Scientific and Technical Aerospace Reports Volume 39 April 6, 2001

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In October 2000, the Airway Facilities organization plans to transition the National Airspace System (NAS) monitoring responsibilities to three regional Operations Control Centers (OCCs). Teams in these facilities will be different from those that currently exist in Maintenance Control Centers. A research team from the NAS Human Factors Branch, ACT-530, reviewed the implications of this new environment on potential OCC team performance issues. They conducted a two-pronged study. The first part examined team processes in current and future Airway Facilities (AF) environments. This involved assessing task analyses and flowcharts depicting workflow and communication processes for AF maintenance work and conducting site interviews at key field sites. The second part of the study focused on identifying key factors with implications for team performance in the literature and applying them to the OCC environment. The study led to nine recommendations for facilitating the transition to OCCs. DTIC Air Traffic Control; Teams; National Airspace System; Human Performance 20010026205 Sandia National Labs., Albuquerque, NM USA Conceptual Design of a 50--100 MW Electron Beam Accelerator System for the National Hypersonic Wind Tunnel Program Schneider, L. X.; Jun. 01, 2000; 13p; In English Report No.(s): DE00-759452; SAND2000-1458; No Copyright; Avail: Department of Energy Information Bridge The National Hypersonic Wind Tunnel program requires an unprecedented electron beam source capable of 1--2 MeV at a beam power level of 50--100 MW. Direct-current electron accelerator technology can readily generate high average power beams to approximately 5 MeV at output efficiencies greater than 90%. However, due to the nature of research and industrial applications, there has never been a requirement for a single module with an output power exceeding approximately 500 kW. Although a 50--100 MW module is a two-order extrapolation from demonstrated power levels, the scaling of accelerator components appears reasonable. This paper presents an evaluation of component and system issues involved in the design of a 50--100 MW electron beam accelerator system with precision beam transport into a high pressure flowing air environment. NTIS Electron Beams; Electron Accelerators; Wind Tunnel Tests; Design Analysis 12 15 LAUNCH VEHICLES AND LAUNCH OPERATIONS �� 20010023095 Orbital Sciences Corp., Dulles, VA USA Enabling Launch Vehicle Technology for Mars Sample Return Missions Dorsch, M., Orbital Sciences Corp., USA; Patel, B., Orbital Sciences Corp., USA; Mauritz, A., Orbital Sciences Corp., USA; Concepts and Approaches for Mars Exploration; July 2000, Part 1, pp. 98; In English; See also 20010023036; No Copyright; Abstract Only; Available from CASI only as part of the entire parent document Sample return missions constitute an important element of the overall strategy for the exploration of Mars. A launch vehicle (booster) is required to successfully transfer samples from the Martian surface to orbiting spacecraft. This booster must survive harsh Martian environments while providing high performance within tight mass and power constraints. Leveraging its unparalleled expertise at the successful development of new small launch vehicles, Orbital Sciences Corporation (Orbital) developed a booster system for NASA JPL’s Mars Ascent Vehicle (MAV) study and RFP in 1999. The MAV was an integral element in the overall Mars Sample Return (MSR) architecture. The booster is a two-stage, solid rocket system that can launch approximately 6 kg into a 500 km circular orbit around Mars. The booster system total mass is less than 135 kg, while the design accommodates stringent planetary protection requirements and complex interfaces with the lander. Operationally, the system requires minimal interaction with mission controllers for launch preparations. It possesses the capability to erecting itself from a stowed position to the desired initial launch azimuth. Solid rocket motors designed for long duration space exposure are provided by Thiokol based on heritage from its proven Star series. The Guidance, Navigation, and Control (GNC) system is based on Orbital’s highly proven Pegasus and Taurus launch vehicles. The lightweight booster avionics hardware derives extensive heritage from Orbital’s spacecraft programs. In addition to the MSR scenario, there exist other mission implementations where the sample is not necessarily returned to Earth for analyses, but is instead analyzed onboard a spacecraft in Mars orbit. Orbital’s booster systems is capable of supporting either mission scenario. A rendering of the MAV is contained in the original abstract. Author Mars Sample Return Missions; Launch Vehicles
20010025824 Pratt and Whitney Aircraft, Liquid Space Propulsion, West Palm Beach, FL USA 2nd Generation Reusable Launch Vehicle (2G RLV) Final Report, 28 Jul. 2000 - 31 Jan. 2001 Matlock, Steve, Pratt and Whitney Aircraft, USA; Sides, Steve, Pratt and Whitney Aircraft, USA; Kmiec, Tom, Pratt and Whitney Aircraft, USA; Arbogast, Tim, Pratt and Whitney Aircraft, USA; Mayers, Tom, Pratt and Whitney Aircraft, USA; Doehnert, Bill, Pratt and Whitney Aircraft, USA; Feb. 23, 2001; 110p; In English; Original contains color illustrations Contract(s)/Grant(s): NAS8-00168; NRA8-27 Report No.(s): LS-50-Rev; No Copyright; Avail: CASI; A06, Hardcopy; A02, Microfiche This is a revised final report and addresses all of the work performed on this program. Specifically, it covers vehicle architecture background, definition of six baseline engine cycles, reliability baseline (space shuttle main engine QRAS), and component level reliability/performance/cost for the six baseline cycles, and selection of 3 cycles for further study. This report further addresses technology improvement selection and component level reliability/performance/cost for the three cycles selected for further study, as well as risk reduction plans, and recommendation for future studies. Author Reusable Launch Vehicles; Rocket Engine Design; Liquid Rocket Propellants; Space Shuttle Main Engine; Performance Prediction 16 SPACE TRANSPORTATION AND SAFETY �� 20010022499 NASA Johnson Space Center, Houston, TX USA STS-102 Crew Activity Report/Flight Day 1 Highlights Mar. 08, 2001; In English; Videotape: 20 min. 1 sec. playing time, in color, with sound Report No.(s): NONP-NASA-VT-2001031588; BRF1427A; No Copyright; Avail: CASI; B02, Videotape-Beta; V02, Videotape- VHS The crew of STS-102 (Commander James D. Wetherbee, Pilot James M. Kelly, and Mission Specialists Andrew S. W. Thomas and Paul Richards) and the Expedition 2 crew (James S. Voss, Susan J. Helms, and Yuriy V. Usachev) are seen during the prelaunch breakfast, suiting up, leaving the Operations and Checkout (O&C) Building, and boarding the Discovery Orbiter. The launch of Discovery is seen from the ground and from an onboard camera. CASI Discovery (Orbiter); Checkout; Spacecraft Launching; Crew Procedures (Preflight) 20010022500 NASA Johnson Space Center, Houston, TX USA STS-102 Crew Activity Report/Flight Day 3 Highlights Mar. 10, 2001; In English; Videotape: 16 min. 36 sec. playing time, in color, with sound Report No.(s): NONP-NASA-VT-2001031587; BRF1427C; No Copyright; Avail: CASI; B02, Videotape-Beta; V02, Videotape- VHS Footage shows the docking of the Discovery Orbiter with the International Space Station (ISS). The STS-102 crew (Commander James D. Wetherbee, Pilot James M. Kelly, and Mission Specialists Andrew S. W. Thomas and Paul Richards) and the Expedition 2 crew (James S. Voss, Susan J. Helms, and Yuriy V. Usachev) are seen greeting the Expedition 1 crew (William M. Shepherd, Yuri P. Gidzenko, and Sergei K. Krikalev) after Commander Wetherbee opens the hatch connecting Discovery to the ISS. CASI Discovery (Orbiter); International Space Station; Hatches; Spacecraft Docking; Crew Procedures (Inflight) 20010022501 NASA Johnson Space Center, Houston, TX USA STS-102 Crew Activity Report/Flight Day 2 Highlights Mar. 09, 2001; In English; Videotape: 21 min. 32 sec. playing time, in color, with sound Report No.(s): NONP-NASA-VT-2001031586; BRF1427B; No Copyright; Avail: CASI; B02, Videotape-Beta; V02, Videotape- VHS 13
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: Subject Categories of the Division
Page 13 and 14: 73 Nuclear Physics 263 Includes nuc
Page 15 and 16: Document Availability Information T
Page 17 and 18: Avail: NASA Public Document Rooms.
Page 19 and 20: Hardcopy & Microfiche Prices Code N
Page 21 and 22: ALABAMA AUBURN UNIV. AT MONTGOMERY
Page 23 and 24: ��
Page 25 and 26: 03 AIR TRANSPORTATION AND SAFETY
Page 27 and 28: work of the JAA had established thi
Page 29 and 30: 20010024868 Federal Aviation Admini
Page 31 and 32: 20010023437 Defence Science and Tec
Page 33: The Models for Aeroelastic Validati
Page 37 and 38: 20010023064 NASA Langley Research C
Page 39 and 40: 17 SPACE COMMUNICATIONS, SPACECRAFT
Page 41 and 42: 20010026207 NASA, Washington, DC US
Page 43 and 44: The objective of the proposed resea
Page 45 and 46: 20010022640 Stanford Univ., Center
Page 47 and 48: ustion, showing that these can have
Page 49 and 50: 20010026184 Oak Ridge National Lab.
Page 51 and 52: film. Subsequent electroless metal
Page 53 and 54: 20010024029 Houston Univ., Dept. of
Page 55 and 56: equipment indicate a change in the
Page 57 and 58: interaction, the main gas products
Page 59 and 60: Contract(s)/Grant(s): W-7405-eng-48
Page 61 and 62: for detecting and measuring deviato
Page 63 and 64: work, additional significant effect
Page 65 and 66: 20010026182 Oak Ridge National Lab.
Page 67 and 68: 20010024162 Army Research Lab., Ade
Page 69 and 70: matching funds. MIRSL purchased an
Page 71 and 72: 20010023557 North Dakota State Univ
Page 73 and 74: 20010026217 Princeton Univ., NJ USA
Page 75 and 76: 20010024108 Center for Naval Analys
Page 79 and 80: undertaken to isolated it are descr
Page 83 and 84: non-buoyant axisymmetric jet issuin
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point. The other turbulent problem
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20010024042 Houston Univ., Dept. of
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The research carried out in the Hea
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along the heater surface and depart
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cal transducers. Additionally, the
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tial for its successful commercial
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This project represents a combined
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20010024910 Johns Hopkins Univ., De
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e caused by a non-uniform temperatu
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metric shear cell, employed upon th
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20010024919 Alabama Univ., Huntsvil
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Newtonian fluids in the laboratory,
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Boussinesq convection where due to
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20010024930 Creare, Inc., Hanover,
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Illumination of a space-borne objec
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The hydrodynamics near steadily mov
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to be done is the full coupled syst
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liquid crystal host. Since the ulti
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the inorganic synthesis using press
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when the buoyancy is removed, for e
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20010024956 NASA Ames Research Cent
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2.2-second drop tower at NASA Glenn
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we have examined the dynamical beha
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position of the interface. An oscil
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the first time, non-intrusive, high
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’axial curvature pressure’. A t
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moons when disturbed by low velocit
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particle size was studied. In a den
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colliding drops. The viscous resist
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20010024983 Notre Dame Univ., Physi
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20010024986 TDA Research, Inc., Whe
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drop deposition, using Schiaffino a
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and extended to reduced gravity flo
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from an isolated bubble regime to a
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20010025000 Case Western Reserve Un
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our experimental measurements and w
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sured using a hot film probe flush
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the stationary bubble entrains anot
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we have collaborated on 3D experime
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of the most attractive characterist
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apply either steady shear flow perp
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20010025024 NASA, Washington, DC US
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neously the gamma scattered method
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20010023125 Colorado Univ., Lab. fo
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Contract(s)/Grant(s): F19628-95-C-0
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ics Technology Letters; March 2000;
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The BOREAS RSS-1 team collected sur
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ically corrected; however, files of
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with wavelength bands specific to t
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20010022099 NASA Goddard Space Flig
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within the polygon). There are thre
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A03, Hardcopy; A01, Microfiche Cana
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storms in Africa and smoke plumes f
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Greenland, with the objective of qu
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The BOReal Ecosystem-Atmosphere Stu
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The BOREAS TGB-8 team collected dat
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Report No.(s): NASA/TM-2000-209891/
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The BOREAS TF-10 team collected tow
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cally Active Radiation (FPAR) absor
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tributing to the overall understand
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cal ’tour de force’ allows EPV
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20010023558 Texas Univ., Center for
Page 223 and 224:
the atmospheric concentrations of m
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20010023278 Lembaga Penerbangan dan
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Atmospheric radiation in the infrar
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20010022976 Desert Research Inst.,
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The primary purpose of AASERT Grant
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with only small ice-covered areas r
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Task 2 - abstraction of Medical rec
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non-steroidal activators of the rec
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20010023796 Massachusetts Univ. Med
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20010024166 Chicago Univ., Chicago,
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20010025069 Cleveland Clinic Founda
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Prior to 1994, measurement of tumor
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20010025730 Illinois Univ., Broad o
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the processing for enhancement of s
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strides in detection, diagnosis, an
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20010025763 California Univ., Lawre
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The ability to detect carcinoma cel
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ations found in clinical and geneti
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20010021850 Michigan Univ., Dept. o
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20010021985 National Inst. of Healt
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20010023264 Department of Health an
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on the BBB in rats, researchers not
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navigation method shows an advantag
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ange, and for some combinations of
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consider two specific issues in app
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planning with the Remote Agent expe
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training courses for the CAD tools.
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In this report, we consider the pro
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of the neural network and hence, th
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65 STATISTICS AND PROBABILITY �
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from the Lagrangian of the system.
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The average U-235 neutron total cro
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20010026201 Sandia National Labs.,
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to be 8.5-10.5 degrees which concur
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77 PHYSICS OF ELEMENTARY PARTICLES
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20010026247 Abdus Salam Internation
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Board (Access Board) under the auth
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currently underway or planned durin
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transfer function that would cover
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90 ASTROPHYSICS ��
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strates that as the gyroradius incr
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20010023043 Jet Propulsion Lab., Ca
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climatic variations. This can only
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try), allowing the same samples, in
Page 311 and 312:
This work will describe the Thermal
Page 313 and 314:
20010023068 Tennessee Univ., Dept.
Page 315 and 316:
is crucial to the successful landin
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flat-plate Michelson interferometer
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general public is definitely intere
Page 321 and 322:
Page 323 and 324:
exploration, examine specific optio
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tions of water. Often, due to lower
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With the exploration strategy for M
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necessary to ensure delivery of a s
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Page 333 and 334:
spectral studies to the field, and
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93 SPACE RADIATION ��
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ATMOSPHERIC RADIATION, 163, 205 ATM
Page 339 and 340:
DEW POINT, 165 DIAGNOSIS, 217, 220,
Page 341 and 342:
GRAVITATION, 54, 84, 88, 110, 111,
Page 343 and 344:
MATRIX THEORY, 270 MEASURING INSTRU
Page 345 and 346:
ST-10 Q QUALITY CONTROL, 11, 213 QU
Page 347 and 348:
ST-12 T TARGET RECOGNITION, 265 TAS
Page 349 and 350:
A Abdelguerfi, Mahdi, 252 Abramo, R
Page 351 and 352:
Cledassou, R., 311 Clemmet, J., 306
Page 353 and 354:
Gorelick, N., 294 Gorevan, S. P., 4
Page 355 and 356:
Kupinski, Matthew A., 256 Kuznetz,
Page 357 and 358:
Parks, C. H., 249 Parr, T. P., 38 P
Page 359 and 360:
Swisdak, Michael M., Jr., 37 Szalew
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Scientific and Technical Aerospace Reports Volume 39 April 6, 2001

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