Scientific and Technical Aerospace Reports Volume 38 July 28, 2000

More documents

Recommendations

Info

cies for runs with up to 64 processors are shown. It can be seen that when using a small number of processors, the fully distributed version of the code with dynamic load balancing outperforms the other methods of load balancing for the HSCT problem. However, as the number of processors increase, the static load balancing and hierarchical dynamic load balancing are the most efficient. The reason for this behavior is that with fewer processors the number of tasks per processor is increased and differences in evaluation time are magnified, making the problem better suited to dynamic load balancing. With more processors, the processor load imbalance becomes negligible and dynamic load balancing is not needed. For the parallel computer used, the extra overhead in the threaded dynamic load balancing scheme caused its efficiency to decrease more than the schemes without threads as the number of processors was increased. The global optimizer proved to be a useful tool for design space exploration. The optimizer was able to methodically search a high dimensional design space and identify regions of promise containing different design concepts with surprisingly few function evaluations. The sensitivity of load balancing performance to variation in function evaluation time for large MDO problems was also observed. It was seen that when there is a small variation in design evaluation time, the computational overhead needed for dynamic load balancing impeded the parallel performance, and it was more efficient to use static load balancing. However, when the variation in design evaluation times is sufficiently large, fully distributed versions of the code with dynamic load balancing performed best. Author Aircraft Design; Design Analysis; Massively Parallel Processors; Multidisciplinary Design Optimization; Parallel Processing (Computers) 20000064717 NASA Marshall Space Flight Center, Huntsville, AL USA Starfire I/ Consort III Launch May 16, 1990; In English; Videotape: 28 min. 11 sec. playing time, in color. with sound Report No.(s): NONP-NASA-VT-2000081529; No Copyright; Avail: CASI; B02, Videotape-Beta; V02, Videotape-VHS The Consort 3 is a commercial suborbital rocket that carried 12 microgravity experiments. It was launched on a Starfire rocket on May 16, 1990, from the Naval Ordnance Missile Test Station facilities at the U.S. Army’s White Sands Missile Range (WSMR), NM. The videotape opens with approximately 2 minutes of a man speaking into a microphone but there is no sound. This is followed by a brief summary of the payload, and the expected trajectory, a view of the launch vehicle, the countdown and the launch. The videotape then shows a film clip from the University of Alabama, with Dr. Francis Wessling, project manager for the Consort 3 project, speaking about the mission goals in the materials sciences experimentation. The video shows footage of the payload being assembled. The next section is a discussion by Dr. Roy Hammustedt, of Pennsylvania State University, who reviews the Penn State Bio Module,and the goal of learning about the effects of gravity on physiology. This is followed by George Maybee, from McDonald Douglas, who spoke about the payload integration process while the video shows some of the construction. The last section of the videotape shows a press conference at the launch site. Ana Villamil answers questions from the press about the flight. CASI Launching; Microgravity; Payloads; Low Gravity Manufacturing; Gravitational Physiology; Physiological Effects 20000064899 NASA Kennedy Space Center, Cocoa Beach, FL USA AC-67/FLTSATCOM Launch with Isolated Cam Views/ Freeze of Lightning/ Press Conference Mar. 26, 1987; In English; Videotape: 34 min. playing time, in color, with sound Report No.(s): NONP-NASA-VT-2000078604; No Copyright; Avail: CASI; B03, Videotape-Beta; V03, Videotape-VHS The FLTSATCOM system provides worldwide, high-priority UHF communications between naval aircraft, ships, submarines, and ground stations and between the Strategic Air Command and the national command authority network. This videotape shows the attempted launch of the 6th member of the satellite system on an Atlas Centaur rocket. Within a minute of launch a problem developed. The initial sign of the problem was the loss of telemetry data. The videotape shows three isolated views of the launch, and then a freeze shot of a lightning strike shortly after the launch. The tape then shows a press conference, with Mr. Wolmaster, Mr. Gibbs, and Air Force Colonel Alsbrooke. Mr. Gibbs summarizes the steps that would be taken to review the launch failure. The questions from the press mostly concern the weather conditions, and the possibility that the weather might have caused the mission failure. CASI Fleet Satellite Communication System; Launching; Lightning; Failure; Liftoff (Launching); Launchers 36
20000067665 NASA Kennedy Space Center, Cocoa Beach, FL USA TOPEX/POSEIDON Launch from Guiana Space Center Aboard an Ariane 42P Aug. 10, 1992; In English; Videotape: 22 min. 23 sec. playing time, in color, with sound Report No.(s): NONP-NASA-VT-2000081530; No Copyright; Avail: CASI; B02, Videotape-Beta; V02, Videotape-VHS Footage shows the Launch Control Center (LCC) as they prepare for launch. During preparation Charles Bigot, Chairman and C.E.O. of Arianespace, and Jean-Daniel Levi, Director of CNES spoke briefly about the join effort between National Aeronautics and Space Administration (NASA) and the European Space Agency (ESA). The NASA administrator, Don Golding also made a brief speech via telephone before the launching. Live footage also shows the launching of the TOPEX/POSEIDON satellite. CASI Poseidon Satellite; TOPEX; Spacecraft Launching; Ariane Launch Vehicle 20000067668 NASA Kennedy Space Center, Cocoa Beach, FL USA Pegasus Departs from KSC Feb. 09, 1993; In English; Videotape: 2 min. 32 sec. playing time, in color, with sound Report No.(s): NONP-NASA-VT-2000081536; KSC93-30261; No Copyright; Avail: CASI; B01, Videotape-Beta; V01, Videotape-VHS Footage shows the departure of the Pegasus launch vehicle from Kennedy Space Center (KSC). CASI Pegasus Air-Launched Booster; Air Launching; B-52 Aircraft 19 SPACECRAFT INSTRUMENTATION AND ASTRIONICS �� 20000063380 NASA Glenn Research Center, Cleveland, OH USA Quasi-Steady Acceleration Direction Indicator in Three Dimensions DeLombard, Richard, NASA Glenn Research Center, USA; Nelson, Emily S., NASA Glenn Research Center, USA; Jules, Kenol, NASA Glenn Research Center, USA; May 2000; 12p; In English; 38th; Aerospace Sciences, 10-13 Jan. 2000, Reno, NV, USA; Sponsored by American Inst. of Aeronautics and Astronautics, USA Contract(s)/Grant(s): RTOP 398-95-0G Report No.(s): NASA/TM-2000-209931; E-12175; NAS 1.15:209931; AIAA Paper 2000-0570; No Copyright; Avail: CASI; A03, Hardcopy; A01, Microfiche Many materials processing and fluids physics experiments conducted in a microgravity environment require knowledge of the orientation of the low-frequency acceleration vector. This need becomes especially acute for space experiments such as directional solidification of a molten semiconductor, which is extremely sensitive to orientation and may involve tens of hours of operations of a materials furnace. These low-frequency acceleration data have been measured for many Shuttle missions with the Orbital Acceleration Research Experiment. Previous attempts at using fluid chambers for acceleration measurements have met with limited success due to pointing and vehicle attitude complications. An acceleration direction indicator is described, which is comprised of two orthogonal short cylinders of fluid, each with a small bubble. The motion and the position of the bubble within the chamber will indicate the direction of the acceleration experienced at the sensor location. The direction of the acceleration vector may then be calculated from these data. The frequency response of such an instrument may be tailored for particular experiments with the proper selection of fluid and gas parameters, surface type, and geometry. A three-dimensional system for sensing and displaying the low-frequency acceleration direction via an innovative technique described in this paper has advantages in terms of size, mass, and power compared with electronic instrumentation systems. Author Accelerometers; Semiconductors (Materials); Low Frequencies; Directional Solidification (Crystals); Attitude (Inclination); Microgravity 37
Page 1 and 2:
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 and 54: 20000063520 NASA Kennedy Space Cent
Page 55 and 56: primary issues for it’s adaptatio
Page 57: Footage shows the night vertical ta
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
Page 105 and 106: ment phase demonstrate desired feat
Page 107 and 108: esolution mode with resolving power
Page 109 and 110:
to track 1% or 0.5% changes was hig
Page 111 and 112:
20000067643 NASA Marshall Space Fli
Page 113 and 114:
37 MECHANICAL ENGINEERING ��
Page 115 and 116:
solver based on overset grid techno
Page 117 and 118:
Page 119 and 120:
20000064621 Rensselaer Polytechnic
Page 121 and 122:
that for a specific example of a be
Page 123 and 124:
km x 1000 km). As with the nearly c
Page 125 and 126:
20000064527 Analytical Imaging and
Page 127 and 128:
20000064533 Austin State Univ., Dep
Page 129 and 130:
20000064539 California Univ., Inst.
Page 131 and 132:
20000064547 Jet Propulsion Lab., Ca
Page 133 and 134:
in Yellowstone National Park. We ar
Page 135 and 136:
terns of community hysteresis based
Page 137 and 138:
20000064565 Jet Propulsion Lab., Ca
Page 139 and 140:
tion model (DEM) fitting to the sca
Page 141 and 142:
The Carolina slate belt is a 10- to
Page 143 and 144:
20000063373 Los Alamos National Lab
Page 145 and 146:
20000064912 New Energy and Industri
Page 147 and 148:
and discusses the issues and resear
Page 149 and 150:
The objective of this study was to
Page 151 and 152:
distributions with engine test resu
Page 153 and 154:
7.6, while the 1926 events appear t
Page 155 and 156:
We investigate the compositional di
Page 157 and 158:
Flight Center, USA; Moore, T. E., N
Page 159 and 160:
This report presents the Applied Me
Page 161 and 162:
in Goa, India, by 3 - 4 days. Wind
Page 163 and 164:
51 LIFE SCIENCES (GENERAL) Includes
Page 165 and 166:
20000062717 Joint Inst. for Nuclear
Page 167 and 168:
20000064015 Institute for Human Fac
Page 169 and 170:
during 50% (SD 4%) of the breathing
Page 171 and 172:
20000064711 Massachusetts Inst. of
Page 173 and 174:
The analysis of this smaller data s
Page 175 and 176:
vided a functional helmet mount. Th
Page 177 and 178:
61 COMPUTER PROGRAMMING AND SOFTWAR
Page 179 and 180:
The goal of multi-image classificat
Page 181 and 182:
20000063526 Defence Science and Tec
Page 183 and 184:
85 dB amplifier design evolved by o
Page 185 and 186:
20000064594 New Mexico Univ., Elect
Page 187 and 188:
20000064615 NASA Ames Research Cent
Page 189 and 190:
declarations with a pattern recogni
Page 191 and 192:
containing point where interpolatio
Page 193 and 194:
has his own responsibility, while t
Page 195 and 196:
the people, documents and projects
Page 197 and 198:
and experimental technology, many o
Page 199 and 200:
tems. In particular this applicatio
Page 201 and 202:
Over the past decade, high performa
Page 203 and 204:
expensive than a single analysis. I
Page 205 and 206:
20000064726 Carnegie-Mellon Univ.,
Page 207 and 208:
20000064099 Teledyne Brown Engineer
Page 209 and 210:
20000066597 Geophysical Observatory
Page 211 and 212:
20000065633 Institute TNO of Applie
Page 213 and 214:
important conclusion is that for su
Page 215 and 216:
est frame of the string. The modifi
Page 217 and 218:
isotopes. The method and program we
Page 219 and 220:
A detailed study is undertaken, usi
Page 221 and 222:
20000063497 Kaiser Electro-Optics,
Page 223 and 224:
delivers 60% of the x-ray flux from
Page 225 and 226:
76 SOLID-STATE PHYSICS ��
Page 227 and 228:
20000064660 Abdus Salam Internation
Page 229 and 230:
Page 231 and 232:
20000064703 Institute of Atomic Ene
Page 233 and 234:
The BRST approach is applied to the
Page 235 and 236:
20000067671 Hampton Univ., VA USA A
Page 237 and 238:
82 DOCUMENTATION AND INFORMATION SC
Page 239 and 240:
ecoming almost too cumbersome to be
Page 241 and 242:
physical world. These are the two p
Page 243 and 244:
with WFPC2 data. Tests of HSTphot
Page 245 and 246:
A brief description is given of the
Page 247 and 248:
20000064070 NASA Ames Research Cent
Page 249 and 250:
gas, show variations that have rema
Page 251 and 252:
egy, called Power In that would all
Page 253 and 254:
20000065631 NASA Kennedy Space Cent
Page 255 and 256:
20000064089 Smithsonian Astrophysic
Page 257 and 258:
A ABERRATION, 143, 198 ABRASION, 22
Page 259 and 260:
COMPRESSIBLE FLOW, 83 COMPRESSION L
Page 261 and 262:
FATIGUE (MATERIALS), 50, 93, 96 FAT
Page 263 and 264:
LASING, 90 LATE STARS, 224 LATITUDE
Page 265 and 266:
PATCH ANTENNAS, 74 PATHOLOGY, 98 PA
Page 267 and 268:
SPACE PLATFORMS, 38 SPACE PROBES, 2
Page 269 and 270:
WIND PROFILES, 137 WIND TUNNEL TEST
Page 271 and 272:
Brown, Andy, 38 Brown, April S., 20
Page 273 and 274:
Grosvenor, C. A., 70 Grosvenor, J.
Page 275 and 276:
Lu, Gui-Ying, 50 Lugg, Desmond J.,
Page 277 and 278:
Robertson, Tony, 39 Robinson, Jeffr
Page 279:
Warner, J. D., 63 Warren, James, 16
show all

Scientific and Technical Aerospace Reports Volume 38 July 28, 2000

Create successful ePaper yourself

Delete template?

Save as template?