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F/A-18E/F experience, to gain insights into the flow physics associated with wing drop, and to develop methods and analytical tools so that future programs could identify this type of problem before going to flight test. The paper reviews, for the major goals of the AWS Program, the status of the technology before the program began, the program objectives, accomplishments, and impacts. Lessons learned are presented for the benefit of future programs that must assess whether a vehicle will have uncommanded lateral motions before going to flight test. Finally, recommended future research needs are presented in light of the AWS Program experience. Author Wings; Aerodynamic Stalling; Flight Tests; Leading Edges; Flapping 20030031333 NASA Langley Research Center, Hampton, VA, USA Static Aeroelastic Predictions for a Transonic Transport Model Using an Unstructured-Grid Flow Solver Coupled With a Structural Plate Technique Allison, Dennis O.; Cavallo, Peter A.; January 03, 2003; 52 pp.; In English; Original contains black and white illustrations Contract(s)/Grant(s): WU 719-10-40-10 Report No.(s): NASA/TP-2003-212156; L-18027; NAS 1.60:212156; No Copyright; Avail: CASI; A04, Hardcopy An equivalent-plate structural deformation technique was coupled with a steady-state unstructured-grid three-dimensional Euler flow solver and a two-dimensional strip interactive boundary-layer technique. The objective of the research was to assess the extent to which a simple accounting for static model deformations could improve correlations with measured wing pressure distributions and lift coefficients at transonic speeds. Results were computed and compared to test data for a wing-fuselage model of a generic low-wing transonic transport at a transonic cruise condition over a range of Reynolds numbers and dynamic pressures. The deformations significantly improved correlations with measured wing pressure distributions and lift coefficients. This method provided a means of quantifying the role of dynamic pressure in wind-tunnel studies of Reynolds number effects for transonic transport models. Author Aeroelasticity; Unstructured Grids (Mathematics); Three Dimensional Flow; Aerodynamic Coeffıcients; Dynamic Pressure; Pressure Distribution 20030032187 NASA Wallops Flight Center, Wallops Island, VA, USA An Overview of the NASA Sounding Rocket and Balloon Programs Eberspeaker, Philip J.; Smith, Ira S.; [2003]; 1 pp.; In English; ESA Symposium, 2-5 Jun. 2003, Switzerland; No Copyright; Avail: Other Sources; Abstract Only The U.S. National Aeronautics and Space Administration (NASA) Sounding Rockets and Balloon Programs conduct a total of 50 to 60 missions per year in support of the NASA scientific community. These missions support investigations sponsored by NASA’s Offices of Space Science, Life and Microgravity Sciences & Applications, and Earth Science. The Goddard Space Flight Center has management and implementation responsibility for these programs. The NASA Sounding Rockets Program provides the science community with payload development support, environmental testing, launch vehicles, and launch operations from fixed and mobile launch ranges. Sounding rockets continue to provide a cost-effective way to make in situ observations from 50 to 1500 km in the near-earth environment and to uniquely cover the altitude regime between 50 km and 130 km above the Earth’s surface. New technology efforts include GPS payload event triggering, tailored trajectories, new vehicle configuration development to expand current capabilities, and the feasibility assessment of an ultra high altitude sounding rocket vehicle. The NASA Balloon Program continues to make advancements and developments in its capabilities for support of the scientific ballooning community. The Long Duration Balloon (LDB) is capable of providing flight durations in excess of two weeks and has had many successful flights since its development. The NASA Balloon Program is currently engaged in the development of the Ultra Long Duration Balloon (ULDB), which will be capable of providing flight times up to 100-days. Additional development efforts are focusing on ultra high altitude balloons, station keeping techniques and planetary balloon technologies. Author Balloons; NASA Space Programs; Sounding Rockets; General Overviews 3
05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE Includes all stages of design of aircraft and aircraft structures and systems. Also includes aircraft testing, performance, and evaluation, and aircraft and flight simulation technology. For related information see also 18 Spacecraft Design, Testing and Performance; and 39 Structural Mechanics. For land transportation vehicles see 85 Technology Utilization and Surface Transportation. 20030022708 Defence Science and Technology Organisation, Fishermans Bend, Australia Importance of Reliability Assessment to Helicopter Structural Component Fatigue Life Prediction Lombardo, D. C.; Fraser, K. F.; June 2002; 22 pp.; In English Report No.(s): DSTO-TN-0462; DODA-AR-012-522; Copyright; Avail: Other Sources This paper discusses the need for understanding reliability within the context of helicopter structures and presents a case for why such understanding is essential to successfully implementing better usage monitoring programs. Author Fatigue (Materials); Fatigue Life; Helicopters; Reliability Engineering; Reliability Analysis; Performance Prediction; Risk 20030022714 NASA Ames Research Center, Moffett Field, CA, USA Aerodynamic Shape Optimization using an Evolutionary Algorithm Hoist, Terry L.; Pulliam, Thomas H.; January 2003; 32 pp.; In English; No Copyright; Avail: CASI; A03, Hardcopy A method for aerodynamic shape optimization based on an evolutionary algorithm approach is presented and demonstrated. Results are presented for a number of model problems to access the effect of algorithm parameters on convergence efficiency and reliability. A transonic viscous airfoil optimization problem-both single and two-objective variations is used as the basis for a preliminary comparison with an adjoint-gradient optimizer. The evolutionary algorithm is coupled with a transonic full potential flow solver and is used to optimize the inviscid flow about transonic wings including multi-objective and multi-discipline solutions that lead to the generation of pareto fronts. The results indicate that the evolutionary algorithm approach is easy to implement, flexible in application and extremely reliable. Author Algorithms; Shape Optimization; Aerodynamic Configurations; Parameterization 20030025280 NASA Goddard Space Flight Center, Greenbelt, MD, USA Science Goal Driven Observing: A Step Towards Maximizing Science Returns and Spacecraft Autonomy Koratkar, Anuradha; Grosvenor, Sandy; Jones, Jeremy; Memarsadeghi, Nargess; Wolf, Karl; [2002]; 12 pp.; In English; SPIE 2002, 22-28 Aug. 2002, Waikoloa, HI, USA; Original contains black and white illustrations; Copyright; Avail: CASI; A03, Hardcopy In the coming decade, the drive to increase the scientific returns on capital investment and to reduce costs will force automation to be implemented in many of the scientific tasks that have traditionally been manually overseen. Thus, spacecraft autonomy will become an even greater part of mission operations. While recent missions have made great strides in the ability to autonomously monitor and react to changing health and physical status of spacecraft, little progress has been made in responding quickly to science driven events. The new generation of space-based telescopes/observatories will see deeper, with greater clarity, and they will generate data at an unprecedented rate. Yet, while onboard data processing and storage capability will increase rapidly, bandwidth for downloading data will not increase as fast and can become a significant bottleneck and cost of a science program. For observations of inherently variable targets and targets of opportunity, the ability to recognize early if an observation will not meet the science goals of variability or minimum brightness, and react accordingly, can have a major positive impact on the overall scientific returns of an observatory and on its operational costs. If the observatory can reprioritize the schedule to focus on alternate targets, discard uninteresting observations prior to downloading, or download them at a reduced resolution its overall efficiency will be dramatically increased. We are investigating and developing tools for a science goal monitoring (SGM) system. The SGM will have an interface to help capture higher-level science goals from scientists and translate them into a flexible observing strategy that SGM can execute and monitor. SGM will then monitor the incoming data stream and interface with data processing systems to recognize significant events. When an event occurs, the system will use the science goals given it to reprioritize observations, and react appropriately and/or communicate with ground systems - both human and machine - for confirmation and/or further high priority analyses. Author Telescopes; Proving; Operating Costs; Onboard Data Processing; Data Processing Equipment; Data Flow Analysis; Flight Vehicles 4
Page 2 and 3: NASA STI Program ... in Profile Sin
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Page 8 and 9: SCIENTIFIC AND TECHNICAL AEROSPACE
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Page 30 and 31: a long period of time for two NASA
Page 32 and 33: A viewgraph presentation on guidanc
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Page 36 and 37: The specific heater control require
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condensable DEPosits. Both the QCM
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This viewgraph presentation provide
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straining. This reduction was due p
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20030020877 NASA Goddard Space Flig
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There is a significant interest in
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daily measurement campaign that was
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universe, evolution of the SFR at 0
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The influence of the uniform large-
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Northern Hemisphere (NH) ozone flux
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development of new radiative transf
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A new approach is proposed to asses
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dance in the Arabian Sea and Bay of
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Operational Vertical Sounder) Verti
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The Moderate Resolution Imaging Spe
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droughts of the 1930s and 1950s. Th
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Data from the Tropical Rainfall Mea
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Mid-latitude forest ecosystems have
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Understanding functional associatio
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cyanobacterial mats, oxygenic photo
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as CIAO/SDP software developers, we
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Exploration Rover (MER) expeditions
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62 COMPUTER SYSTEMS Includes comput
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data in guard cells leads to the pr
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71 ACOUSTICS Includes sound generat
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20030025751 NASA Langley Research C
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analyzed using quantum kinetic theo
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Science Through ARts (STAR) is an e
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85 TECHNOLOGY UTILIZATION AND SURFA
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20030022798 California Inst. of Tec
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mostly at intermediate velocities.
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close to the spacecraft. We then us
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This source had been a bright persi
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the X-ray properties of the cluster
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We revise the physics of primary el
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size of the gullies in relation to
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92 SOLAR PHYSICS Includes solar act
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society, GISS is part of the Earth
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Initial Operation and Checkout of S
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ATMOSPHERIC EFFECTS The Sun’s Imp
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Effect of a BN Interphase that Debo
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Scalability of a Low-Cost Multi-Ter
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DATA TRANSMISSION Reliable Transpor
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Atomic Data for the K-Vacancy State
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FORMATION FLYING A Nonlinear, Six-D
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HIGH TEMPERATURE Alumina Volatility
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Atomic Data for the K-Vacancy State
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MATRICES (MATHEMATICS) A Time Integ
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NASA’s Sentinels Monitoring Weath
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PACIFIC OCEAN Tropospheric Ozone Ov
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PROVING Experimental Verification o
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SACCHAROMYCES Redundancies in Large
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SOLAR CORONA Are CME ‘interaction
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STANDARDS NASA GSFC Mechanical Engi
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TENSILE STRESS Temperature Dependen
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TYPE 3 BURSTS Energetic Particle Pr
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Rayleigh-Taylor Gravity Waves and Q
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Balagadde, Frederick The Electrical
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Casey, Carolyn A. Systems Engineeri
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Donnelly, Michael Performance of th
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Gliebe, Philip Recent Progress in E
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Hughes, S. P. Primer Vector Optimiz
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Kirk, C. Laurence Effective Frequen
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Luckring, J. M. Transonic Reynolds
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Naasz, Bo J. Integrated Orbit and A
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Raffaelle, Ryne Future Photovoltaic
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Shirron, Peter J. A Cryogenic, Insu
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Urban and Rural Ozone Collect over
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Xu, Yun-Jun Coupled Attitude and Or
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