Issue 11 Volume 43 June 3, 2005 38 Quality Assurance and Reliability 132 39 Structural Mechanics 136 Geosciences 42 Geosciences (General) 138 43 Earth Resources and Remote Sensing 139 44 Energy Production and Conversion 141 45 Environment Pollution 144 46 Geophysics 151 47 Meteorology and Climatology 168 Life Sciences 51 Life Sciences (General) 173 52 Aerospace Medicine 216 53 Behavioral Sciences 217 54 Man/System Technology and Life Support 217 Mathematical and Computer Sciences 59 Mathematical and Computer Sciences (General) 221 60 Computer Operations and Hardware 223 61 Computer Programming and Software 224 62 Computer Systems 236 63 Cybernetics, Artificial Intelligence and Robotics 239 64 Numerical Analysis 244 65 Statistics and Probability 258 66 Systems Analysis and Operations Research 261 67 Theoretical Mathematics 264 Physics 70 Physics (General) 264 71 Acoustics 283 72 Atomic and Molecular Physics 287 73 Nuclear Physics 288 74 Optics 288 75 Plasma Physics 290 76 Solid-State Physics 291 77 Physics of Elementary Particles and Fields 302 Social and Information Sciences 80 Social and Information Sciences (General) 304 81 Administration and Management 305 82 Documentation and Information Science 309 83 Economics and Cost Analysis 318 Space Sciences 88 Space Sciences (General) 319 89 Astronomy 319 90 Astrophysics 322 91 Lunar and Planetary Science and Exploration 325 92 Solar Physics 413 General 99 General 414 Indexes Two indexes are available. You may use the find command under the tools menu while viewing the PDF file for direct match searching on any text string. You may also select either of the two indexes provided for linking to the corresponding document citation from NASA Thesaurus terms and personal author names. Subject Term Index Personal Author Index 02 AERODYNAMICS Includes aerodynamics of flight vehicles, test bodies, airframe components and combinations, wings, and control surfaces. Also includes aerodynamics of rotors, stators, fans, and other elements of turbomachinery. For related information see also 34 Fluid Mechanics and Thermodynamics. 20050173293 Tsentralni Aerogidrodinamicheskii Inst., Zhukovsky, Russia Enhancement of Efficiency of Operation of High-Speed Aircraft Engine Elements by Means of Separation Flow Controlling Guryleva, N. V.; Ivankin, M. A.; Kolesnikov, O. M.; Lavrukhin, G. N.; Merekin, D. V.; Oct. 2003; 3 pp.; In English Report No.(s): AD-A432570; No Copyright; Avail: Defense Technical Information Center (DTIC) Results of investigations of the mechanism of appearance and destruction of separation zones in supersonic gas flows are presented. Methods for controlling separation phenomena were developed to increase the operation efficiency of ducts combustors inlets and outlets of high-speed aircrafts. The main trends of investigations were: 1) Study of deceleration flows in ducts of various shapes with pseudoshock; 2) Development of non-traditional manners of spatial implementation of combustion in supersonic flows; 3) Computational analysis of optimum methods of energy supply in internal flows with separation zones; 4) Control of separation phenomena for increasing efficiency of power plant outlets. The following major results were obtained: For 1st trend: Features of the structure of the non-steady separation in the ducts with deceleration of the supersonic flow in the pseudoshock were determined. Methods for controlling the pseudoshock were developed. Conditions for forming separation zones under interference of various shear layers (vortex jet) generated ahead of the entrance and in ducts with the pseudoshock were studied. For 2nd trend: For the first time in the world practice the gasdynamic stabilizers of combustion were developed. Their principle of operation was based on artificial generation of free-hanging separation zones in the supersonic flow. Successful experimental try-out of some schemes of gasdynamic stabilizers was carried out at the TsAGI’s hypersonic test rig T-131 at M=2.5 - 2.6. They permitted to obtain self-ignition and stable combustion of hydrogen: DTIC Aircraft Engines; Augmentation 20050173296 Moscow State Univ., Russia Burning of the Supersonic Propane-Air Mixture in the Aerodynamic Channel With the Stagnant Zone Shibkov, V. M.; Chernikov, V. A.; Ershov, A. P.; Karachev, A. A.; Konstantinovskij, R. S.; Voskanyan, A. V.; Zlobin, V. V.; Oct. 2003; 11 pp.; In English Report No.(s): AD-A432573; No Copyright; Avail: Defense Technical Information Center (DTIC) In the report the pulsed-periodical discharges created on an external surface of a flat plate being flown around of supersonic airflow and under condition of a stagnant zone located on a wide wall of the aerodynamic channel of rectangular section were investigated. It was show that the surface pulsed-periodical discharge results to ignition beforehand mixed supersonic propane-air fuel in the aerodynamic channel. In experimental conditions the combustion front speed reaches value of v(sub c)=40-45 m/s that well coordinates to the data which was got at investigation of burning into the fire-resistant channel. The kinetical model is working out for finding-out of influence of different channels on ignition of combustible mixtures in supersonic flow. The preliminary calculations demonstrate that at low initial gas temperature the induction time of H2-O2 mixture decreases on some orders of magnitude at taking into account of dissociation active radicals and charged particles. DTIC Aerodynamics; Combustion; Supersonic Flow SCIENTIFIC AND TECHNICAL AEROSPACE REPORTS A Biweekly Publication of the National Aeronautics and Space Administration VOLUME 43, JUNE 3, 2005 1 20050173423 Army Aviation and Missile Command, Redstone Arsenal, AL USA Oblique Wing Aerodynamics McDaniel, Melissa A.; Wilks, Brett L.; Dec. 2004; 3 pp.; In English; Original contains color illustrations Report No.(s): AD-A432841; No Copyright; Avail: Defense Technical Information Center (DTIC) The aerodynamic performance of a wing at an oblique deployment orientation has been found through wind tunnel testing to affect both the lateral and longitudinal stability of a cruise missile. While conventional analysis tools are insufficient for calculating the aerodynamics of an oblique wing, a suitable method has been determined for use with the USAF Missile DATCOM code. Comparisons made between wind tunnel results and Missile DATCOM calculations show that Missile DATCOM can produce a reasonable approximation of the aerodynamics of a wing at oblique deployment angles. DTIC Aerodynamics; Oblique Wings 20050173428 Army Research Lab., Hampton, VA USA Multibody Dynamics Simulation And Experimental Investigation of a Model-Scale Tiltrotor Singleton, Jeffrey D.; Shen, Jinwei; Piatak, David J.; Dec. 2004; 3 pp.; In English; Original contains color illustrations Report No.(s): AD-A432851; No Copyright; Avail: Defense Technical Information Center (DTIC) The objective of this investigation is to develop a multibody analytical simulation model to predict the dynamic response, aeroelastic stability, and blade loading of a soft-inplane tiltrotor wind-tunnel model and correlate that with experimental data. A Joint Vertical Aircraft Task Force is currently developing requirements to meet Army and Navy needs for a heavy lift transport rotorcraft that is expected to include, at a minimum, a 20-ton payload lift capability. Development of soft-inplane tiltrotor technology is beneficial for providing viable lightweight hub design options for this future application. Experimental testing, either in flight testing or with a wind tunnel test article, is becoming prohibitively expensive. Advanced simulation and modeling of these complex tiltrotor hub configurations using multibody dynamics codes may prove to be an alternative to such expensive experimental verifications in the future. The use of multibody dynamics codes to predict and reduce the risk of encountering aeromechanical instabilities and adverse loading situations for a soft-inplane tiltrotor hub design is detailed in this investigation. Comprehensive rotorcraft-based multibody analyses enable simulation and modeling of the rotor system to a high level of detail such that complex mechanics and nonlinear e ects associated with control system geometry and joint free-play may be considered. The influence of these and other nonlinear e ects on the aeromechanical behavior of the tiltrotor model is examined. A parametric study of the design parameters which influence the aeromechanics of the soft-inplane rotor system is also included in this investigation. DTIC Dynamic Response; Helicopters; Scale Models; Simulation; Tilt Rotor Aircraft 20050173484 Academy of Sciences (USSR), Moscow, USSR Numerical Research of Capabilities of Flat Thermochemical Reactor as Element of a Hypersonic Flight Vehicle Heat Protection Vasilyev, V. K.; Korabelnikov, A. V.; Fedotov, A. V.; Oct. 2003; 12 pp.; In English Report No.(s): AD-A432960; No Copyright; Avail: Defense Technical Information Center (DTIC) Thermal protection of heat-stressed surfaces of a hypersonic flight vehicle (HFV) flying in dense layers of atmosphere with hypersonic velocities (M greater than or equal 7) is now one of the most actual problems 1,2. In HFV developed under the ‘Ajax’ concept it is supposed that in the most heat- stressed parts of a skin and engine the chemical catalytic reactors will be placed in which the high endothermic processes of decomposition of initial hydrocarbon fuel with the help of steam and carbon dioxide reforming of methane and its liquid homologues have to be implemented 3. Such organization of the process of thermochemical conversion of hydrocarbons onboard a flight vehicle (FV) will enable 4: - to increase a portion of useful usage of a FV power resource at the expense of a chemical recuperation of heat losses connected as with aerodynamic heating of a skin under the hypersonic flight conditions and power plant operation; - to increase cooling capability of fuel by means of physical-chemical transformations (heating vaporization endothermic reactions) of initial components; - to provide an active thermal protection (ATP) of heat-stressed parts of construction using not only heat removal by means of convection and radiation but also its absorption in a catalytic reaction run directly on the protected surface; - to influence positively on the conditions of a FV airflow-around at the expense of a skin construction cooling; - to obtain in reaction a synthesis gas (mixture of H2 and CO) which will be directed to the combustion chamber for improvement of a fuel combustion characteristics. Thermochemical reactors (TCR) of various kinds used as elements of a HFV thermal protection as usual should decide two problems: DTIC Hypersonic Vehicles; Thermal Protection; Thermochemistry; Thermodynamics 2 03 AIR TRANSPORTATION AND SAFETY Includes passenger and cargo air transport operations; airport ground operations; flight safety and hazards; and aircraft accidents. Systems and hardware specific to ground operations of aircraft and to airport construction are covered in 09 Research and Support Facilities (Air). Air traffic control is covered in 04 Aircraft Communications and Navigation. For related information see also 16 Space Transportation and Safety and 85 Technology Utilization and Surface Transportation. 20050173263 Space and Naval Warfare Systems Center, San Diego, CA USA Transitioning Unmanned Ground Vehicle Research Technologies Pacis, E. B.; Everett, H. R.; Farrington, N.; Kogut, G.; Sights, B.; Kramer, T.; Thompson, M.; Bruemmer, D.; Few, D.; Jan. 2005; 12 pp.; In English; Original contains color illustrations Report No.(s): AD-A432516; No Copyright; Avail: Defense Technical Information Center (DTIC) The Technology Transfer project employs a spiral development process to enhance the functionality and autonomy of mobile systems in the Joint Robotics Program (JRP) Robotic Systems Pool (RSP). The approach is to harvest prior and on-going developments that address the technology needs identified by emergent in-theatre requirements and users of the RSP. The component technologies are evaluated on a transition platform to identify the best features of the different approaches which are then integrated and optimized to work in harmony in a complete solution. The result is an enabling mechanism that continuously capitalizes on state-of-the-art results from the research environment to create a standardized solution that can be easily transitioned to ongoing development programs. This paper focuses on particular research areas, specifically collision avoidance, simultaneous localization and mapping (SLAM), and target-following and describes the results of their combined integration and optimization over the past 12 months. DTIC Unmanned Ground Vehicles 20050173347 Massachusetts Inst. of Tech., Lexington, MA USA Information Theoretic Comparison of MIMO Wireless Communication Receivers in the Presence of Interference Bliss, Daniel W.; Forsythe, Keith W.; Dec. 2004; 30 pp.; In English; Original contains color illustrations Report No.(s): AD-A432690; No Copyright; Avail: Defense Technical Information Center (DTIC) Multiple-input multiple-output (MI MO) wireless communication provides a number of advantages over traditional single-input single-output (SISO) approaches including increased data rates for a given total transmit power and improved robustness to interference. Many of these advantages depend strongly upon the details of the receiver implementation. For practical communication systems a competition between communication performance and computational complexity exists. To reduce computation complexity suboptimal receivers are commonly employed. In this paper the details of a variety of receivers are incorporated into the effects of the channel so that information-theoretic performance bounds can be exploited to evaluate receiver approaches. The performance of these receivers is investigated for a range of environments. Two classes of environments are considered: first channel complexity characterized by the shape of the narrowband channel-matrix singular-value distribution and second external interference Receiver approaches include minimum-mean-squared error minimum interference and multichannel multiuser detection (MCMUD) given various assumed limitations on channel and interference estimation Receiver performance implications are also demonstrated using experimental data. DTIC Information Theory; MIMO (Control Systems); Receivers; Wireless Communication 20050173377 Telcordia Technologies, Inc., Red Bank, NJ USA Iterative Detection for Multi-User MIMO Systems Liberti, Joseph; Martin, Carol C.; Mar. 2004; 25 pp.; In English; Original contains color illustrations Report No.(s): AD-A432744; No Copyright; Avail: Defense Technical Information Center (DTIC) Multi-input multi-output (MIMO) systems can serve as the building blocks for spectrally efficient mobile multi-user tactical wireless systems; however, care must be taken to translate high per-link spectral efficiency into high network throughput. Mobile tactical networks generally have several features that complicate achievement of high multi-user MIMO spectral efficiency, including non-centralized, infrastructure-free operation and operation when all nodes are mobile, as well as requirements to minimize probability of interception and susceptibility to jamming. The paper presents results from both simulations and an extensive over-the-air measurement campaign, which illustrate the key features needed for spectrally efficient multi-user MIMO systems. High MIMO network throughput can be achieved by combining efficient MAC (taking into account MIMO signal processing resources) and transmitter stream control, as well as high performance MIMO signal 3 processing and waveforms that minimize per-link signal-to-interference-and-noise ratio (SINR) requirements leading to effective spectral reuse. Iterative detection schemes provide such high spectral efficiency at low SINRs, achieving performance that approaches the Shannon bound, and provide scalable complexity. These methods are also well suited to operation in multi-user environments, supporting both interference- mitigation and joint detection approaches. The paper provides analysis and experimental results for waveforms and receiver signal processing for Space-Time Bit Interleaved Coded Modulation using multi- carrier waveforms. Results and parameter trades are presented for variations of this approach using List Sphere Detection and Soft-Symbol Cancellation as well as structures based on convolutional codes and turbo codes. DTIC MIMO (Control Systems); Pulse Rate; Scalers 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION Includes all modes of communication with and between aircraft; air navigation systems (satellite and ground based); and air traffic control. For related information see also 06 Avionics and Aircraft Instrumentation, 17 Space Communications, Spacecraft Communications, Command and Tracking, and 32 Communications and Radar. 20050173231 University of West Florida, Pensacola, FL USA Naval Automation and Information Management Technology Pratt, Jerry; Neuhaus, Peter; Bradshaw, Jeffrey; Suri, Niranjan; Allen, James; Galescu, Lucian; Jan. 2003; 16 pp.; In English; Original contains color illustrations Contract(s)/Grant(s): N00014-03-1-0780 Report No.(s): AD-A432433; No Copyright; Avail: Defense Technical Information Center (DTIC) Military uses of unmanned systems are growing. The use of unmanned systems, particularly UAVs, in the campaign in Afghanistan and in Iraqi Freedom operations demonstrated beyond any doubt the effectiveness and viability of unmanned systems in !SR as well as weapons delivery missions. As a result, in future military scenarios, large numbers of unmanned ground, air, underwater, and surface vehicles will work together, coordinated by an ever smaller number of human operators. In order to be operationally efficient, effective and useful, these robots must have competent physical and sensing abilities, must be able to perform complex tasks semi-autonomously, must be able to coordinate with each other, and must ultimately be observable and controllable in a useful and intuitive fashion by human operators. Under the Naval Automation and Information Management Technology Program (NAlMT), The Institute for Human and Machine Cognition (IHMC) of the University of West Florida has conducted advanced research on unmanned systems in the areas of (1) unmanned underwater vehicle mobility, (2) human-agent teamwork and agile computing and (3) mixed initiative human control. Progress made in FYO3 in each of these three areas is described below. DTIC Information Management; Management Systems; Military Technology; Remotely Piloted Vehicles 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. 20050169564 North Carolina State Univ., Raleigh, NC, USA Distributed Actuation and Sensing on an Uninhabited Aerial Vehicle Barnwell, William Garrard; UAV Flight Control Using Distributed Actuation and Sensing; 2003; 120 pp.; In English Contract(s)/Grant(s): NAG1-01069; No Copyright; Avail: CASI; A06, Hardcopy An array of effectors and sensors has been designed, tested and implemented on a Blended Wing Body Uninhabited Aerial Vehicle (UAV). The UAV is modified to serve as a flying, controls research, testbed. This effector/sensor array provides for the dynamic vehicle testing of controller designs and the study of decentralized control techniques. Each wing of the UAV is equipped with 12 distributed effectors that comprise a segmented array of independently actuated, contoured control surfaces. A single pressure sensor is installed near the base of each effector to provide a measure of deflections of the effectors. The UAV wings were tested in the North Carolina State University Subsonic Wind Tunnel and the pressure distribution that result from the deflections of the effectors are characterized. The results of the experiments are used to develop a simple, but 4 accurate, prediction method, such that for any arrangement of the effector array the corresponding pressure distribution can be determined. Numerical analysis using the panel code CMARC verifies this prediction method. Author Subsonic Wind Tunnels; Blended-Wing-Body Configurations; Pilotless Aircraft; Numerical Analysis; Control Systems Design 20050170033 NASA Lewis Research Center, Cleveland, OH, USA, McDonnell-Douglas Helicopter Co., USA, Lucas Western, Inc., USA, Illinois Univ., Chicago, IL, USA Face Gear Technology for Aerospace Power Transmission Progresses [2005]; 2 pp.; In English; No Copyright; Avail: CASI; A01, Hardcopy The use of face gears in an advanced rotorcraft transmission design was first proposed by the McDonnell Douglas Helicopter Company during their contracted effort with the U.S. Army under the Advanced Rotorcraft Transmission (ART) program. Face gears would be used to turn the corner between the horizontal gas turbine engine and the vertical output rotor shaft a function currently done by spiral bevel gears. This novel gearing arrangement would substantially lower the drive system weight partly because a face gear mesh would be used to split the input power between two output gears. However, the use of face gears and their ability to operate successfully at the speeds and loads required for an aerospace environment was unknown. Therefore a proof-of-concept phase with an existing test stand at the NASA Lewis Research Center was pursued. Hardware was designed that could be tested in Lewis’ Spiral Bevel Gear Test Rig. The initial testing indicated that the face gear mesh was a feasible design that could be used at high speeds and load. Surface pitting fatigue was the typical failure mode, and that could lead to tooth fracture. An interim project was conducted to see if slight modifications to the gear tooth geometry or an alternative heat treating process could overcome the surface fatigue problems. From the initial and interim tests, it was apparent that for the surface fatigue problems to be overcome the manufacturing process used for this component would have to be developed to the level used for spiral bevel gears. The current state of the art for face gear manufacturing required using less than optimal gear materials and manufacturing techniques because the surface of the tooth form does not receive final finishing after heat treatment as it does for spiral bevel gears. This resulted in less than desirable surface hardness and manufacturing tolerances. An Advanced Research and Projects Agency (ARPA) Technology Reinvestment Project has been funded to investigate the effects of manufacturing process improvements on the operating characteristics of face gears. The program is being conducted with McDonnell Douglas Helicopter Co., Lucas Western Inc., the University of Illinois at Chicago, and a NASA/U.S. Army team. The goal of the project is develop the grinding process, experimentally verify the improvement in face gear fatigue life, and conduct a full-scale helicopter transmission test. The theory and methodology to grind face gears has been completed, and manufacture of the test hardware is ongoing. Experimental verification on test hardware is scheduled to begin in fiscal 1996. Author Gear Teeth; Rotary Wing Aircraft; Technology Utilization; Transmissions (Machine Elements); Aerospace Systems; Power Transmission 20050170431 General Electric Co., USA First Test of Fan Active Noise Control (ANC) Completed [2005]; 2 pp.; In English; No Copyright; Avail: CASI; A01, Hardcopy With the advent of ultrahigh-bypass engines, the space available for passive acoustic treatment is becoming more limited, whereas noise regulations are becoming more stringent. Active noise control (ANC) holds promise as a solution to this problem. It uses secondary (added) noise sources to reduce or eliminate the offending noise radiation. The first active noise control test on the low-speed fan test bed was a General Electric Company system designed to control either the exhaust or inlet fan tone. This system consists of a ‘ring source,’ an induct array of error microphones, and a control computer. Fan tone noise propagates in a duct in the form of spinning waves. These waves are detected by the microphone array, and the computer identifies their spinning structure. The computer then controls the ‘ring source’ to generate waves that have the same spinning structure and amplitude, but 180 out of phase with the fan noise. This computer generated tone cancels the fan tone before it radiates from the duct and is heard in the far field. The ‘ring source’ used in these tests is a cylindrical array of 16 flat-plate acoustic radiators that are driven by thin piezoceramic sheets bonded to their back surfaces. The resulting source can produce spinning waves up to mode 7 at levels high enough to cancel the fan tone. The control software is flexible enough to work on spinning mode orders from -6 to 6. In this test, the fan was configured to produce a tone of order 6. The complete modal (spinning and radial) structure of the tones was measured with two builtin sets of rotating microphone rakes. These rakes provide a measurement of the system performance independent from the control system error microphones. In addition, the far-field noise was measured with a semicircular array of 28 microphones. This test represents the first in a series of tests that 5 demonstrate different active noise control concepts, each on a progressively more complicated modal structure. The tests are in preparation for a demonstration on a flight-type engine. Author Active Control; Aerodynamic Noise; Fan Blades; Aeroacoustics; Turbofan Engines 20050170640 NASA Dryden Flight Research Center, Edwards, CA, USA Doing Systems Engineering Without Thinking About It at NASA Dryden Flight Research Center Bohn-Meyer, Marta; Kilp, Stephen; Chun, Peggy; Mizukami, Masashi; [2004]; 16 pp.; In English; IEEE Aerospace Conference, 5-12 Mar. 2005, Big Sky, MT, USA; Original contains color illustrations Report No.(s): IEEEAC Paper 1194; No Copyright; Avail: CASI; A03, Hardcopy When asked about his processes in designing a new airplane, Burt Rutan responded: there is always a performance requirement. So I start with the basic physics of an airplane that can get those requirements, and that pretty much sizes an airplane Then I look at the functionality And then I try a lot of different configurations to meet that, and then justify one at a time, throwing them out Typically I’ll have several different configurations But I like to experiment, certainly. I like to see if there are other ways to provide the utility. This kind of thinking engineering as a total systems engineering approach is what is being instilled in all engineers at the NASA Dryden Flight Research Center. Author Systems Engineering; NASA Programs; Research and Development; Flight Tests 20050171017 NASA Lewis Research Center, Cleveland, OH, USA, Department of the Army, USA High-Temperature Magnetic Bearings for Gas Turbine Engines Research and Technology 1995; March 1996; 2 pp.; In English; No Copyright; Avail: CASI; A01, Hardcopy Magnetic bearings are the subject of a new NASA Lewis Research Center and U.S. Army thrust with significant industry participation, and coordination with other Government agencies. The NASA/Army emphasis is on high-temperature applications for future gas turbine engines. Magnetic bearings could increase the reliability and reduce the weight of these engines by eliminating the lubrication system. They could also increase the DN (diameter of the bearing times rpm) limit on engine speed and allow active vibration cancellation systems to be used resulting in a more efficient, ‘more electric’ engine. Finally, the Integrated High-Performance Turbine Engine Technology (IHPTET) Program, a joint Department of Defense/ industry program, identified a need for a hightemperature (as high as 1200 F) magnetic bearing that could be demonstrated in a phase III engine. This magnetic bearing is similar to an electric motor. It has a laminated rotor and stator made of cobalt steel. Wound around the stator are a series of electrical wire coils that form a series of electric magnets around the circumference. The magnets exert a force on the rotor. A probe senses the position of the rotor, and a feedback controller keeps it in the center of the cavity. The engine rotor, bearings, and case form a flexible structure that contains a large number of modes. The bearing feedback controller, which could cause some of these modes to become unstable, could be adapted to varying flight conditions to minimize seal clearances and monitor the health of the system. Cobalt steel has a curie point greater than 1700 F, and copper wire has a melting point beyond that. Therefore, practical limitations associated with the maximum magnetic field strength in the cobalt steel and the stress in the rotating components limit the temperature to about 1200 F. The objective of this effort is to determine the limits in temperature and speed of a magnetic bearing operating in an engine. Our approach is to use our in-house experience in magnets, mechanical components, high-temperature materials, and surface lubrication to build and test a magnetic bearing in both a rig and an engine. Testing will be done at Lewis or through cooperative programs in industrial facilities. Derived from text Gas Turbine Engines; Magnetic Bearings; High Temperature; Engine Design 20050172103 NASA Lewis Research Center, Cleveland, OH, USA, MacNeal-Schwendler Corp., USA MSC/NASTRAN DMAPAlter Used for Closed-Form Static Analysis With Inertia Relief and Displacement-Dependent Loads Research and Technology 1995; March 1996; 1 pp.; In English; No Copyright; Avail: Other Sources; Abstract Only Solving for the displacements of free-free coupled systems acted upon by static loads is a common task in the aerospace industry. Often, these problems are solved by static analysis with inertia relief. This technique allows for a free-free static analysis by balancing the applied loads with the inertia loads generated by the applied loads. For some engineering applications, the displacements of the free-free coupled system induce additional static loads. Hence, the applied loads are equal to the original loads plus the displacement-dependent loads. A launch vehicle being acted upon by an aerodynamic 6 loading can have such applied loads. The final displacements of such systems are commonly determined with iterative solution techniques. Unfortunately, these techniques can be time consuming and labor intensive. Because the coupled system equations for free-free systems with displacement-dependent loads can be written in closed form, it is advantageous to solve for the displacements in this manner. Implementing closed-form equations in static analysis with inertia relief is analogous to implementing transfer functions in dynamic analysis. An MSC/NASTRAN (MacNeal-Schwendler Corporation/NASA Structural Analysis) DMAP (Direct Matrix Abstraction Program) Alter was used to include displacement-dependent loads in static analysis with inertia relief. It efficiently solved a common aerospace problem that typically has been solved with an iterative technique. Author Displacement; Inertia; Nastran; Static Loads; NASA Programs 20050172129 NASA Dryden Flight Research Center, Edwards, CA, USA Deflection-Based Structural Loads Estimation From the Active Aeroelastic Wing F/A-18 Aircraft Lizotte, Andrew M.; Lokos, William A.; May 2005; 27 pp.; In English; 46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, 18-21 Apr. 2005, Austin, TX, USA Contract(s)/Grant(s): WU 723-56-00-SE-PR Report No.(s): NASA/TM-2005-212871; H-2598; No Copyright; Avail: CASI; A03, Hardcopy Traditional techniques in structural load measurement entail the correlation of a known load with strain-gage output from the individual components of a structure or machine. The use of strain gages has proved successful and is considered the standard approach for load measurement. However, remotely measuring aerodynamic loads using deflection measurement systems to determine aeroelastic deformation as a substitute to strain gages may yield lower testing costs while improving aircraft performance through reduced instrumentation weight. This technique was examined using a reliable strain and structural deformation measurement system. The objective of this study was to explore the utility of a deflection-based load estimation, using the active aeroelastic wing F/A-18 aircraft. Calibration data from ground tests performed on the aircraft were used to derive left wing-root and wing-fold bending-moment and torque load equations based on strain gages, however, for this study, point deflections were used to derive deflection-based load equations. Comparisons between the strain-gage and deflection-based methods are presented. Flight data from the phase-1 active aeroelastic wing flight program were used to validate the deflection-based load estimation method. Flight validation revealed a strong bending-moment correlation and slightly weaker torque correlation. Development of current techniques, and future studies are discussed. Author Aeroelasticity; Deflection; Wings; F-18 Aircraft; Aerodynamic Loads 20050173136 Department of Defense, Arlington, VA USA Summary of Reports Issued and Participation on Management Advisory Teams and Special Audit/Evaluation Efforts Mar. 2004; 23 pp.; In English; Original contains color illustrations Report No.(s): AD-A432222; No Copyright; Avail: Defense Technical Information Center (DTIC) This document is a summary of reports issued and participation on Management Advisory Teams and Special Audit/Evaluation efforts. DTIC Acquisition; Finance; Management Planning 20050173137 Naval Postgraduate School, Monterey, CA USA How Will the Indian Military’s Upgrade and Modernization of Its ISR, Precision Strike, and Missile Defense Affect the Stability in South Asia? Dewan, Jay P.; Mar. 2005; 89 pp.; In English; Original contains color illustrations Report No.(s): AD-A432223; No Copyright; Avail: Defense Technical Information Center (DTIC) India has made a concerted effort to upgrade its ISR, precision strike, and missile defense capabilities as it competes with China and Pakistan for regional power. The Phalcon Airborne Warning and Control System, Su-30MKI fighter-bomber aircraft, and S-300PMU surface-to-air missile system are some examples of the new capabilities India is acquiring. I argue that if India continues its military modernization, Pakistan will become more insecure. The increase in the conventional military capabilities gap will likely upset the existing balance of power in South Asia, leading to a regional arms race, lowering the nuclear threshold, and increasing instability in the region. The strategic stability/ tactical instability paradox that exists between two nuclear countries may lead them to engage in ‘small’wars. India’s increasing military capabilities may encourage 7 [...]... mobile transporters; and test chambers and simulators Also includes extraterrestrial bases and supporting equipment For related information see also 09 Research and Support Facilities (Air) 2005 017 1025 NASA Lewis Research Center, Cleveland, OH, USA INTEX Ka-Band Experiment Ground Terminal Research and Technology 19 95; March 19 96; 1 pp.; In English; No Copyright; Avail: CASI; A 01, Hardcopy The INTEX... December 19 96 and will land on Mars on July 4, 19 97 Author Mars Pathfinder; Mars Roving Vehicles; Onboard Equipment; Experimentation 15 LAUNCH VEHICLES AND LAUNCH OPERATIONS Includes all classes of launch vehicles, launch/space vehicle systems, and boosters; and launch operations For related information see also 18 Spacecraft Design, Testing and Performance; and 20 Spacecraft Propulsion and Power 2005 017 315 4... Flights; Preflight Analysis 17 17 SPACE COMMUNICATIONS, SPACECRAFT COMMUNICATIONS, COMMAND AND TRACKING Includes space systems telemetry; space communications networks; astronavigation and guidance; and spacecraft radio blackout For related information see also 04 Aircraft Communications and Navigation; and 32 Communications and Radar 2005 017 1032 NASA Lewis Research Center, Cleveland, OH, USA Low-Complexity,... engine test stands Also includes airport ground equipment and systems For airport ground operations see 03 Air Transportation and Safety For astronautical facilities see 14 Ground Support Systems and Facilities (Space) 2005 017 1029 NASA Lewis Research Center, Cleveland, OH, USA Laser Sheet Flow Visualization Developed for Lewis’ Icing Research Tunnel Research and Technology 19 95; March 19 96; 2 pp.; In... within and outside of NASA Author ACTS; Extremely High Frequencies; Space Communication; Ground Stations 2005 017 1036 NASA Lewis Research Center, Cleveland, OH, USA Mach 6 Integrated Systems Tests of Lewis’ Hypersonic Tunnel Facility Research and Technology 19 95; March 19 96; 2 pp.; In English; No Copyright; Avail: CASI; A 01, Hardcopy A series of 15 integrated systems tests were conducted at the NASA Lewis... Propulsion and Power, 28 Propellants and Fuels, 15 Launch Vehicles and Launch Operations, and 44 Energy Production and Conversion 2005 016 9740 NASA Lewis Research Center, Cleveland, OH, USA Advanced Power Regulator Developed for Spacecraft [2005]; 2 pp.; In English; No Copyright; Avail: CASI; A 01, Hardcopy The majority of new satellites generate electrical power using photovoltaic solar arrays and store... space rescue techniques For related information see also 03 Air Transportation and Safety; 15 Launch Vehicles and Launch Operations; and 18 Spacecraft Design, Testing and Performance For space suits see 54 Man/System Technology and Life Support 2005 016 9563 NASA Stennis Space Center, Stennis Space Center, MS, USA SMARR (Safety and Mission Assurance Readiness Review) Failla, David P.; April 20, 2005; 4... No.(s): SPPT-8600-00 01; No Copyright; Avail: CASI; A 01, Hardcopy This document from the Stennis Space Center Office of Safety and Mission Assurance rates flight preparation elements for Space Shuttle mission STS -11 4 All elements are rated with the status ‘Standard Open Work or Completed’, and marked in green on the document, which contains a Certificate of Flight Readiness for STS -11 4 Author Aerospace Safety;... R and 10 50 psia were obtained with typical test times of 20 to 45 sec Author Hypersonic Wind Tunnels; Systems Integration; Wind Tunnel Tests 2005 017 1038 NASA Lewis Research Center, Cleveland, OH, USA, Jet Propulsion Lab., California Inst of Tech., Pasadena, CA, USA Lewis Mars Pathfinder Microrover Experiments Research and Technology 19 95; March 19 96; 2 pp.; In English; No Copyright; Avail: CASI; A 01, ... flight and manned and unmanned space vehicles, platforms or objects launched into, or assembled in, outer space; and related components and equipment Also includes manufacturing and maintenance of such vehicles or platforms For specific topics in astronautics see categories 13 through 20 For extraterrestrial exploration see 91 Lunar and Planetary Science and Exploration 2005 017 3384 RAND Corp., Santa . Production and Conversion 14 1 45 Environment Pollution 14 4 46 Geophysics 15 1 47 Meteorology and Climatology 16 8 Life Sciences 51 Life Sciences (General) 17 3 52 Aerospace Medicine 216 53 Behavioral. Research and Support Facilities (Air). 2005 017 1025 NASA Lewis Research Center, Cleveland, OH, USA INTEX Ka-Band Experiment Ground Terminal Research and Technology 19 95; March 19 96; 1 pp.; In. Transportation and Safety; 15 Launch Vehicles and Launch Operations; and 18 Spacecraft Design, Testing and Performance. For space suits see 54 Man/System Technology and Life Support. 2005 016 9563 NASA Stennis