3474 EP + DI 10.1109/IGARSS.2006.891 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989402077 ER PT S AU Ramapriyan, H Isaac, D Yang, W Bonnlander, B Danks, D AF Ramapriyan, H. Isaac, D. Yang, W. Bonnlander, B. Danks, D. GP IEEE TI An Intelligent Archive Testbed Incorporating Data Mining - Lessons and Observations SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci AB The advances of the last two decades in remote sensing instruments, computational, storage and communications hardware, and launches of a series of Earth observing satellites by U.S. and international agencies, have created a data rich environment for scientific research and applications. NASA's Earth Observing System (EOS) Data and Information System (EOSDIS) has now been operational for over 11 years, and has been effectively capturing, processing, archiving and distributing a few tera-bytes of standard data products each day to a diverse and globally distributed user community and, along with other NASA sponsored data system activities, forming a "value chain" for users to obtain valuable data. Visions for the future include a highly distributed system of data and service providers and users' being able to locate, fuse and utilize data with location transparency and high degree of interoperability, and being able to convert data to information and usable knowledge in an efficient, convenient manner, aided significantly by automation. We can look upon the distributed provider environment with capabilities to convert data to information and to knowledge as an Intelligent Archive in the Context of a Knowledge Building system (IA/KBS). There have been several research investigations into intelligent data understanding including data mining and knowledge discovery. However, these investigations typically perform proofs of concept on a relatively small scale. Before their contributions can be implemented on a large scale commensurate with today's Earth science data archives, it is necessary to test them in a pseudo-operational environment. The purpose of this paper is to describe a testbed that serves this purpose and discuss some of the observations and lessons learned from its implementation. C1 [Ramapriyan, H.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Isaac, D.] Business Performence Syst, Falls Church, VA USA. [Yang, W.] George Mason Univ, Lab Adv Informat Technol & Standards, Greenbelt, MD USA. [Bonnlander, B.] Inst Human Mach Cognit, Pensacola, FL USA. [Danks, D.] Carnegie Mellon Univ, Pittsburgh, PA USA. RP Ramapriyan, H (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. FU NASA George Mason University [NCC5-645] FX This work was performed by the first author as part of his duties as a U.S. Government employee. The remaining authors worked in support of this effort under Cooperative Agreement NCC5-645 between NASA and George Mason University. The opinions expressed are those of the authors and do not necessarily reflect the official position of NASA. NR 6 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 3482 EP + DI 10.1109/IGARSS.2006.893 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989402079 ER PT S AU Rienecker, MM Suarez, MJ Koster, RD Reichle, R Keppenne, C Adamec, D Schubert, SD AF Rienecker, Michele M. Suarez, Max J. Koster, Randal D. Reichle, Rolf Keppenne, Christian Adamec, David Schubert, Siegfried D. GP IEEE TI Improving Short-term Climate Forecasts with Satellite Observations SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE El Nino; satellite data; seasonal forecasts AB Understanding and predicting seasonal-to-interannual climate variations is a central goal within U.S. climate research. At NASA's Global Modeling and Assimilation Office, we are developing a coupled model forecast system to optimize the use of existing and planned satellite data, together with in situ observations, for experimental predictions of short-term climate variations. Our focus is on using satellite data to initialize the ocean and land surface, the slower components of the climate system that have the potential memory to enhance climate prediction. C1 [Rienecker, Michele M.; Suarez, Max J.; Koster, Randal D.; Reichle, Rolf; Keppenne, Christian; Adamec, David; Schubert, Siegfried D.] NASA, Goddard Space Flight Ctr, Global Modeling & Assimilat Off, Greenbelt, MD 20771 USA. RP Rienecker, MM (reprint author), NASA, Goddard Space Flight Ctr, Global Modeling & Assimilat Off, Greenbelt, MD 20771 USA. RI Reichle, Rolf/E-1419-2012; Koster, Randal/F-5881-2012 OI Koster, Randal/0000-0001-6418-6383 NR 6 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 3498 EP 3501 DI 10.1109/IGARSS.2006.897 PG 4 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989402083 ER PT S AU Jedlovec, G Goodman, S Goodman, M Lapenta, B AF Jedlovec, Gary Goodman, Steve Goodman, Michael Lapenta, Bill GP IEEE TI Use of Earth Observing System Data in Weather Forecasting SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE GEOSS; IEOS; MODIS; AIRS; AMSR-E AB The U.S. contribution to Global Earth Observation Systems of Systems (GEOSS) is the Integrated Earth Observing System (IEOS). The GEOSS and IEOS will facilitate the sharing and applied usage of global, regional, and local data from satellites, ocean buoys, weather stations, and other surface and airborne Earth observing instruments. Sensors on current NASA EOS polar orbiting satellites are making unique global observations of the land surface, biosphere, solid Earth, atmosphere, and oceans to enable an improved understanding of the Earth as an integrated system. Many of these datasets are being used to improve weather forecasts on the global, regional, and local scale by providing a better depiction of changing environmental conditions, through model initialization and direct data assimilation. C1 [Jedlovec, Gary; Goodman, Steve; Goodman, Michael; Lapenta, Bill] NASA, George C Marshall Space Flight Ctr, Earth Sci Off, Huntsville, AL 35805 USA. RP Jedlovec, G (reprint author), NASA, George C Marshall Space Flight Ctr, Earth Sci Off, VP61,320 Sparkman Dr, Huntsville, AL 35805 USA. EM gary.jedlovec@nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 3502 EP 3505 DI 10.1109/IGARSS.2006.898 PG 4 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989402084 ER PT S AU van Leeuwen, WJD Hutchinson, CF Sheffner, E Doorn, B Kaupp, VH AF van Leeuwen, Willem J. D. Hutchinson, Charles F. Sheffner, Ed Doorn, Brad Kaupp, Verne H. GP IEEE TI Integrated Crop Production Observations and Information System SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE Agriculture; Decision Support Data and Tools AB The US Department of Agriculture (USDA), the National Aeronautics and Space Administration (NASA) and several academic institutions partnered in transitioning selected NASA Earth science data products, knowledge, capacity, and systems into solutions to enhance a decision support system (DSS) of the Foreign Agricultural Services (FAS) Production Estimates and Crop Assessment Division (PECAD). This enhancement improves PECAD's decision support to the World Agricultural Outlook Board (WAOB) by providing improved monthly estimates of global production (based on crop yield and planted area) of selected agricultural commodities. C1 [van Leeuwen, Willem J. D.; Hutchinson, Charles F.] Univ Arizona, Off Arid Lands Studies & Geog, Tucson, AZ 85721 USA. [Doorn, Brad] USDA, FAS PECAD, Washington, DC USA. [Sheffner, Ed] NASA HQ, Washington, DC USA. [Kaupp, Verne H.] Univ Missouri, Elect Engn, Columbia, MO 65211 USA. RP van Leeuwen, WJD (reprint author), Univ Arizona, Off Arid Lands Studies & Geog, Tucson, AZ 85721 USA. EM leeuw@ag.arizona.edu; chuck@ag.arizona.edu; esheffne@hq.nasa.gov; brad.doorn@fas.usda.gov; kauppv@missouri.edu FU NASA's Applied Sciences Program FX Sponsored by NASA's Applied Sciences Program NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 3506 EP + DI 10.1109/IGARSS.2006.899 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989402085 ER PT S AU Toll, DL Engman, E Arsenault, K Friedl, L Peters-Lidard, C Pinheiro, A Nigro, J Triggs, J AF Toll, David L. Engman, Edwin Arsenault, Kristi Friedl, Lawrence Peters-Lidard, Christa Pinheiro, Ana Nigro, Joe Triggs, Jonathan GP IEEE TI Protect and Monitor Water Resources SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci AB NASA's Applied Sciences Program (ASP) has the primary responsibility to accelerate the use of NASA data and science results in applications and to help solve problems important to society and the economy. The primary goal of the ASP Program is to improve future and current operational systems by infusing them with scientific knowledge of the Earth system gained through space-based observation, assimilation of new observations, and development and deployment of enabling technologies, systems, and capabilities. This paper describes the NASA's Water Management Applications Program and opportunities for the water resources community to participate. C1 [Toll, David L.] NASA, Goddard Space Flight Ctr, Hydrol Sci Branch 614 3, Greenbelt, MD 20771 USA. [Engman, Edwin] SAIC, Chesapeake, MD USA. [Arsenault, Kristi; Triggs, Jonathan] UMBU GEST, Sarasota, FL USA. [Friedl, Lawrence] NASA HQ, Washington, DC 05350 USA. [Peters-Lidard, Christa] NASA, GSFC, Washington, DC 05350 USA. [Pinheiro, Ana] NASA, GSFC NPP, Washington, DC 05350 USA. SSAI, Boston, MA USA. RP Toll, DL (reprint author), NASA, Goddard Space Flight Ctr, Hydrol Sci Branch 614 3, Greenbelt, MD 20771 USA. EM Dave.toll@nasa.gov NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 3509 EP + DI 10.1109/IGARSS.2006.900 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989402086 ER PT S AU Haynes, JA Venezia, RA AF Haynes, John A. Venezia, Robert A. GP IEEE TI Understanding the Effects of Environmental Factors on Human Health and Well-Being through NASA Earth Science Research Results SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE Decision Support; Satellite; Global; Modeling; Meteorology; Climate AB As one of the twelve areas of national priority for the National Aeronautics and Space Administration's (NASA's) Applied Sciences Program the Public Health Program Element http://science.hq.nasa.gov/earth-sun/applications/theme11.html extends the benefits of increased knowledge and capabilities resulting from NASA research and development of Earth-Sun spacecraft observations, model predictive capabilities, and technology, into partners' decision support systems for public health, medical, and environmental health issues. Through the Public Health Program, NASA and partnering organizations have built a network that focuses on the relationships between NASA Earth observation systems, modeling systems, and partner-led decision support systems for epidemiologic surveillance in the areas of infectious disease, environmental health, and bioterrorism. C1 [Haynes, John A.] NASA, Appl Sci Program, Washington, DC 20546 USA. [Venezia, Robert A.] NASA, John C Stennis Space Cter, Stennis Space Ctr, MS USA. RP Haynes, JA (reprint author), NASA, Appl Sci Program, Washington, DC 20546 USA. EM jhaynes@nasa.gov; Robert.A.Venezia@ssc.nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 3513 EP + DI 10.1109/IGARSS.2006.901 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989402087 ER PT S AU Stackhouse, PW Renne, D Beyer, HG Wald, L Meyer, R Perez, R Suri, M AF Stackhouse, P. W., Jr. Renne, D. Beyer, H. -G. Wald, L. Meyer, R. Perez, R. Suri, M. GP IEEE TI Towards Designing an Integrated Earth Observation System for the Provision of Solar Energy Resource and Assessment SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE energy; solar energy; renewable energy; GEOSS AB The GEOSS strategic plan specifically targets the area of improved energy resource management due to the importance of these to the economic and social viability of every nation of the world. With the world's increasing demand for energy resources, the need for new alternative energy resources grows. This paper overviews a new initiative within the International Energy Agency that addresses needs to better manage and develop solar energy resources worldwide. The goal is to provide the solar energy industry, the electricity sector, governments, and renewable energy organizations and institutions with the most suitable and accurate information of the solar radiation resources at the Earth's surface in easily-accessible formats and understandable quality metrics. The scope of solar resource assessment information includes historic data sets and currently derived data products using satellite imagery and other means. Thus, this new task will address the needs of the solar energy sector while at the same time will serve as a model that satisfies GEOSS objectives and goals. C1 [Stackhouse, P. W., Jr.] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Wald, L.] CNRS, Ecole Mines, Ctr Energetique Procedes, F-06904 Paris C, France. [Renne, D.] Natl Renewable Energy Lab, Golden, CO USA. [Meyer, R.] DLR, Inst Atmospher Phys, D-82234 Wessling, Germany. [Beyer, H. -G.] Unit Appl Sci Magdeburg Stendal, Inst Elect Engn, D-39114 Magdeburg, Germany. [Perez, R.] Albany State Univ, Albany, GA 31705 USA. [Suri, M.] DG Joint Res Ctr, European Commiss, Ispra, Italy. RP Stackhouse, PW (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM paul.w.stackhouse@nasa.gov RI Wald, Lucien/C-1284-2009 OI Wald, Lucien/0000-0002-2916-2391 FU NASA Applied Science Program Energy Management Theme; respective governments under the IEA agreement FX Funding for the main authors work is provided through the NASA Applied Science Program Energy Management Theme; Co-author funding is provided through respective governments under the IEA agreement NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 3517 EP + DI 10.1109/IGARSS.2006.902 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989402088 ER PT S AU Jacobs, P Miller, C Wolff, J Sun, XH Coronado, PL Zhang, GQ AF Jacobs, Paul Miller, Christian Wolff, Jared Sun, Xiuhong Coronado, Patrick L. Zhang, Guo-Qiang GP IEEE TI Spectral Decomposition Methods for Hyperspectral Image Compression SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci AB The Spectral Image Decomposition (SPID) compressor uses techniques borrowed from spectral image analysis to achieve a high degree of compression on hyperspectral images. The purpose of this compressor is to provide real-time compression for images captured one line at a time using a "push-broom" method. In addition, the process is aimed at platforms such as satellites where only limited hardware may be deployed; memory, CPU time, and storage space must all be conserved. Spectral image decomposition and temporal differencing techniques were used to achieve a compression ratio of 23:1 in a low error near-lossless mode and 4.25:1 in lossless mode. SPID is a flexible compressor that can provide optimal performance for a variety of objectives. C1 [Jacobs, Paul; Miller, Christian; Wolff, Jared; Zhang, Guo-Qiang] Case Western Reserve Univ, Dept Elect Engn & Comp Sci, Cleveland, OH 44106 USA. [Sun, Xiuhong] FLight Landata Inc, Lawrence, KS 01843 USA. [Coronado, Patrick L.] NASA, Goddard Space Flight Ctr, Appl Informat Sci, Greenbelt, MD 20771 USA. RP Jacobs, P (reprint author), Case Western Reserve Univ, Dept Elect Engn & Comp Sci, Cleveland, OH 44106 USA. FU NASA [NNG05CA91C] FX The authors would like to thank the support of NASA for STTR 2004 Phase I Award NNG05CA91C, under which this project was carried out NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 3529 EP + DI 10.1109/IGARSS.2006.905 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989402091 ER PT S AU Weissman, DE Hristova-Veleva, S Callahan, P AF Weissman, David E. Hristova-Veleva, Svetla Callahan, Philip GP IEEE TI SeaWinds Scatterometer Wind Vector Retrievals Within Hurricanes Using AMSR and NEXRAD To Perform Corrections for Precipitation Effects: Comparison of AMSR and NEXRAD retrievals of rain SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci AB The opportunity provided by satellite scatterometers to measure ocean surface winds in strong storms and hurricanes is diminished by the errors in the received backscatter (SIGMA-0) caused by the attenuation, scattering and surface roughening produced by heavy rain. Providing a good rain correction is a very challenging problem, particularly at Ku band (13.4 GHz) where rain effects are strong. Corrections to the scatterometer measurements of ocean surface winds can be pursued with either of two different methods: empirical or physical modeling. The latter method is employed in this study because of the availability of near Simultaneous and collocated measurements provided by the MIDORI-II suite of instruments. The AMSR was designed to measure atmospheric water-related parameters on a spatial scale comparable to the SeaWinds scatterometer. These quantities can be converted into volumetric attenuation and scattering at the Ku-band frequency of SeaWinds. Optimal estimates of the volume backscatter and attenuation require a knowledge of the three dimensional distribution of reflectivity oil a scale comparable to that of the precipitation. Studies selected near the US coastline enable the much higher resolution NEXRAD reflectivity measurements evaluate the AMSR estimates. We are also conducting research into the effects of different beam geometries and nonuniform beamfilling of precipitation within the field-of-view of the AMSR and the scatterometer. Furthermore, both AMSR and NEXRAD estimates of atmospheric correction can be used to produce corrected SIGMA-0s, which are then input to the JPL wind retrieval algorithm C1 [Weissman, David E.] Hofstra Univ, Hempstead, NY 11768 USA. [Hristova-Veleva, Svetla; Callahan, Philip] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Weissman, DE (reprint author), Hofstra Univ, Hempstead, NY 11768 USA. EM eggdew@hofstra.edu NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 3557 EP + DI 10.1109/IGARSS.2006.912 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989402098 ER PT S AU Yueh, SH AF Yueh, Simon H. GP IEEE TI Polarimetric Microwave Remote Sensing of Hurricane Ocean Winds SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE Sea surface wind; microwave polarimetry; hurricanes ID TROPICAL CYCLONES; MODEL FUNCTION; RADIOMETER AB We presente the analysis of Windsat data for hurricanes Isabel and Fabian in 2003. The polarimetric third and fourth Stokes parameter observations from the Windsat 10, 18 and 37 GHz channels were collocated with the ocean surface winds from the Holland wind model, the QuikSCAT wind vectors and the Global Data Assimilation System (GDAS) operated by the National Center for Environmental Prediction (NCEP). The collocated data were binned as a function of wind speed and wind direction, and were expanded by sinusoidal series of the relative azimuth angles between wind and observation directions. The coefficients of the sinusoidal series, corrected for atmospheric attenuation, have been used to develop an empirical geophysical model function (GMF). The Windsat GMF for extreme high wind compares very well with the aircraft radiometer and radar measurements. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Yueh, SH (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. EM Simon.Yueh@jpl.nasa.gov NR 11 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 3563 EP 3566 DI 10.1109/IGARSS.2006.913 PG 4 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989402099 ER PT B AU Tilton, JC AF Tilton, James C. GP IEEE TI Cloud Mask Generation for MODIS Utilizing Hierarchical Segmentation SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing (IGARSS) LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE image segmentation; image region analysis; image processing; MODIS AB The hierarchical segmentation algorithm (HSEG) is a hybrid of hierarchical step-wise optimization and constrained spectral clustering that produces a hierarchical set of image segmentations. This segmentation hierarchy organizes image data in a manner that makes the image's information content more accessible for analysis by enabling region-based analysis. This paper describes the use of segmentation hierarchies for generating cloud masks from MODIS data, and compares and contrasts these results to the corresponding MODIS standard products. C1 NASA, Goddard Space Flight Ctr, Computat & Informat Sci & Technol Off 606 3, Greenbelt, MD 20771 USA. RP Tilton, JC (reprint author), NASA, Goddard Space Flight Ctr, Computat & Informat Sci & Technol Off 606 3, Greenbelt, MD 20771 USA. EM James.C.Tilton@nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 3708 EP 3711 DI 10.1109/IGARSS.2006.950 PG 4 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989402136 ER PT S AU Chung, YC England, AW De Roo, RD Weininger, E AF Chung, Y. C. England, A. W. De Roo, R. D. Weininger, Etai GP IEEE TI Effects of Vegetation and of Heat and Vapor Fluxes from Soil on Snowpack Evolution and Radiobrightness SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE snow; soil; radiobrightness AB The radiobrightness of a snowpack is strongly linked to the snow moisture content profile, to the point that the only operational inversion algorithms require dry snow. Forward dynamic models do not include the effects of freezing and thawing of the soil beneath the snowpack and the effect of vegetation within the snow or above the snow. To get a more realistic description of the evolution of the snowpack, we reported an addition to the Snow-Soil-Vegetation-Atmosphere-Transfer (SSVAT) model, wherein we coupled soil processes of the Land Surface Process (LSP) model with the snow model SNTHERM. In the near future we will be adding a radiobrightness prediction based on the modeled moisture, temperature and snow grain size profiles. The initial investigations with this SSVAT for a late winter and early spring snow pack indicate that soil processes warm the snowpack and the soil. Vapor diffusion needs to be considered whenever the ground is thawed. In the early spring, heat flow from the ground into a snow and a strong temperature gradient across the snow lead to thermal convection. The buried vegetation can be ignored for a late winter snow pack. The warmer surface snow temperature will affect radiobrightness since it is most sensitive to snow surface characteristics. Comparison to data shows that SSVAT provides a more realistic representation of the temperature and moisture profiles in the snowpack and its underlying soil than SNTHERM. The radiobrightness module will be optimized for the prediction of brightness when the snow is moist. The liquid water content of snow causes considerable absorption compared to dry snow, and so longer wavelengths are likely to be most revealing as to the state of a moist snowpactr. For volumetric moisture contents below about 7% (the pendular regime), the water forms rings around the contact points between snow grains. Electrostatic modeling of these pendular rings shows that the absorption of these rings is significantly higher than a sphere of the same volume. The first implementation of the radiobrightness module will therefore be a simple radiative transfer model without scattering. C1 [Chung, Y. C.; England, A. W.; De Roo, R. D.] Univ Michigan, Ann Arbor, MI 48109 USA. [Weininger, Etai] Jet Prop Lab, Pasadena, CA USA. RP Chung, YC (reprint author), Univ Michigan, Ann Arbor, MI 48109 USA. EM chungyc@umich.edu RI De Roo, Roger/J-2208-2012 OI De Roo, Roger/0000-0001-8391-2950 NR 18 TC 1 Z9 1 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 3746 EP + DI 10.1109/IGARSS.2006.960 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989402146 ER PT S AU Zhang, KQ Houle, PA Ross, MS Ruiz, PL Simard, M AF Zhang, Keqi Houle, Patricia A. Ross, Michael S. Ruiz, Pablo L. Simard, Marc GP IEEE TI Airborne Laser Mapping of Mangroves on the Biscayne Bay Coast, Miami Florida SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE LIDAR; mangrove; vegetation structure AB In this paper we present a method using airborne laser mapping data to describe the vertical structure of a coastal mangrove forest in southeastern Florida. Mangroves are critical to coastal processes and the maintenance of vital habitats; however they are also highly threatened due to coastal development and rising sea levels. Access to mangroves for detailed ground surveys is extremely difficult due to dense vegetation and lack of stable ground in the tidal zone. Airborne laser mapping can provide accurate measurements of vegetation structure over large areas without the logistical difficulties of extensive ground surveys. In our method we derive frequency height histograms from the laser mapping data followed by the creation of image objects from areas sharing similar vertical height profiles. These image objects are classified based on their vertical height profiles and related to heights of mangrove forest communities obtained from field surveys. We show that airborne laser mapping technology can be used to classify mangrove forests and to study the spatial relationships among the different forest types. C1 [Zhang, Keqi; Houle, Patricia A.; Ross, Michael S.; Ruiz, Pablo L.] Florida Int Univ, Dept Environm Studies, Int Hurricane Res Ctr, Miami, FL 33199 USA. [Simard, Marc] CALTECH, Jet Prop Lab, Radar & Engn Sect, Pasadena, CA USA. RP Zhang, KQ (reprint author), Florida Int Univ, Dept Environm Studies, Int Hurricane Res Ctr, Miami, FL 33199 USA. OI Simard, Marc/0000-0002-9442-4562 NR 11 TC 1 Z9 1 U1 0 U2 5 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 3750 EP + DI 10.1109/IGARSS.2006.961 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989402147 ER PT S AU Huang, HG Liu, QH Liu, Q Li, XW Qin, WH AF Huang, Huaguo Liu, Qinhuo Liu, Qiang Li, Xiaowen Qin, Wenhan GP IEEE TI An Extended Radiosity-Graphics Model for Directional Brightness Temperature Research SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE RGM; Radiosity; DBT ID CANOPY AB RGM (Radiosity-Graphics Combined Model) is a 3D computer radiosity-graphics combined model that calculates the radiation regime and BRF (the bidirectional reflectance factor) of complex 3-D scene, such as vegetation canopy. It was originally developed to work in the short wavelengths (0.3-3 mu m) within 3D natural scenes that are represented as surface elements with finite dimension and orientation such as leaves, stems, soil patches, etc. RGM was recently, transplanted from UNIX workstation to Windows platform and modified to extend its domain of application. This paper presents the changes that were implemented for extending its functions and demonstrated the validity of updated version for DBT (directional brightness temperature) research. Presently, this model works with agricultural crops, on the whole optical domain (thermal infrared included) and with a multi-spectral approach that uses optical databases from 0.3 mu m up to 15 mu m. C1 [Huang, Huaguo; Liu, Qinhuo; Liu, Qiang; Li, Xiaowen] Chinese Acad Sci, Inst Remote Sensing Applicat, State Key Lab Remote Sensing Sci, Beijing, Peoples R China. [Qin, Wenhan] NASA Goddard Space Flight Ctr, Greenbelt, MD USA. RP Huang, HG (reprint author), Chinese Acad Sci, Inst Remote Sensing Applicat, State Key Lab Remote Sensing Sci, Beijing, Peoples R China. EM hawhhg@263.net; qhliu@irsa.ac.cn; wenhan_qin@ssaihq.com FU National Science Foundation [40371087] FX The National Science Foundation supported this work (Grant# 40371087) NR 11 TC 0 Z9 0 U1 1 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 3778 EP + DI 10.1109/IGARSS.2006.968 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989402154 ER PT B AU Im, E Durden, SL AF Im, Eastwood Durden, Stephen L. GP IEEE TI Advanced Spaceborne Rain Radar Instrument Concepts and Technology SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing (IGARSS) LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE precipitation; hurricane; radar; antenna; TRMM AB Two of the advanced instrument concepts and technologies developed under NASA's Earth Science Instrument Incubator Program are the Second-Generation Precipitation Radar (PR-2) and the Nexrad-In-Space (NIS). PR-2 is a 14/35-GHz dual-frequency, dual-polarized Doppler rain radar with a deployable scanning antenna for Low-Earth orbit (LEO) operations to provide improved rainfall profile measurements. NIS is designed to be a 35-GHz Geostationary Earth Orbiting (GEO) radar for providing hourly monitoring of the life cycle of hurricanes and tropical storms. It uses a 35-m, spherical, lightweight membrane antenna and Doppler processing to acquire 3-dimensional information on the intensity and vertical motion of hurricane rainfall. C1 [Im, Eastwood; Durden, Stephen L.] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Im, E (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. EM Eastwood.Im@jpl.nasa.gov NR 3 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 3853 EP 3856 DI 10.1109/IGARSS.2006.988 PG 4 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989402174 ER PT B AU Lambrigtsen, B Tanner, A Gaier, T Kangaslahti, P Brown, S AF Lambrigtsen, Bjorn Tanner, Alan Gaier, Todd Kangaslahti, Pekka Brown, Shannon GP IEEE TI A Microwave Sounder for GOES-R: Developing the GeoSTAR Mission SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing (IGARSS) LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci AB The Geostationary Synthetic Thinned Aperture Radiometer (GeoSTAR) is a new concept for a microwave sounder, intended to be deployed on NOAA's next generation of geostationary weather satellites, the GOES-R series - due to first launch in 2012. This will rill a serious gap in our remote sensing capabilities of long standing - a key capability that NOAA is book keeping at the top of its list of "pre-planned product improvements" for GOES-R - i.e. the most urgently needed additional payload, which will be added as soon as funding has been allocated and programmatic issues resolved. Although real-aperture GEO microwave sounders have been proposed over the years, only GeoSTAR is capable of meeting the measurement requirements and is therefore now the leading candidate. A ground based prototype has been developed at the Jet Propulsion Laboratory, under NASA Instrument Incubator Program sponsorship, and is currently undergoing tests and performance characterization. Initial tests have been very successful, and images of the sun transiting through the field of view - the first successful imaging using a 2D aperture synthesis system and in effect constituting proof of concept - as well as images of stationary scenes, both indoors and outdoors, demonstrate that the system is very stable and that aperture synthesis is a feasible approach. The initial space version of GeoSTAR will have performance characteristics similar to those of microwave sounders currently operating on polar orbiting environmental satellites, but subsequent versions will significantly outperform those systems. In addition to all-weather temperature and humidity soundings, GeoSTAR will provide continuous rain mapping - full-disc coverage with updates every 5 minutes, tropospheric wind profiling and real time storm tracking. With the aperture synthesis approach used by GeoSTAR it is possible to achieve very high spatial resolutions without having to deploy the impractically large parabolic reflector antenna that is required with the conventional approach. GeoSTAR therefore offers both a feasible way of getting a microwave sounder with adequate spatial resolution in GEO as well as a clear upgrade path to meet future requirements. GeoSTAR offers a number of other advantages over real-aperture systems as well, such as 2D spatial coverage without mechanical scanning, system robustness and fault tolerance, operational flexibility, high quality beam formation, and open ended performance expandability. The technology and system design required for GeoSTAR are rapidly maturing, and it is expected that a space demonstration mission can be developed before the first GOES-R launch. GeoSTAR will be ready for operational deployment 1-2 years after that. Although the GeoSTAR team has been closely collaborating with the NOAA Office of System Development, which is responsible for overseeing the development of GOES-F there are programmatic barriers that make it difficult for NOAA to develop new-technology payloads. Traditionally this has been the role of NASA, and both organizations are working on finding ways to implement this "research to operations" model without negatively impacting their other objectives. GeoSTAR is a good candidate for this model, and it is expected to go forward as a space mission within the next decade. C1 [Lambrigtsen, Bjorn; Tanner, Alan; Gaier, Todd; Kangaslahti, Pekka; Brown, Shannon] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Lambrigtsen, B (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 3 TC 1 Z9 2 U1 1 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 3964 EP 3967 DI 10.1109/IGARSS.2006.1017 PG 4 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989402203 ER PT S AU Tanner, AB Wilson, WJ Lambrigsten, BH Dinardo, SJ Brown, ST Kangaslahti, P Gaier, TC Ruf, CS Gross, SM Lim, BH Musko, S Rogacki, S AF Tanner, Alan B. Wilson, W. J. Lambrigsten, B. H. Dinardo, S. J. Brown, S. T. Kangaslahti, P. Gaier, T. C. Ruf, C. S. Gross, S. M. Lim, B. H. Musko, S. Rogacki, S. GP IEEE TI Initial results of the Geosynchronous Synthetic Thinned Array Radiometer (GeoSTAR) SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE remote sensing; radiometer; interferometer AB The design and preliminary test results of a 50-56 GHz synthetic aperture radiometer demonstration system are discussed. An error budget is presented to meet 1 Kelvin radiometric accuracy in a geostationary atmospheric sounder with 50 kin spatial resolution on the earth. The gain and phase errors are weighted by the magnitude of visibility versus antenna separation, and requirements range between similar to 0.5% and 0.3 degrees of amplitude and phase, respectively, for the closest spacings at the center of the array, and about 5% and 3 degrees for the majority of the array. The latter requirement is met by our design without any special testing or stabilizations by reference signals. The former is met using an internal noise diode reference and by measuring the detailed antenna patterns on the antenna range. Biases and other additive errors in the raw visibility samples must be below about 2 mK on average, and this requirement is met by a phase shifting scheme applied to the local oscillator distribution. An outline of the data processing is presented, along with the first images from this system. C1 [Tanner, Alan B.; Wilson, W. J.; Lambrigsten, B. H.; Dinardo, S. J.; Brown, S. T.; Kangaslahti, P.; Gaier, T. C.] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. [Ruf, C. S.; Gross, S. M.; Lim, B. H.; Musko, S.; Rogacki, S.] Univ Michigan, Ann Arbor, MI USA. RP Tanner, AB (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. EM Alan.b.tanner@jpl.nasa.gov RI Ruf, Christopher/I-9463-2012 FU National Aeronautics and Space Administration FX This work has been carried out at the Jet Propulsion Laboratory, California Institute of Technology under a contract with the National Aeronautics and Space Administration. NR 3 TC 2 Z9 2 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 3968 EP + DI 10.1109/IGARSS.2006.1018 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989402204 ER PT S AU Middleton, EM Corp, LA Daughtry, CST Campbell, PKE AF Middleton, E. M. Corp, L. A. Daughtry, C. S. T. Campbell, P. K. Entcheva GP IEEE TI Chlorophyll Fluorescence Emissions of Vegetation Canopies From High Resolution Field Reflectance Spectra SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE chlorophyll fluorescence; solar induced fluorescence; corn; carbon/nitrogen ratio ID A FLUORESCENCE; CORN AB A two-year experiment was performed on corn (Zea mays L.) crops under nitrogen (N) fertilization regimes to examine the use of hyperspectral canopy reflectance information for estimating chlorophyll fluorescence (ChlF) and vegetation production. Fluorescence of foliage in the laboratory has proven more rigorous than reflectance for correlation to plant physiology. Especially useful are emissions produced from two stable red and far-red chlorophyll ChlF peaks centered at 685 +/- 10 nm and 735 +/- 5 nm. Methods have been developed elsewhere to extract steady state solar induced fluorescence (SIF) from apparent reflectance of vegetation canopies/landscapes using the Fraunhofer Line Depth (FLD) principal. Our study utilized these methods in conjunction with field-acquired high spectral resolution canopy reflectance spectra obtained in 2004 and 2005 over corn crops, as part of an ongoing multi-year experiment at the USDA/Agriculture Research Service in Beltsville, MD. SIF intensities for ChlF were derived directly from canopy reflectance spectra in specific narrow-band regions associated with atmospheric oxygen absorption features centered at 688 and 760 nm. The N treatments accounted for 80% of the variation in the foliar C/N ratios, which declined from similar to 23 in the lowest N treatment to similar to 14 at the highest N treatment. A leaf-level steady state fluorescence ratio, Fs/Chl, was positively related to foliar C/N ratio (r(2) = 0.84, n = 102). Similarly, the red/far-red SIF ratio derived from the field reflectance spectra was positively related to the foliar C/N ratio (r(2) = 0.64, n = 109). Both fluorescence ratios were inversely, and non-linearly correlated with crop grain yield (Kg / ha) determined at harvest a month later (Fs/Chl ratio, r = 0.92; SIF Red/Far-Red ratio, r = 0.85). This study has relevance to future passive satellite remote sensing approaches to monitoring C dynamics from space. C1 [Middleton, E. M.] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. [Corp, L. A.] Sci Syst & Applicat Inc, Lanham, MD USA. [Daughtry, C. S. T.] USDA, Hydrol & Remote Sensing Lab, Beltsville, MD USA. [Campbell, P. K. Entcheva] Univ Maryland Baltimore Cty, Joint Ctr Earth Syst Technol, Baltimore, MD USA. RP Middleton, EM (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. EM M.Middleton@nasa.gov; lcorp@hydrolab.arsusda.gov RI Campbell, Petya/G-4931-2013; Campbell, Petya/L-7486-2013 OI Campbell, Petya/0000-0002-0505-4951; Campbell, Petya/0000-0002-0505-4951 NR 13 TC 1 Z9 1 U1 0 U2 4 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 4064 EP + DI 10.1109/IGARSS.2006.1042 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989402228 ER PT S AU Gao, F Masek, JG AF Gao, Feng Masek, Jeffery G. GP IEEE TI Mapping Wildland Fire Scar Using Fused Landsat and MODIS Surface Reflectance SO 2006 IEEE INTERNATIONAL GEOSCIENCE AND REMOTE SENSING SYMPOSIUM, VOLS 1-8 SE IEEE International Symposium on Geoscience and Remote Sensing IGARSS LA English DT Proceedings Paper CT IEEE International Geoscience and Remote Sensing Symposium (IGARSS) CY JUL 31-AUG 04, 2006 CL Denver, CO SP IEEE, IEEE Geosci & Remote Sensing Soc, Canadian Remote Sensing Soc, NASA, NOAA, Off Naval Res, Natl Polar Orbiting Operat Environm Satellite Syst, Japan Aerosp Explorat Agcy, Ball Aerosp & Technologies Corp, Cooperat Inst Res Atmosphere, Colorado State Univ, Univ Colorado, Int Union Radio Sci DE Data fusion; remote sensing; wildland fire; rapid response; MODIS; Landsat AB This paper presents a new data fusion approach to map the evolution of wildland fire scars using MODIS and Landsat observations. The frequent MODIS observations and high-resolution Landsat data are fused to depict fire scars both temporally and spatially. The approach could be used for producing fused fine resolution observations for daily fire planning and evaluation in rapid response systems. The 2002 Colorado Hayman fire is selected to demonstrate the approach. C1 [Gao, Feng] Earth Resources Technol Inc, Jessup, MD 20794 USA. [Gao, Feng; Masek, Jeffery G.] NASA, Goddard Space Flight Ctr, Biospher Sci Branch, Greenbelt, MD 20771 USA. RP Gao, F (reprint author), Earth Resources Technol Inc, Jessup, MD 20794 USA. EM Feng.Gao@nasa.gov RI Masek, Jeffrey/D-7673-2012 NR 5 TC 2 Z9 2 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-6996 BN 978-0-7803-9509-1 J9 INT GEOSCI REMOTE SE PY 2006 BP 4172 EP + DI 10.1109/IGARSS.2006.1070 PG 2 WC Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Geology; Remote Sensing; Imaging Science & Photographic Technology GA BIN08 UT WOS:000260989402256 ER PT S AU Leon, R Chen, Y AF Leon, R. Chen, Y. GP IEEE TI Cryogenic performance and reliability of GaAsCHFETs SO 2006 IEEE INTERNATIONAL INTEGRATED RELIABILITY WORKSHOP, FINAL REPORT SE IEEE International Integrated Reliability Workshop Final Report LA English DT Proceedings Paper CT IEEE International Integrated Reliability Workshop CY OCT 16-19, 2006 CL S Lake Tahoe, CA ID HEAVILY-DOPED SEMICONDUCTORS; IRRADIATED GAAS AB GaAs CHFETs (Complementary Heterostructure Field Effect Transistors) were characterized before and after stress testing at both room temperature and in cryogenic conditions. Various values of drain and gate voltages were used for stress conditions, and the effects of temperature on both performance and reliability were examined. A decrease in drain saturation current is observed below 150 K as well as an exponential decrease of gate leakage with decreasing temperature. Parametric degradation that follows a log-log relationship was observed under all stress conditions. For high electrical stress, the degradation was found to be worse at cryogenic temperatures. C1 [Leon, R.; Chen, Y.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Leon, R (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. EM rosa.leon@jpl.nasa.gov NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1930-8841 BN 978-1-4244-0296-0 J9 INT INTEG REL WRKSP PY 2006 BP 148 EP + DI 10.1109/IRWS.2006.305232 PG 3 WC Engineering, Electrical & Electronic; Physics, Condensed Matter SC Engineering; Physics GA BFX08 UT WOS:000245236100034 ER PT S AU White, M Vu, D Nguyen, D Ruiz, R Chen, Y Bernstein, JB AF White, Mark Vu, Duc Nguyen, Duc Ruiz, Ron Chen, Yuan Bernstein, Joseph B. GP IEEE TI Product reliability trends, derating considerations and failure mechanisms with scaled CMOS SO 2006 IEEE INTERNATIONAL INTEGRATED RELIABILITY WORKSHOP, FINAL REPORT SE IEEE International Integrated Reliability Workshop Final Report LA English DT Proceedings Paper CT IEEE International Integrated Reliability Workshop CY OCT 16-19, 2006 CL S Lake Tahoe, CA AB As microelectronics are scaled into the deep sub-micron regime, space and aerospace users of advanced technology CMOS are reassessing how scaling effects impact long-term product reliability. The effects of Electromigration (EM), Time-DependentDielectric-Breakdown (TDDB) and Hot Carrier Degradation (HCI and NBTI) wearout mechanisms on scaled technologies and product reliability are investigated, accelerated stress testing across several technology nodes is performed, and FA is conducted to confirm the failure mechanism(s). C1 [White, Mark; Vu, Duc; Nguyen, Duc; Ruiz, Ron; Chen, Yuan] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. [White, Mark; Bernstein, Joseph B.] Univ Maryland, College Pk, MD 20742 USA. RP White, M (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. EM Mark.White@jpl.nasa.gov NR 8 TC 2 Z9 2 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1930-8841 BN 978-1-4244-0296-0 J9 INT INTEG REL WRKSP PY 2006 BP 156 EP + DI 10.1109/IRWS.2006.305234 PG 3 WC Engineering, Electrical & Electronic; Physics, Condensed Matter SC Engineering; Physics GA BFX08 UT WOS:000245236100036 ER PT S AU Duong, TA Liu, DL Kanik, I AF Duong, Tuan A. Liu, De-Ling Kanik, Isik GP IEEE TI Neural network prediction of reduced ion mobility of chemical compound based on molecular structure SO 2006 IEEE INTERNATIONAL JOINT CONFERENCE ON NEURAL NETWORK PROCEEDINGS, VOLS 1-10 SE IEEE International Joint Conference on Neural Networks (IJCNN) LA English DT Proceedings Paper CT IEEE International Joint Conference on Neural Network CY JUL 16-21, 2006 CL Vancouver, CANADA SP IEEE ID ORGANIC-COMPOUNDS; AMINO-ACIDS; SPECTROMETRY; CONSTANTS AB We present a user-friendly hardware learning algorithm called the Cascade Error Projection (CEP) that was developed at JPL and was equipped with a new input feature mapping technique. This new technique is based on Riemannian metric tensor to enhance the learning capability for predicting the reduced ion mobility based on the molecular structure. Our simulation results are reported and compared with the current state-of-the-art ADAPT tools developed by Pennsylvania State University. In addition, our approach is superior in our novel hardware implementation approach enabling a low power, low cost and miniaturized system for remote applications e.g., NASA mission. C1 [Duong, Tuan A.; Liu, De-Ling; Kanik, Isik] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Duong, TA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 27 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2161-4393 BN 978-0-7803-9490-2 J9 IEEE IJCNN PY 2006 BP 1078 EP + PG 3 WC Computer Science, Artificial Intelligence SC Computer Science GA BFW67 UT WOS:000245125902002 ER PT S AU Chen, Y Westergard, L Mojaradi, M Billman, C Cozy, S Kolawa, E AF Chen, Yuan Westergard, Lynett Mojaradi, Mohammad Billman, Curtis Cozy, Scott Kolawa, Elizabeth GP IEEE TI Approach to extrapolating reliability of circuits operating in a varying and low temperature range SO 2006 IEEE INTERNATIONAL RELIABILITY PHYSICS SYMPOSIUM PROCEEDINGS - 44TH ANNUAL SE International Reliability Physics Symposium LA English DT Proceedings Paper CT 44th Annual IEEE International Reliability Physics Symposium CY MAR 26-30, 2006 CL San Jose, CA SP IEEE Electron Devices Soc, IEEE Reliabil Soc DE circuit reliability; product reliability; low temperature electronics; use condition extrapolation AB We present an approach to extrapolating circuit reliability to use conditions with a varying and low temperature range. The approach integrates the impact of the statistical nature of transistor lifetime on circuit reliability to give a more realistic circuit reliability projection. Even though the approach is demonstrated for low temperature applications by focusing oil hot carrier aging failure mechanism, it can be applied and easily extended to other failure mechanisms for any varying temperature operating conditions. C1 [Chen, Yuan; Mojaradi, Mohammad; Cozy, Scott; Kolawa, Elizabeth] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Westergard, Lynett; Billman, Curtis] AMI Semicond, Pocatello, ID 83201 USA. RP Chen, Y (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM yuan.chen@jpl.nasa.gov FU National Aeronautics and Space Administration FX This work was carried out at Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. NR 12 TC 2 Z9 2 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1541-7026 BN 0-7803-9498-4 J9 INT RELIAB PHY SYM PY 2006 BP 307 EP + DI 10.1109/RELPHY.2006.251233 PG 2 WC Engineering, Electrical & Electronic; Physics, Condensed Matter SC Engineering; Physics GA BFB59 UT WOS:000240855800048 ER PT S AU Fang, WC AF Fang, Wai-Chi GP IEEE TI Lossless data compression core design for integrated space data and communication system-on-chip SO 2006 IEEE INTERNATIONAL SYMPOSIUM ON CIRCUITS AND SYSTEMS, VOLS 1-11, PROCEEDINGS SE IEEE International Symposium on Circuits and Systems LA English DT Proceedings Paper CT IEEE International Symposium on Circuits and Systems CY MAY 21-24, 2006 CL Kos, GREECE SP IEEE AB A CCSDS-compliant lossless data compressor core for space data and communication system-on-chip designs has been developed to meet the increasing strong demands on high-bandwidth high-speed space data systems. This data compressor core is based on CCSDS lossless data compression standard and designed with space-qualified 150-nm CMOS technology. It occupies a compact chip area of about 700 mu m x 700 mu m. The total power dissipation is 0.2 watts at a throughput rate of 66 Msarnples/sec. This compressor core meets low-power, high-throughput, and user-transparent requirements and will be one of valuable silicon intellectual properties for developing next generation high-performance system-on-chip based space data and communication systems. C1 CALTECH, Jet Prop Lab, NASA, Pasadena, CA 91109 USA. RP Fang, WC (reprint author), CALTECH, Jet Prop Lab, NASA, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0271-4302 BN 978-0-7803-9389-9 J9 IEEE INT SYMP CIRC S PY 2006 BP 297 EP 300 PG 4 WC Computer Science, Hardware & Architecture; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BFY13 UT WOS:000245413500075 ER PT S AU Chen, MK Moision, BE Hamkins, J Nakashima, MA AF Chen, Michael K. Moision, Bruce E. Hamkins, Jon Nakashima, Michael A. GP IEEE TI An interleaver implementation for the serially concatenated pulse-position modulation decoder SO 2006 IEEE INTERNATIONAL SYMPOSIUM ON CIRCUITS AND SYSTEMS, VOLS 1-11, PROCEEDINGS SE IEEE International Symposium on Circuits and Systems LA English DT Proceedings Paper CT IEEE International Symposium on Circuits and Systems CY MAY 21-24, 2006 CL Kos, GREECE SP IEEE ID CODES AB We describe novel interleaver and deinterleaver architectures that support bandwidth efficient memory access for decoders of turbo-like codes that are used in conjunction with high order modulations. The presentation focuses on a decoder for serially concatenated pulse-position modulation (SCPPM), which is a forward-error-correction code designed by NASA to support laser communications from Mars at mega-bits-per-second (Mbps) rates. For 64-ary PPM, the new architectures effectively triple the fan-in of the interleaver and fan-out of the deinterleaver, enabling parallelization that doubles the overall throughput. The techniques described here can be readily modified for other PPM orders. C1 [Chen, Michael K.; Moision, Bruce E.; Hamkins, Jon; Nakashima, Michael A.] CALTECH, Jet Propuls Lab, Pasadena, CA 91109 USA. RP Chen, MK (reprint author), CALTECH, Jet Propuls Lab, Pasadena, CA 91109 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0271-4302 BN 978-0-7803-9389-9 J9 IEEE INT SYMP CIRC S PY 2006 BP 4244 EP + PG 2 WC Computer Science, Hardware & Architecture; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BFY13 UT WOS:000245413504144 ER PT B AU Whittlesey, A Erickson, K AF Whittlesey, Albert Erickson, Ken GP IEEE TI A Stable CS01 Tester for Switch Mode Power Supplies SO 2006 IEEE INTERNATIONAL SYMPOSIUM ON ELECTROMAGNETIC COMPATIBILITY, VOLS 1-3, PROCEEDINGS LA English DT Proceedings Paper CT IEEE Symposium on Electromagnetic Compatibility CY AUG 01, 2006 CL Portland, OR SP IEEE AB The traditional EMC CS01 test method uses an injection transformer to couple voltage from a generator onto the dc power lines of the device under test. It is not recent, but either is it generally known that "chopper" do to do power,converters can have a potentially damaging adverse reaction because of the use of the injection transformer. This paper discusses the reason, some early attempts to eliminate the oscillation (that may not perform as well as hoped), and e scribes one alternative CS01 test method to certainly avoid the problem. It is unconscionable that MIL-STD-461 does not provide warning and a work-around for this situation. C1 [Whittlesey, Albert; Erickson, Ken] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Whittlesey, A (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0293-9 PY 2006 BP 203 EP 207 DI 10.1109/ISEMC.2006.1706293 PG 5 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BII44 UT WOS:000259733100043 ER PT B AU Whittlesey, A Campbell, L Pierce, T AF Whittlesey, Albert Campbell, Larry Pierce, Thomas GP IEEE TI The EMC Program for NASA's Mars Reconnaissance Orbiter SO 2006 IEEE INTERNATIONAL SYMPOSIUM ON ELECTROMAGNETIC COMPATIBILITY, VOLS 1-3, PROCEEDINGS LA English DT Proceedings Paper CT IEEE Symposium on Electromagnetic Compatibility CY AUG 01, 2006 CL Portland, OR SP IEEE AB The EMC {r1` C1 [Whittlesey, Albert] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Whittlesey, A (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0293-9 PY 2006 BP 219 EP 223 DI 10.1109/ISEMC.2006.1706296 PG 5 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BII44 UT WOS:000259733100046 ER PT B AU Scully, RC Kent, BM Brezinski, KA Kempf, DR Johnk, RT AF Scully, R. C. Kent, B. M. Brezinski, K. A. Kempf, D. R. Johnk, R. T. GP IEEE TI Radio Frequency (RF) Attenuation Measurements of the Space Shuttle Vehicle SO 2006 IEEE INTERNATIONAL SYMPOSIUM ON ELECTROMAGNETIC COMPATIBILITY, VOLS 1-3, PROCEEDINGS LA English DT Proceedings Paper CT IEEE Symposium on Electromagnetic Compatibility CY AUG 01, 2006 CL Portland, OR SP IEEE DE Columbia; CAIB; Space Shuttle vehicle; Kennedy Space Center; radio freqeuncy attenuation; RF attenuation; Air Force Research Laboratory; NIST; NAVAL Air Warfare Center; PAX River AB Following the loss of Columbia, the Columbia Accident Investigation Board (CAIB) provided recommendations to be addressed prior to Return To Flight (RTF). As a part of CAIB Recommendation 3.4.1 - Ground Based Imagery, new C-band and X-band radars were added to the array of ground-based radars and cameras already in-situ at Kennedy Space Center. Because of higher power density considerations and new operating frequencies, the team of Subject Matter Experts (SMEs) assembled to investigate the technical details of introducing the new radars recommended a series of radio frequency (RF) attenuation tests be performed on the Space Shuttle vehicle to establish the attenuation of the vehicle outer mold line structure with respect to its external RF environment. Because of time and complex logistical constraints, it was decided to split the test into two separate efforts. The first of these would be accomplished with the assistance of the Air Force Research Laboratory (AFRL), performing RF attenuation measurements on the aft section of OV-103 (Discovery) while in-situ in Orbiter Processing Facility (OPF) 3, located at Kennedy Space Center. The second would be accomplished with the assistance of the National Institute of Standards and Technology (NIST) and the electromagnetic interference (EMI) laboratory out of the Naval Air Warfare Center, Patuxent River, Maryland (PAX River), performing RF attenuation measurements on OV-105 (Endeavour) in-situ inside the Space Shuttle Landing Facility (SLF) hangar, also located at Kennedy Space Center. This paper provides a summary description of these efforts and their results. C1 [Scully, R. C.] NASA, Lyndon B Johnson Space Ctr, Avion Syst Div, Houston, TX 77058 USA. RP Scully, RC (reprint author), NASA, Lyndon B Johnson Space Ctr, Avion Syst Div, Houston, TX 77058 USA. NR 0 TC 1 Z9 1 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0293-9 PY 2006 BP 224 EP 227 DI 10.1109/ISEMC.2006.1706297 PG 4 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BII44 UT WOS:000259733100047 ER PT B AU Nguyen, TX Ely, JJ Dudley, KL Scearce, SA Hatfield, MO Richardson, RE AF Nguyen, Truong X. Ely, Jay J. Dudley, Kenneth L. Scearce, Stephen A. Hatfield, Michael O. Richardson, Robert E. GP IEEE TI Passenger transmitters as a possible cause of aircraft fuel ignition SO 2006 IEEE INTERNATIONAL SYMPOSIUM ON ELECTROMAGNETIC COMPATIBILITY, VOLS 1-3, PROCEEDINGS LA English DT Proceedings Paper CT IEEE Symposium on Electromagnetic Compatibility CY AUG 01, 2006 CL Portland, OR SP IEEE DE TWA-800; aircraft accident investigation; Portable Electronic Devices; RF; FQIS AB An investigation was performed to study the potential for radio frequency (RF) power radiated from transmitting Portable Electronic Devices (PEDs) to create an arcing/sparking event within the fuel tank of a large transport aircraft. A survey of RF emissions from typical intentional transmitting PEDs was first performed. Aircraft measurements of RF coupling to the fuel tank and its wiring were also performed to determine the PEDs induced power on the wiring, and the re-radiated power within the fuel tank. Laboratory simulations were conducted to determine the required RF power level for an arcing/sparking event. Data analysis shows large positive safety margins, even with simulated faults on the wiring. C1 [Nguyen, Truong X.; Ely, Jay J.; Dudley, Kenneth L.; Scearce, Stephen A.] NASA, Langley Res Ctr, Hampton, VA 23665 USA. RP Nguyen, TX (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. NR 8 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0293-9 PY 2006 BP 228 EP 233 DI 10.1109/ISEMC.2006.1706298 PG 6 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BII44 UT WOS:000259733100048 ER PT B AU Sukumar, V Alahmad, M Buck, K Braley, M Nance, J Zghoul, FN Hess, H Cox, HD Mojarradi, MM West, WC Whitacre, JF AF Sukumar, Vinesh Alahmad, Mahmoud Buck, Kevin Braley, Mathew Nance, Jasper Zghoul, Fadi Nessir Hess, Herbert Cox, HarryLi Dave Mojarradi, M. M. West, W. C. Whitacre, J. F. BE Lavoie, M AlHaddad, K Lagace, PJ TI High impedance nano charger for on-chip 50nAH rated microbatteries SO 2006 IEEE INTERNATIONAL SYMPOSIUM ON INDUSTRIAL ELECTRONICS, VOLS 1-7 LA English DT Proceedings Paper CT IEEE International Symposium on Industrial Electronics CY JUL 09-13, 2006 CL Montreal, CANADA SP IEEE Ind Elect Soc, ABB Canada, Ecol Technol Superieure AB Integrated microbatteries are being currently developed to act as a "micropower" source in microsatellites. They help provide localized current capacities or embedded power supplies at the chip level, for space exploration. The microbatteries are charged using these complementary algorithms based on constant current, constant voltage and pulsed current. The charging current is in the range of nano-amperes. A unique experimental setup is developed to implement the nano charging algorithms. This designed setup is completely automated for maximum efficiency. Laboratory results are shown as part of this paper to prove the validity of the designed work. The microbatteries used are rated at 50nAH capacity and are solid state lithium electrolyte based. C1 [Sukumar, Vinesh; Alahmad, Mahmoud; Buck, Kevin; Braley, Mathew; Nance, Jasper; Zghoul, Fadi Nessir; Hess, Herbert; Cox, HarryLi Dave] Univ Idaho, Microelect Res & Commun Inst, Moscow, ID 83843 USA. [Mojarradi, M. M.; West, W. C.; Whitacre, J. F.] CALTECH, Jet Propuls Lab, Pasadena, CA USA. RP Sukumar, V (reprint author), Univ Idaho, Microelect Res & Commun Inst, Moscow, ID 83843 USA. EM Vinesh@mrc.uidabo.edu NR 8 TC 0 Z9 0 U1 1 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0496-4 PY 2006 BP 2719 EP + DI 10.1109/ISIE.2006.296043 PG 2 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic SC Automation & Control Systems; Computer Science; Engineering GA BFS70 UT WOS:000244382905031 ER PT B AU Divsalar, D Dolinar, S Jones, C AF Divsalar, Dariush Dolinar, Sam Jones, Christopher GP IEEE TI Construction of protograph LDPC codes with linear minimum distance SO 2006 IEEE INTERNATIONAL SYMPOSIUM ON INFORMATION THEORY, VOLS 1-6, PROCEEDINGS LA English DT Proceedings Paper CT IEEE International Symposium on Information Theory CY JUL 09-14, 2006 CL Seattle, WA SP IEEE Informat Theory Soc, USN, Dept Navy Sci & Technol, Microsoft Res, Natl Nat Sci Fdn ID PARITY-CHECK CODES; CAPACITY; GRAPHS AB A construction method for protograph-based LDPC codes that simultaneously achieve low iterative decoding threshold and linear minimum distance is proposed. We start with a high-rate protograph LDPC code with variable node degrees of at least 3. Lower rate codes are obtained by splitting check nodes and connecting them by degree-2 nodes. This guarantees the linear minimum distance property for the lower-rate codes. Excluding checks connected to degree-1 nodes, we show that the number of degree-2 nodes should be at most one less than the number of checks for the protograph LDPC code to have linear minimum distance. Iterative decoding thresholds are obtained by using the reciprocal channel approximation. Thresholds are lowered by using either precoding or at least one very high-degree node in the base protograph. A family of high- to low-rate codes with minimum distance linearly increasing in block size and with capacity-approaching performance thresholds is presented. FPGA simulation results for a few example codes show that the proposed codes perform as predicted. C1 [Divsalar, Dariush; Dolinar, Sam; Jones, Christopher] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Divsalar, D (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Dariush.Divsalar@jpl.nasa.gov; sam@shannon.jpl.nasa.gov; christop@jpl.nasa.gov NR 22 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0505-3 PY 2006 BP 664 EP + DI 10.1109/ISIT.2006.261868 PG 2 WC Telecommunications SC Telecommunications GA BFX53 UT WOS:000245289701038 ER PT B AU Dolinar, S Andrews, K AF Dolinar, Sam Andrews, Kenneth GP IEEE TI Compound pulse position modulation codes SO 2006 IEEE INTERNATIONAL SYMPOSIUM ON INFORMATION THEORY, VOLS 1-6, PROCEEDINGS LA English DT Proceedings Paper CT IEEE International Symposium on Information Theory CY JUL 09-14, 2006 CL Seattle, WA SP IEEE Informat Theory Soc, USN, Dept Navy Sci & Technol, Microsoft Res, Natl Nat Sci Fdn AB A general class of nonlinear compound pulse position modulation (CPPM) codes is introduced to incorporate nonlinear low-rate PPM constraints directly into a Tanner-like code graph on which iterative decoding can be performed. The iterative decoding algorithm is specified for these codes, including the extrinsic message computations at the nonlinear constraint nodes. For a particular subclass of CPPM codes a simple but strange encoding algorithm is defined that encodes a variable number of source bits for each code block. The encoding algorithm is applied to calculate the average information rate of a partictilar type of parallel concatenated CPPM code ensemble called turbo PPM-. C1 [Dolinar, Sam; Andrews, Kenneth] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Dolinar, S (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM sam@shannon.jpl.nasa.gov; andrews@shannon.jpl.nasa.gov FU IND Technology Program; Jet Propulsion Laboratory; California Institute of Technology, under with the National Aeronautics and Space Administration FX This work was funded by the IND Technology Program and performed at the Jet Propulsion Laboratory, California Institute of Technology, under contract with the National Aeronautics and Space Administration. NR 5 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0505-3 PY 2006 BP 1529 EP + DI 10.1109/ISIT.2006.262124 PG 2 WC Telecommunications SC Telecommunications GA BFX53 UT WOS:000245289703014 ER PT B AU Divsalar, D AF Divsalar, Dariush GP IEEE TI Ensemble weight enumerators for protograph LDPC codes SO 2006 IEEE International Symposium on Information Theory, Vols 1-6, Proceedings LA English DT Proceedings Paper CT IEEE International Symposium on Information Theory CY JUL 09-14, 2006 CL Seattle, WA SP IEEE Informat Theory Soc, USN, Dept Navy Sci & Technol, Microsoft, Natl Sci Fdn ID PARITY-CHECK CODES; DISTANCE DISTRIBUTIONS AB Recently, LDPC codes with projected graph, or protograph structures have been proposed. In this paper, finite length ensemble weight enumerators for LDPC codes with protograph structures are obtained. Asymptotic results are derived as the block size goes to infinity. In particular, we are interested in obtaining ensemble average weight enumerators for protograph LDPC codes which have typical minimum distance that grows linearly with block size. As with irregular ensembles, linear minimum distance property is sensitive to the proportion of degree-2 variable nodes. In this paper, the derived results on ensemble weight enumerators show that linear minimum distance condition on degree distribution of unstructured irregular LDPC codes is a sufficient but not a necessary condition for protograph LDPC codes. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Divsalar, D (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 21 TC 1 Z9 1 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0505-3 PY 2006 BP 1554 EP 1558 DI 10.1109/ISIT.2006.262129 PG 5 WC Telecommunications SC Telecommunications GA BFX53 UT WOS:000245289703019 ER PT B AU Klimesh, M McEliece, RJ AF Klimesh, Matthew McEliece, Robert J. GP IEEE TI Existence, uniqueness, and optimality of sibling-property codes for infinite sources SO 2006 IEEE INTERNATIONAL SYMPOSIUM ON INFORMATION THEORY, VOLS 1-6, PROCEEDINGS LA English DT Proceedings Paper CT IEEE International Symposium on Information Theory CY JUL 09-14, 2006 CL Seattle, WA SP IEEE Informat Theory Soc, USN, Dept Navy Sci & Technol, Microsoft Res, Natl Nat Sci Fdn ID OPTIMAL PREFIX CODES; INTEGER ALPHABETS; HUFFMAN; DISTRIBUTIONS AB By definition Huffman codes only exist for finite sources, since the Huffman algorithm cannot be applied to an infinite source. On the other hand, Gallager's sibling property, which was introduced as a characterization of Huffman codes, extends naturally to (countably) infinite sources. Thus we define a Huffman- Gallager code as any code that has the sibling property, and we present some basic facts about such codes: (1) For any source, a Huffman-Gallager code exists and its list of node probabilities is unique. (2) A Huffman-Gallager code is optimal, and given an optimal code, there exists a Huffman-Gallager code with the same codeword lengths. (3) For sources with infinite entropy, the existence and uniqueness results continue to hold, and the optimality results hold for a natural extended form of optimality. C1 [Klimesh, Matthew; McEliece, Robert J.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. RP Klimesh, M (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. EM matthew.a.klimesh@jpl.nasa.gov; rjm@systems.caltech.edu NR 13 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0505-3 PY 2006 BP 2536 EP + DI 10.1109/ISIT.2006.262089 PG 2 WC Telecommunications SC Telecommunications GA BFX53 UT WOS:000245289705021 ER PT B AU Wintucky, EG Simons, RN Vaden, KR Lesny, GG Glass, JL AF Wintucky, E. G. Simons, R. N. Vaden, K. R. Lesny, G. G. Glass, J. L. GP IEEE TI High power combining of Ka-band TWTs for deep space communications SO 2006 IEEE INTERNATIONAL VACUUM ELECTRONICS CONFERENCE HELD JOINTLY WITH 2006 IEEE INTERNATIONAL VACUUM ELECTRON SOURCES SE IEEE International Vacuum Electronics Conference IVEC LA English DT Proceedings Paper CT 7th IEEE International Vacuum Electronics Conference (IVEC)/6th IEEE International Vacuum Electron Sources Conference (IVESC) CY APR 25-27, 2006 CL Monterey, CA SP IEEE Electron Devices Soc DE power combining; traveling wave tubes; Ka band; space communications; waveguide hybrid junctions AB This paper presents the results of a high efficiency power combining demonstration of two 100 W Ka-band space TWTs using a 4-port magic-T hybrid junction-based waveguide circuit. Power combining efficiencies of about 90% over a 1GHz frequency band centered at 32.05 GHz and a high data transmission rate of 622 Mbps were successfully demonstrated. C1 [Wintucky, E. G.; Simons, R. N.; Vaden, K. R.] NASA, Glenn Res Ctr, Commun Div, 2100 Brookpk Rd, Cleveland, OH 44135 USA. RP Wintucky, EG (reprint author), NASA, Glenn Res Ctr, Commun Div, 2100 Brookpk Rd, Cleveland, OH 44135 USA. EM Edwin.G.Wintucky@nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 1-4244-0108-9 J9 IEEE INT VAC ELECT C PY 2006 BP 63 EP + DI 10.1109/IVELEC.2006.1666185 PG 2 WC Engineering, Electrical & Electronic SC Engineering GA BEW82 UT WOS:000239893200028 ER PT B AU Wilson, JD Chevalier, CT AF Wilson, Jeffrey D. Chevalier, Christine T. GP IEEE TI Robust design algorithm for high-frequency traveling-wave tube slow-wave circuits SO 2006 IEEE INTERNATIONAL VACUUM ELECTRONICS CONFERENCE HELD JOINTLY WITH 2006 IEEE INTERNATIONAL VACUUM ELECTRON SOURCES SE IEEE International Vacuum Electronics Conference IVEC LA English DT Proceedings Paper CT 7th IEEE International Vacuum Electronics Conference (IVEC)/6th IEEE International Vacuum Electron Sources Conference (IVESC) CY APR 25-27, 2006 CL Monterey, CA SP IEEE Electron Devices Soc DE traveling-wave tube; optimization; simulated annealing; robust design; algorithm ID EFFICIENCY AB An optimization algorithm has been developed to provide robust designs for slow-wave circuits of high frequency traveling-wave tubes. A simulated statistical performance test of a robust design for a 94-GHz folded waveguide circuit shows significantly less sensitivity to dimensional tolerance variations. C1 [Wilson, Jeffrey D.] NASA, Glenn Res Ctr, 21000 Brookpk Rd,MS 54-5, Cleveland, OH 44135 USA. RP Wilson, JD (reprint author), NASA, Glenn Res Ctr, 21000 Brookpk Rd,MS 54-5, Cleveland, OH 44135 USA. EM Jeffrey.D.Wilson@nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 1-4244-0108-9 J9 IEEE INT VAC ELECT C PY 2006 BP 285 EP + DI 10.1109/IVELEC.2006.1666296 PG 2 WC Engineering, Electrical & Electronic SC Engineering GA BEW82 UT WOS:000239893200139 ER PT B AU Vancil, B Mueller, R Hawken, K Wintucky, EG Kory, C AF Vancil, Bernard Mueller, R. Hawken, K. Wintucky, Edwin G. Kory, C. GP IEEE TI Electrostatically focused multibeam klystron SO 2006 IEEE INTERNATIONAL VACUUM ELECTRONICS CONFERENCE HELD JOINTLY WITH 2006 IEEE INTERNATIONAL VACUUM ELECTRON SOURCES SE IEEE International Vacuum Electronics Conference IVEC LA English DT Proceedings Paper CT 7th IEEE International Vacuum Electronics Conference (IVEC)/6th IEEE International Vacuum Electron Sources Conference (IVESC) CY APR 25-27, 2006 CL Monterey, CA SP IEEE Electron Devices Soc DE multibeam klystron; electrostatic focusing C1 [Vancil, Bernard; Mueller, R.; Hawken, K.] E Beam Inc, 21070 SW Tile Flat Rd, Beaverton, OR 97007 USA. [Wintucky, Edwin G.; Kory, C.] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Vancil, B (reprint author), E Beam Inc, 21070 SW Tile Flat Rd, Beaverton, OR 97007 USA. EM bernie@ebeaminc.com FU NASA [NNCO4CB17C] FX This work is supported by NASA Contract No.NNCO4CB17C. NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 1-4244-0108-9 J9 IEEE INT VAC ELECT C PY 2006 BP 309 EP + DI 10.1109/IVELEC.2006.1666307 PG 2 WC Engineering, Electrical & Electronic SC Engineering GA BEW82 UT WOS:000239893200150 ER PT B AU Vancil, B Wintucky, EG AF Vancil, Bernard Wintucky, Edwin G. GP IEEE TI Reservoir cathodes - Recent development SO 2006 IEEE INTERNATIONAL VACUUM ELECTRONICS CONFERENCE HELD JOINTLY WITH 2006 IEEE INTERNATIONAL VACUUM ELECTRON SOURCES SE IEEE International Vacuum Electronics Conference IVEC LA English DT Proceedings Paper CT 7th IEEE International Vacuum Electronics Conference (IVEC)/6th IEEE International Vacuum Electron Sources Conference (IVESC) CY APR 25-27, 2006 CL Monterey, CA SP IEEE Electron Devices Soc DE thermionic cathodes; reservoir cathodes; dispenser cathodes C1 [Vancil, Bernard] E Beam Inc, 21070 SW Tile Flat Rd, Beaverton, OR 97007 USA. [Wintucky, Edwin G.] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Vancil, B (reprint author), E Beam Inc, 21070 SW Tile Flat Rd, Beaverton, OR 97007 USA. EM bernie@ebeaminc.com NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 1-4244-0108-9 J9 IEEE INT VAC ELECT C PY 2006 BP 311 EP + DI 10.1109/IVELEC.2006.1666308 PG 2 WC Engineering, Electrical & Electronic SC Engineering GA BEW82 UT WOS:000239893200151 ER PT B AU Komm, DS AF Komm, David S. GP IEEE TI High voltage breakdown levels in various EPC potting materials SO 2006 IEEE INTERNATIONAL VACUUM ELECTRONICS CONFERENCE HELD JOINTLY WITH 2006 IEEE INTERNATIONAL VACUUM ELECTRON SOURCES SE IEEE International Vacuum Electronics Conference IVEC LA English DT Proceedings Paper CT 7th IEEE International Vacuum Electronics Conference (IVEC)/6th IEEE International Vacuum Electron Sources Conference (IVESC) CY APR 25-27, 2006 CL Monterey, CA SP IEEE Electron Devices Soc DE high voltage; breakdown; potting; encapsulating; power supply; EPC; HVPS; TWTA C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Komm, DS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM david.komm@jpl.nasa.gov NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 1-4244-0108-9 J9 IEEE INT VAC ELECT C PY 2006 BP 381 EP 382 DI 10.1109/IVELEC.2006.1666342 PG 2 WC Engineering, Electrical & Electronic SC Engineering GA BEW82 UT WOS:000239893200185 ER PT B AU Simons, V AF Simons, Vaden GP IEEE TI Computer aided design of Ka-band waveguide hybrid junctions for power combining architectures in interplanetary spacecraft SO 2006 IEEE INTERNATIONAL VACUUM ELECTRONICS CONFERENCE HELD JOINTLY WITH 2006 IEEE INTERNATIONAL VACUUM ELECTRON SOURCES SE IEEE International Vacuum Electronics Conference IVEC LA English DT Proceedings Paper CT 7th IEEE International Vacuum Electronics Conference (IVEC)/6th IEEE International Vacuum Electron Sources Conference (IVESC) CY APR 25-27, 2006 CL Monterey, CA SP IEEE Electron Devices Soc DE Hybrid Junctions; Power Combining; TWTA; Ka-band; communications AB NASA's Prometheus program proposes using nuclear fission to provide unprecedented power capabilities for future interplanetary missions. Through nuclear fission, we can consider power-combining techniques using multiple TWTAs as opposed to multiple solid-state devices. Waveguide architectures represent one method of combining the power of multiple TWYAs and the fundamental element of waveguide combining architectures is the hybrid junction. We present the simulated transmission characteristics of four waveguide hybrid junctions designed for use in a TWTA power combining system capable of producing a kWof power. C1 NASA, Glenn Res Ctr, Electron & Opt Devices Branch, Brookpark, OH 44135 USA. RP Simons, V (reprint author), NASA, Glenn Res Ctr, Electron & Opt Devices Branch, 21000 Brookpk Rd, Brookpark, OH 44135 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 BN 1-4244-0108-9 J9 IEEE INT VAC ELECT C PY 2006 BP 383 EP 384 DI 10.1109/IVELEC.2006.1666343 PG 2 WC Engineering, Electrical & Electronic SC Engineering GA BEW82 UT WOS:000239893200186 ER PT B AU Ribaya, B Niemann, D Gunther, N Rahman, M Nguyen, CV AF Ribaya, Bryan Niemann, Darrell Gunther, Norman Rahman, Mahmud Nguyen, Cattien V. GP IEEE TI An experimental study and modeling of the field emission properties of an isolated individual multi-walled carbon nanotube SO 2006 IEEE INTERNATIONAL VACUUM ELECTRONICS CONFERENCE HELD JOINTLY WITH 2006 IEEE INTERNATIONAL VACUUM ELECTRON SOURCES SE IEEE International Vacuum Electronics Conference IVEC LA English DT Proceedings Paper CT 7th IEEE International Vacuum Electronics Conference (IVEC)/6th IEEE International Vacuum Electron Sources Conference (IVESC) CY APR 25-27, 2006 CL Monterey, CA SP IEEE Electron Devices Soc DE isolated individual carbon nanotube; Fowler-Nordheim emission; thermodynamics-based variational modeling; Technology Computer-Aided Design (TCAD) C1 [Ribaya, Bryan; Niemann, Darrell; Gunther, Norman; Rahman, Mahmud] Santa Clara Univ, Dept Elect Engn, Santa Clara, CA 95053 USA. [Nguyen, Cattien V.] ELORET Corp, Moffett Field, CA 94035 USA. [Nguyen, Cattien V.] NASA, Ames Res Ctr Nanotechnol, Moffett Field, CA 94035 USA. RP Ribaya, B (reprint author), Santa Clara Univ, Dept Elect Engn, Santa Clara, CA 95053 USA. EM cvnguyen@mail.arc.nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 1-4244-0108-9 J9 IEEE INT VAC ELECT C PY 2006 BP 505 EP + DI 10.1109/IVELEC.2006.1666404 PG 2 WC Engineering, Electrical & Electronic SC Engineering GA BEW82 UT WOS:000239893200247 ER PT S AU Meehan, TK Robison, D Munson, TN Young, LE Stoyanov, S AF Meehan, Tom K. Robison, David Munson, Tim N. Young, Larry E. Stoyanov, Stephen GP IEEE TI Orbiting GPS receiver modified to track new L2C signal SO 2006 IEEE/ION POSITION, LOCATION AND NAVIGATION SYMPOSIUM, VOLS 1-3 SE IEEE-ION Position Location and Navigation Symposium LA English DT Proceedings Paper CT IEEE/ION Position, Location, and Navigation Symposium CY APR 24-27, 2006 CL Coronado, CA SP IEEE, ION AB The L2C signal is a great step forward for civil applications of GPS, enabling high-accuracy dual-frequency measurements. Engineers from the Jet Propulsion Laboratory and ITT teamed to reprogram FPGA firmware and add tracking software on an orbiting receiver to track the new GPS L2C signal from SAC-C. SAC-C is an Argentinean science satellite and was launched in November 2000 with a BlackJack GPS receiver. This is a dual-frequency digital receiver with 48 tracking channels and four antennas. On SAC-C, it provides precise orbits, atmospheric occultation data, tests of GPS surface reflections, and serves as an orbiting test bed for new GPS development such as the L2C tracking reported here. C1 [Meehan, Tom K.; Robison, David; Munson, Tim N.; Young, Larry E.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Stoyanov, Stephen] ITT Space, Syst Div, Clifton Pk, NY 07014 USA. RP Meehan, TK (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 IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2153-358X BN 0-7803-9453-4 J9 IEEE POSITION LOCAT PY 2006 BP 1071 EP + DI 10.1109/PLANS.2006.1650711 PG 2 WC Engineering, Aerospace; Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BFG11 UT WOS:000241665600130 ER PT S AU Roychoudhuri, C Prasad, N AF Roychoudhuri, Chandrasekhar Prasad, Narasimha GP IEEE TI Various ambiguities in re-constructing laser pulse parameters SO 2006 IEEE LEOS ANNUAL MEETING CONFERENCE PROCEEDINGS, VOLS 1 AND 2 SE IEEE Lasers and Electro-Optics Society (LEOS) Annual Meeting LA English DT Proceedings Paper CT 19th Annual Meeting of the IEEE-Lasers-and-Electro-Optics-Society CY OCT 29-NOV 02, 2006 CL Montreal, CANADA SP IEEE Lasers & Electro Opt Soc C1 [Roychoudhuri, Chandrasekhar] Univ Connecticut, Dept Phys, Storrs, CT 06269 USA. [Prasad, Narasimha] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Roychoudhuri, C (reprint author), Univ Connecticut, Dept Phys, Storrs, CT 06269 USA. EM chandra@phys.uconn.edu NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1092-8081 BN 978-0-7803-9555-8 J9 IEEE LEOS ANN MTG PY 2006 BP 881 EP + DI 10.1109/LEOS.2006.279107 PG 2 WC Engineering, Electrical & Electronic; Materials Science, Multidisciplinary; Optics SC Engineering; Materials Science; Optics GA BGD41 UT WOS:000246167900445 ER PT S AU Gunapala, SD Bandara, SV Ting, DZ Hill, CJ Mumolo, IM Liu, JK Rafol, SB Blazejewski, ER Levan, PD Tidrow, MZ AF Gunapala, S. D. Bandara, S. V. Ting, D. Z. Hill, C. J. Mumolo, I. M. Liu, J. K. Rafol, S. B. Blazejewski, E. R. Levan, P. D. Tidrow, M. Z. GP IEEE TI Quantum well and quantum dot based detector arrays for infrared imaging SO 2006 IEEE LEOS ANNUAL MEETING CONFERENCE PROCEEDINGS, VOLS 1 AND 2 SE IEEE Lasers and Electro-Optics Society (LEOS) Annual Meeting LA English DT Proceedings Paper CT 19th Annual Meeting of the IEEE-Lasers-and-Electro-Optics-Society CY OCT 29-NOV 02, 2006 CL Montreal, CANADA SP IEEE Lasers & Electro Opt Soc C1 [Gunapala, S. D.; Bandara, S. V.; Ting, D. Z.; Hill, C. J.; Mumolo, I. M.; Liu, J. K.; Rafol, S. B.; Blazejewski, E. R.] CALTECH, Jet Propuls Lab, Pasadena, CA 91109 USA. [Levan, P. D.] Air Force Res Lab, Kirtland AFB, NM 87117 USA. Missile Def Agency AS, Washington, DC 20301 USA. RP Gunapala, SD (reprint author), CALTECH, Jet Propuls Lab, Pasadena, CA 91109 USA. NR 2 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1092-8081 BN 978-0-7803-9555-8 J9 IEEE LEOS ANN MTG PY 2006 BP 919 EP + DI 10.1109/LEOS.2006.279146 PG 2 WC Engineering, Electrical & Electronic; Materials Science, Multidisciplinary; Optics SC Engineering; Materials Science; Optics GA BGD41 UT WOS:000246167900464 ER PT B AU Njoku, EG Chan, SK Armstrong, RL Brodzik, MJ Savoie, MH Knowles, K AF Njoku, E. G. Chan, S. K. Armstrong, R. L. Brodzik, M. J. Savoie, M. H. Knowles, K. GP IEEE TI Stable targets for spaceborne microwave radiometer calibration SO 2006 IEEE MICRORAD LA English DT Proceedings Paper CT 9th Specialist Meeting on Microwave Radiometry and Remote Sensing Applications (MicroRad 2006) CY FEB 28-MAR 03, 2006 CL San Juan, PR SP IEEE ID DOME-C; ANTARCTICA AB Beginning in the 1970s, continuous observations of the Earth have been made by spaceborne microwave radiometers. Since these instruments have different observational characteristics, care must be taken in combining their data to form consistent long term records of brightness temperatures and derived geophysical quantities. To be useful for climate studies, data from different instruments must be calibrated relative to each other and to reference targets on the ground whose characteristics are stable and can be monitored continuously. Identifying such targets over land is not straightforward due to the heterogeneity and complexity of the land surface and cover. In this work, we provide an analysis of multi-sensor brightness temperature statistics over ocean, tropical forest, and ice sheet locations, spanning the period from 1978 to the present, and indicate the potential of these sites as continuous calibration monitoring targets. C1 [Njoku, E. G.; Chan, S. K.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Armstrong, R. L.; Brodzik, M. J.; Savoie, M. H.; Knowles, K.] Univ Colorado, CIRES Natl Snow & Ice Data Ctr, Boulder, CO 80309 USA. RP Njoku, EG (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 15 TC 0 Z9 0 U1 0 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-0-7803-9417-9 PY 2006 BP 1 EP + DI 10.1109/MICRAD.2006.1677052 PG 2 WC Engineering, Electrical & Electronic; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BFW80 UT WOS:000245203200001 ER PT B AU Brown, S Desai, S Keihm, S Ruf, C AF Brown, Shannon Desai, Shailen Keihm, Stephen Ruf, Christopher GP IEEE TI JMR noise diode stability and recalibration methodology after three years on-orbit SO 2006 IEEE MICRORAD LA English DT Proceedings Paper CT 9th Specialist Meeting on Microwave Radiometry and Remote Sensing Applications (MicroRad 2006) CY FEB 28-MAR 03, 2006 CL San Juan, PR SP IEEE DE JMR; noise diode; microwave radiometer; calibration; path delay ID MICROWAVE RADIOMETERS; CALIBRATION AB Long term drifts and shifts in the Jason Microwave Radiometer (JMR) geophysical retrievals, relative to ground truth, have been attributed to long term changes in the JMR noise diode (ND) brightness, which is used for gain calibration. An optimal estimation based calibration system is developed to find an optimal set of calibration coefficients which minimize the root-mean-square (RMS) difference between the JMR brightness temperatures (T(B)s) and on-Earth references. This calibration system is used to derive a time series of the ND brightness. Changes in the ND brightness, on the order of 1-2%, are observed over the first three years of the mission. Results of the recalibration effort and validation of the retrieved ND time series are presented. C1 [Brown, Shannon; Desai, Shailen; Keihm, Stephen] Jet Prop Lab, Pasadena, CA 91109 USA. [Ruf, Christopher] Univ Michigan, Atmospher & Space Sci Dept, Ann Arbor, MI 48109 USA. RP Brown, S (reprint author), Jet Prop Lab, Pasadena, CA 91109 USA. EM Shannon.T.Brown@jpl.nasa.gov; Shailen.Desai@jpl.nasa.gov; Stephen.Keihm@jpl.nasa.gov; cruf@umich.edu RI Ruf, Christopher/I-9463-2012 NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-0-7803-9417-9 PY 2006 BP 7 EP + DI 10.1109/MICRAD.2006.1677053 PG 2 WC Engineering, Electrical & Electronic; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BFW80 UT WOS:000245203200002 ER PT B AU O'Neill, PE Lang, RH Kurum, M Utku, C Carver, KR AF O'Neill, Peggy E. Lang, Roger H. Kurum, Mehmet Utku, Cuneyt Carver, Keith R. GP IEEE TI Multi-sensor microwave soil moisture remote sensing: NASA's combined radar/radiometer (ComRAD) system SO 2006 IEEE MICRORAD LA English DT Proceedings Paper CT 9th Specialist Meeting on Microwave Radiometry and Remote Sensing Applications (MicroRad 2006) CY FEB 28-MAR 03, 2006 CL San Juan, PR SP IEEE AB This paper describes the development of a ground-based radar/radiometer system called ComRAD. The system under development is an outgrowth of a network analyzer-based L, C, and X band polarimetric radar system developed jointly by NASA/GSFC and the George Washington University. The system is mounted on a 19-m hydraulic boom truck and has provided reliable calibrated radar data in soil moisture field campaigns across the United States since the early 1990's. The truck instrument system is now being upgraded with the addition of a dual polarized 1.4 GHz total power radiometer. The new system includes a temperature monitoring and control system to keep the radiometer at a constant temperature. All front-end components have been placed on an aluminium plate whose temperature stability has been achieved by using Peltier cells. Periodic switching to the internal noise sources is used to reduce the influence of gain variations in the output voltage. A novel broadband stacked-patch dual-polarized feed resonates at both the 1.4 GHz radiometer and 1.25 GHz radar frequencies, enabling both the radar and the radiometer to share the same 1.22-m parabolic dish antenna. Having the radar and radiometer utilize the same antenna with the same 12 field of view greatly simplifies the development of active/passive microwave retrieval algorithms. With these new capabilities, ComRAD will be an important tool in examining Earth Science research topics such as the synergistic effects between active/passive microwave sensors for soil moisture estimation in the presence of vegetation. C1 [O'Neill, Peggy E.] NASA, Goddard Space Flight Ctr, Hydrol Sci Branch, Code 614-3, Greenbelt, MD 20771 USA. [Lang, Roger H.; Kurum, Mehmet; Utku, Cuneyt] George Washington Univ, Dept Elect & Comp Engn, Washington, DC 20052 USA. [Carver, Keith R.] Univ Massachusetts, Dept Elect & Comp Engn, Amherst, MA 01003 USA. RP O'Neill, PE (reprint author), NASA, Goddard Space Flight Ctr, Hydrol Sci Branch, Code 614-3, Greenbelt, MD 20771 USA. EM Peggy.E.ONeill@nasa.gov; lang@gwu.edu; kurum@gwu.edu; cuxu@gwu.edu; kcarver@ecs.umass.edu NR 3 TC 1 Z9 1 U1 0 U2 4 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-0-7803-9417-9 PY 2006 BP 50 EP + DI 10.1109/MICRAD.2006.1677061 PG 2 WC Engineering, Electrical & Electronic; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BFW80 UT WOS:000245203200010 ER PT B AU Chikando, E Piepmeier, JR Levine, E White, C AF Chikando, Eric Piepmeier, Jeffrey R. Levine, Elissa White, Carl GP IEEE TI Handheld L-Band microwave radiometer SO 2006 IEEE MICRORAD LA English DT Proceedings Paper CT 9th Specialist Meeting on Microwave Radiometry and Remote Sensing Applications (MicroRad 2006) CY FEB 28-MAR 03, 2006 CL San Juan, PR SP IEEE DE FPAA; handheld; GLOBE; impedance mismatch; L-Band radiometer; soil moisture AB Continued support for remote sensing science requires increased awareness of the general public towards the benefits of this important tool. Unfortunately, information about remote sensing instrumentation and techniques remains inaccessible to many higher-educational institutions due to high cost and lack of expertise and other resources. In an effort to develop more expertise in this field, early exposure of students to remote sensing applications is desired. In this paper, recent results of an innovative low-cost handheld L-Band radiometer applied to soil moisture measurements are demonstrated. The use of this instrument for education and outreach purposes within the GLOBE program is demonstrated, and a comparative study of results using the handheld device versus a gravimetric field technique is also detailed. C1 [Chikando, Eric; White, Carl] Morgan State Univ, CAMRA, Baltimore, MD 21239 USA. [Chikando, Eric; Piepmeier, Jeffrey R.] NASA, Goddard Space Flight Ctr, Microwave Instrument Technol Branch, Greenbelt, MD USA. [Levine, Elissa] NASA, Goddard Space Flight Ctr, Biospher Sci Branch, Greenbelt, MD USA. RP Chikando, E (reprint author), Morgan State Univ, CAMRA, Baltimore, MD 21239 USA. NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-0-7803-9417-9 PY 2006 BP 55 EP + DI 10.1109/MICRAD.2006.1677062 PG 2 WC Engineering, Electrical & Electronic; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BFW80 UT WOS:000245203200011 ER PT B AU Le Vine, DM Pellerano, F Lagerloef, GSE Yueh, S Colomb, R AF Le Vine, D. M. Pellerano, F. Lagerloef, G. S. E. Yueh, S. Colomb, R. GP IEEE TI Aquarius: A mission to monitor sea surface salinity from space SO 2006 IEEE MICRORAD LA English DT Proceedings Paper CT 9th Specialist Meeting on Microwave Radiometry and Remote Sensing Applications (MicroRad 2006) CY FEB 28-MAR 03, 2006 CL San Juan, PR SP IEEE ID L-BAND; OCEAN SALINITY AB Aquarius is a combination passive/active L-band microwave instrument being developed to map the surface salinity field of the oceans from space. It is part of the Aquarius/SAC-D mission, a partnership between the USA (NASA) and Argentina (CONAE) with launch scheduled for early in 2009. The primary science objective of this mission is to monitor the seasonal and interannual variation of the large scale features of the surface salinity field in the open ocean with a spatial resolution of 150 km and a retrieval accuracy of 0.2 psu globally on a monthly basis. C1 [Le Vine, D. M.; Pellerano, F.] Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Lagerloef, G. S. E.] Earth & Space Res, Seattle, WA 98102 USA. [Colomb, R.] Comis Nacl Actividades Espaciales, Buenos Aires, DF, Argentina. [Yueh, S.] CALTECH, Jet Propuls Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Le Vine, DM (reprint author), Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 12 TC 0 Z9 0 U1 0 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-0-7803-9417-9 PY 2006 BP 87 EP + DI 10.1109/MICRAD.2006.1677068 PG 3 WC Engineering, Electrical & Electronic; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BFW80 UT WOS:000245203200017 ER PT B AU Dinnat, EP Le Vine, DM AF Dinnat, Emmanuel P. Le Vine, David M. GP IEEE TI Effects of the antenna aperture on remote sensing of sea surface salinity at L-band. SO 2006 IEEE MICRORAD LA English DT Proceedings Paper CT 9th Specialist Meeting on Microwave Radiometry and Remote Sensing Applications (MicroRad 2006) CY FEB 28-MAR 03, 2006 CL San Juan, PR SP IEEE AB Remote sensing of sea surface salinity; to meet the needs of global oceanography; requires accuracy on the order of 0.1K. But since spatial and temporal scales are very large, it, is possible to use antennas with large footprints and averaging to meet this goal. However; antennas with large footprints introduce other problems such as variations over the footprint of the incidence angle and of the polarization vector directions. Examples of these effects are illustrated for antennas representative of those that will be flown on the Aquarius mission being developed for remote sensing of salinity from space. It is shown that the antenna temperature integrated over the field of view is biased relative to the value at boresight because of changes across the field of view. The bias can be as much as 4K and depends on polarization. Polarization mixing; because of the variations of the local plane of incidence across the footprint; also induces biased polarimetric measurements (peculiarly for the third Stokes parameter). The antenna effects vary with geophysical conditions, peculiarly with surface roughness. Finally, land in the field of view contributes noticeably to the signal up to several hundred kilometers from the coast line. C1 [Dinnat, Emmanuel P.; Le Vine, David M.] Goddard Space Flight Ctr, Hydrospheric & Biospheric Sci Lab, Instrumentat Sci Branch, Greenbelt, MD 20771 USA. RP Dinnat, EP (reprint author), Goddard Space Flight Ctr, Hydrospheric & Biospheric Sci Lab, Instrumentat Sci Branch, Greenbelt, MD 20771 USA. EM dinnat@neptune.gsfc.nasa.gov RI Dinnat, Emmanuel/D-7064-2012 OI Dinnat, Emmanuel/0000-0001-9003-1182 FU NASA Postdoctoral Program FX Manuscript received June 2, 2006; revised September 17, 2006. This work was supported by the NASA Postdoctoral Program. NR 6 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-0-7803-9417-9 PY 2006 BP 97 EP + DI 10.1109/MICRAD.2006.1677070 PG 2 WC Engineering, Electrical & Electronic; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BFW80 UT WOS:000245203200019 ER PT B AU Lang, RH Chauhan, N Utku, C Le Vine, DM AF Lang, R. H. Chauhan, N. Utku, C. Le Vine, D. M. GP IEEE TI L-band active and passive sensing of soil moisture through forests SO 2006 IEEE MICRORAD LA English DT Proceedings Paper CT 9th Specialist Meeting on Microwave Radiometry and Remote Sensing Applications (MicroRad 2006) CY FEB 28-MAR 03, 2006 CL San Juan, PR SP IEEE ID BACKSCATTERING; VEGETATION; RADAR; MODEL; LAYER AB Remote sensing of soil moisture under a mature forest canopy by active and passive techniques is discussed. Emphasis is placed on examining the sensitivity of the backscattering coefficient and the brightness temperature to soil moisture variations. The effects of the underlying surface roughness of the forest floor on these sensitivities are addressed. The backscattering coefficient from the forest is modeled using the distorted Born approximation. Using this method the backscatter response is decomposed into a direct or volume scattering component, an interaction component between the vegetation and the average surface, an interaction component between the vegetation and the surface fluctuations and finally direct backscatter from the surface attenuated by the vegetation. Peak's method is used to determine the brightness temperature. The models are validated using ground truth and remote sensing data taken during the Forest Ecosystem Dynamics (FED) experiment conducted near Howland, Maine USA in 1990. During this period, the AIRSAR synthetic aperture radar and the Push Broom Microwave Radiometer overflew the Howland area collecting data. Once the model predictions are compared with the passive and active data, the results of a sensitivity analysis involving soil moisture and surface roughness will be presented. C1 [Lang, R. H.; Utku, C.] George Washington Univ, Dept ECE, Washington, DC 20052 USA. [Chauhan, N.] NPOESS, Aerosp Integrated Program Off, Silver Spring, MD 20910 USA. [Le Vine, D. M.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20077 USA. RP Lang, RH (reprint author), George Washington Univ, Dept ECE, Washington, DC 20052 USA. NR 8 TC 0 Z9 0 U1 0 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-0-7803-9417-9 PY 2006 BP 193 EP + DI 10.1109/MICRAD.2006.1677087 PG 2 WC Engineering, Electrical & Electronic; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BFW80 UT WOS:000245203200036 ER PT S AU Kangaslahti, P Gaier, T Seiffert, M Weinreb, S Harding, D Dawson, D Soria, M Lawrence, C Hooberman, B Miller, A AF Kangaslahti, Pekka Gaier, Todd Seiffert, Michael Weinreb, Sander Harding, Dennis Dawson, Douglas Soria, Mary Lawrence, Charles Hooberman, Benjamin Miller, Amber GP IEEE TI Planar polarimetry receivers for large imaging arrays at Q-band SO 2006 IEEE MTT-S INTERNATIONAL MICROWAVE SYMPOSIUM DIGEST, VOLS 1-5 SE IEEE MTT-S International Microwave Symposium LA English DT Proceedings Paper CT IEEE MTT-S International Microwave Symposium CY JUN 11-16, 2006 CL San Francisco, CA SP IEEE MTTS DE polarimetry; millimeter wave radiometry; millimeter wave phase shifters; MMICs; millimeter wave imaging; cosmic microwave background (CMB) AB The characterization of the intensity fluctuations of the Cosmic Microwave Background (CMB) will be followed by the mapping of the polarization fluctuations of the CMB. Measurement of the polarization fluctuations requires highly sensitive instruments that are only possible by increasing the number of receivers. We are developing a large receiver array for the Q, U Imaging Experiment (QUIET) by building individual receivers that have noise temperatures close to the physical limit and that are simple, and low cost to build and operate. We developed these planar polarimetry receivers for Q-band by designing InP MMIC amplifiers with noise below 20 K, low loss and highly balanced phase switches and an entirely planar hybrid thin film circuit for the detection of the Stokes parameters Q and U. Our receivers achieve 25 K noise temperature over 8 GHz bandwidth and provide the I, Q and U parameters simultaneously. These planar modules have a simple plug in architecture that enables automated production of a large number of receivers and simple integration of large arrays of receivers. C1 [Kangaslahti, Pekka; Gaier, Todd; Seiffert, Michael; Weinreb, Sander; Harding, Dennis; Dawson, Douglas; Soria, Mary; Lawrence, Charles] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Hooberman, Benjamin; Miller, Amber] Columbia Univ, New York, NY 10027 USA. RP Kangaslahti, P (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. FU Roger Hoyland FX The research described in this paper was carried out at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration.The authors wish to acknowledge the support of Roger Hoyland in phase switch development and the support of the Q,U, Imaging ExperimenT collaboration. NR 8 TC 8 Z9 8 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0149-645X BN 978-0-7803-9541-1 J9 IEEE MTT S INT MICR PY 2006 BP 89 EP + DI 10.1109/MWSYM.2006.249935 PG 2 WC Engineering, Electrical & Electronic SC Engineering GA BFS69 UT WOS:000244379000022 ER PT S AU Vanin, FM Wollack, EJ Zaki, K Schmitt, D AF Vanin, Felice Maria Wollack, Edward J. Zaki, Kawthar Schmitt, Dietmar GP IEEE TI Polarization-preserving quadruple-ridge waveguide filter and four-fold symmetric transformer SO 2006 IEEE MTT-S INTERNATIONAL MICROWAVE SYMPOSIUM DIGEST, VOLS 1-5 SE IEEE MTT-S International Microwave Symposium LA English DT Proceedings Paper CT IEEE MTT-S International Microwave Symposium CY JUN 11-16, 2006 CL San Francisco, CA SP IEEE MTTS DE filters; waveguide filters; polarization; ridge waveguides; impedance transformer AB Current astrophysical and space applications require waveguide filters to exhibit wide stop-band performances and to preserve the dual polarization states of the electromagnetic field. The aim of this work is to present a waveguide filter that exhibits four-fold symmetry and significant stop-band improvements over the performances of standard circular and square waveguide technologies. Positive results have been achieved using quadruple ridge waveguide cross-sections and attenuation poles. This work also presents a polarization preserving transformer that converts a quadruple ridge waveguide cross-section into a square cross-section. Design examples are presented to show good performances of both filter and transformer. C1 [Vanin, Felice Maria; Zaki, Kawthar] Univ Maryland, Dept Elect Engn, College Pk, MD 20740 USA. [Wollack, Edward J.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Schmitt, Dietmar] ESA, Estec, Noordwijk, Netherlands. RP Vanin, FM (reprint author), Univ Maryland, Dept Elect Engn, College Pk, MD 20740 USA. RI Wollack, Edward/D-4467-2012 OI Wollack, Edward/0000-0002-7567-4451 NR 7 TC 4 Z9 4 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0149-645X BN 978-0-7803-9541-1 J9 IEEE MTT S INT MICR PY 2006 BP 127 EP + DI 10.1109/MWSYM.2006.249410 PG 2 WC Engineering, Electrical & Electronic SC Engineering GA BFS69 UT WOS:000244379000031 ER PT S AU Samoska, L AF Samoska, Lorene GP IEEE TI Towards terahertz MMIC amplifiers: Present status and trends SO 2006 IEEE MTT-S INTERNATIONAL MICROWAVE SYMPOSIUM DIGEST, VOLS 1-5 SE IEEE MTT-S International Microwave Symposium LA English DT Proceedings Paper CT IEEE MTT-S International Microwave Symposium CY JUN 11-16, 2006 CL San Francisco, CA SP IEEE MTTS DE MMICs; terahertz; amplifiers; HEMTs; InP ID LOW-NOISE AMPLIFIER; POWER-AMPLIFIER; G-BAND; GHZ; MW AB In this paper, we present an overview of high frequency Monolithic Millimeter-wave Integrated Circuit (MMIC) amplifiers and discuss the state of the art for low noise amplifiers and power amplifiers. We report on the challenges and innovations required to achieve small-signal and power gain above 300 GHz, and present a review of present technology status. The highest frequency MMIC amplifiers ever developed to date will be presented, starting at W-Band (75-110 GHz) and above. Highlights include a MMIC low noise amplifier with gain up to 260 GHz, and a MMIC power amplifier operating up to 190 GHz. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Samoska, L (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 29 TC 18 Z9 18 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0149-645X BN 978-0-7803-9541-1 J9 IEEE MTT S INT MICR PY 2006 BP 333 EP 336 DI 10.1109/MWSYM.2006.249519 PG 4 WC Engineering, Electrical & Electronic SC Engineering GA BFS69 UT WOS:000244379000081 ER PT S AU Mehdi, I Chattopadhyay, G Schlecht, E Ward, J Gill, J Maiwald, F Maestrini, A AF Mehdi, I. Chattopadhyay, G. Schlecht, E. Ward, J. Gill, J. Maiwald, F. Maestrini, A. GP IEEE TI Terahertz multiplier circuits SO 2006 IEEE MTT-S INTERNATIONAL MICROWAVE SYMPOSIUM DIGEST, VOLS 1-5 SE IEEE MTT-S International Microwave Symposium LA English DT Proceedings Paper CT IEEE MTT-S International Microwave Symposium CY JUN 11-16, 2006 CL San Francisco, CA SP IEEE MTTS DE terahertz technology; LO sources; frequency multipliers; Schottky diodes; heterodyne receivers; varactors ID GHZ AB Robust radiation sources in the 1-2 THz range have been sorely lacking from the repertoire of terahertz technologists and scientists. This paper will review the progress in chip fabrication technology, based on planar GaAs Schottky diodes, that has enabled the design and fabrication of multiplier circuits working well into the terahertz range. Recent results obtained with multiplied sources in the 1-2 THz range will be summarized. C1 [Mehdi, I.; Chattopadhyay, G.; Schlecht, E.; Ward, J.; Gill, J.; Maiwald, F.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Maestrini, A.] Universite Pierre et Marie Curie, F-75252 Paris, France. RP Mehdi, I (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 10 TC 9 Z9 10 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0149-645X BN 978-0-7803-9541-1 J9 IEEE MTT S INT MICR PY 2006 BP 341 EP + DI 10.1109/MWSYM.2006.249521 PG 2 WC Engineering, Electrical & Electronic SC Engineering GA BFS69 UT WOS:000244379000083 ER PT S AU Dengler, RJ Maiwald, F Siegel, PH AF Dengler, Robert J. Maiwald, Frank Siegel, Peter H. GP IEEE TI A compact 600 GHz electronically tunable vector measurement system for submillimeter wave imaging SO 2006 IEEE MTT-S INTERNATIONAL MICROWAVE SYMPOSIUM DIGEST, VOLS 1-5 SE IEEE MTT-S International Microwave Symposium LA English DT Proceedings Paper CT IEEE MTT-S International Microwave Symposium CY JUN 11-16, 2006 CL San Francisco, CA SP IEEE MTTS DE submillimeter wave imaging; submillimeter wave mixers; phase measurement ID PERMITTIVITY MEASUREMENTS AB A compact submillimeter wave transmission/reflection measurement system has been demonstrated at 560-635 GHz, with electronic tuning over the entire band. Maximum dynamic range measured at a single frequency is 90 dB (60 dB typical), and phase noise is less than +/- 2 degrees. By using a frequency steerable lens at the source output and mixer input, the frequency agility of the system can be used to scan the source and receive beams, resulting in near real-time imaging capability using only a single pixel. C1 [Dengler, Robert J.; Maiwald, Frank; Siegel, Peter H.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Dengler, RJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 12 TC 3 Z9 3 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0149-645X BN 978-0-7803-9541-1 J9 IEEE MTT S INT MICR PY 2006 BP 1923 EP + DI 10.1109/MWSYM.2006.249792 PG 2 WC Engineering, Electrical & Electronic SC Engineering GA BFS69 UT WOS:000244379004064 ER PT S AU Fung, AK Dawson, D Samoska, L Lee, K Oleson, C Boll, G AF Fung, A. K. Dawson, D. Samoska, L. Lee, K. Oleson, C. Boll, G. GP IEEE TI On-wafer vector network analyzer measurements in the 220-325 GHz frequency band SO 2006 IEEE MTT-S INTERNATIONAL MICROWAVE SYMPOSIUM DIGEST, VOLS 1-5 SE IEEE MTT-S International Microwave Symposium LA English DT Proceedings Paper CT IEEE MTT-S International Microwave Symposium CY JUN 11-16, 2006 CL San Francisco, CA SP IEEE MTTS DE MMIC amplifiers; coplanar transmission lines; coplanar waveguides; measurement ID F(T) AB We report on a full two-port on-wafer vector network analyzer test set for the 220-325 GHz (WR3) frequency band. The test set utilizes Oleson Microwave Labs frequency extenders with the Agilent 8510C network analyzer. Two port on-wafer measurements are made with GGB Industries coplanar waveguide (CPW) probes. With this test set we have measured the WR3 band S-parameters of amplifiers on-wafer, and the characteristics of the CPW wafer probes. Results for a three stage InP HEMT amplifier show 10 dB gain at 235 GHz [1], and that of a single stage amplifier, 2.9 dB gain at 231 GHz The approximate upper limit of loss per CPW probe range from 3.0 to 4.8 dB across the WR3 frequency band. C1 [Fung, A. K.; Dawson, D.; Samoska, L.; Lee, K.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Oleson, C.] Oleson Microwave Labs, Morgan Hill, CA 95037 USA. [Boll, G.] GGB Ind, Naples, FL 34101 USA. RP Fung, AK (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 9 TC 12 Z9 13 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0149-645X BN 978-0-7803-9541-1 J9 IEEE MTT S INT MICR PY 2006 BP 1931 EP + DI 10.1109/MWSYM.2006.249811 PG 2 WC Engineering, Electrical & Electronic SC Engineering GA BFS69 UT WOS:000244379004066 ER PT S AU Bloser, PF McConnell, ML Ryan, JM Barbier, LM Centa, A Hunter, SD Krizmanic, JF Link, JT de Nolfo, GA Son, SH AF Bloser, Peter F. McConnell, Mark L. Ryan, James M. Barbier, Louis M. Centa, Alan Hunter, Stanley D. Krizmanic, John F. Link, Jason T. de Nolfo, Georgia A. Son, Seunghee GP IEEE TI Simulated Performance of 3-DTI Gamma-Ray Telescope Concepts SO 2006 IEEE NUCLEAR SCIENCE SYMPOSIUM CONFERENCE RECORD, VOL 1-6 SE IEEE Nuclear Science Symposium Conference Record LA English DT Proceedings Paper CT 15th International Workshop on Room-Temperature Semiconductor X- and Gamma-Ray Detectors/ 2006 IEEE Nuclear Science Symposium CY OCT 29-NOV 04, 2006 CL San Diego, CA SP IEEE ID POLARIZATION; DIFFUSION; MISSION; MEGA AB We present Monte Carlo simulations of two astronomical gamma-ray telescope concepts based on the Three-Dimensional Track Imager (3-DTI) detector. The 3-DTI consists of a time projection chamber with two-dimensional, crossed-strip micro-well detector readout. The full three-dimensional reconstruction of charged-particle tracks in the gas volume is obtained from transient digitizers, which record the time signature of the charge collected in the wells of each strip. Such detectors hold great promise for advanced Compton telescope (ACT) and advanced pair telescope (APT) concepts due to the very precise measurement of charged particle momenta that is possible (Compton recoil electrons and electron-positron pairs, respectively). We have investigated the performance of baseline ACT and APT designs based on the 3-DTI detector using simulation tools based on GEANT3 and GEANT4, respectively. We present the expected imaging, spectroscopy, polarimetry, and background performance of each design. C1 [Bloser, Peter F.; McConnell, Mark L.; Ryan, James M.] Univ New Hampshire, Ctr Space Sci, Durham, NH 03824 USA. [Barbier, Louis M.; Centa, Alan; Hunter, Stanley D.; Krizmanic, John F.; Link, Jason T.; de Nolfo, Georgia A.; Son, Seunghee] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Bloser, PF (reprint author), Univ New Hampshire, Ctr Space Sci, Durham, NH 03824 USA. EM Peter.Bloser@unh.edu RI de Nolfo, Georgia/E-1500-2012 FU NASA APRA program FX This work was supported by the NASA APRA program NR 26 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1082-3654 BN 978-1-4244-0561-9 J9 IEEE NUCL SCI CONF R PY 2006 BP 411 EP 416 DI 10.1109/NSSMIC.2006.356186 PG 6 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BUC53 UT WOS:000288875600089 ER PT S AU Hunter, SD Baker, RG Barbier, LM Bloser, PF Cooper, L Krizmanic, JF Link, JT McConnell, ML de Nolfo, GA Ryan, JM Singh, S Son, S AF Hunter, Stanley D. Baker, Robert G. Barbier, Louis M. Bloser, Peter F. Cooper, LaVida Krizmanic, John F. Link, Jason T. McConnell, Mark L. de Nolfo, Georgia A. Ryan, James M. Singh, Satpal Son, Seunghee GP IEEE TI Medium-Energy Gamma-Ray Astrophysics with the 3-DTI Gamma-Ray Telescope SO 2006 IEEE NUCLEAR SCIENCE SYMPOSIUM CONFERENCE RECORD, VOL 1-6 SE IEEE Nuclear Science Symposium Conference Record LA English DT Proceedings Paper CT 15th International Workshop on Room-Temperature Semiconductor X- and Gamma-Ray Detectors/ 2006 IEEE Nuclear Science Symposium CY OCT 29-NOV 04, 2006 CL San Diego, CA SP IEEE ID DETECTORS AB Gamma-ray observations in the medium energy range (0.50-50.0 MeV) are central to unfolding many outstanding questions in astrophysics. The challenges of medium-energy gamma-ray observations, however, are the low photon statistics and large backgrounds. We review these questions, address the telescope technology requirements, and describe our development of the 3-Dimensional Track Imaging (3-DTI) Compton telescope and its performance for a new medium-energy gamma-ray mission. The 3-DTI is a large-volume time projection chamber (TPC) with a 2-dimensional gas micro-well detector (MWD) readout. C1 [Hunter, Stanley D.; Baker, Robert G.; Barbier, Louis M.; Cooper, LaVida; Singh, Satpal] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Bloser, Peter F.; McConnell, Mark L.; Ryan, James M.] Univ New Hampshire, Ctr Space Sci, Durham, NH 03824 USA. [Krizmanic, John F.; Link, Jason T.; de Nolfo, Georgia A.] NASA, CRESST, Greenbelt, MD 20771 USA. [Son, Seunghee] NASA, GSFC, Greenbelt, MD 20771 USA. RP Hunter, SD (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM Stanley.D.Hunter@nasa.gov RI Hunter, Stanley/D-2942-2012; de Nolfo, Georgia/E-1500-2012 NR 5 TC 2 Z9 2 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1082-3654 BN 978-1-4244-0561-9 J9 IEEE NUCL SCI CONF R PY 2006 BP 778 EP 782 DI 10.1109/NSSMIC.2006.355967 PG 5 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BUC53 UT WOS:000288875600155 ER PT S AU Stiles, BW Gim, Y Hamilton, G Hensley, S Johnson, WTK Shimada, J West, RD Callahan, P AF Stiles, Bryan W. Gim, Yonggyu Hamilton, Gary Hensley, Scott Johnson, William T. K. Shimada, Joanne West, Richard D. Callahan, Phil GP IEEE TI Ground processing of Cassini RADAR imagery of Titan SO 2006 IEEE RADAR CONFERENCE, VOLS 1 AND 2 SE IEEE Radar Conference LA English DT Proceedings Paper CT 2006 IEEE Radar Conference CY APR 24-27, 2006 CL Verona, NY SP IEEE Aerosp & Elect Syst Soc, Radar Syst Panel AB The Cassini RADAR instrument onboard the Cassini Orbiter is currently collecting SAR Imagery of the surface of Saturn's largest moon, Titan. This paper describes the ground processing of Cassini SAR data. We focus upon the unusual features of the data and how these features impact the processing. We exhibit a data dependent mechanism we have implemented for eliminating artifacts due to attitude and ephemeris knowledge error. Finally we describe how we trade-off SAR performance vs. area of coverage when we design our spacecraft pointing profiles. C1 [Stiles, Bryan W.; Gim, Yonggyu; Hamilton, Gary; Hensley, Scott; Johnson, William T. K.; Shimada, Joanne; West, Richard D.; Callahan, Phil] CALTECH, Jet Propuls Lab, Pasadena, CA 91125 USA. RP Stiles, BW (reprint author), CALTECH, Jet Propuls Lab, Pasadena, CA 91125 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1097-5764 BN 978-0-7803-9496-4 J9 IEEE RAD CONF PY 2006 BP 1 EP + DI 10.1109/RADAR.2006.1631767 PG 2 WC Engineering, Electrical & Electronic; Remote Sensing; Telecommunications SC Engineering; Remote Sensing; Telecommunications GA BFS08 UT WOS:000244174500001 ER PT S AU Im, E Durden, SL Tanelli, S AF Im, Eastwood Durden, Stephen L. Tanelli, Simone GP IEEE TI Recent advances in spaceborne Precipitation Radar measurement techniques and technology SO 2006 IEEE RADAR CONFERENCE, VOLS 1 AND 2 SE IEEE Radar Conference LA English DT Proceedings Paper CT 2006 IEEE Radar Conference CY APR 24-27, 2006 CL Verona, NY SP IEEE Aerosp & Elect Syst Soc, Radar Syst Panel AB NASA is currently developing advanced instrument concepts and technologies for future spaceborne atmospheric radars, with an over-arching objective of making such instruments more capable in supporting future science needs and more cost effective. Two such examples are the Second-Generation Precipitation Radar (PR-2) and the Nexrad-InSpace (NIS). PR-2 is a 14/35-GHz dual-frequency rain radar with a deployable 5-meter, wide-swath scanned membrane antenna, a dual-polarized/dual-frequency receiver, and a realtime digital signal processor. It is intended for Low Earth Orbit (LEO) operations to provide greatly enhanced rainfall profile retrieval accuracy while consuming only a fraction of the mass of the current TRMM Precipitation Radar (PR). NIS is designed to be a 35-GHz Geostationary Earth Orbiting (GEO) radar for providing hourly monitoring of the life cycle of hurricanes and tropical storms. It uses a 35-m, spherical, lightweight membrane antenna and Doppler processing to acquire 3-dimensional information on the intensity and vertical motion of hurricane rainfall. C1 [Im, Eastwood; Durden, Stephen L.; Tanelli, Simone] CALTECH, Jet Propuls Lab, Pasadena, CA 91125 USA. RP Im, E (reprint author), CALTECH, Jet Propuls Lab, Pasadena, CA 91125 USA. EM eastwood.im@jpl.nasa.gov FU Earth-Sun System Technology Office (ESTO); Tropical Rain fall Measuring Mission (TRMM); Global Precipitation Measurements (GPM) Mission of NASA FX There search described in this paper was performed at the Jet Propulsion Laboratory, California Institute of Technology, under contract with the National Aeronautics and Space Administration (NASA). The authors would like to acknowledge the supports provided by the Earth-Sun System Technology Office (ESTO), the Tropical Rain fall Measuring Mission (TRMM) and the Global Precipitation Measurements (GPM) Mission of NASA. NR 5 TC 2 Z9 5 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1097-5764 BN 978-0-7803-9496-4 J9 IEEE RAD CONF PY 2006 BP 15 EP + DI 10.1109/RADAR.2006.1631769 PG 2 WC Engineering, Electrical & Electronic; Remote Sensing; Telecommunications SC Engineering; Remote Sensing; Telecommunications GA BFS08 UT WOS:000244174500003 ER PT S AU Rosen, PA Hensley, S Wheeler, K Sadowy, G Miller, T Shaffer, S Muellerschoen, R Jones, C Zebker, H Madsen, S AF Rosen, Paul A. Hensley, Scott Wheeler, Kevin Sadowy, Greg Miller, Tim Shaffer, Scott Muellerschoen, Ron Jones, Cathleen Zebker, Howard Madsen, Soren GP IEEE TI UAVSAR: A new NASA airborne SAR system for science and technology research SO 2006 IEEE RADAR CONFERENCE, VOLS 1 AND 2 SE IEEE Radar Conference LA English DT Proceedings Paper CT 2006 IEEE Radar Conference CY APR 24-27, 2006 CL Verona, NY SP IEEE Aerosp & Elect Syst Soc, Radar Syst Panel DE electronically scanned array; interferometry; radar; SAR; UAV ID RADAR INTERFEROMETRY AB NASA's Jet Propulsion Laboratory is currently building a reconfigurable, polarimetric L-band synthetic aperture radar (SAR), specifically designed to acquire airborne repeat track SAR data for differential interferometnic measurements. Differential interferometry can provide key deformation measurements, important for studies of earthquakes, volcanoes and other dynamically changing phenomena. Using precision real-time GPS and a sensor controlled flight management system, the system will be able to fly predefined paths with great precision. The expected performance of the flight control system will constrain the flight path to be within a 10 m diameter tube about the desired flight track. The radar will be designed to be operable on a UAV (Unpiloted Arial Vehicle) but will initially be demonstrated on a on a NASA Gulfstream III. The radar will be fully polarimetric, with a range bandwidth of 80 MHz (2 m range resolution), and will support a 16 km range swath. The antenna will be electronically steered along track to assure that the antenna beam can be directed independently, regardless of the wind direction and speed. Other features supported by the antenna include elevation monopulse and pulse-to-pulse re-steering capabilities that will enable some novel modes of operation. The system will nominally operate at 45,000 ft (13800 m). The program began as an Instrument Incubator Project (HP) funded by NASA Earth Science and Technology Office (ESTO). C1 [Rosen, Paul A.; Hensley, Scott; Wheeler, Kevin; Sadowy, Greg; Miller, Tim; Shaffer, Scott; Muellerschoen, Ron; Jones, Cathleen; Zebker, Howard; Madsen, Soren] CALTECH, Jet Propuls Lab, Radar Sci & Engn Sect, Pasadena, CA 91125 USA. RP Rosen, PA (reprint author), CALTECH, Jet Propuls Lab, Radar Sci & Engn Sect, Pasadena, CA 91125 USA. EM Paul.A.Rosen@jpl.nasa.gov NR 5 TC 11 Z9 12 U1 4 U2 6 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1097-5764 BN 978-0-7803-9496-4 J9 IEEE RAD CONF PY 2006 BP 22 EP + DI 10.1109/RADAR.2006.1631770 PG 2 WC Engineering, Electrical & Electronic; Remote Sensing; Telecommunications SC Engineering; Remote Sensing; Telecommunications GA BFS08 UT WOS:000244174500004 ER PT S AU Chapin, E Chan, SF Chapman, BD Chen, CW Martin, JM Michel, TR Muellerschoen, RJ Pi, XQ Rosen, PA AF Chapin, Elaine Chan, Samuel F. Chapman, Bruce D. Chen, Curtis W. Martin, Jan M. Michel, Thierry R. Muellerschoen, Ronald J. Pi, Xiaoqing Rosen, Paul A. GP IEEE TI Impact of the ionosphere on an L-band space based radar SO 2006 IEEE RADAR CONFERENCE, VOLS 1 AND 2 SE IEEE Radar Conference LA English DT Proceedings Paper CT 2006 IEEE Radar Conference CY APR 24-27, 2006 CL Verona, NY SP IEEE Aerosp & Elect Syst Soc, Radar Syst Panel ID POLAR IONOSPHERE; FARADAY-ROTATION; SCINTILLATION; IRREGULARITIES; PHASE; INTERFEROMETRY; LINKS; CAP AB We have quantified the impact that the ionosphere would have on a L-band interferometric Synthetic Aperture Radar (SAR) mission using a combination of simulation, modeling, Global Positioning System (GPS) data collected during the last solar maximum, and existing spaceborne SAR data. Using the Jet Propulsion Laboratory's Global Ionospheric Maps (GIM) total electron content (TEC) estimates derived from the worldwide array of GPS stations, we determined that the sun synchronous orbit which would minimize TEC at the time of imaging has dawn and dusk equator crossings. Such an orbit also avoids the equatorial post-sunset irregularities. We used the GIM data to examine the day-to-day variability in the background ionosphere and to quantify the impact of the background ionosphere on single pass SAR performance. With the exception of Faraday rotation related effects on single polarization systems, degradation due to the background ionosphere can be avoided if a reasonable model for the ionosphere is used during processing. Our studies reveal that Faraday rotation angles rarely exceeded the 10 degrees threshold that impacts biomass retrieval and that repeat pass interferometric SAR decorrelation due to variations in the background ionosphere causing variable Faraday rotations is a negligible effect. Even a dawn-dusk orbit will not avoid high latitude ionospheric irregularities. We evaluated the strength of the ionospheric irregularities using GPS scintillation data collected at Fairbanks, Alaska and modeled the impact of these irregularities on azimuth resolution, azimuth displacement, peak sidelobe ratio (PSLR), and integrated sidelobe ratio (ISLR). Our examination of ionospheric artifacts in InSAR data has revealed that the artifacts occur primarily in the polar cap data, not auroral zone data as was previously thought. C1 [Chapin, Elaine; Chan, Samuel F.; Chapman, Bruce D.; Chen, Curtis W.; Martin, Jan M.; Michel, Thierry R.; Muellerschoen, Ronald J.; Pi, Xiaoqing; Rosen, Paul A.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Chapin, E (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Elaine.Chapin@jpl.nasa.gov NR 22 TC 7 Z9 7 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1097-5764 BN 978-0-7803-9496-4 J9 IEEE RAD CONF PY 2006 BP 51 EP + DI 10.1109/RADAR.2006.1631775 PG 2 WC Engineering, Electrical & Electronic; Remote Sensing; Telecommunications SC Engineering; Remote Sensing; Telecommunications GA BFS08 UT WOS:000244174500009 ER PT S AU Ni, JJ Arndt, D Ngo, P Phan, C Gross, J AF Ni, Jianjun Arndt, Dickey Ngo, Phong Phan, Chau Gross, Julia GP IEEE TI Ultra-wideband two-cluster tracking system design with Angle of Arrival algorithm SO 2006 IEEE RADAR CONFERENCE, VOLS 1 AND 2 SE IEEE Radar Conference LA English DT Proceedings Paper CT 2006 IEEE Radar Conference CY APR 24-27, 2006 CL Verona, NY SP IEEE Aerosp & Elect Syst Soc, Radar Syst Panel AB This paper describes a design effort for a prototype ultra-wideband (UWB) tracking system that is currently under development at NASA Johnson Space Center (JSC). The system is being studied for use in tracking of lunar/Mars rovers during early exploration missions when satellite navigation systems are not available. The UWB technology is exploited to implement the tracking system due to its properties such as high data rate, fine time resolution, low power spectral density and multipath immunity. A two-cluster prototype design using commercially available UWB products is proposed to implement the Angle Of Arrival (AOA) tracking methodology in this research effort. Simulations show that the AOA algorithm can achieve the fine tracking resolution with low noise Time Difference Of Arrival (TDOA) estimates. The outdoor tests demonstrate the UWB tracking feasibility. C1 [Ni, Jianjun; Arndt, Dickey; Ngo, Phong; Phan, Chau; Gross, Julia] NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Ni, JJ (reprint author), NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. EM david.ni1@jsc.nasa.gov FU National Research Council Research Associateship Award at NASA Johnson Space Center FX This research was performed while the author held a National Research Council Research Associateship Award at NASA Johnson Space Center. NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1097-5764 BN 978-0-7803-9496-4 J9 IEEE RAD CONF PY 2006 BP 148 EP + PG 2 WC Engineering, Electrical & Electronic; Remote Sensing; Telecommunications SC Engineering; Remote Sensing; Telecommunications GA BFS08 UT WOS:000244174500023 ER PT S AU Muellerschoen, RJ Chen, CW Hensley, S Rodriguez, E AF Muellerschoen, Ronald J. Chen, Curtis W. Hensley, Scott Rodriguez, Ernesto GP IEEE TI Error analysis for high resolution topography with bi-static single-pass SAR interferometry SO 2006 IEEE RADAR CONFERENCE, VOLS 1 AND 2 SE IEEE Radar Conference LA English DT Proceedings Paper CT 2006 IEEE Radar Conference CY APR 24-27, 2006 CL Verona, NY SP IEEE Aerosp & Elect Syst Soc, Radar Syst Panel ID RADAR AB We present a flow down error analysis from the radar system to topographic height errors for bi-static single pass SAR interferometry for a satellite tandem pair. Because of orbital dynamics the baseline length and baseline orientation evolve spatially and temporally, the height accuracy of the system is modeled as a function of the spacecraft position and ground location. Vector sensitivity equations of height and the planar error components due to metrology, media effects, and radar system errors are derived and evaluated globally for a baseline mission. Included in the model are terrain effects that contribute to layover and shadow and slope effects on height errors. The analysis also accounts for non-overlapping spectra and the non-overlapping bandwidth due to differences between the two platforms' viewing geometries. The model is applied to a 514 kin altitude 97.4 degree inclination tandem satellite mission with a 300 in baseline separation and X-band SAR. Results from our model indicate that global DTED (Digital Terrain Elevation Data) level 3 can be achieved. C1 [Muellerschoen, Ronald J.; Chen, Curtis W.; Hensley, Scott; Rodriguez, Ernesto] CALTECH, Jet Prop Lab, Radar Sci & Engn, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. RP Muellerschoen, RJ (reprint author), CALTECH, Jet Prop Lab, Radar Sci & Engn, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. EM Ronald.J.Muellerschoen@jpl.nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1097-5764 BN 978-0-7803-9496-4 J9 IEEE RAD CONF PY 2006 BP 626 EP + DI 10.1109/RADAR.2006.1631866 PG 2 WC Engineering, Electrical & Electronic; Remote Sensing; Telecommunications SC Engineering; Remote Sensing; Telecommunications GA BFS08 UT WOS:000244174500100 ER PT S AU Gurrola, EM Rosen, PA Aivazis, M AF Gurrola, Eric M. Rosen, Paul A. Aivazis, Michael GP IEEE TI Distributed computing framework for synthetic aperture radar application SO 2006 IEEE Radar Conference, Vols 1 and 2 SE Radar Conference LA English DT Proceedings Paper CT 2006 IEEE Radar Conference CY APR 24-27, 2006 CL Verona, NY SP IEEE Aerosp & Elect Syst Soc, Radar Syst Panel ID EARTHS SURFACE; INTERFEROMETRY AB We are developing an extensible software framework, in response to Air Force and NASA needs for distributed computing facilities for a variety of radar applications. The objective of this work is to develop a Python-based software framework, that is the framework elements of the middleware that allows developers to control processing flow on a grid in a distributed computing environment Framework architectures to date allow developers to connect processing functions together as interchangeable objects, thereby allowing a data flow graph to be devised for a specific problem to be solved. The Pyre framework, developed at the California Institute of Technology (Caltech), and now being used as the basis for next-generation radar processing at JPL, is a Python-based software framework. We have extended the Pyre framework to include new facilities to deploy processing components as services, including components that monitor and assess the state of the distributed network for eventual real-time control of grid resources. C1 CALTECH, NASA, Jet Prop Lab, Radar Sci & Engn Sect, Pasadena, CA 91125 USA. RP Gurrola, EM (reprint author), CALTECH, NASA, Jet Prop Lab, Radar Sci & Engn Sect, Pasadena, CA 91125 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1097-5764 BN 978-0-7803-9496-4 J9 RADAR CONF PY 2006 BP 696 EP 701 DI 10.1109/RADAR.2006.1631877 PG 6 WC Engineering, Electrical & Electronic; Remote Sensing; Telecommunications SC Engineering; Remote Sensing; Telecommunications GA BFS08 UT WOS:000244174500111 ER PT B AU Stancliff, SB Dolan, JM Trebi-Ollermu, A AF Stancliff, S. B. Dolan, J. M. Trebi-Ollermu, A. GP IEEE TI Mission reliability estimation for multirobot team design SO 2006 IEEE/RSJ INTERNATIONAL CONFERENCE ON INTELLIGENT ROBOTS AND SYSTEMS, VOLS 1-12 LA English DT Proceedings Paper CT IEEE/RSJ International Conference on Intelligent Robots and Systems CY OCT 09-13, 2006 CL Beijing, PEOPLES R CHINA SP IEEE, RSJ DE mobile robots; multirobot systems; mission design; reliability AB One reason given for the use of multirobot systems is that many cheap robots are more reliable than one expensive robot. To date, however, there has been no quantitative analysis to support this assertion. This paper presents the first quantitative support for the argument that larger teams of less-reliable robots can perform certain missions more reliably than smaller teams of more-reliable robots. Our results show that for short missions, in fact, a team of four robots can provide greater mission reliability than a team of two robots, even when the individual robots in the team of four have reliability that is an order of magnitude lower. These results suggest that considerable cost reductions can be achieved for some missions by choosing larger teams of less-reliable robots over smaller teams of more-reliable robots. C1 Carnegie Mellon Univ, Inst Robot, Pittsburgh, PA 15213 USA. Jet Propuls Lab, Pasadena, CA 91109 USA. RP Stancliff, SB (reprint author), Carnegie Mellon Univ, Inst Robot, Pittsburgh, PA 15213 USA. EM stancliff@cmu.edu; jmd@cs.cmu.edu; Ashitey.Trebi-Ollennu@jpl.nasa.gov NR 12 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0258-8 PY 2006 BP 2206 EP 2211 DI 10.1109/IROS.2006.282562 PG 6 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Robotics SC Automation & Control Systems; Computer Science; Robotics GA BFY57 UT WOS:000245452402055 ER PT B AU Serrano, N AF Serrano, Navid GP IEEE TI A Bayesian framework for landing site selection during autonomous spacecraft descent SO 2006 IEEE/RSJ International Conference on Intelligent Robots and Systems, Vols 1-12 LA English DT Proceedings Paper CT IEEE/RSJ International Conference on Intelligent Robots and Systems CY OCT 09-13, 2006 CL Beijing, PEOPLES R CHINA SP IEEE, RSJ DE autonomous spacecraft; safe landing; terrain characterization; Bayesian Networks AB The success of a landed space exploration mission depends largely on the final landing site. Factors influencing site selection include safety, fuel-consumption, and scientific return. This paper addresses the problem of selecting the best available landing site based on these factors in real-time during autonomous spacecraft descent onto a planetary surface. The problem is modeled probabilistically using Bayesian Networks (BNs). BNs provide a means of representing the causal relationships between variables that impact the quality of a landing site. The final landing site is determined via probabilistic reasoning based on terrain safety derived from on-board sensors, available fuel based on spacecraft descent dynamics, and regions of interest defined by mission scientists. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Serrano, N (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 14 TC 4 Z9 4 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0258-8 PY 2006 BP 5112 EP 5117 DI 10.1109/IROS.2006.282603 PG 6 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Robotics SC Automation & Control Systems; Computer Science; Robotics GA BFY57 UT WOS:000245452405031 ER PT S AU Amoozegar, F AF Amoozegar, Farid GP IEEE TI Large phased array radar using networked small parabolic reflectors SO 2006 IEEE SENSOR ARRAY AND MULTICHANNEL SIGNAL PROCESSING WORKSHOP PROCEEDINGS, VOLS 1 AND 2 SE Proceedings of the IEEE Sensor Array and Multichannel Signal Processing Workshop LA English DT Proceedings Paper CT 4th IEEE Sensor Array and Multichannel Signal Processing Workshop CY JUL 12-14, 2006 CL Waltham, MA SP IEEE Signal Proc Soc, IEEE Boston Sect, Air Force Res Lab, Def Adv Res Projects Agcy, Air Force Off Sci Res, Off Naval Res AB Multifunction phased array systems with radar, telecom, and imaging applications have already been established for flat plate phased arrays of dipoles, or waveguides. In this paper the design trades and candidate options for combining the radar and telecom functions of the deep space network (DSN) into a single large transmit array of small parabolic reflectors will be discussed. In particular the effect of combing the radar and telecom functions on the sizes of individual antenna apertures and the corresponding spacing between the antenna elements of the array will be analyzed. A heterogeneous architecture for the DSN large transmit array is proposed to meet the radar and telecom requirements while considering the budget, scheduling, and strategic planning constrains. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Amoozegar, F (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Farid.Amoozegar@jpl.nasa.gov NR 16 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1551-2282 BN 1-4244-0308-1 J9 PR IEEE SEN ARRAY PY 2006 BP 607 EP 615 PG 9 WC Computer Science, Artificial Intelligence; Remote Sensing; Imaging Science & Photographic Technology SC Computer Science; Remote Sensing; Imaging Science & Photographic Technology GA BFN69 UT WOS:000243341900128 ER PT S AU Woodard, SE Taylor, BD AF Woodard, Stanley E. Taylor, Bryant D. GP IEEE TI A magnetic field response recorder: A new tool for measurement acquisition SO 2006 IEEE SENSORS, VOLS 1-3 SE IEEE Sensors LA English DT Proceedings Paper CT 5th IEEE Sensors Conference CY OCT 22-25, 2006 CL Daegu, SOUTH KOREA SP IEEE AB A magnetic field response recorder was developed to facilitate a measurement acquisition method that uses magnetic fields to power and to interrogate all sensors. Sensors are designed as electrically passive inductive-capacitive or passive inductive-capacitive-resistive circuits that produce magnetic field responses when electrically activated by oscillating magnetic fields. When electrically activated, the sensor's magnetic field response attributes (frequency, amplitude and bandwidth) correspond to the one or more physical states that each sensor measures. The response recorder makes it possible to simultaneously measure two unrelated physical properties using this class of sensors. The recorder is programmable allowing it to analyze one or more response attributes simultaneously. A single sensor design will be used to demonstrate that the acquisition method and the sensor example can be used to for all phases of a component's life from manufacturing to damage that can destroy it. C1 [Woodard, Stanley E.] NASA, Res & Technol Directorate, Langley Res Ctr, Hampton, VA 23665 USA. [Taylor, Bryant D.] Swales Corp, Hampton, VA 23665 USA. RP Woodard, SE (reprint author), NASA, Res & Technol Directorate, Langley Res Ctr, Hampton, VA 23665 USA. EM Stanley.E.Woodard@nasa.gov; B.D.Taylor@larc.nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1930-0395 BN 978-1-4244-0375-2 J9 IEEE SENSOR PY 2006 BP 789 EP + PG 3 WC Acoustics; Engineering, Electrical & Electronic; Optics SC Acoustics; Engineering; Optics GA BGN28 UT WOS:000248587500199 ER PT B AU Bolton, ML Bass, EJ Comstock, JR AF Bolton, Matthew L. Bass, Ellen J. Comstock, James R., Jr. GP IEEE TI A toolset to support the development of spatial and temporal judgment experiments for Synthetic Vision Systems SO 2006 IEEE SYSTEMS AND INFORMATION ENGINEERING DESIGN SYMPOSIUM LA English DT Proceedings Paper CT IEEE Systems and Information Engineering Design Symposium CY APR 28, 2006 CL Charlottesville, VA SP IEEE AB Synthetic Vision Systems (SVS) are cockpit technologies which depict computer generated perspective displays of terrain surrounding an aircraft in order to prevent incidents of controlled flight into terrain. This paper describes a toolset designed to support an experiment that assessed the ability of different SVS displays to convey spatial awareness (the ability of a pilot to identify terrain, his ability to identify its relative location, and his ability to identify its relative location in the future) using spatial and temporal judgments. This toolset was used successfully to design and conduct this experiment. Work is currently being conducted to generalize the applicability of the toolset so that it can be used to support a wider range of experiments. C1 [Bolton, Matthew L.; Bass, Ellen J.] Univ Virginia, Charlottesville, VA 22904 USA. [Bolton, Matthew L.; Bass, Ellen J.; Comstock, James R., Jr.] NASA Langley Res Ctr, Hampton, VA 23681 USA. RP Bolton, ML (reprint author), Univ Virginia, Charlottesville, VA 22904 USA.; Bolton, ML (reprint author), NASA Langley Res Ctr, Hampton, VA 23681 USA. EM mlb4b@Virginia.edu; ejb4n@virginia.edu; J.R.Comstock@larc.nasa.gov FU NIA Rising Star Fellowship for Matthew Bolton [UVA-03-01, 4817-UV] FX Manuscript received April 10, 2006. This work was supported in part by NIA Rising Star Fellowship for Matthew Bolton, UVA-03-01, Sub-Award Number: 4817-UV NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0473-5 PY 2006 BP 55 EP + DI 10.1109/SIEDS.2006.278713 PG 2 WC Computer Science, Artificial Intelligence; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Transportation Science & Technology SC Computer Science; Engineering; Transportation GA BFW73 UT WOS:000245140100010 ER PT S AU Gifford, KK Kuzminsky, S Williams, S Saiz, JR AF Gifford, Kevin K. Kuzminsky, Sebastian Williams, Shea Saiz, John R. GP IEEE TI BioNet: A developer-centric middleware architecture for heterogeneous devices and protocols SO 2006 IEEE WIRELESS COMMUNICATIONS AND NETWORKING CONFERENCE (WCNC 2006), VOLS 1-4 SE IEEE Wireless Communications and Networking Conference LA English DT Proceedings Paper CT IEEE Wireless Communications and Networking Conference CY APR 03-06, 2006 CL Las Vegas, NV SP IEEE AB This paper overviews a wireless middleware architecture, entitled "BioNet", which is under development in support of NASA's Exploration Systems Mission. The middleware architecture is novel from the standpoint of the heterogeneity of both devices and protocols supported. A fundamental design decision allows for multi-developer system extensibility which alleviates the problem of the monopolistic single-vendor model where only the original developer of the middleware architecture can efficiently extend the system functionality. C1 [Gifford, Kevin K.; Kuzminsky, Sebastian; Williams, Shea] Univ Colorado, Boulder, CO 80309 USA. [Saiz, John R.] NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Gifford, KK (reprint author), Univ Colorado, Boulder, CO 80309 USA. NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1525-3511 BN 978-1-4244-0269-4; 978-1-4244-0270-0 J9 IEEE WCNC PY 2006 BP 520 EP 525 PG 6 WC Computer Science, Hardware & Architecture; Engineering, Electrical & Electronic; Telecommunications SC Computer Science; Engineering; Telecommunications GA BTE80 UT WOS:000286659000086 ER PT S AU Baloch, S Arslan, T Stoica, A AF Baloch, S. Arslan, T. Stoica, A. BE Koch, A Leong, P Koch, A TI An efficient fault tolerance scheme for preventing single event disruptions in reconfigurable architectures SO 2006 INTERNATIONAL CONFERENCE ON FIELD PROGRAMMABLE LOGIC AND APPLICATIONS, PROCEEDINGS SE International Conference on Field Programmable and Logic Applications LA English DT Proceedings Paper CT 16th International Conference on Field Programmable Logic and Applications CY AUG 28-30, 2006 CL Madrid, SPAIN SP Univ Autonoma Madrid, Sch Engn, IEEE Circuits & Syst Soc AB Reconfigurable architectures are becoming increasingly popular with space related design engineers as they are inherently flexible to meet multiple requirements and offer significant performance and cost savings for critical applications. As the microelectronics industry has advanced, Integrated Circuit (IQ design and reconfigurable architectures (FPGAs, reconfigurable SoC and etc) have experienced dramatic increase in density and speed. These advancements have serious implications for the reconfigurable architectures when used in space environment where IC is subject to total ionization dose (TID) and single event effects as well. Due to transient nature of single event upsets (SEUs), these are most difficult to avoid in space-borne reconfigurable architectures. We present a unique SEU fault tolerance technique based upon double redundancy with comparison to overcome the overheads associated with the conventional schemes. C1 [Baloch, S.; Arslan, T.; Stoica, A.] Univ Edinburgh, Sch Elect & Engn, Kings Bldg,Mayfield Rd, Edinburgh EH9 3JL, Midlothian, Scotland. [Baloch, S.; Arslan, T.] Inst Syst Level Integrat, Livingston EH547EG, Scotland. [Stoica, A.] NASA, JPL, Pasadena, CA 91109 USA. RP Baloch, S (reprint author), Univ Edinburgh, Sch Elect & Engn, Kings Bldg,Mayfield Rd, Edinburgh EH9 3JL, Midlothian, Scotland. NR 14 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1946-1488 BN 978-1-4244-0312-7 J9 I C FIELD PROG LOGIC PY 2006 BP 705 EP 708 PG 4 WC Computer Science, Hardware & Architecture; Computer Science, Interdisciplinary Applications SC Computer Science GA BFW14 UT WOS:000245038300110 ER PT S AU Stefatos, EF Arslan, T Keymeulen, D Ferguson, I AF Stefatos, Evangelos F. Arslan, Tughrul Keymeulen, Didier Ferguson, Ian BE Koch, A Leong, P Koch, A TI Integrating the electronics of the control-loops of the JPL/Boeing gyroscope within an evolvable hardware architecture SO 2006 INTERNATIONAL CONFERENCE ON FIELD PROGRAMMABLE LOGIC AND APPLICATIONS, PROCEEDINGS SE International Conference on Field Programmable and Logic Applications LA English DT Proceedings Paper CT 16th International Conference on Field Programmable Logic and Applications CY AUG 28-30, 2006 CL Madrid, SPAIN SP Univ Autonoma Madrid, Sch Engn, IEEE Circuits & Syst Soc AB This paper presents an autonomous custom reconfigurable architecture that employs Evolvable Hardware technology to accomplish the electronics of the control-loops of the JPL/Boeing gyroscope. The proposed adaptive hardware presents two functional modes. The switch between these two is controlled by an evolutionary strategy with only objective the most efficient adaptation of the system's functionality. The choice of operational mode mainly depends on the density of faults that occur on the hardware. Simulation results have shown that our architecture is able to adapt the functionality of the sensor's electronics within the presence of permanent stuck-at faults that occur on the user and configuration memory of the system. Moreover, the analysis of the power consumption reveals that the electronics that are accomplished within our reconfigurable architecture consume significantly less power compared with equavalent circuits, which are designed within industrial FPGAs. C1 [Stefatos, Evangelos F.; Arslan, Tughrul] Univ Edinburgh, Sch Engn & Elect, Kings Bldg,Mayfield Rd, Edinburgh EH9 3JL, Midlothian, Scotland. [Keymeulen, Didier; Ferguson, Ian] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Stefatos, EF (reprint author), Univ Edinburgh, Sch Engn & Elect, Kings Bldg,Mayfield Rd, Edinburgh EH9 3JL, Midlothian, Scotland. EM Evangelos.Stefatos@ee.ed.ac.uk; Didier.Keymeulen@jpl.nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1946-1488 BN 978-1-4244-0312-7 J9 I C FIELD PROG LOGIC PY 2006 BP 861 EP 864 PG 4 WC Computer Science, Hardware & Architecture; Computer Science, Interdisciplinary Applications SC Computer Science GA BFW14 UT WOS:000245038300145 ER PT B AU Silk, EA Kim, J Kiger, K AF Silk, Eric A. Kim, Jungho Kiger, Ken GP IEEE TI Enhanced surface spray cooling with embedded and compound extended surface structures SO 2006 PROCEEDINGS 10TH INTERSOCIETY CONFERENCE ON THERMAL AND THERMOMECHANICAL PHENOMENA IN ELECTRONICS SYSTEMS, VOLS 1 AND 2 LA English DT Proceedings Paper CT 10th Intersociety Conference on Thermal and Thermomechanical Phenomena in Electronic Systems CY MAY 30-JUN 02, 2006 CL San Diego, CA SP IEEE, CPMT, Heat Transfer Div K 16, ASME, Elect & Photon Packaging Div DE enhanced surfaces; spray cooling; heat transfer; dissolved gasses ID CRITICAL HEAT-FLUX; TRANSFER MECHANISM; ROUGHNESS; FC-72 AB Experiments were conducted to study the effects of enhanced surface structures on heat flux using spray cooling. The surface enhancements consisted of embedded structures (dimples, pores, and tunnels) and compound extended surface enhancements (straight fins, cubic pin fins and dimples) machined on and within the top surface of copper heater blocks. Each copper block had a projected cross-sectional area of 2.0 cm(2). Measurements were also obtained on a heater block with a flat surface for baseline comparison purposes. A 2x2 nozzle array was used with PF-5060 as the working fluid. Thermal performance data was obtained under nominally degassed (chamber pressure of 41.4 kPa) and gassy conditions (chamber with N-2 gas at 101 kPa) with a bulk fluid temperature of 20.5 degrees C. Results for both the nominally degassed and gassy cases show that the highest critical heat flux (CHF) was attained using straight fins and porous tunnels. For the nominally degassed case, both had a CHF of approximate to 142 W/cm(2) while for the gassy case their CHF values increased to 175 W/cm(2). This gave an enhancement relative to the respective flat surface degassed/gassy cases of approximate to 77% and 62% respectively. C1 [Silk, Eric A.] NASA, Goddard Space Flight Ctr, Thermal Engn Branch, Code 661, Greenbelt, MD 20771 USA. [Kim, Jungho; Kiger, Ken] Univ Maryland, Dept Engn Mech, College Pk, MD 20742 USA. RP Silk, EA (reprint author), NASA, Goddard Space Flight Ctr, Thermal Engn Branch, Code 661, Greenbelt, MD 20771 USA. EM Eric.A.Silk@nasa.gov; kimjh@umd.edu; kkiger@umd.edu FU Thermal Management group of the Laboratory for Physical Sciences; Laser Risk Reduction Program (LRRP) at the NASA Goddard Space Flight Center; Office of Naval Research [N000140410315] FX This research was supported by the Thermal Management group of the Laboratory for Physical Sciences and funded by the Laser Risk Reduction Program (LRRP) at the NASA Goddard Space Flight Center. Dr. Jungho Kim and Dr.Kenneth Kiger would like to acknowledge the generous support of the Office of Naval Research under contract number N000140410315 directed by Dr. Mark Spector. The authors would like to thank Dr. Paul Boudreaux, for his assistance, as well as J.B. Dotellis and Lester Lorentz for their support in machining the copper test articles and their surfaces. Special thanks is also given to Richard Freburger and Alice Rector of NASA Goddard Space Flight Center, Juan Rodriguez of University of Puerto Rico at Mayaguez for their test support as well as Parker Hannifins Gas Turbine Fluid Systems Division (GTFSD) for supplying the spray nozzle. NR 22 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-0-7803-9523-7 PY 2006 BP 215 EP + PG 3 WC Thermodynamics; Engineering, Manufacturing; Engineering, Electrical & Electronic; Engineering, Mechanical SC Thermodynamics; Engineering GA BFP48 UT WOS:000243624500029 ER PT B AU Tasooji, A Ghaffarian, R Rinaldi, A AF Tasooji, Amaneh Ghaffarian, Reza Rinaldi, Antonio GP IEEE TI Design parameters influencing reliability of CCGA assembly: A sensitivity analysis SO 2006 PROCEEDINGS 10TH INTERSOCIETY CONFERENCE ON THERMAL AND THERMOMECHANICAL PHENOMENA IN ELECTRONICS SYSTEMS, VOLS 1 AND 2 LA English DT Proceedings Paper CT 10th Intersociety Conference on Thermal and Thermomechanical Phenomena in Electronic Systems CY MAY 30-JUN 02, 2006 CL San Diego, CA SP IEEE, CPMT, Heat Transfer Div K 16, ASME, Elect & Photon Packaging Div DE cCGA; solder; reliability; creep; fatigue; thermal cycling; microelectronic pack-age; column grid array AB Area Array microelectronic packages with small pitch and large I/O counts are now widely used in microelectronics packaging. The impact of various package design and materials/process parameters on reliability has been studied through extensive literature review. Reliability of Ceramic Column Grid Array (CCGA) package assemblies has been evaluated using JPL thermal cycle test results (-50 degrees/75 degrees C, -55 degrees/100 degrees C, and -55 degrees/125 degrees C), as well as those reported by other investigators. A sensitivity analysis has been performed using the literature data to study the impact of design parameters and global/local stress conditions on assembly reliability. The applicability of various life-prediction models for CCGA design has been investigated by comparing model's predictions with the experimental thermal cycling data. Finite Element Method (FEM) analysis has been conducted to assess the state of the stress/strain in CCGA assembly under different thermal cycling, and to explain the different failure modes and locations observed in JPL test assemblies. C1 [Tasooji, Amaneh; Rinaldi, Antonio] Arizona State Univ, POB 876006, Tempe, AZ 85287 USA. [Ghaffarian, Reza] CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Tasooji, A (reprint author), Arizona State Univ, POB 876006, Tempe, AZ 85287 USA. EM Amaneh.tasooji@asu.edu; Raza.Ghaffrian@JPL.NASA.GOV; anto@asu.edu NR 19 TC 2 Z9 2 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-0-7803-9523-7 PY 2006 BP 1056 EP + PG 2 WC Thermodynamics; Engineering, Manufacturing; Engineering, Electrical & Electronic; Engineering, Mechanical SC Thermodynamics; Engineering GA BFP48 UT WOS:000243624500145 ER PT B AU Rahim, MK Suhling, JC Jaeger, RC Lall, P Knight, R Strickland, M Blanche, J AF Rahim, M. Kaysar Suhling, Jeffrey C. Jaeger, Richard C. Lall, Pradeep Knight, Roy Strickland, Mark Blanche, Jim GP IEEE TI Reliability of flip chip assemblies subjected to extreme low temperatures SO 2006 PROCEEDINGS 10TH INTERSOCIETY CONFERENCE ON THERMAL AND THERMOMECHANICAL PHENOMENA IN ELECTRONICS SYSTEMS, VOLS 1 AND 2 LA English DT Proceedings Paper CT 10th Intersociety Conference on Thermal and Thermomechanical Phenomena in Electronic Systems CY MAY 30-JUN 02, 2006 CL San Diego, CA SP IEEE, CPMT, Heat Transfer Div K 16, ASME, Elect & Photon Packaging Div DE space electronics; cryogenic; flip chip; test chip; stress; reliability AB Electronic assemblies are approximately "stress free" near their assembly temperature, which is typically above 150 degrees C when encapsulants and solders are involved. As the assemblies are cooled below room temperature, the temperature difference between ambient and "stress free" conditions becomes extremely high, and the thermal expansion mismatch induced stresses, strains, and deformations in the assembly can become very large. This phenomenon is exacerbated by the changes in material behavior that occur at extreme low temperatures present in proposed NASA lunar and Mars missions. In particular, encapsulants become much more stiff/brittle losing their typical nonlinear/inelastic stress-strain characteristics and high strains to failure, and the yield stresses for solders become very high. In this work, we evaluated the mechanical performance and reliability of flip chip on laminate assemblies subjected to extreme low temperatures. Stress measurements have been made in the flip chip assemblies during thermal cycling using stress test chips incorporating piezoresistive sensor rosettes. The (111) silicon test chips were 5 x 5 mm in size, with perimeter solder balls on a 200-micron pitch. The obtained stress measurement data correlated well with the predictions of nonlinear finite element models. A microtester has been used to characterize the stress-strain behavior of the solder, underfill encapsulant, and PCB from -180 to +150C to aid in the numerical simulations. C1 [Rahim, M. Kaysar; Suhling, Jeffrey C.; Jaeger, Richard C.; Lall, Pradeep; Knight, Roy] Auburn Univ, Ctr Adv Vehicle Elect, Auburn, AL 36849 USA. [Strickland, Mark; Blanche, Jim] NASA, Huntsville, AL 35812 USA. RP Rahim, MK (reprint author), Auburn Univ, Ctr Adv Vehicle Elect, Auburn, AL 36849 USA. EM jsuhling@eng.auburn.edu FU NASA Center for Space Power and Advanced Electronics (CSPAE) [NCC8-237]; NASA Marshall Space Flight Center; NSF Center for Advanced Vehicle Electronics (CAVE) FX This work was funded by the NASA Center for Space Power and Advanced Electronics (CSPAE) under Cooperative Agreement NCC8-237 from the NASA Marshall Space Flight Center, and the NSF Center for Advanced Vehicle Electronics (CAVE). NR 15 TC 0 Z9 0 U1 1 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-0-7803-9523-7 PY 2006 BP 1379 EP + PG 2 WC Thermodynamics; Engineering, Manufacturing; Engineering, Electrical & Electronic; Engineering, Mechanical SC Thermodynamics; Engineering GA BFP48 UT WOS:000243624500190 ER PT B AU Tong, T Majumdar, A Zhao, Y Kasham, A Delzeit, L Meyyappan, M AF Tong, Tao Majumdar, Arun Zhao, Yang Kasham, Ali Delzeit, Lance Meyyappan, M. GP IEEE TI Indium assisted multiwalled carbon nanotube array thermal interface materials SO 2006 PROCEEDINGS 10TH INTERSOCIETY CONFERENCE ON THERMAL AND THERMOMECHANICAL PHENOMENA IN ELECTRONICS SYSTEMS, VOLS 1 AND 2 LA English DT Proceedings Paper CT 10th Intersociety Conference on Thermal and Thermomechanical Phenomena in Electronic Systems CY MAY 30-JUN 02, 2006 CL San Diego, CA SP IEEE, CPMT, Heat Transfer Div K 16, ASME, Elect & Photon Packaging Div DE carbon nanotubes; multiwalled; thermal interface materials; indium ID CONDUCTIVITY AB The state-of-the-art thermal interface materials (TIMs) for electronic cooling is briefly reviewed with an emphasis on the emerging trend of employing carbon nanotubes (CNTs) for enhanced thermal conduction across interfaces. Previous studies on CNT TIMs, however, indicated that despite the high thermal conductivities of CNTs themselves, heat conduction is limited by the direct contact interface between CNTs and the target surface. This has greatly limited the practical application of CNT TIMs. In this study, we thermally welded a thin indium layer between the CNT surface and the target surface, and observed an order of magnitude increase in thermal conductance similar to 10(6) W/m(2.)K across the interface compared with direct contact interface. With vacuum and cryogenic temperature compatibility, indium assisted CNT TIMs may find their future applications in areas from electronic chip cooling, cryogenic pumps, to thermal management in spacecrafts. C1 [Tong, Tao; Majumdar, Arun] Univ Calif Berkeley, Dept Mech Engn, Berkeley, CA 94720 USA. [Zhao, Yang; Kasham, Ali] Atlas Scientif Inc, San Jose, CA 95120 USA. [Delzeit, Lance; Meyyappan, M.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Tong, T (reprint author), Univ Calif Berkeley, Dept Mech Engn, Berkeley, CA 94720 USA. EM ttong@me.berkeley.edu FU NASA through SBIR program [18521] FX Financial support for this work was provided by NASA through SBIR program 18521. The authors thank Robert G. Azevedo for helpful discussion on indium deposition. The authors thank UC Berkeley Microlab for providing some experimental facilities. NR 20 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-0-7803-9523-7 PY 2006 BP 1406 EP + PG 2 WC Thermodynamics; Engineering, Manufacturing; Engineering, Electrical & Electronic; Engineering, Mechanical SC Thermodynamics; Engineering GA BFP48 UT WOS:000243624500193 ER PT S AU Brall, A AF Brall, Aron GP IEEE TI Human reliability issues in medical care - A customer viewpoint SO 2006 Proceedings - Annual Reliability and Maintainability Symposium, Vols 1 and 2 SE PROCEEDINGS : ANNUAL RELIABILITY AND MAINTAINABILITY SYMPOSIUM LA English DT Proceedings Paper CT Annual Reliability and Maintainability Symposium CY JAN 23-26, 2006 CL Newport Beach, CA SP IEEE DE human reliability; human error; customer complaint; error proofing AB Many errors occur in medical practice due to the lack of significant preventive methodologies. The presence of significant numbers of errors has been reported on in professional journals, as well as the popular press. Significant improvement in medical care may be possible through the application of error proofing methods from other disciplines including Reliability and Quality as applied in Manufacturing, Defense, and High Tech Hardware and Software Design. This has started to occur in several regions of the United States including Pittsburgh, PA. The institution of systematic policies, procedures, checklists, etc. has the capability of dramatic improvements in human error rates. C1 NASA, Goddard Space Flight Ctr, SRS Technol, Greenbelt, MD 20771 USA. RP Brall, A (reprint author), NASA, Goddard Space Flight Ctr, SRS Technol, Code 302-9,Bldg 6, Greenbelt, MD 20771 USA. NR 5 TC 4 Z9 4 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0149-144X BN 978-1-4244-0007-2 J9 P REL MAINT S PY 2006 BP 46 EP 50 PG 5 WC Computer Science, Software Engineering; Operations Research & Management Science; Statistics & Probability SC Computer Science; Operations Research & Management Science; Mathematics GA BGT51 UT WOS:000250419100008 ER PT S AU Datta, K AF Datta, Koushik GP IEEE TI Current knowledge about nanotechnology safety SO 2006 Proceedings - Annual Reliability and Maintainability Symposium, Vols 1 and 2 SE PROCEEDINGS : ANNUAL RELIABILITY AND MAINTAINABILITY SYMPOSIUM LA English DT Proceedings Paper CT Annual Reliability and Maintainability Symposium CY JAN 23-26, 2006 CL Newport Beach, CA SP IEEE DE nanotechnology; nanoparticle; nanomaterial; risk; safety; inhalation; ingestion; dermal; skin ID CARBON NANOTUBE MATERIAL; EXPOSURE AB This review paper provides insight into the risk faced by laboratory workers from suspected nanoparticle hazards. The potential hazard and risk is examined with respect to the dermal, inhalation, and ingestion pathways into the human body. Based on the current understanding, the risks are presented qualitatively from a system safety perspective as a function of likelihood and consequence. Without protective equipment, the likelihood of dermal exposure for carbon nanoparticles is high, but is low and very low for inhalation and ingestion pathways, respectively. The consequence for dermal exposure is likely to be dermatitis, but for the other two pathways there has been no clear evidence of any consequence. However, the consequences will be better judged after nanotechnology has had time to establish itself and more studies have been performed on the toxicological effects of nanoparticles. The surveyed papers propose that because nanoparticles vary in their chemical composition and biological and immunological properties, the risks posed by them also vary. Thus, each nanomaterial should be assessed individually for its health risks. C1 NASA, Ames Res Ctr, Stanford, CA 94305 USA. RP Datta, K (reprint author), NASA, Ames Res Ctr, MS 218-7, Stanford, CA 94305 USA. NR 6 TC 0 Z9 0 U1 0 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0149-144X BN 978-1-4244-0007-2 J9 P REL MAINT S PY 2006 BP 70 EP 74 PG 5 WC Computer Science, Software Engineering; Operations Research & Management Science; Statistics & Probability SC Computer Science; Operations Research & Management Science; Mathematics GA BGT51 UT WOS:000250419100012 ER PT S AU Feather, MS Cornford, SL AF Feather, Martin S. Cornford, Steven L. GP IEEE TI Relating risk and reliability predictions to design and development choices SO 2006 PROCEEDINGS - ANNUAL RELIABILITY AND MAINTAINABILITY SYMPOSIUM, VOLS 1 AND 2 SE Reliability and Maintainability Symposium LA English DT Proceedings Paper CT 52nd Annual Reliability and Maintainability Symposium CY JAN 23-26, 2006 CL Newport Beach, CA SP IEEE DE risk; reliability; design; optimization AB Ideally, planning and managing the design and development of a complex systems should: Consider the entire lifecycle (design, development, testing, integration, deployment, operation and decommissioning). Take risk and reliability into account, as well as more traditional measures such as cost and performance, when making tradeoff decisions. Provide understanding, and therefore motivation, as to the purpose of design artifacts (that piece is there to) and development activities (we'll be performing this test to). A key enabler to all of the above is the ability to relate design and development choices to risk and reliability predictions. If the number of choices were small (e.g., selection between a handful of alternatives) it would suffice to perform reliability analysis on them individually, and view the results side-by-side. The challenge is that in many cases the number of design and development alternatives is large. In this context, the problem of relating reliability predictions to design and development choices is non-trivial. Ongoing work towards a solution to this problem is the focus of this paper. Over several years we have developed a risk-based model the hallmark of which is the explicit representation of risk mitigations as options. We describe how this model functions, and the major implications of making mitigation options first class objects within an (otherwise relatively simple) analysis model. We also describe elaborations to this model's representation of risks, notably by the incorporation of fault tree notions. These improve the fidelity of the designs we are able to represent, and also offer the ability to represent design alternatives within the same framework. Finally, we describe the connections we are building between our risk analysis tool and other risk tools. The latter have greater strengths in their ability to represent and calculate over more elaborate risk structures, while our approach lends to them the aforementioned explicit treatment of the various forms of options for risk reduction. C1 [Feather, Martin S.; Cornford, Steven L.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Feather, MS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Martin.S.Feather@jpl.nasa.gov; Steven.L.Cornford@jpl.nasa.gov NR 17 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0149-144X BN 978-1-4244-0007-2 J9 P REL MAINT S PY 2006 BP 492 EP + DI 10.1109/RAMS.2006.1677422 PG 3 WC Computer Science, Software Engineering; Operations Research & Management Science; Statistics & Probability SC Computer Science; Operations Research & Management Science; Mathematics GA BGT51 UT WOS:000250419100081 ER PT S AU Datta, K Wiltsee, CB Briceno, A AF Datta, Koushik Wiltsee, Christopher B. Briceno, Anthony GP IEEE TI Does SOFIA require a crew escape system? SO 2006 PROCEEDINGS - ANNUAL RELIABILITY AND MAINTAINABILITY SYMPOSIUM, VOLS 1 AND 2 SE Reliability and Maintainability Symposium LA English DT Proceedings Paper CT 52nd Annual Reliability and Maintainability Symposium CY JAN 23-26, 2006 CL Newport Beach, CA SP IEEE DE SOFIA; crew escape; PRA; hazard analysis; decision making AB National Aeronautics and Space Administration (NASA) and Deutsches Zentrum fur Luft- and Raumfahrt (DLR) have been working together to create the Stratospheric Observatory For Infrared Astronomy (SOFIA). The design and modifications have progressed to the point that SOFIA will begin its development-phase flight tests in 2006. This paper shows the rationale for the SOFIA program's decision to not require a crew escape system during the development-phase flight tests. The dominant risk during the flight test phase is stall testing that has to be performed to meet NASA airworthiness and Federal Aviation Administration (FAA) certification requirements. The assessment showed that under a loss of control/loss of aircraft scenario during a stall test, the aircraft is unlikely to remain stable enough to allow existing crew escape systems to be effective. Similar examination of all other major risks showed that, apart from fire risks, potential crew escape systems are unlikely to be effective. Fire risks have been adequately mitigated by other means. In summary, current qualitative and quantitative safety analyses provided support for SOFIA's program position that SOFIA does not require a crew escape capability during the development-phase flight tests. C1 [Datta, Koushik; Wiltsee, Christopher B.; Briceno, Anthony] NASA, Ames Res Ctr, MS 218-7, Moffett Field, CA 94035 USA. RP Datta, K (reprint author), NASA, Ames Res Ctr, MS 218-7, Moffett Field, CA 94035 USA. EM Koushik.Datta@nasa.gov; Christopher.B.Wiltsee@nasa.gov; abriceno@mail.arc.nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0149-144X BN 978-1-4244-0007-2 J9 P REL MAINT S PY 2006 BP 539 EP + DI 10.1109/RAMS.2006.1677429 PG 3 WC Computer Science, Software Engineering; Operations Research & Management Science; Statistics & Probability SC Computer Science; Operations Research & Management Science; Mathematics GA BGT51 UT WOS:000250419100088 ER PT S AU Meshkat, L Girerd, A Edwards, CD AF Meshkat, Leila Girerd, Andre Edwards, Charles D. GP IEEE TI An integrated approach for the probabilistic risk assessment of the Mars Relay Network SO 2006 PROCEEDINGS - ANNUAL RELIABILITY AND MAINTAINABILITY SYMPOSIUM, VOLS 1 AND 2 SE Reliability and Maintainability Symposium LA English DT Proceedings Paper CT 52nd Annual Reliability and Maintainability Symposium CY JAN 23-26, 2006 CL Newport Beach, CA SP IEEE DE risk assessment; probabilistic analysis; Mars Relay Network AB The Mars Relay Network consists of Mars orbiters, relay radios, and ground systems from several different countries. It provides communications, timing, and navigation services to in-situ probes at and near Mars. The Mars Relay Network currently consists of the NASA Mars Global Surveyor and Mars Odyssey orbiters, and the ESA Mars Express orbiter. The NASA Mars Reconnaissance Orbiter will join these orbiters in 2006. Estimations of risk, robustness and capability are important to the Mars Program Office for long-term decisions about the relay network. One element of this is the expected reliability of the relay capability of each of the orbiters. This paper addresses the generation of a unified framework for the reliability analysis of the Mars Relay Network. The proposed analysis is based on the development of probabilistic models for the reliability assessment of each of the current and planned Mars orbiters and the integration of these reliability measures into a framework for a system level analysis of the Network. The results emphasize the sensitivity of the input data and the need for further research and investigation into the failure characteristics of the system elements being modeled. Furthermore, a multi-state risk analysis, in addition to the reliability analysis, may be conducted to determine the probability of various states for each of the orbiters. C1 [Meshkat, Leila; Girerd, Andre; Edwards, Charles D.] CALTECH, Jet Prop Lab, M-S 301-340,4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Meshkat, L (reprint author), CALTECH, Jet Prop Lab, M-S 301-340,4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM chad.edwards@jpl.nasa.gov NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0149-144X BN 978-1-4244-0007-2 J9 P REL MAINT S PY 2006 BP 618 EP + DI 10.1109/RAMS.2006.1677442 PG 3 WC Computer Science, Software Engineering; Operations Research & Management Science; Statistics & Probability SC Computer Science; Operations Research & Management Science; Mathematics GA BGT51 UT WOS:000250419100101 ER PT B AU Ponchak, GE Tentzeris, MM Ponchak, GE Tentzeris, MM AF Ponchak, GE Tentzeris, MM Ponchak, GE Tentzeris, MM BE Drayton, RF TI Multiple modes on embedded inverted microstrip lines SO 2006 TOPICAL MEETING ON SILICON MONOLITHIC INTEGRATED CIRCUITS IN RF SYSTEMS, DIGEST OF PAPERS LA English DT Proceedings Paper CT Topical Meeting on Silicon Monolithic Integrated Circuits in RF Systems CY JAN 18-20, 2006 CL San Diego, CA SP IEEE Microwave Theory & Tech Soc DE microstrip; inverted microstrip; MMIC; multi-layer circuits ID INTERCONNECTS; INDUCTORS; POLYIMIDE; DOMAIN; FILM AB Embedded transmission lines are commonly used in silicon radio frequency integrated circuits to reduce insertion loss and decrease circuit size. In this paper, experimental measurements and Finite Difference Time Domain (FDTD) analysis are used to show that embedded inverted microstrip lines are not suitable for use above a few GHz. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. Georgia Inst Technol, Atlanta, GA 30332 USA. RP NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 14 TC 4 Z9 4 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 0-7803-9472-0 PY 2006 BP 107 EP + PG 2 WC Engineering, Electrical & Electronic SC Engineering GA BDW61 UT WOS:000235866900026 ER PT B AU Menzies, T Richardson, J AF Menzies, Tim Richardson, Julian TI Qualitative modeling for requirements engineering SO 30TH ANNUAL IEEE/NASA SOFTWARE ENGINEERING WORKSHOP, PROCEEDINGS LA English DT Proceedings Paper CT 30th Annual NASA/IEEE Software Engineering Workshop CY APR 24-28, 2006 CL Loyola Coll, Columbia Campus, Columbia, MD SP NASA Software Engn Lab, NASA Goddard Space Flight Ctr, Informat Syst Div, IEEE Comp Soc, TCSE HO Loyola Coll, Columbia Campus AB Acquisition of "quantitative" models of sufficient accuracy to enable effective analysis of requirements tradeoffs is hampered by the slowness and difficulty of obtaining sufficient data. "Qualitative " models, based on expert opinion, can be built quickly and therefore used earlier Such qualitative models are nondeterminate which makes them hard to use for making categoricalpolicy decisions over the model. The non-determinacy of qualitative models can be tamed using "stochastic sampling " and "treatment learning ". These tools can quickly find and set the "master variables" that restrain qualitative simulations. Once tamed, qualitative modeling can be used in requirements engineering to assess more options, earlier in the life cycle. C1 [Menzies, Tim] Portland State Univ, Comp Sci, Portland, OR 97207 USA. [Richardson, Julian] NASA, Ames Res Ctr, USRA, RIACS, Moffett Field, CA 94035 USA. RP Menzies, T (reprint author), Portland State Univ, Comp Sci, Portland, OR 97207 USA. EM tim@menzies.us; julianr@riacs.edu FU NASA; Portland State University; NASA Office of Safety and Mission Assurance under Software Assurance Research Program FX Reference herein to any specific commercial product, process, or service by trade name, trademark, manufacturer, or otherwise, does not constitute or imply its endorsement by the United States Government. This research was conducted at the NASA Ames Research Center, funded by NASA, and at Portland State University, partially sponsored by the NASA Office of Safety and Mission Assurance under the Software Assurance Research Program led by the NASA IV&V Facility. NR 31 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 978-0-7695-2624-9 PY 2006 BP 11 EP + PG 2 WC Computer Science, Software Engineering SC Computer Science GA BFY32 UT WOS:000245430400003 ER PT S AU Ghaffarian, R AF Ghaffarian, Reza GP IEEE TI Thermal cycle reliability of PBGA/CCGA 717 I/Os SO 56TH ELECTRONIC COMPONENTS & TECHNOLOGY CONFERENCE 2006, VOL 1 AND 2, PROCEEDINGS SE Electronic Components and Technology Conference LA English DT Proceedings Paper CT 56th Electronic Components and Technology Conference CY 2006 CL San Diego, CA SP Elect Components, Assembilies & Mat Assoc, Elect Ind Alliance, IEEE Components, Packaging & Mfg Technol Soc, IEEE AB Status of thermal cycle test results for a nonfunctional daisy-chained peripheral ceramic column grid array (CCGA) and its plastic ball grid array (PBGA) version, both having 560 I/Os, were presented in last year's conference. Test results included environmental data for three different thermal cycle regimes (-55 degrees/125 degrees C, -55 degrees/100 degrees C, and -50 degrees/75 degrees C). Update information on these-especially failure type for assemblies with high and low solder volumes-were presented. The thermal cycle test procedure followed those recommended by IPC-9701 for tin-lead solder joint assemblies. Revision A of this specification covers guideline thermal cycle requirements for Pb-free solder joints. Some background information discussed during release of this specification with its current guideline recommendations were also presented. In a recent reliability investigation a fully populated CCGA with 717 I/Os was also considered for assembly reliability evaluation. The functional package is a field-programmable gate array that has much higher processing power than its previous version. This new package is smaller in dimension, has no interposer, and has a thinner column wrapped with copper for reliability improvement. This paper will also present thermal cycle test results for this package assembly and its plastic version with 728 I/Os, both of which were exposed to three different cycle regimes. Two cycle profiles were those specified by IPC-9701A for tin-lead, i.e. 55 to 100 degrees C and -55 to 125 degrees C and one was a cycle profile specified by Mil-Std-883, i.e., -65 degrees C/150 degrees C which is generally used for ceramic hybrid packages. Per IPC-9701A, test vehicles were built using daisy chain packages and were continuously monitored. The effects of many process and assembly variables-including corner staking commonly used for improving resistance to mechanical loading such as drop and vibration loads-were also considered as part of the test matrix. Optical photomicrographs were taken at various thermal cycle intervals to document damage progress and behavior. Representative samples of these along with cross-sectional photomicrographs at higher magnification taken by scanning electron microscopy (SEM) to determine crack propagation and failure analyses for packages are also presented. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Ghaffarian, R (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. EM Reza.Ghaffrian@JPL.NASA.Gov NR 16 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0569-5503 BN 1-4244-0151-8 J9 ELEC COMP C PY 2006 SI 2006 BP 364 EP 376 DI 10.1109/ECTC.2006.1645672 PG 13 WC Engineering, Manufacturing; Engineering, Electrical & Electronic; Materials Science, Multidisciplinary SC Engineering; Materials Science GA BEP36 UT WOS:000238566600055 ER PT S AU Teverovsky, A AF Teverovsky, Alexander GP IEEE TI Effect of environments on degradation of molding compound and wire bonds in PEMs SO 56TH ELECTRONIC COMPONENTS & TECHNOLOGY CONFERENCE 2006, VOL 1 AND 2, PROCEEDINGS SE Electronic Components and Technology Conference LA English DT Proceedings Paper CT 56th Electronic Components and Technology Conference CY 2006 CL San Diego, CA SP Elect Components, Assembilies & Mat Assoc, Elect Ind Alliance, IEEE Components, Packaging & Mfg Technol Soc, IEEE ID EPOXY-RESINS; BALL BONDS AB Degradation of wire bonds (WBs) is one of the major factors limiting reliability of plastic encapsulated microcircuits (PEMs) at high temperatures. Use of PEMs in military and aerospace applications requires extended and thorough evaluation of encapsulating materials and reliability of packages in harsh environments. However, the effect of environmental conditions on characteristics of molding compounds (MCs) and reliability of wire bonds has not been studied sufficiently to date. In this work, two types of PEMs in QFP-style packages have been stored in different environments at temperatures from 130 degrees C to 225 degrees C for up to 4,500 hours in some cases. To assess the effect of oxygen, the parts were aged at 198 degrees C in air and vacuum chambers. The effect of humidity was evaluated during long-term highly accelerated temperature and humidity stress testing (HAST) at temperatures of 130 degrees C and 150 degrees C. Thermo-mechanical and thermo-gravimetrical analyses were used to evaluate the effect of environment on characteristics of molding compound used. Measurements of contact resistances of wire bonds and their mechanical strength were employed to monitor degradation of wire bonds throughout the testing. Correlation between degradation of MC and WB failures has been analyzed. The effect of environmental conditions on accelerating factors of WB failures has been assessed, and the mechanism of wire bond degradation due to the presence of moisture and oxygen is discussed. C1 NASA, Goddard Space Flight Ctr, QSS Grp Inc, Greenbelt, MD 20771 USA. RP Teverovsky, A (reprint author), NASA, Goddard Space Flight Ctr, QSS Grp Inc, Code 562, Greenbelt, MD 20771 USA. EM Alexander.A.Teverovsky.1@gsfc.nasa.gov NR 27 TC 2 Z9 2 U1 0 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0569-5503 BN 1-4244-0151-8 J9 ELEC COMP C PY 2006 SI 2006 BP 1415 EP 1424 DI 10.1109/ECTC.2006.1645842 PG 10 WC Engineering, Manufacturing; Engineering, Electrical & Electronic; Materials Science, Multidisciplinary SC Engineering; Materials Science GA BEP36 UT WOS:000238566601051 ER PT S AU Ghaffarian, R Ramkumar, SM Varanasi, A AF Ghaffarian, Reza Ramkumar, S. Manian Varanasi, Arun GP IEEE TI Thermal cycle/aging reliability of lead free 0201 assemblies SO 56TH ELECTRONIC COMPONENTS & TECHNOLOGY CONFERENCE 2006, VOL 1 AND 2, PROCEEDINGS SE Electronic Components and Technology Conference LA English DT Proceedings Paper CT 56th Electronic Components and Technology Conference CY 2006 CL San Diego, CA SP Elect Components, Assembilies & Mat Assoc, Elect Ind Alliance, IEEE Components, Packaging & Mfg Technol Soc, IEEE DE 0201 assembly; lead-free process; lead-free surface finish; modified apertures; thermal aging; thermal cycle; isothermal aging; shear load AB This paper presents the test results and comparative literature data on the influence of a few key manufacturing parameters and defects associated with the 0201. components using lead-free and tin-lead solder alloys. A large number of test vehicles assembled with 0201 components were subjected to isothermal aging at 150 degrees C and thermal cycling in the range of -55 degrees to 100 degrees C in order to establish their reliability. The shear tests were carried out at various aging intervals up to 500 hours to determine the effects of aging damage on the solder joint strength and this data will be presented and compared to virgin assemblies. Weibull plots will be given for reliability to establish solder joint aging behavior for the lead free assemblies compared to lead based solder as well as data correlation for various sets of data. Optical inspection photos taken during thermal cycling to establish damage progress, scanning electron microscopy (SEM) photos to reveal details of damage at 1500 cycles, and cross-sectional photomicrographs showing interconnect microstructural changes and intermetallic formation will also be presented. C1 [Ghaffarian, Reza; Ramkumar, S. Manian] CALTECH, Jet Propuls Lab, Pasadena, CA 91109 USA. RP Ghaffarian, R (reprint author), CALTECH, Jet Propuls Lab, Pasadena, CA 91109 USA. FU Metro Circuits; Indium Corporation; Photostencil FX Part of the research described in this publication was conducted at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration.; The authors would like to acknowledge the generous support of Metro Circuits, Indium Corporation, and Photostencil. The author S.Manian Ramkumar would like to acknowledge the effort of his graduate assistants Rahul Newasekar who conducted the experimental runs and defect data collection and Riyaz Shaikh who prepared the cross-sections for analysis. He would also like to express his gratitude to Dr. Sean Rommel and Dr. Alan Raisanen of the Semiconductor & Microsystems Fabrication Laboratory for their support with the SEM. Dr. Ghaffarian would like to acknowledge Ana Rosa Arreola and Ken Evans at JPL for their support in test vehicle thermal cycling and failure analysis, respectively. The author extends his appreciation to program mangers at NASA Electronic Parts and Packaging Program (NEPP) including Michael Sampson, Dr. Charles Barnes, and Phillip Zulueta for their continuous support and encouragement. NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0569-5503 BN 1-4244-0151-8 J9 ELEC COMP C PY 2006 SI 2006 BP 1940 EP + DI 10.1109/ECTC.2006.1645927 PG 2 WC Engineering, Manufacturing; Engineering, Electrical & Electronic; Materials Science, Multidisciplinary SC Engineering; Materials Science GA BEP36 UT WOS:000238566601136 ER PT S AU Bellin, B Tixador, P Deleglise, M Vallier, JC Pavard, S Bruzek, CE AF Bellin, B. Tixador, P. Deleglise, M. Vallier, J. C. Pavard, S. Bruzek, C. E. BE Weber, HW Sauerzopf, FM TI Cryogenic design of a 800 kJ HTS SMESa SO 7TH EUROPEAN CONFERENCE ON APPLIED SUPERCONDUCTIVITY (EUCAS'05) SE Journal of Physics Conference Series LA English DT Proceedings Paper CT 7th European Conference on Applied Superconductivity CY SEP 11-15, 2005 CL Vienna Univ Technol, Vienna, AUSTRIA HO Vienna Univ Technol AB In the context of a DGA (Delegation Generale pour l'Armement) project, we have designed a 800 kJ SMES. The conductor is made with 3 or 4 Bi-2212 PIT tapes insulated and assembled by Nexans France. The operating temperature is 20 K. The cryogenic design of the SMES is presented. The thermal operation model was calculated using FLUX (R), a F. E. M. (Finite Element Model) software. We present the results of the measurements of thermal and electrical resistances and the results of the tests on a small-scale double pancake coil. C1 [Bellin, B.; Tixador, P.] CNRS CRTBT LEG, BP 166, F-38042 Grenoble 09, France. [Vallier, J. C.] NASA Langley Res Ctr, Hampton, VA USA. RP Bellin, B (reprint author), CNRS CRTBT LEG, BP 166, F-38042 Grenoble 09, France. EM boris.bellin@grenoble.cnrs.fr NR 2 TC 9 Z9 9 U1 0 U2 6 PU IOP PUBLISHING LTD PI BRISTOL PA DIRAC HOUSE, TEMPLE BACK, BRISTOL BS1 6BE, ENGLAND SN 1742-6588 J9 J PHYS CONF SER PY 2006 VL 43 BP 817 EP 820 DI 10.1088/1742-6596/43/1/199 PG 4 WC Physics, Applied; Physics, Condensed Matter SC Physics GA BOS72 UT WOS:000277479400199 ER PT B AU Lee, JK Newman, TS Gary, GA AF Lee, Jong Kwan Newman, Timothy S. Gary, G. Allen GP IEEE Computer Society TI Dynamic aperture-based solar loop segmentation SO 7TH IEEE SOUTHWEST SYMPOSIUM ON IMAGE ANALYSIS AND INTERPRETATION LA English DT Proceedings Paper CT 7th IEEE Southwest Symposium on Image Analysis and Interpretation (SSIAI 2006) CY MAR 26-28, 2006 CL Denver, CO ID REGION AB A new method to automatically segment arc-like loop structures from intensity images of the Sun's corona is introduced The method constructively segments credible loop structures by exploiting the Gaussian-like shape of loop cross-sectional intensity profiles. The experimental results show that the method reasonably segments most of the well-defined loops in coronal images. The method is only the second published automated solar loop segmentation method. Its advantage over the other published method is that it operates independently of supplemental time specific data. C1 [Lee, Jong Kwan; Newman, Timothy S.] Univ Alabama, Dept Comp Sci, Huntsville, AL 35899 USA. [Gary, G. Allen] NASA, Marshall Space Flight Ctr, Huntsville, AL 35811 USA. RP Lee, JK (reprint author), Univ Alabama, Dept Comp Sci, Huntsville, AL 35899 USA. EM jlee@cs.uah.edu; tnewman@cs.uah.edu; Allen.Gary@nasa.gov FU NASAs Office of Space Science Solar and Heliospheric Physics Supporting Research and Technology program. FX This work was supported by NASAs Office of Space Science Solar and Heliospheric Physics Supporting Research and Technology program. NR 8 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 1-4244-0069-4 PY 2006 BP 91 EP + PG 2 WC Imaging Science & Photographic Technology SC Imaging Science & Photographic Technology GA BEG27 UT WOS:000237208000019 ER PT J AU Whedon, GD Rambaut, PC AF Whedon, GD Rambaut, PC TI Effects of long-duration space flight on calcium metabolism: Review of human studies from Skylab to the present SO ACTA ASTRONAUTICA LA English DT Review ID ACUTE ANTERIOR POLIOMYELITIS; RENAL STONE FORMATION; PROLONGED BED REST; INDUCED BONE LOSS; POSTMENOPAUSAL WOMEN; BIOCHEMICAL MARKERS; ANTIORTHOSTATIC HYPOKINESIA; SODIUM FLUORIDE; MINERAL BALANCE; IN-VIVO AB One of the major effects of prolonged weightlessness seen in long-duration space flights has been an extended loss of bone from the skeleton. The principal characteristics of this loss were shown in the metabolic studies carried out on the Skylab flights of 1, 2 and 3 months in 1973 and 1974. These studies now provide the background for a comprehensive review of the considerable number of subsequent calcium studies in humans during space flights from that time until the present. Because of the close similarities in pattern and degree between space flight and bed rest in effects on calcium metabolism, relevant long-term human bed rest studies have been included. An analysis is presented of the bone calcium loss data with respect to degree, duration and significance, as well as relative failure of reversibility or recovery following flights. Possible mechanisms of bone loss are discussed: the physiological condition of disuse atrophy, increase in bone resorption, decrease (later and lesser) in bone formation, decrease in intestinal calcium absorption, increase in glucocorticoids, along with the threat of urinary tract stone formation and proposed countermeasures. Considerable future research is needed, particularly on mechanisms of bone loss and on countermeasures, to be carried out on the International Space Station and via bed rest studies, before a mission to and return from Mars is undertaken. (c) 2005 Elsevier Ltd. All rights reserved. C1 Natl Inst Arthrit Diabet Digest & Kidney Dis, NIH, Bethesda, MD USA. NASA, Biomed Res, Hilo, HI 96720 USA. RP Whedon, GD (reprint author), 1290 Gulf Blvd,Apt 1802, Clearwater Beach, FL 33767 USA. EM prambaut@compuserve.com NR 110 TC 10 Z9 12 U1 0 U2 2 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0094-5765 J9 ACTA ASTRONAUT JI Acta Astronaut. PD JAN PY 2006 VL 58 IS 2 BP 59 EP 81 DI 10.1016/j.actaastro.2005.03.074 PG 23 WC Engineering, Aerospace SC Engineering GA 993JI UT WOS:000233950000001 ER PT J AU Zheng, QN Lai, RJ Huang, NE Pan, JY Timothy, LW AF Zheng, QN Lai, RJ Huang, NE Pan, JY Timothy, LW TI Observation of ocean current response to 1998 Hurricane Georges in the Gulf of Mexico SO ACTA OCEANOLOGICA SINICA LA English DT Article DE shelf dynamics; hurricane; ocean current; air-sea interaction ID INERTIAL OSCILLATIONS; MOVING STORM; GENERATION; SCALES; WAVES; WAKE AB The ocean current response to a hurricane on the shelf-break is examined. The study area is the DeSoto Canyon in the northeast Gulf of Mexico, and the event is the passage of 1998 Hurricane Georges with a maximum wind speed of 49 m/s. The data sets used for analysis consist of the mooring data taken by the Field Program of the DeSoto Canyon Eddy Intrusion Study, and simultaneous winds observed by NOAA (National Oceanic and Atmospheric Administration) Moored Buoy 42040. Time-depth ocean current energy density images derived from the observed data show that the ocean currents respond almost immediately to the hurricane with important differences on and off the shelf. On the shelf, in the shallow water of 100 m, the disturbance penetrates rapidly downward to the bottom and forms two energy peaks, the major peak is located in the mixed layer and the secondary one in the lower layer. The response dissipates quickly after external forcing disappears. Off the shelf, in the deep water, the major disturbance energy seems to be trapped in the mixed layer with a trailing oscillation; although the disturbance signals may still be observed at the depths of 500 and 1 290 m. Vertical dispersion analysis reveals that the near-initial wave packet generated off the shelf consists of two modes. One is a barotropic wave mode characterized by a fast decay rate of velocity amplitude of 0.020 s(-1), and the other is baroclinic wave mode characterized by a slow decay rate of 0.006 9 s(-1). The band-pass-filtering and empirical function techniques are employed to the frequency analysis. The results indicate that 411 frequencies shift above the local inertial frequency. On the shelf, the average frequency is 1.04f in the mixed layer, close to the diagnosed frequency of the first baroclinic mode, and the average frequency increases to 1.07f in the thermocline. Off the shelf, all frequencies are a little smaller than the diagnosed frequency of the first mode. The average frequency decreases from 1.035f in the mixed layer to 1.02f in the thermocline, implying a trend for the shift in frequency of the oscillations towards f with the depth. C1 Univ Maryland, Dept Atmospher & Ocean Sci, College Pk, MD 20742 USA. US Dept Interior, Minerals Management Serv, Herndon, VA 20170 USA. NASA, Goddard Space Flight Ctr, Ocean & Ice Branch, Greenbelt, MD 20771 USA. Oregon Grad Inst, Dept Environm & Biomol Syst, Beaverton, OR 97006 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Zheng, QN (reprint author), Univ Maryland, Dept Atmospher & Ocean Sci, College Pk, MD 20742 USA. EM quanan@atmos.umd.edu RI Zheng, Quanan/F-9025-2010 NR 26 TC 32 Z9 39 U1 1 U2 10 PU CHINA OCEAN PRESS PI BEIJING PA INTERNATIONAL DEPT, 8 DA HUI SHI, BEIJING 100081, PEOPLES R CHINA SN 0253-505X J9 ACTA OCEANOL SIN JI Acta Oceanol. Sin. PY 2006 VL 25 IS 1 BP 1 EP 14 PG 14 WC Oceanography SC Oceanography GA 021LI UT WOS:000235984300001 ER PT S AU Maleki, L Matsko, AB Savchenkov, AA Strekalov, D AF Maleki, Lute Matsko, Andrey B. Savchenkov, Anatoliy A. Strekalov, Dmitry BE Coufal, HJ Hasan, ZU Craig, AE TI Slow light in vertically coupled whispering gallery mode resonators SO Advanced Optical and Quantum Memories and Computing III SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Advanced Optical and Quantum Memories and Computing III CY JAN 24-25, 2006 CL San Jose, CA DE whispering gallery modes; slow light; Electromagnetically induced transparency ID ELECTROMAGNETICALLY INDUCED TRANSPARENCY; ATOMIC VAPOR; WAVE-GUIDE; PHOTONIC CRYSTAL; NONLINEAR OPTICS; COHERENT MEDIA; GROUP-VELOCITY; LINE; PULSE; GAS AB We theoretically study propagation of light in a vertically coupled whispering gallery mode resonator (WGMR) waveguide consisting of a chain of disc WGMRs etched on the surface of a cylinder made of an optically transparent material. The waveguide is capable of reducing the group velocity of light by as much as a factor of a billion, is much more efficient than usual coupled resonator optical waveguides, and compete with slow light atomic systems. We discuss practical as well as fundamental advantages and disadvantages of the resonator and atomic delay lines. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Maleki, L (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 54 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 0-8194-6172-5 J9 P SOC PHOTO-OPT INS PY 2006 VL 6130 BP U160 EP U176 PG 17 WC Computer Science, Hardware & Architecture; Computer Science, Theory & Methods; Optics SC Computer Science; Optics GA BEI11 UT WOS:000237288300017 ER PT S AU Sun, XL Jester, PL Palm, SP AF Sun, Xiaoli Jester, Peggy L. Palm, Stephen P. BE Becker, W TI In orbit performance of Si avalanche photodiode single photon counting modules (SPCM) used in the Geoscience Laser Altimeter System on ICESat SO ADVANCED PHOTON COUNTING TECHNIQUES SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Advanced Photon Counting Techniques CY OCT 01-03, 2006 CL Boston, MA SP SPIE, Boston Elect Corp, Becker & Hickl GmbH DE Si APD; photon counting; space radiation damage AB Si avalanche photodiode (APD) single photon counting modules (SPCMs) are used in the Geoscience Laser Altimeter System (GLAS) on Ice, Cloud, and land Elevation Satellite (ICESat), currently in orbit measuring Earth surface elevation and atmosphere backscattering. These SPCMs are used to measure cloud and aerosol backscattering to the GLAS laser light at 532-nm wavelength, with quantum efficiencies of 60 to 70% and maximum count rates greater than 13 millions/s. The performance of the SPCMs has been monitored since ICESat launch on January 12, 2003. There has been no measurable change in the quantum efficiency when comparing the average photon count rates in response to the background light from the sunlit Earth. The linearity and the afterpulsing, seen from the cloud and surface backscattering profiles have been the same as those during ground testing. The detector dark counts rates monitored while the spacecraft was in the dark side of the Earth have increased linearly at about 55.5 counts/s per day due to space radiation damage, which is a little lower than what we expected based on the ground testing and sufficiently low to provide useful atmosphere measurements through the end of the ICESat mission. The radiation damage appeared to be slightly dependent of the device temperature. There was also a distinct increase in the dark counts during the solar storm in 28-31 October 2003. These SPCMs have been in orbit for almost four years to date. The accumulated operating time has reached to over 380 days (9150 hours). These SPCMs have provided unprecedented receiver sensitivity and clarity in atmosphere backscattering measurements from space. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Sun, XL (reprint author), NASA, Goddard Space Flight Ctr, Code 690, Greenbelt, MD 20771 USA. EM xiaoli.sun-1@nasa.gov RI Sun, Xiaoli/B-5120-2013 NR 6 TC 4 Z9 4 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 978-0-8194-6470-5 J9 PROC SPIE PY 2006 VL 6372 DI 10.1117/12.685539 PG 8 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BFQ90 UT WOS:000243901500020 ER PT J AU Helmick, DM Roumeliotis, SI Cheng, Y Clouse, DS Bajracharya, M Matthies, LH AF Helmick, Daniel M. Roumeliotis, Stergios I. Cheng, Yang Clouse, Daniel S. Bajracharya, Max Matthies, Larry H. TI Slip-compensated path following for planetary exploration rovers SO ADVANCED ROBOTICS LA English DT Article; Proceedings Paper CT IEEE/RSJ International Conference on Intelligent Robots and Systems CY AUG 02-06, 2005 CL Edmonton, CANADA SP IEEE, Robot Soc Japan DE rover navigation; visual odometry; slip compensation; Kalman filter; rover kinematics ID GENERATION; ROBOTS AB A system that enables continuous slip compensation for a Mars rover has been designed, implemented and field-tested. This system is composed of several components that allow the rover to accurately and continuously follow a designated path, compensate for slippage and reach intended goals in high-slip environments. These components include visual odometry, vehicle kinematics, a Kalman filter pose estimator and a slip-compensated path follower. Visual odometry tracks distinctive scene features in stereo imagery to estimate rover motion between successively acquired stereo image pairs. The kinematics for a rocker-bogie suspension system estimates vehicle motion by measuring wheel rates, and rocker, bogie and steering angles. The Kalman filter processes measurements from an inertial measurement unit and visual odometry. The filter estimate is then compared to the kinematic estimate to determine whether slippage has occurred, taking into account estimate uncertainties. If slippage is detected, the slip vector is calculated by differencing the current Kalman filter estimate from the kinematic estimate. This slip vector is then used to determine the necessary wheel velocities and steering angles to compensate for slip and follow the desired path. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Univ Minnesota, Dept Comp Sci & Engn, Minneapolis, MN 55455 USA. RP Helmick, DM (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM dmh@jpl.nasa.gov NR 29 TC 36 Z9 36 U1 0 U2 8 PU TAYLOR & FRANCIS LTD PI ABINGDON PA 2-4 PARK SQUARE, MILTON PARK, ABINGDON OR14 4RN, OXON, ENGLAND SN 0169-1864 EI 1568-5535 J9 ADV ROBOTICS JI Adv. Robot. PY 2006 VL 20 IS 11 BP 1257 EP 1280 DI 10.1163/156855306778792470 PG 24 WC Robotics SC Robotics GA 125GT UT WOS:000243431100005 ER PT S AU Smith, JS Dean, BH Haghani, S AF Smith, Jeffrey S. Dean, Bruce H. Haghani, Shadan BE Lewis, H Bridger, A TI Distributed computing architecture for image-based wavefront sensing and 2D FFTs - art. no. 627421 SO Advanced Software and Control for Astronomy SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Advanced Software and Control for Astronomy CY MAY 24-26, 2006 CL Orlando, FL SP SPIE DE Digital Signal Processors (DSP); Fast Fourier Transform (FFT); James Webb Space Telescope (JWST); Field Programmable Gate Arrays (FPGA); phase retrieval ID DIFFRACTION PLANE PICTURES; PHASE AB Image-based wavefront sensing provides significant advantages over interferometric-based wavefront sensors such as optical design simplicity and stability. However, the image-based approach is computationally intensive, and therefore, applications utilizing the image-based approach gain substantial benefits using specialized high-performance computing architectures. The development and testing of these computing architectures are essential to missions such as James Webb Space Telescope (JWST), Terrestrial Planet Finder-Coronagraph (TPF-C and CorSpec), and the Spherical Primary Optical Telescope (SPOT). The algorithms implemented on these specialized computing architectures make use of numerous two-dimensional Fast Fourier Transforms (FFTs) which necessitate an all-to-all communication when applied on a distributed computational architecture. Several solutions for distributed computing are presented with an emphasis on a 64 Node cluster of digital signal processors (DSPs) and multiple DSP field programmable gate arrays (FPGAs), offering a novel application of low-diameter graph theory. Timing results and performance analysis are presented. The solutions offered could be applied to other computationally complex all-to-all communication problems. C1 NASA, Goddard Space Flight Ctr, Opt Branch, Greenbelt, MD 20771 USA. RP Smith, JS (reprint author), NASA, Goddard Space Flight Ctr, Opt Branch, Code 551, Greenbelt, MD 20771 USA. NR 24 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 0-8194-6339-6 J9 P SOC PHOTO-OPT INS PY 2006 VL 6274 BP 27421 EP 27421 AR 627421 DI 10.1117/12.672842 PG 10 WC Astronomy & Astrophysics; Computer Science, Interdisciplinary Applications; Optics SC Astronomy & Astrophysics; Computer Science; Optics GA BFB36 UT WOS:000240720200066 ER PT S AU Garcia, JI Colavita, MM Booth, AJ AF Garcia, Jean I. Colavita, M. Mark Booth, Andrew J. BE Lewis, H Bridger, A TI Real-time control system for the Keck Interferometer Nuller: methods and maintenance - art. no. 62740K SO Advanced Software and Control for Astronomy SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Advanced Software and Control for Astronomy CY MAY 24-26, 2006 CL Orlando, FL SP SPIE DE real-time control; control systems; nulling; interferometry; atmospheric dispersion AB The real-time control system for the Keck Interferometer Nuller provides the N-band fringe tracking capabilities of the instrument, as well as correcting for atmospheric dispersion in the system. There are three closed-loop servos for controlline, the N-band path, as well as two K-band servos which provide open-loop control. A system of synchronized "gates" allows all N-band fringe trackers to operate simultaneously, making it possible to interleave servo corrections with data collection. Several methods of improving servo performance and maintenance of control schemes are discussed. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Garcia, JI (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 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 0-8194-6339-6 J9 P SOC PHOTO-OPT INS PY 2006 VL 6274 BP K2740 EP K2740 AR 62740K DI 10.1117/12.670618 PG 10 WC Astronomy & Astrophysics; Computer Science, Interdisciplinary Applications; Optics SC Astronomy & Astrophysics; Computer Science; Optics GA BFB36 UT WOS:000240720200019 ER PT S AU Sidick, E Kuhnert, AC Trauger, JT AF Sidick, Erkin Kuhnert, Andreas C. Trauger, John T. BE Giles, MK Gonglewski, JD Carreras, RA TI Broadband performance of TPF's high-contrast imaging testbed: Modeling and simulations - art. no. 63060U SO Advanced Wavefront Control: Methods, Devices, and Applications IV SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Advanced Wavefront Control - Methods, Devices, and Applications IV CY AUG 14-15, 2006 CL San Diego, CA SP SPIE DE TPF; integrated modeling; speckle-nulling; high-contrast coronagraph ID PLANET FINDER CORONAGRAPH AB The broadband performance of the high-contrast imaging testbed (HCIT) at JPL is investigated through optical modeling and simulations. The analytical tool is an optical simulation algorithm developed by combining the HCIT's optical model with a speckle-nulling algorithm that operates directly on coronagraphic images, an algorithm identical to the one currently being used on the HCIT to actively suppress scattered light via a deformable mirror. It is capable of performing full three-dimensional end-to-end near-field diffraction analysis on the HCIT's optical system. By conducting speckle-nulling optimization, we clarify the HCIT's capability and limitations in terms of its broadband contrast performance under various realistic conditions. Considered cases include non-ideal occulting masks, such as a mask with optical density and wavelength dependent parasitic phase-delay errors (i.e., a not band-limited occulting mask) and the one with an optical-density profile corresponding to a measured, non-standard profile, as well as the independently measured phase errors of all optics. Most of the information gathered on the HCIT's optical components through measurement and characterization over the last several years at JPL has been used in this analysis to make the predictions as accurate as possible. The best contrast values predicted so far by our simulations obtainable on the HCIT illuminated with a broadband light having a bandwidth of 80nm and centered at 800nm wavelength are C-m=1.1x10(-8) (mean) and C-4=4.9x10(-8) (at 4 lambda/D), respectively. In this paper we report our preliminary findings about the broadband light performance of the HCIT. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Sidick, E (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 9 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 0-8194-6385-X J9 P SOC PHOTO-OPT INS PY 2006 VL 6306 BP U3060 EP U3060 AR 63060U DI 10.1117/12.680685 PG 11 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BFI37 UT WOS:000242009600029 ER PT S AU Serabyn, E Wallace, JK Troy, M Mennesson, B Haguenauer, P Gappinger, RO Bloemhof, EE AF Serabyn, E. Wallace, J. K. Troy, M. Mennesson, B. Haguenauer, P. Gappinger, R. O. Bloemhof, E. E. BE Ellerbroek, BL Calia, DB TI Extreme Adaptive Optics using an off-axis subaperture on a ground-based telescope - art. no. 62722W SO Advances in Adaptive Optics II, Prs 1-3 SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Advances in Adaptive Optics II CY MAY 24-31, 2006 CL Orlando, FL SP SPIE DE extreme adaptive optics ID PHASE-MASK CORONAGRAPH AB The next generation of adaptive optics (AO) systems, often referred to as extreme adaptive optics (ExAO), will use higher numbers of actuators to achieve wavefront correction levels below 100 nm, and so enable a host of new observations such as high-contrast coronagraphy. However, the number of potential coronagraph types is increasing rapidly, and selection of the most advantageous coronagraph is subject to many factors. Here it is pointed out that experiments in the ExAO regime can already be carried. out with existing hardware, by using a well-corrected subaperture on an existing telescope. For example, by magnifying a 1.5 m diameter off-axis subaperture onto the AO system's deformable mirror (DM) on the Palomar Hale telescope, we have recently achieved stellar Strehl ratios as high as 92% to 94%, corresponding to wavefront errors of 85 - 100 nm. Using this approach, a wide variety of ExaO experiments can thus be carried out well before "next generation" ExAO systems are deployed on large telescopes. The potential experiments include infrared ExAO imaging and performance optimization, a comparison of coronagraphic approaches in the ExAO regime, visible wavelength AO, and predictive AO. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Serabyn, E (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 11 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 0-8194-6337-X J9 P SOC PHOTO-OPT INS PY 2006 VL 6272 BP U988 EP U996 AR 62722W DI 10.1117/12.672650 PN 1-3 PG 9 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BEZ51 UT WOS:000240348301035 ER PT S AU Troy, M Crossfield, I Chanan, G Dumont, P Green, JJ Macintosh, B AF Troy, Mitchell Crossfield, Ian Chanan, Gary Dumont, Philip Green, Joseph J. Macintosh, Bruce BE Ellerbroek, BL Calia, DB TI Effects of diffraction and static wavefront errors on high-contrast imaging from the thirty meter telescope - art. no. 62722C SO Advances in Adaptive Optics II, Prs 1-3 SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Advances in Adaptive Optics II CY MAY 24-31, 2006 CL Orlando, FL SP SPIE DE telescopes; segmented mirrors; adaptive optics; diffraction; high-contrast ID PLANETS AB High-contrast imaging, particularly direct detection of extrasolar planets, is a major science driver for the next generation of extremely large telescopes such as the segmented Thirty Meter Telescope. This goal requires more than merely diffraction-limited imaging, but also attention to residual scattered light from wavefront errors and diffraction effects at the contrast level of 10(-8)-10(-9). Using a wave-optics simulation of adaptive optics and a diffraction suppression system we investigate diffraction from the segmentation geometry, intersegment gaps, obscuration by the secondary mirror and its supports. We find that the large obscurations pose a greater challenge than the much smaller segment gaps. In addition the impact of wavefront errors from the primary mirror, including segment alignment and figure errors, are analyzed. Segment-to-segment reflectivity variations and residual segment figure error will be the dominant error contributors from the primary mirror. Strategies to mitigate these errors are discussed. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Troy, M (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 17 TC 4 Z9 4 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 0-8194-6337-X J9 P SOC PHOTO-OPT INS PY 2006 VL 6272 BP U807 EP U817 AR 62722C DI 10.1117/12.671667 PN 1-3 PG 11 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BEZ51 UT WOS:000240348301017 ER PT S AU Vasisht, G Crossfield, IJ Dumont, PJ Levine, BM Troy, M Shao, M Shelton, JC Wallace, JK AF Vasisht, G. Crossfield, I. J. Dumont, P. J. Levine, B. M. Troy, M. Shao, M. Shelton, J. C. Wallace, J. K. BE Ellerbroek, BL Calia, DB TI Post-coronagraph wavefront sensing for the TMT planet formation imager - art. no. 627253 SO Advances in Adaptive Optics II, Prs 1-3 SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Advances in Adaptive Optics II CY MAY 24-31, 2006 CL Orlando, FL SP SPIE DE Extreme Adaptive Optics; planet detection AB Direct detection of exo-planets from the ground may be feasible with the advent of extreme-adaptive optics (ExAO) on large telescopes. A major hurdle to achieving high contrasts behind a star suppression system (10(-8)/hr(-1/2)) at small angular separations, is the "speckle noise" due to residual atmospheric and telescope-based quasistatic amplitude and phase errors at mid-spatial frequencies. We examine the potential of a post-coronagraphic, interferometric wavefront sensor to sense and adaptively correct just such errors. Pupil and focal plane sensors are considered and the merits and drawbacks of each scheme are outlined. It is not inconceivable to implement both schemes or even a hybrid scheme within a single instrument to significantly improve its scientific capabilities. This work was carried out in context of the proposed Planet Formation Imager instrument for Thirty Meter Telescope (TMT) project. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Vasisht, G (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 3 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 0-8194-6337-X J9 P SOC PHOTO-OPT INS PY 2006 VL 6272 BP U1664 EP U1675 AR 627253 DI 10.1117/12.672571 PN 1-3 PG 12 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BEZ51 UT WOS:000240348302048 ER PT S AU Wallace, JK Bartos, R Rao, S Samuele, R Schmidtlin, E AF Wallace, J. Kent Bartos, Randall Rao, Shanti Samuele, Rocco Schmidtlin, Edouard BE Ellerbroek, BL Calia, DB TI A laboratory experiment for demonstrating post-coronagraph wave front sensing and control for extreme adaptive optics - art. no. 62722L SO Advances in Adaptive Optics II, Prs 1-3 SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Advances in Adaptive Optics II CY MAY 24-31, 2006 CL Orlando, FL SP SPIE DE planet detection; coronography; nulling interferometry; wave front sensing AB Direct detection of exo-planets from the ground will become a reality with the advent of a new class of extreme-adaptive optics instruments that will come on-line within the next few years. In particular, the Gemini Observatory will be developing the Gemini Planet Imager (GPI) that will be used to make direct observations of young exo-planets. One major technical challenge in reaching the requisite high contrast at small angles is the sensing and control of residual wave front errors after the starlight suppression system. This paper will discuss the nature of this problem, and our approach to the sensing and control task. We will describe a laboratory experiment whose purpose is to provide a means of validating our sensing techniques and control algorithms. The experimental demonstration of sensing and control will be described. Finally, we will comment on the applicability of this technique to other similar high-contrast instruments. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Wallace, JK (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 7 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 0-8194-6337-X J9 P SOC PHOTO-OPT INS PY 2006 VL 6272 BP U899 EP U905 AR 62722L DI 10.1117/12.672516 PN 1-3 PG 7 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BEZ51 UT WOS:000240348301026 ER PT J AU Chiu, LS Liu, Z Vongsaard, J Morain, S Budge, A Neville, P Bales, C AF Chiu, LS Liu, Z Vongsaard, J Morain, S Budge, A Neville, P Bales, C TI Comparison of TRMM and water district rain rates over New Mexico SO ADVANCES IN ATMOSPHERIC SCIENCES LA English DT Article; Proceedings Paper CT 3rd International Ocean Atmosphere Conference CY JUN 28-30, 2004 CL Inst Atmospher Phys, Beijing, PEOPLES R CHINA SP Chinese Meteorol Soc, Chinese Soc Oceanog, Nat Sci Fdn China, Chinese Acad Sci, Nanjing Univ Informat Sci & Technol HO Inst Atmospher Phys DE satellite precipitation; TRMM; Water District; New Mexico; surface rain ID MEASURING MISSION TRMM; GLOBAL PRECIPITATION; PROFILING ALGORITHM; SATELLITE; RADAR AB This paper compares monthly and seasonal rain rates derived from the Version 5 (V5) and Version 6 (V6) TRMM Precipitation Radar (TPR, TSDIS reference 2A25), TRMM Microwave Imager (TMI, 2A12), TRMM Combined Instrument (TCI, 2B31), TRMM calibrated IR rain estimates (3B42) and TRMM merged gauge and satellite analysis (3B43) algorithms over New Mexico (NM) with rain gauge analyses provided by the Now Mexico water districts (WD). The average rain rates over the NM region for 1998-2002 are 0.91 mm d(-1) for WD and 0.75, 1.38, 1.49, 1.27, and 1.07 mm d(-1) for V5 3B43, 3B42, TMI, PR and TCA; and 0.74, 1.38, 0.87 and 0.97 mm d(-1) for V6 3B43, TMI, TPR and TCA, respectively. Comparison of V5 3B43 with WD rain rates and the daily TRMM mission index (TPR and TMI) suggests that the low bias of V5 3B43 for the wet months (summer to early fall) may be clue to the non-inclusion of some rain events in the operational gauge analyses that are used in the production of V5 3B43. Correlation analyses show that the WD rain rates vary in phase, with higher correlation between neighboring WDs. High temporal correlations (>0.8) exist between WD and the combined algorithms (3B42, 3B43 and TCA for both V5 and V6) while satellite instrument algorithms (PR, TMI and TCI) are correlated best among themselves at the monthly scale. Paired t-tests of the monthly time series show that V5 3B42 and TMI are statistically different from the WD rain rates while no significant difference exists between WD and the other products. The agreements between the TRMM satellite and WD gauge estimates are best for the spring and fall and worst for winter and summer. The reduction in V6 TMI (-7.4%) and TPR (-31%) rain rates (compared to V5) results in better agreement between WD estimates and TMI in winter and TPR during summer. C1 NASA, Goddard Space Flight Ctr, Distributed Act Arch Ctr, Greenbelt, MD 20771 USA. George Mason Univ, Ctr Earth Observing & Space Res, Sch Computat Sci, Fairfax, VA 22030 USA. Univ New Mexico, Earth Data Anal Ctr, Albuquerque, NM 87131 USA. Thai Royal Mil Acad, Bangkok, Thailand. RP Chiu, LS (reprint author), NASA, Goddard Space Flight Ctr, Distributed Act Arch Ctr, Greenbelt, MD 20771 USA. EM lchiu@gmu.edu RI AAS, AAS/C-2949-2014 NR 24 TC 36 Z9 41 U1 0 U2 6 PU SCIENCE PRESS PI BEIJING PA 16 DONGHUANGCHENGGEN NORTH ST, BEIJING 100717, PEOPLES R CHINA SN 0256-1530 J9 ADV ATMOS SCI JI Adv. Atmos. Sci. PD JAN PY 2006 VL 23 IS 1 BP 1 EP 13 DI 10.1007/s00376-006-0001-x PG 13 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 006EM UT WOS:000234878300002 ER PT J AU Yang, RH Guo, J Riishojgaard, P AF Yang, RH Guo, J Riishojgaard, P TI Application of an error statistics estimation method to the PSAS forecast error covariance model SO ADVANCES IN ATMOSPHERIC SCIENCES LA English DT Article; Proceedings Paper CT 3rd International Ocean Atmosphere Conference CY JUN 28-30, 2004 CL Inst Atmospher Phys, Beijing, PEOPLES R CHINA SP Chinese Meteorol Soc, Chinese Soc Oceanog, Nat Sci Fdn China, Chinese Acad Sci, Nanjing Univ Informat Sci & Technol HO Inst Atmospher Phys DE forecast error statistics estimation; data analysis; forecast error covariance model ID MAXIMUM-LIKELIHOOD-ESTIMATION; RADIOSONDE DATA; ANALYSIS SYSTEM; PARAMETERS AB In atmospheric data assimilation systems, the forecast error covariance model is an important component. However, the parameters required by a, forecast error covariance model are difficult to obtain due to the absence of the truth. This study applies an error statistics estimation method to the Physical-space Statistical Analysis System (PSAS) height-wind forecast error covariance model. This method consists of two components: the first component computes the error statistics by using the National Meteorological Center (NMC) method, which is a lagged-forecast difference approach, within the framework of the PSAS height-wind forecast error covariance model; the second obtains a calibration formula, to rescale the error standard deviations provided by the NMC method. The calibration is against the error statistics estimated by using a maximum-likelihood estimation (MLE) with rawindsonde height observed-minus-forecast residuals. A complete set of formulas for estimating the error statistics and for the calibration is applied to a one-month-long dataset generated by a general circulation model of the Global Model and Assimilation Office (GMAO), NASA. There is a clear constant relationship between the error statistics estimates of the NMC-method and MLE. The final product provides a full set of 6-hour error statistics required by the PSAS height-wind forecast error covariance model over the globe. The features of these error statistics are examined and discussed. C1 Sci Syst & Applicat Inc, Lanham, MD 20706 USA. Sci Applicat Int Corp, Beltsville, MD USA. UMBC, Joint Ctr Earth Syst Technol, Baltimore, MD USA. NASA, Goddard Space Flight Ctr, Global Modeling & Assimilat Off, Greenbelt, MD 20771 USA. RP Yang, RH (reprint author), Sci Syst & Applicat Inc, Lanham, MD 20706 USA. EM ryang@gmao.gsfc.nasa.gov RI AAS, AAS/C-2949-2014 NR 10 TC 0 Z9 0 U1 0 U2 1 PU SCIENCE PRESS PI BEIJING PA 16 DONGHUANGCHENGGEN NORTH ST, BEIJING 100717, PEOPLES R CHINA SN 0256-1530 J9 ADV ATMOS SCI JI Adv. Atmos. Sci. PD JAN PY 2006 VL 23 IS 1 BP 33 EP 44 DI 10.1007/s00376-006-0004-7 PG 12 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 006EM UT WOS:000234878300005 ER PT J AU Xiong, XX Barnes, W AF Xiong, XX Barnes, W TI An overview of MODIS radiometric calibration and characterization SO ADVANCES IN ATMOSPHERIC SCIENCES LA English DT Article; Proceedings Paper CT 3rd International Ocean Atmosphere Conference CY JUN 28-30, 2004 CL Inst Atmospher Phys, Beijing, PEOPLES R CHINA SP Chinese Meteorol Soc, Chinese Soc Oceanog, Nat Sci Fdn China, Chinese Acad Sci, Nanjing Univ Informat Sci & Technol HO Inst Atmospher Phys DE EOS; remote sensing; terra; aqua MODIS; sensor; calibration; radiometry ID RESOLUTION IMAGING SPECTRORADIOMETER; TERRA MODIS; AQUA; PERFORMANCE; EOS-AM1; BANDS AB The Moderate Resolution Imaging Spectroradiometer (MODIS) is one of the key instruments for NASA's Earth Observing System (EOS), currently operating on both the Terra and Aqua satellites. The MODIS is a major advance over the previous generation of sensors in terms of its spectral, spatial, and temporal resolutions. It has 36 spectral bands: 20 reflective solar bands (RSB) with center wavelengths from 0.41 to 2.1 mu m and 16 thermal emissive bands (TEB) with center wavelengths from 3.7 to 14.4 mu m, making observations at three spatial resolutions: 250 in (bands 1-2), 500 m (hands 3-7), and 1km (bands 8-36). MODIS is a cross-track scanning radiometer with a wide field-of-view, providing a complete global coverage of the Earth in less than 2 days. Both Terra and Aqua MODIS went through extensive pre-launch calibration and characterization at various levels. In orbit, the calibration and characterization tasks are performed using its on-board calibrators (OBCs) that include a solar diffuser (SD) and a solar diffuser stability monitor (SDSM), a v-grooved flat panel blackbody (BB), and a spectro-radiometric calibration assembly (SRCA). In this paper, we present an overview of MODIS calibration and characterization activities, methodologies, and lessons learned from pre-launch characterization and in-orbit operation. Key issues discussed in this paper include in-orbit efforts of monitoring the noise characteristics of the detectors, tracking the solar diffuser and optics degradations, and updating the sensor's response versus scan angle. The experiences and lessons learned through MODIS have played and will continue to play major roles in the design and characterization of future sensors. C1 NASA, Goddard Space Flight Ctr, Earth Sci Directorate, Greenbelt, MD 20771 USA. Univ Maryland Baltimore Cty, Baltimore, MD 21205 USA. RP Xiong, XX (reprint author), NASA, Goddard Space Flight Ctr, Earth Sci Directorate, Greenbelt, MD 20771 USA. EM Xiaoxiong.xiong.1@gsfc.nasa.gov RI AAS, AAS/C-2949-2014 NR 20 TC 154 Z9 166 U1 5 U2 28 PU SCIENCE PRESS PI BEIJING PA 16 DONGHUANGCHENGGEN NORTH ST, BEIJING 100717, PEOPLES R CHINA SN 0256-1530 J9 ADV ATMOS SCI JI Adv. Atmos. Sci. PD JAN PY 2006 VL 23 IS 1 BP 69 EP 79 DI 10.1007/s00376-006-0008-3 PG 11 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 006EM UT WOS:000234878300009 ER PT J AU Shie, CL Tao, WK Simpson, J AF Shie, CL Tao, WK Simpson, J TI A note on the relationship between temperature and water vapor over oceans, including sea surface temperature effects SO ADVANCES IN ATMOSPHERIC SCIENCES LA English DT Article; Proceedings Paper CT 3rd International Ocean Atmosphere Conference CY JUN 28-30, 2004 CL Inst Atmospher Phys, Beijing, PEOPLES R CHINA SP Chinese Meteorol Soc, Chinese Soc Oceanog, Nat Sci Fdn China, Chinese Acad Sci, Nanjing Univ Informat Sci & Technol HO Inst Atmospher Phys DE moisture temperature relationship; quasi-equilibrium states; Tropics; oceans ID RADIATIVE-CONVECTIVE EQUILIBRIUM; RESOLVING MODEL; TROPICS; SENSITIVITY; RAINFALL; STATES AB An ideal and simple formulation is successfully derived that well represents a quasi-linear relationship found between the domain-averaged water vapor, Q (mm), and temperature, T (K), fields for the three tropical oceans (i.e., the Pacific, Atlantic and Indian Oceans) based on eleven GEOS-3 [Goddard Earth Observing System (EOS) Version-3] global re-analysis monthly products. A Q - T distribution analysis is also performed for the tropical and extra-tropical regions based on in-situ sounding data and numerical Simulations [GEOS-3 and the Goddard Cumulus Ensemble (GCE) model]. A similar positively correlated Q - T distribution is found over the entire oceanic and tropical regions; however, Q increases faster with T for the former region. It is suspected that the tropical oceans may possess a moister boundary layer than the Tropics. The oceanic regime falls within the lower bound of the tropical regime embedded in a global, curvilinear Q - T relationship. A positive correlation is also found between T and sea surface temperature (SST); however, for one degree of increase in T, SST is found to increase 1.1 degrees for a warmer ocean, which is slightly less than an increase of 1.25 degrees for a colder ocean. This seemingly indicates that more (less) heat is needed for an open ocean to maintain an air mass above it with a same degree of temperature rise during a colder (warmer) season [or in a colder (warmer) region]. Q and SST are also found to be positively correlated. Relative humidity (RH) exhibits similar behaviors for oceanic and tropical regions. RH increases with increasing SST and T over oceans, while it increases with increasing T in the Tropics. RH, however, decreases with increasing temperature in the extratropics. It is suspected that the tropical and oceanic regions may possess a moister local boundary layer than the extratropics so that a faster moisture increase than a saturated moisture increase is favored for the former regions. T, Q, saturated water vapor, RH, and SST are also examined with regard to the warm and cold "seasons" over individual oceans. The Indian Ocean warm season dominates in each of the live quantities, while the Atlantic Ocean cold season has the lowest values in most categories. The higher values for the Indian Ocean may be due to its relatively high percentage of tropical coverage compared to the other two oceans. However, Q is found to increase faster for colder months from individual oceans, which differs from the general finding in the global Q - T relationship that Q increases slower for a colder climate. The modified relationship may be attributed to a possible seasonal (warm and cold) variability in boundary layer depth over oceans, or to the small sample size used in each individual oceanic group. C1 Univ Maryland Baltimore Cty, Goddard Earth Sci & Technol Ctr, Baltimore, MD 21250 USA. NASA, Goddard Space Flight Ctr, Atmospheres Lab, Greenbelt, MD 20771 USA. RP Shie, CL (reprint author), Univ Maryland Baltimore Cty, Goddard Earth Sci & Technol Ctr, Baltimore, MD 21250 USA. EM shie@agnes.gsfc.nasa.gov RI AAS, AAS/C-2949-2014 NR 17 TC 2 Z9 2 U1 0 U2 8 PU SCIENCE PRESS PI BEIJING PA 16 DONGHUANGCHENGGEN NORTH ST, BEIJING 100717, PEOPLES R CHINA SN 0256-1530 J9 ADV ATMOS SCI JI Adv. Atmos. Sci. PD JAN PY 2006 VL 23 IS 1 BP 141 EP 148 DI 10.1007/s00376-006-0014-5 PG 8 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 006EM UT WOS:000234878300015 ER PT J AU Chen, QH Huang, N Riemenschneider, S Xu, YS AF Chen, QH Huang, N Riemenschneider, S Xu, YS TI A B-spline approach for empirical mode decompositions SO ADVANCES IN COMPUTATIONAL MATHEMATICS LA English DT Article DE B-splines; nonlinear and nonstationary signals; empirical mode decompositions; Hilbert transforms ID HILBERT SPECTRUM AB We propose an alternative B-spline approach for empirical mode decompositions for nonlinear and nonstationary signals. Motivated by this new approach, we derive recursive formulas of the Hilbert transform of B-splines and discuss Euler splines as spline intrinsic mode functions in the decomposition. We also develop the Bedrosian identity for signals having vanishing moments. We present numerical implementations of the B-spline algorithm for an earthquake signal and compare the numerical performance of this approach with that given by the standard empirical mode decomposition. Finally, we discuss several open mathematical problems related to the empirical mode decomposition. C1 Hubei Univ, Fac Math & Comp Sci, Wuhan 430062, Peoples R China. NASA, Goddard Space Flight Ctr, Lab Hydrospher Proc, Oceans & Ice Branch, Greenbelt, MD 20771 USA. W Virginia Univ, Dept Math, Morgantown, WV 26506 USA. Syracuse Univ, Dept Math, Syracuse, NY 13244 USA. Chinese Acad Sci, Inst Math, Acad Math & Syst Sci, Beijing 100080, Peoples R China. NR 27 TC 104 Z9 138 U1 3 U2 20 PU SPRINGER PI NEW YORK PA 233 SPRING STREET, NEW YORK, NY 10013 USA SN 1019-7168 J9 ADV COMPUT MATH JI Adv. Comput. Math. PD JAN PY 2006 VL 24 IS 1-4 BP 171 EP 195 DI 10.1007/s10444-004-7614-3 PG 25 WC Mathematics, Applied SC Mathematics GA 033FV UT WOS:000236833200010 ER PT S AU Karlmann, PB Klein, KJ Halverson, PG Peters, RD Levine, MB Van Buren, D Dudik, MJ AF Karlmann, P. B. Klein, K. J. Halverson, P. G. Peters, R. D. Levine, M. B. Van Buren, D. Dudik, M. J. BE Balachandran, U TI Linear thermal expansion measurements of single crystal silicon for validation of interferometer based cryogenic dilatometer SO ADVANCES IN CRYOGENIC ENGINEERING, VOL 52A & 52B SE AIP Conference Proceedings LA English DT Proceedings Paper CT International Cryogenic Materials Conference CY AUG 29-SEP 02, 2005 CL Keystone, CO SP US DOE, Fermi Natl Accele Lab, Los Alamos Natl Lab, Off Naval Res, Oak Ridge Natl Lab DE single crystal silicon; thermal expansion; thermal strain; dilatometer ID SPACE-TELESCOPE AB Linear thermal expansion measurements were performed for high-purity P-type single crystal silicon over a temperature range of 30K to 310K to validate the accuracy of JPL's interferometer-based Cryogenic Dilatometer Facility. This system was developed to better characterize thermophysical properties of precision engineering materials at cryogenic temperatures for space-based optical systems. An accurate measurement of these properties is critical for the success of missions such as the James Webb Space Telescope and the Terrestrial Planet Finder Coronagraph where picometer-level instabilities and thermal deformations impact performance. Results from these single crystal silicon measurements show a mean system repeatability of 4 ppb/K in the coefficient of thermal expansion (CTE) from 35K to 305K. Comparison with NIST/CODATA recommended values shows agreement of better than 2 ppb/K from 30K to 80K, better than 11 ppb/K from 80K to 165K, and better than 2 ppb/K from 165K to 305K. C1 [Karlmann, P. B.; Klein, K. J.; Halverson, P. G.; Peters, R. D.; Levine, M. B.; Van Buren, D.; Dudik, M. J.] CALTECH, Jet Prop Lab, NASA, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Karlmann, PB (reprint author), CALTECH, Jet Prop Lab, NASA, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 5 TC 6 Z9 6 U1 1 U2 4 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 0-7354-0316-3 J9 AIP CONF PROC PY 2006 VL 824 BP 35 EP + PG 2 WC Thermodynamics; Materials Science, Multidisciplinary SC Thermodynamics; Materials Science GA BEF10 UT WOS:000237080500005 ER PT S AU Taylor, RP Nellis, GF Klein, SA Hoch, DW Fellers, J Roach, P Park, JM Gianchandani, Y AF Taylor, R. P. Nellis, G. F. Klein, S. A. Hoch, D. W. Fellers, J. Roach, P. Park, J. M. Gianchandani, Y. BE Balachandran, U TI Measurements of the material properties of a laminated piezoelectric stack at cryogenic temperatures SO ADVANCES IN CRYOGENIC ENGINEERING, VOL 52A & 52B SE AIP Conference Proceedings LA English DT Proceedings Paper CT International Cryogenic Materials Conference CY AUG 29-SEP 02, 2005 CL Keystone, CO SP US DOE, Fermi Natl Accele Lab, Los Alamos Natl Lab, Off Naval Res, Oak Ridge Natl Lab DE microvalve; MEMS; piezoelectric; coefficient of thermal expansion AB Future NASA missions require cooling of large structures in space. One class of thermal management solutions for providing controlled, distributed cooling would utilize actively controlled micro-scale valves that are integrated with heat exchangers and sensors in order to provide independent, local temperature control. The most attractive actuation method for these micro-valves is a multilayer piezoelectric (PZT) stack because this technology is capable of providing large force using reasonable voltages (e.g., < 100 V) with minimal power draw. In order to design a micro-valve configuration that takes advantage of this actuation technique, it is necessary to obtain information regarding the behavior of piezoelectric materials at cryogenic temperatures. This paper describes a test facility that was designed to achieve precise measurements of the coefficient of thermal expansion (CTE) and PZT stack actuator constant ((d(33)) over bar) from 40 K to room temperature. The operation of the facility is validated by measuring the CTE of a copper alloy with well-known behavior. Experimental measurements are subsequently presented for a commercially available PZT stack. C1 [Taylor, R. P.; Nellis, G. F.; Klein, S. A.; Hoch, D. W.] Univ Wisconsin, Cryogen Engn Lab, Madison, WI 53706 USA. [Fellers, J.; Roach, P.] NASA, Ames Res Ctr, Cryogen Grp, Moffett Field, CA 94035 USA. [Park, J. M.; Gianchandani, Y.] Univ Michigan, Solid State Elect Lab, Ann Arbor, MI 48109 USA. RP Taylor, RP (reprint author), Univ Wisconsin, Cryogen Engn Lab, Madison, WI 53706 USA. FU NASA [MSMT-2004-0082-0045] FX This work was supported by NASA under contract #MSMT-2004-0082-0045. NR 4 TC 6 Z9 6 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 0-7354-0316-3 J9 AIP CONF PROC PY 2006 VL 824 BP 200 EP + PG 2 WC Thermodynamics; Materials Science, Multidisciplinary SC Thermodynamics; Materials Science GA BEF10 UT WOS:000237080500026 ER PT S AU Canavan, ER Tuttle, JG AF Canavan, E. R. Tuttle, J. G. BE Balachandran, U TI Thermal conductivity and specific heat measurements of candidate structural materials for the JWST optical bench SO ADVANCES IN CRYOGENIC ENGINEERING, VOL 52A & 52B SE AIP Conference Proceedings LA English DT Proceedings Paper CT International Cryogenic Materials Conference CY AUG 29-SEP 02, 2005 CL Keystone, CO SP US DOE, Fermi Natl Accele Lab, Los Alamos Natl Lab, Off Naval Res, Oak Ridge Natl Lab DE thermal conductivity; specific heat; carbon composite; invar; titanium alloy AB The James Webb Space Telescope will include an optical bench known as the integrated science instrument module (ISIM). Candidate structural materials for the ISIM must have low density, high stiffness, and low thermal expansion coefficient at the operating temperature of 30 Kelvin. The thermal conductivity and specific heat are important in modeling the on-orbit cooldown. We built two different systems for measuring the thermal conductivity and specific heat of samples between 4 Kelvin and 290 Kelvin. Both experiments were carefully designed to minimize potential errors due to radiative heat transfer. We chose the cooling system and instrumentation to allow long-term unattended operation. Software was developed to automate each experiment. It used an algorithm designed to ensure that each system was in steady state before a measurement was taken. We describe the two experiments and present the data. C1 [Canavan, E. R.; Tuttle, J. G.] NASA, Goddard Space Flight Ctr, Cryogen & Fluids Branch, Code 552, Greenbelt, MD 20771 USA. RP Canavan, ER (reprint author), NASA, Goddard Space Flight Ctr, Cryogen & Fluids Branch, Code 552, Greenbelt, MD 20771 USA. FU NASA Goddard Space Flight Center FX This work is supported by the JWST Program at NASA Goddard Space Flight Center. We thank D.Gretz, T. Hait, and E. Kunes for technical assistance. NR 6 TC 4 Z9 4 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 0-7354-0316-3 J9 AIP CONF PROC PY 2006 VL 824 BP 233 EP + PG 2 WC Thermodynamics; Materials Science, Multidisciplinary SC Thermodynamics; Materials Science GA BEF10 UT WOS:000237080500030 ER PT S AU Plachta, DW Christie, RJ Jurns, JM Kittel, P AF Plachta, D. W. Christie, R. J. Jurns, J. M. Kittel, P. BE Weisend, JG Barclay, J Breon, S Demko, J DiPirro, M Kelley, JP Kittel, P Klebaner, A Lock, J Maddocks, J Peterson, T Pfotenhauer, J Rowe, A VanSciver, S Zeller, A TI ZBO cryogenic propellant storage applied to a Mars sample return mission concept SO Advances in Cryogenic Engineering, Vols 51A and B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Cryogenic Engineering Conference 2005 CY AUG 29-SEP 02, 2005 CL Keystone, CO SP US DOE, Off High Energy Phys, Fermi Natl Accele Lab, Los Alamos Natl Lab, Off Naval Res & Naval Res Lab, Oak Ridge Natl Lab DE space cryogenics; thermal control; zero boil-off; pressure control; propellant storage; cryocoolers AB Zero Boil-Off (ZBO) Cryogenic Propellant Systems were designed and analyzed for a Mars sample return mission. JPL designed the spacecraft, and NASA GRC/ARC and contractors designed the cryogenic storage systems. The performance of those systems are compared to traditional storable propellant propulsion systems. The cryogenic storage system modeling included cryocoolers, heat pipes, a radiator, shadowing, MLI, foam, and tank internal components. Model descriptions and tools developed are shown, along with the systems performances and masses. Models show that the ZBO systems applied to cryogenic propellants are beneficial to the Mars mission. C1 NASA Glenn Res Ctr, Cleveland, OH 44135 USA. RP Plachta, DW (reprint author), NASA Glenn Res Ctr, Cleveland, OH 44135 USA. NR 8 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 0-7354-0317-1 J9 AIP CONF PROC PY 2006 VL 823 BP 205 EP 212 PG 8 WC Thermodynamics; Physics, Multidisciplinary SC Thermodynamics; Physics GA BEL54 UT WOS:000237990200025 ER PT S AU Hedayat, A Nelson, SL Hastings, LJ Flachbart, RH Tucker, SP AF Hedayat, A. Nelson, S. L. Hastings, L. J. Flachbart, R. H. Tucker, S. P. BE Weisend, JG Barclay, J Breon, S Demko, J DiPirro, M Kelley, JP Kittel, P Klebaner, A Lock, J Maddocks, J Peterson, T Pfotenhauer, J Rowe, A VanSciver, S Zeller, A TI Liquid nitrogen (oxygen simulant) thermodynamic vent system test data analysis SO Advances in Cryogenic Engineering, Vols 51A and B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Cryogenic Engineering Conference 2005 CY AUG 29-SEP 02, 2005 CL Keystone, CO SP US DOE, Off High Energy Phys, Fermi Natl Accele Lab, Los Alamos Natl Lab, Off Naval Res & Naval Res Lab, Oak Ridge Natl Lab DE cryogenic; liquid nitrogen; heat transfer; data analysis AB In designing systems for the long-term storage of cryogens in low-gravity (space) environments, one must consider the effects of thermal stratification on tank pressure that will occur due to environmental heat leaks. During low-gravity operations, a Thermodynamic Vent System (TVS) concept is expected to maintain tank pressure without propellant resettling. A series of TVS tests was conducted at NASA Marshall Space Flight Center (MSFC) using liquid nitrogen (LN2) as a liquid oxygen (LO2) simulant. The tests were performed at tank fill levels of 90%, 50%, and 25%, and with a specified tank pressure control band. A transient one-dimensional TVS performance program is used to analyze and correlate the test data for all three fill levels. Predictions and comparisons of ullage pressure and temperature and bulk liquid saturation pressure and temperature with test data are presented. C1 NASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Hedayat, A (reprint author), NASA, Marshall Space Flight Ctr, 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 0-7354-0317-1 J9 AIP CONF PROC PY 2006 VL 823 BP 232 EP 239 PG 8 WC Thermodynamics; Physics, Multidisciplinary SC Thermodynamics; Physics GA BEL54 UT WOS:000237990200028 ER PT S AU Flachbart, RH Hastings, LJ Hedayat, A Nelson, SL Tucker, SP AF Flachbart, R. H. Hastings, L. J. Hedayat, A. Nelson, S. L. Tucker, S. P. BE Weisend, JG Barclay, J Breon, S Demko, J DiPirro, M Kelley, JP Kittel, P Klebaner, A Lock, J Maddocks, J Peterson, T Pfotenhauer, J Rowe, A VanSciver, S Zeller, A TI Testing of a spray-bar thermodynamic vent system in liquid nitrogen SO Advances in Cryogenic Engineering, Vols 51A and B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Cryogenic Engineering Conference 2005 CY AUG 29-SEP 02, 2005 CL Keystone, CO SP US DOE, Off High Energy Phys, Fermi Natl Accele Lab, Los Alamos Natl Lab, Off Naval Res & Naval Res Lab, Oak Ridge Natl Lab DE cryogenic; test; thermodynamic; vent; nitrogen; helium AB To support development of a microgravity pressure control capability for liquid oxygen (LO2), Thermodynamic Vent System (TVS) testing was conducted at Marshall Space Flight Center (MSFC) using liquid nitrogen (LN2) as an LO2 simulant. The spray-bar TVS hardware used was originally designed by The Boeing Company for testing in liquid hydrogen (LH2). With this concept, a small portion of the tank fluid is passed through a Joule-Thomson (J-T) device, and then through a longitudinal spray-bar mixer/heat exchanger in order to cool the bulk fluid. To accommodate the larger mass flow rates associated with LN2, the TVS hardware was modified by replacing the recirculation pump with an LN2 compatible pump and replacing the J-T valve. The primary advantage of the spray-bar configuration is that tank pressure control can be achieved independent of liquid and vapor location, enhancing the applicability of ground test data to microgravity conditions. Performance testing revealed that the spray-bar TVS was effective in controlling tank pressure within a 6.8-kPa band for fill levels of approximately 90%, 50%, and 25%. Tests were also conducted with gaseous helium (GHe) in the ullage. The TVS operated satisfactorily with GHe in the ullage. However, the total cycle duration increase ranged from 14% to 28% compared to similar tests with gaseous nitrogen (GN(2)). Testing demonstrated that the spray-bar TVS design was flexible enough for use in two different propellants with minimal hardware modifications. C1 NASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Flachbart, RH (reprint author), NASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USA. NR 4 TC 1 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 0-7354-0317-1 J9 AIP CONF PROC PY 2006 VL 823 BP 240 EP 247 PG 8 WC Thermodynamics; Physics, Multidisciplinary SC Thermodynamics; Physics GA BEL54 UT WOS:000237990200029 ER PT S AU Boyle, RF Whitehouse, PL AF Boyle, R. F. Whitehouse, P. L. BE Weisend, JG Barclay, J Breon, S Demko, J DiPirro, M Kelley, JP Kittel, P Klebaner, A Lock, J Maddocks, J Peterson, T Pfotenhauer, J Rowe, A VanSciver, S Zeller, A TI Dewar safety: Risks and corrective actions SO Advances in Cryogenic Engineering, Vols 51A and B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Cryogenic Engineering Conference 2005 CY AUG 29-SEP 02, 2005 CL Keystone, CO SP US DOE, Off High Energy Phys, Fermi Natl Accele Lab, Los Alamos Natl Lab, Off Naval Res & Naval Res Lab, Oak Ridge Natl Lab DE cryogenic; safety; dewar ID SYSTEM; SPACE AB Dewar operations within NASA have occasionally led to overpressurization events, both on flight and non-flight systems. These have never caused personnel injury, but have occasionally led to significant hardware damage. Some of these incidents are described here with descriptions of their corrective actions, to once again raise safety consciousness within the user community. C1 NASA, GSFC, Greenbelt, MD 20771 USA. RP Boyle, RF (reprint author), NASA, GSFC, Code 552, Greenbelt, MD 20771 USA. NR 11 TC 0 Z9 0 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 0-7354-0317-1 J9 AIP CONF PROC PY 2006 VL 823 BP 313 EP 318 PG 6 WC Thermodynamics; Physics, Multidisciplinary SC Thermodynamics; Physics GA BEL54 UT WOS:000237990200037 ER PT S AU Fesmire, JE Augustynowicz, SD Nagy, ZF Sojourner, SJ Shu, QS Cheng, G Susta, JT AF Fesmire, J. E. Augustynowicz, S. D. Nagy, Z. F. Sojourner, S. J. Shu, Q. S. Cheng, G. Susta, J. T. BE Weisend, JG Barclay, J Breon, S Demko, J DiPirro, M Kelley, JP Kittel, P Klebaner, A Lock, J Maddocks, J Peterson, T Pfotenhauer, J Rowe, A VanSciver, S Zeller, A TI Testing of prototype magnetic suspension cryogenic transfer line SO Advances in Cryogenic Engineering, Vols 51A and B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Cryogenic Engineering Conference 2005 CY AUG 29-SEP 02, 2005 CL Keystone, CO SP US DOE, Off High Energy Phys, Fermi Natl Accele Lab, Los Alamos Natl Lab, Off Naval Res & Naval Res Lab, Oak Ridge Natl Lab DE cryogenic pipelines; superconducting magnets; magnetic suspension; experimental testing; thermal insulation; multilayer insulation; heat leak rate AB A 6-meter prototype cryogenic transfer line with magnetic suspension was tested for its mechanical and thermal performance at the Cryogenics Test Laboratory of NASA Kennedy Space Center (KSC). A test facility with two cryogenic end-boxes was designed and commissioned for the testing. Suspension mechanisms were verified through a series of tests with liquid nitrogen. The thermal performance of the prototype was determined using the new test apparatus. The tested prototype has incorporated temperature and vacuum pressure data acquisition ports, customized interfaces to cryogenic end-boxes, and instrumentation. All tests were conducted under simulated onsite transfer line working conditions. A static (boiloff rate measurement) testing method was employed to demonstrate the gross heat leak in the tested article. The real-time temperature distribution, vacuum level, levitation distance, and mass flow rate were measured. The main purpose of this paper is to summarize the testing facility design and preparation, test procedure, and primary test results. Special arrangements (such as turning on/off mechanical support units, observing levitation gap,and setting up the flowmeter) in testing of such a magnetically levitated transfer line are also discussed. Preliminary results show that the heat leak reduction of approximately one-third to one-half is achievable through such transfer lines with a magnetic suspension system. C1 NASA, Kennedy Space Ctr, Kennedy Space Ctr, FL 32899 USA. RP Fesmire, JE (reprint author), NASA, Kennedy Space Ctr, YA-C2-T, Kennedy Space Ctr, FL 32899 USA. NR 10 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 0-7354-0317-1 J9 AIP CONF PROC PY 2006 VL 823 BP 539 EP 546 PG 8 WC Thermodynamics; Physics, Multidisciplinary SC Thermodynamics; Physics GA BEL54 UT WOS:000237990200065 ER PT S AU Ross, RG Johnson, DL AF Ross, R-G., Jr. Johnson, D. L. BE Weisend, JG Barclay, J Breon, S Demko, J DiPirro, M Kelley, JP Kittel, P Klebaner, A Lock, J Maddocks, J Peterson, T Pfotenhauer, J Rowe, A VanSciver, S Zeller, A TI NASA's Advanced Cryocooler Technology Development Program (ACTDP) SO Advances in Cryogenic Engineering, Vols 51A and B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Cryogenic Engineering Conference 2005 CY AUG 29-SEP 02, 2005 CL Keystone, CO SP US DOE, Off High Energy Phys, Fermi Natl Accele Lab, Los Alamos Natl Lab, Off Naval Res & Naval Res Lab, Oak Ridge Natl Lab AB Over the years, NASA has developed a wide variety of new cryocooler technologies, as they represent a significant enabling capability for both Earth and space-science missions. Recent achievements include 50-80K Stirling, pulse tube, and Brayton flight cryocoolers, and multistage development-model coolers at temperatures down to 10K. The largest technology push within NASA right now is in the temperature range of 4 to 6 K. Missions such as the James Web Space Telescope, Terrestrial Planet Finder, and future generations of space telescopes, plan to use infrared detectors operating between 4 and 6K. Similarly, future x-ray and microwave missions plan to use microcalorimeters and bolometers operating at milli-Kelvin temperatures and will require 4-6K cooling to precool their sub-Kelvin refrigerators. To address cryocooler development for these next-generation missions, NASA initiated the Advanced Cryocooler Technology Development Program (ACTDP) in 2001. Since that time, the program has completed detailed designs and development-model hardware of three hybrid pulse tube and Stirling cryocooler concepts for cooling to 4-18 K. This paper presents an overview of the ACTDP program including programmatic objectives and timelines, and summarizes the excellent progress of the three design concepts being fabricated and tested at this time. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Ross, RG (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 13 TC 9 Z9 10 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 0-7354-0317-1 J9 AIP CONF PROC PY 2006 VL 823 BP 607 EP 614 PG 8 WC Thermodynamics; Physics, Multidisciplinary SC Thermodynamics; Physics GA BEL54 UT WOS:000237990200073 ER PT S AU Shirron, PJ DiPirro, MJ Panek, JS Francis, JJ Warner, BA Jackson, ML AF Shirron, P. J. DiPirro, M. J. Panek, J. S. Francis, J. J. Warner, B. A. Jackson, M. L. BE Weisend, JG Barclay, J Breon, S Demko, J DiPirro, M Kelley, JP Kittel, P Klebaner, A Lock, J Maddocks, J Peterson, T Pfotenhauer, J Rowe, A VanSciver, S Zeller, A TI A rapid turnaround two-stage adiabatic demagnetization refrigerator for cooling to 50 mK SO Advances in Cryogenic Engineering, Vols 51A and B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Cryogenic Engineering Conference 2005 CY AUG 29-SEP 02, 2005 CL Keystone, CO SP US DOE, Off High Energy Phys, Fermi Natl Accele Lab, Los Alamos Natl Lab, Off Naval Res & Naval Res Lab, Oak Ridge Natl Lab DE adiabatic demagnetization refrigerator; magnetic refrigeration; low temperature; space astronomy AB Many research and development programs require rapid access to very low temperatures (similar to 50 mK). For detector development, relatively large experiment volumes are also needed for tests involving integrated detectors and readout amplifiers (which may need to be stationed at a different temperature). To provide this capability in a versatile, fast turnaround system, we have constructed a two-stage adiabatic demagnetization refrigerator (ADR) that is operated in a simple bucket-style dewar. The ADR/cryostat is separated into two concentric inserts; the outer insert supports two 3.3 T magnets, magnet leads and magnetic shielding, and the inner one consists of a hermetic experiment volume coupled to the ADR's salt pills and heat switches. The magnet insert remains in the dewar at all times, while the ADR insert may be inserted and removed even when the dewar is cold. The cooldown from room temperature takes less than 1.5 hours, and cycling of the ADR as little as 30 minutes. Future tests will investigate the use of neon exchange gas to accelerate cooling of the ADR and more thermally isolated components such as wiring and structural supports. Design and operation of the system are discussed. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Shirron, PJ (reprint author), NASA, Goddard Space Flight Ctr, Code 661, Greenbelt, MD 20771 USA. NR 3 TC 0 Z9 0 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 0-7354-0317-1 J9 AIP CONF PROC PY 2006 VL 823 BP 954 EP 959 PG 6 WC Thermodynamics; Physics, Multidisciplinary SC Thermodynamics; Physics GA BEL54 UT WOS:000237990200114 ER EF