Scientific and Technical Aerospace Reports Volume 38 July 28, 2000

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ances and vehicle inertia uncertainties. This is a significant advancement in performance over that achieved with linear, gain scheduled control systems currently being used for launch vehicles. Author Reusable Launch Vehicles; Optimal Control; Stability; Decoupling; Angular Velocity 20000067669 NASA Kennedy Space Center, Cocoa Beach, FL USA Atlas/Centaur-SOHO Pre-Launch News Conference Nov. 22, 1995; In English; Videotape: 20 min. 55 sec. playing time, in color, with sound Report No.(s): NONP-NASA-VT-2000081546; No Copyright; Avail: CASI; B02, Videotape-Beta; V02, Videotape-VHS Live coverage of a pre-launch news conference on the Atlas/Centaur SOHO mission is presented. George Diller, NASA Public Affairs, introduces the panel. Floyd Curington, NASA Launch Manager, Kennedy Space Center, presents countdown activities. Pat Symons, Launch Vehicle Manager, NASA Lewis Research Center, analyzes the time duration from liftoff to spacecraft separation. Fabrizio Felici, SOHO Mission Director European Space Agency (ESA), explains the important features of SOHO, which includes a payload of 650 kilos and 12 major instruments with multisensors. Ken Sizemore, International Solar Terrestrial Physics (ISTP) Project Manager Goddard Space Flight Center (GSFC), talks about the successful international collaboration between the ESA and NASA. Joel Tumbiolo, Launch Weather Officer USA Air Force (USAF, presented the weather forecast. SOHO was launched aboard an Atlas II rocket on November 23, 1995. The news conference ends with a brief question and answer period. CASI Atlas Centaur Launch Vehicle; SOHO Mission; Prelaunch Summaries; Spacecraft Launching 32 16 SPACE TRANSPORTATION AND SAFETY �� 20000063511 NASA Johnson Space Center, Houston, TX USA STS 101: Post Flight Presentation Jun. 21, 2000; In English; Videotape: 15 min. 7 sec. playing time, in color, with sound Report No.(s): NONP-NASA-VT-2000087291; JSC-1827; No Copyright; Avail: CASI; B01, Videotape-Beta; V01, Videotape- VHS The crew (Mission Commander James D. Halsell, Jr., Pilot Scott J. Horowitz, and Mission Specialists Mary Ellen Weber, Jeffrey N. Williams, James S. Voss, Susan J. Helms, and Yuri Vladimirovich Usachev) describe the highlights of the STS 101 Mission. The primary scenes reviewed include the spacewalk, incremental assembly/upgrades, space station rendevous, suit testing, critical replacement and repairs to suspect batteries, and reboosting the station from 230 statute miles to 250 statute miles. CASI Space Transportation System Flights; Spacecrews; Space Stations; Space Transportation System 20000067639 NASA Marshall Space Flight Center, Huntsville, AL USA Transportation System Options For The Interstellar Probe Mission Johnson, Charles Les, NASA Marshall Space Flight Center, USA; May 22, 2000; 1p; In English; xThe Outer Heliosphere: The Next Frontiers, 24-28 Jul. 2000, Potsdam, Germany; Sponsored by Committee on Space Research, France; No Copyright; Avail: Issuing Activity; Abstract Only NASA is considering a mission to explore near-interstellar space early in the next decade as the first step toward a vigorous interstellar exploration program. A key enabling technology for such an ambitious science and exploration effort is the development of propulsion systems capable of providing fast trip times. Advanced propulsion technologies that might support an interstellar precursor mission early in the next century include some combination of solar sails, nuclear electric propulsion systems, and aerogravity assists. For years, the scientific community has been interested in the development of solar sail technology to support exploration of the inner and outer planets. Progress in thin-film technology and the development of technologies that may enable the remote assembly of lar2e sails in space are only now maturing to the point where ambitious interstellar precursor missions can be considered. Electric propulsion is now being demonstrated for planetary exploration by the Deep Space I mission. The
primary issues for it’s adaptation to interstellar precursor applications include the nuclear reactor that would be required and the engine lifetime. A propulsion system concept for the proposed Interstellar Probe mission will be described for each. Author Transportation; Interstellar Space; Space Missions; Space Exploration; Nuclear Electric Propulsion; Propulsion System Performance 20000067685 NASA Marshall Space Flight Center, Huntsville, AL USA Manufacturing and NDE of Large Composite Structures for Space Transportation at MSFC McGill, Preston, NASA Marshall Space Flight Center, USA; Russell, Sam, NASA Marshall Space Flight Center, USA; [2000]; 41p; In English; 9th; 2000 ASNT Spring Conference, 29 Mar. 2000, Birmingham, AL, Birmingham, AL, USA, USA; No Copyright; Avail: CASI; A03, Hardcopy; A01, Microfiche This paper presents the Marshall Space Flight Center’s (MSFC’s) vision to manufacture, increase safety and reduce the cost of launch vehicles. Nondestructive evaluations of large composite structures are tested for space transportation at MSFC. The topics include: 1) 6 1/2 Generations of Airplanes in a Century; 2) Shuttle Safety Upgrades; 3) Generations of Reusable Launch Vehicles; 4) RLV Technology Demonstration Path; 5) Second Generation; 6) Key NASA Requirements; 7) X-33 Elements; 8) Future-X Pathfinder Projects and Experiments; 9) Focus Area Technical Goals; 10) X-34 Expanded View; 11) X-38 Spacecraft with De-Orbit Propulsion Stage (DPS); 12) Deorbit Module (DM) Critical Design Review (CDR) Design; 13) Forward Structural Adapter (FSA) CDR Design; 14) X-38 DPS CDR Design; 15) RLV Focused Propulsion Technologies; and 16) Challenges in Technology. This paper is presented in viewgraph form. CASI Composite Structures; Manufacturing; Nondestructive Tests; Reusable Launch Vehicles; Space Transportation 17 SPACE COMMUNICATIONS, SPACECRAFT COMMUNICATIONS, COMMAND AND TRACKING �� 20000063381 NASA Glenn Research Center, Cleveland, OH USA Radiation Hardened, Modulator ASIC for High Data Rate Communications McCallister, Ron, SICOM, Inc., USA; Putnam, Robert, SICOM, Inc., USA; Andro, Monty, NASA Glenn Research Center, USA; Fujikawa, Gene, NASA Glenn Research Center, USA; June 2000; 12p; In English; 18th; Communication Satellite Systems, 10-14 Apr. 2000, Oakland, CA, USA; Sponsored by American Inst. of Aeronautics and Astronautics, USA Contract(s)/Grant(s): NAS3-99096; RTOP 632-6E-51 Report No.(s): NASA/TM-2000-210045; E-12246; NAS 1.15:210045; No Copyright; Avail: CASI; A03, Hardcopy; A01, Microfiche Satellite-based telecommunication services are challenged by the need to generate down-link power levels adequate to support high quality (BER approx. equals 10(exp 12)) links required for modem broadband data services. Bandwidth-efficient Nyquist signaling, using low values of excess bandwidth (alpha), can exhibit large peak-to-average-power ratio (PAPR) values. High PAPR values necessitate high-power amplifier (HPA) backoff greater than the PAPR, resulting in unacceptably low HPA efficiency. Given the high cost of on-board prime power, this inefficiency represents both an economical burden, and a constraint on the rates and quality of data services supportable from satellite platforms. Constant-envelope signals offer improved power-efficiency, but only by imposing a severe bandwidth-efficiency penalty. This paper describes a radiation- hardened modulator which can improve satellite-based broadband data services by combining the bandwidth-efficiency of low-alpha Nyquist signals with high power-efficiency (negligible HPA backoff). Author Telecommunication; Application Specific Integrated Circuits; Modulators; Power Efficiency 33
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Scientific and Technical Aerospace
Page 3 and 4: Introduction Scientific and Technic
Page 5 and 6: Subject Divisions Table of Contents
Page 7 and 8: ground equipment and systems. For a
Page 9 and 10: Subject Categories of the Division
Page 11 and 12: 48 Oceanography 139 Includes the ph
Page 13 and 14: 72 Atomic and Molecular Physics 191
Page 15 and 16: Document Availability Information T
Page 17 and 18: Avail: NASA Public Document Rooms.
Page 19 and 20: NASA CASI Price Tables — Effectiv
Page 21 and 22: ALABAMA AUBURN UNIV. AT MONTGOMERY
Page 23 and 24: ��
Page 25 and 26: 20000061433 Pisa Univ., Dipartiment
Page 27 and 28: English; 34th; 34th Thermophysics C
Page 29 and 30: ciency of the generated derivative
Page 31 and 32: 20000063509 NASA Glenn Research Cen
Page 33 and 34: 05 AIRCRAFT DESIGN, TESTING AND PER
Page 35 and 36: A long tradition of aerodynamic des
Page 37 and 38: sonic and transonic cases will be p
Page 39 and 40: 20000061449 British Aerospace Publi
Page 41 and 42: 20000064593 NASA Langley Research C
Page 43 and 44: performance required for a proposed
Page 45 and 46: ment cost and create better product
Page 47 and 48: tion (NPSS), is focused on the inte
Page 49 and 50: surface measurement techniques used
Page 51 and 52: with emphasis on the search for lin
Page 53: 20000063520 NASA Kennedy Space Cent
Page 57 and 58: Footage shows the night vertical ta
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Page 61 and 62: necessary for ignition modeling, or
Page 63 and 64: engine lifetime, and high power ope
Page 65 and 66: 24 COMPOSITE MATERIALS ��
Page 67 and 68: ments. For the screening of liner m
Page 69 and 70: formation of a neutral, fluorescent
Page 71 and 72: 20000065655 Ames Lab., IA USA Funda
Page 73 and 74: This is a second Triennial Conferen
Page 75 and 76: of completely charged PSSNa solutio
Page 77 and 78: 20000064100 NASA Langley Research C
Page 79 and 80: Spacecraft in low Earth orbit (LEO)
Page 81 and 82: Pressure gradients, i.e. pressure h
Page 83 and 84: agreed that the NO(sub x) levels co
Page 85 and 86: tectural approach to extending the
Page 87 and 88: 20000064078 Physics and Electronics
Page 89 and 90: 20000064925 Institute for Human Fac
Page 91 and 92: 20000066607 Institute for Human Fac
Page 93 and 94: 20000062455 National Inst. of Stand
Page 95 and 96: Added Analysis (Risk Reduction); 6)
Page 97 and 98: shipboard electrical power generati
Page 99 and 100: 20000067664 Jet Propulsion Lab., Ca
Page 101 and 102: other, The theoretical framework go
Page 103 and 104: figures compare the lift and pitchi
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ment phase demonstrate desired feat
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esolution mode with resolving power
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to track 1% or 0.5% changes was hig
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20000067643 NASA Marshall Space Fli
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37 MECHANICAL ENGINEERING ��
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solver based on overset grid techno
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20000064621 Rensselaer Polytechnic
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that for a specific example of a be
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km x 1000 km). As with the nearly c
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20000064527 Analytical Imaging and
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20000064533 Austin State Univ., Dep
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20000064539 California Univ., Inst.
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20000064547 Jet Propulsion Lab., Ca
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in Yellowstone National Park. We ar
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terns of community hysteresis based
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20000064565 Jet Propulsion Lab., Ca
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tion model (DEM) fitting to the sca
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The Carolina slate belt is a 10- to
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20000063373 Los Alamos National Lab
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20000064912 New Energy and Industri
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and discusses the issues and resear
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The objective of this study was to
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distributions with engine test resu
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7.6, while the 1926 events appear t
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We investigate the compositional di
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Flight Center, USA; Moore, T. E., N
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This report presents the Applied Me
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in Goa, India, by 3 - 4 days. Wind
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51 LIFE SCIENCES (GENERAL) Includes
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20000062717 Joint Inst. for Nuclear
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20000064015 Institute for Human Fac
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during 50% (SD 4%) of the breathing
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20000064711 Massachusetts Inst. of
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The analysis of this smaller data s
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vided a functional helmet mount. Th
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61 COMPUTER PROGRAMMING AND SOFTWAR
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The goal of multi-image classificat
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20000063526 Defence Science and Tec
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85 dB amplifier design evolved by o
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20000064594 New Mexico Univ., Elect
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20000064615 NASA Ames Research Cent
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declarations with a pattern recogni
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containing point where interpolatio
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has his own responsibility, while t
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the people, documents and projects
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and experimental technology, many o
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tems. In particular this applicatio
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Over the past decade, high performa
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expensive than a single analysis. I
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20000064726 Carnegie-Mellon Univ.,
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20000064099 Teledyne Brown Engineer
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20000066597 Geophysical Observatory
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20000065633 Institute TNO of Applie
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important conclusion is that for su
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est frame of the string. The modifi
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isotopes. The method and program we
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A detailed study is undertaken, usi
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20000063497 Kaiser Electro-Optics,
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delivers 60% of the x-ray flux from
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76 SOLID-STATE PHYSICS ��
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20000064660 Abdus Salam Internation
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20000064703 Institute of Atomic Ene
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The BRST approach is applied to the
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20000067671 Hampton Univ., VA USA A
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82 DOCUMENTATION AND INFORMATION SC
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ecoming almost too cumbersome to be
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physical world. These are the two p
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with WFPC2 data. Tests of HSTphot
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A brief description is given of the
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20000064070 NASA Ames Research Cent
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gas, show variations that have rema
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egy, called Power In that would all
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20000065631 NASA Kennedy Space Cent
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20000064089 Smithsonian Astrophysic
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A ABERRATION, 143, 198 ABRASION, 22
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COMPRESSIBLE FLOW, 83 COMPRESSION L
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FATIGUE (MATERIALS), 50, 93, 96 FAT
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LASING, 90 LATE STARS, 224 LATITUDE
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PATCH ANTENNAS, 74 PATHOLOGY, 98 PA
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SPACE PLATFORMS, 38 SPACE PROBES, 2
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WIND PROFILES, 137 WIND TUNNEL TEST
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Brown, Andy, 38 Brown, April S., 20
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Grosvenor, C. A., 70 Grosvenor, J.
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Lu, Gui-Ying, 50 Lugg, Desmond J.,
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Robertson, Tony, 39 Robinson, Jeffr
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Warner, J. D., 63 Warren, James, 16
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