nasa scientific and technical aerospace reports phần 1 pdf

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
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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
it to conduct a preventive strike against Pakistan. In such a climate, a regional arms race eventually may lead Pakistan to
establish a ‘hair-trigger’ nuclear posture. India’s effort to achieve a significantly superior conventional military force over
Pakistan paradoxically may reduce Indian security by causing greater instability, and possibly lead to nuclear war. Regional
stability is enhanced to the extent that there is a rough conventional military balance between India and Pakistan.

DTIC
Asia; Bomber Aircraft; Fighter Aircraft; Military Technology; Missile Defense; Stability; Warfare
20050173269 Army Natick Soldier Center, Natick, MA USA
The Pathfinder Raven Small Unmanned Aerial Vehicle
Mawn, Andrew; Tokumaru, Phillip; Dec. 2004; 8 pp.; In English; Original contains color illustrations
Report No.(s): AD-A432526; No Copyright; Avail: Defense Technical Information Center (DTIC)
This paper provides an overview of the development of the Pathfinder Raven Small Unmanned Air Vehicle (SUAV) by
the U.S. Army Natick Soldier Center and AeroVironment, Inc. The concept for this SUAV system was initially explored during
the Military Operations in Urban Terrain (MOUT) Advanced Concept Technology Demonstration (ACTD) and brought to
fruition during the Pathfinder ACTD. The spiral development process, the associated operational requirements and guiding
principles used to quantify vehicle performance, physical characteristics, and methods of operation, are taken from the
conceptual design stage to the current production aircraft. The Pathfinder Raven aircraft has undergone numerous design
refinements and improvements in its evolution from concept to production. The current production Pathfinder Raven SUAV
meets or exceeds the initial design objectives that could be boiled down to ‘do what a Pointer UAV does at half the size, cost,
and weight.’ The production Pathfinder Raven SUAV is currently being used by U.S. Army and USA Special Operations
Command (USSOCOM) forces in combat operations worldwide in the global war on terrorism.
DTIC
Drone Vehicles; Pilotless Aircraft
20050173289 Georgia Inst. of Tech., Arlington, VA USA
Fire Resistant Closed Cell Foams for Aircraft Shelters Technical Review
Vitali, Juan; Beckham, Haskell; Mar. 2004; 48 pp.; In English
Contract(s)/Grant(s): Proj-4347
Report No.(s): AD-A432566; GTRI/EOEML-A7277-01; AFRL-ML-TY-TR-2005-4545; No Copyright; Avail: Defense
Technical Information Center (DTIC)
The objective of the overall effort is to develop a fire resisting closed cell foam with intumescent capabilities in order to
effectively increase fire insulation and enhance safe egress time from aircraft shelters in cases of fire. The present report
addresses the technical review of the state-of-the-art in intumescence matrix components.
DTIC
Fire Prevention; Fires; Foams; Shelters
20050173304 Department of Defense, Arlington, VA USA

Acquisition: Acquisition of the EA-6B Improved Capability III Program
Aug. 2004; 55 pp.; In English
Report No.(s): AD-A432585; IG/DOD-D-2004-113; No Copyright; Avail: Defense Technical Information Center (DTIC)
Who Should Read This Report and Why? Civil service and military managers involved in the management, support, and
oversight of the EA-6B Improved Capability (ICAP) III Program should read this report because it discusses acquisition issues
that must be addressed before the EA-6B ICAP III Program progresses further through the acquisition process. The Services
use the airborne electronic attack capability to suppress and degrade an opposing force’s air defense and communication
systems with airborne electronic jamming before offensive airborne strikes. The Navy’s EA-6B Prowler (EA-6B) is the only
DoD platform that provides the Services with an airborne electronic attack capability and must be able to suppress and degrade
current and future threats through 2015. The EA-6B ICAP III Program will provide the EA-6B aircraft with upgraded
selective-reactive jamming and threat emitter geo-location capabilities. In June 2003, the Assistant Secretary of the Navy
(Research, Development, and Acquisition) approved the program for low-rate initial production. The Program Manager for the
EA-6B (the Program Manager) subsequently awarded the prime contractor, Northrop Grumman Integrated Systems, Bethpage,
New York, a firm-fixedprice modification to the development contract for low-rate initial production of 10 ICAP III system
kits for $102 million. The Navy plans to acquire 35 ICAP III system kits for installation on 35 EA-6B aircraft.As of June 2004,
the ICAP III Program costs consisted of an estimated $335 million in research, development, test and evaluation funds, $458
8
million in procurement funds, and $109 million in operations and support funds for a total program cost of $902 million.
DTIC
Costs; Electronic Aircraft; Jamming; Telecommunication
20050173318 Naval Postgraduate School, Monterey, CA USA
Enhancement of the Daytime Goes-Based Aircraft Icing Potential Algorithm Using MODIS
Alexander, Jeremy B.; Mar. 2005; 106 pp.; In English; Original contains color illustrations
Report No.(s): AD-A432621; No Copyright; Avail: Defense Technical Information Center (DTIC)
In this thesis, a fuzzy logic algorithm is developed for the detection of potential aircraft icing conditions using the
Moderate-Resolution Imaging Spectroradiometer (MODIS). The fuzzy MODIS algorithm is developed in a manner similar to
the cloud mask currently used to process MODIS imagery. The MODIS icing potential detection algorithm uses thresholds
for 8 channels in a series of 12 tests to determine the probability of icing conditions being present within a cloud. The MODIS
algorithm results were compared to results of the GOES icing potential detection algorithm run on MODIS imagery for 4
cases. When compared to positive and icing pilot reports for the cases, the MODIS algorithm identified regions where icing

was encountered more effectively than the GOES algorithm. Furthermore, the use of fuzzy thresholds on MODIS rather than
the hard thresholds of the GOES algorithm allowed for less restrictive coverage of potential icing conditions, making the
MODIS algorithm more reasonable in assessing all cloud regions for icing potential. The results found here are preliminary,
as further statistical analysis with a larger validation dataset would be more effective. Algorithm details are provided in the
appendix for reference.
DTIC
Aircraft Icing; Algorithms; Augmentation; Daytime; Fuzzy Systems; Ice Formation; Imaging Spectrometers; MODIS
(Radiometry); Spectroradiometers
20050173327 Stavatti Military Aerospace, Saint Paul, MN USA
Cold Plasma Cavity Active Stealth Technology
Beskar, Christopher R.; Nov. 2004; 11 pp.; In English; Original contains color illustrations
Report No.(s): AD-A432633; SD-272278-WP; No Copyright; Avail: Defense Technical Information Center (DTIC)
STAVATTI Military Aerospace has undertaken the development of a proprietary mechanism by which to reduce the RCS
of aerospace and surface vehicles. Identified as ‘Cold Plasma Cavity Active Stealth Technology’ by STAVATTI, this
mechanism is appropriate for aircraft/vehicles requiring all-aspect RCS reduction, as well as those destined for export to a
wide variety of allied air forces/militaries as it enables a ‘stealth aircraft/vehicle’ to be reconfigured to a non-stealth
configuration through the removal of critical Line Removable Units (LRUs) responsible for the generation and management
of the cold plasma responsible for electromagnetic attenuation.
DTIC
Cavities; Cold Plasmas; Fighter Aircraft; Radar Cross Sections; Stealth Technology
20050173379 Army Research Lab., Hampton, VA USA
Active-Twist Rotor Control Applications for UAVs
Wilbur, Matthew L.; Wilkie, W. K.; Dec. 2004; 9 pp.; In English; Original contains color illustrations
Report No.(s): AD-A432752; No Copyright; Avail: Defense Technical Information Center (DTIC)
The current state-of-the-art in active-twist rotor control is discussed using representative examples from analytical and
experimental studies, and the application to rotary-wing UAVs is considered. Topics include vibration and noise reduction,
rotor performance improvement, active blade tracking, stability augmentation, and rotor blade de-icing.A review of the current
status of piezoelectric fiber composite actuator technology, the class of piezoelectric actuators implemented in active-twist
rotor systems, is included.
DTIC

Active Control; Noise Reduction; Rotary Wings; Rotors; Stability; Vibration
20050173409 Naval Postgraduate School, Monterey, CA USA
Determining the Fine Structure of the Entrainment Zone in Cloud-Topped Boundary Layers
Horner, Michael S.; Mar. 2005; 93 pp.; In English; Original contains color illustrations
Report No.(s): AD-A432817; No Copyright; Avail: Defense Technical Information Center (DTIC)
The objective of this thesis is to obtain a better understanding of cloud-top entrainment through an in-depth analysis of
9
entrainment-zone structure. In situ aircraft measurements taken during the Atlantic Stratocumulus Transition Experiment
(ASTEX) were used for this purpose. Using data collected from multiple cloud-top penetrations, the presence of an interfacial
layer in-between the top of the cloud mixed-layer and the base of the free atmosphere is identified and consequently defined
as the entrainment zone. The depth of the entrainment zone is on the order of tens of meters, where turbulence and sometimes
cloud droplets are detectable. Inhomogeneous mixing was found to occur within the entrainment zone. Parcels of
inversion-layer air and boundary-layer air are identified within the entrainment zone. Analyses suggest that turbulence
intensity and cloud amount in the entrainment zone vary depending on the distribution of entrainment mixing fraction.
Furthermore, continuous mixing in the entrainment zone appears to dissipate the upper-cloud layer. However, continuous
dissipation of the upper-cloud layer has not been observed. Further study is needed to determine the interaction between
boundary-layer dynamics.
DTIC
Atmospheres; Boundary Layers; Cloud Cover; Cloud Physics; Electronic Aircraft; Entrainment; Fine Structure; Marine
Meteorology
20050173437 Iowa State Univ. of Science and Technology, Ames, IA USA
VR Aided Control of Unmanned Vehicles
Walter, Bryan E.; Knutzon, Jared S.; Sannier, Adrian V.; Oliver, James H.; Dec. 2004; 9 pp.; In English; Original contains
color illustrations
Report No.(s): AD-A432877; No Copyright; Avail: Defense Technical Information Center (DTIC)
A new design for an immersive ground control station is presented that allows operators to monitor and control one or
more semiautonomous unmanned vehicles. This new ground station utilizes a virtual reality visualization of the operational
space and the graphical representation of multiple real time information streams to create a comprehensive immersive
environment designed to significantly enhance an operator’s situational awareness and effectiveness. The environment
simultaneously informs the operator about the position and condition of the vehicles under his or her control while providing

an organizing context for the available information relevant to the engagement. This design is applicable to a range of vehicles
including unmanned aerial vehicles (UAVs) and unmanned ground vehicles (UGVs).
DTIC
Command and Control; Virtual Reality
20050173460 Army Research Lab., Adelphi, MD USA
Acoustic Detection from Aerial Balloon Platform
Reiff, C.; Pham, T.; Scanlon, M.; Noble, J.; Van Landuyt, A.; Petek, J.; Ratches, J.; Dec. 2004; 9 pp.; In English; Original
contains color illustrations
Report No.(s): AD-A432916; No Copyright; Avail: Defense Technical Information Center (DTIC)
The US Army Research Laboratory (ARL) and US Army Night Vision and Electronic Sensors Directorate (NVESD) are
leading the research and development in autonomous sensing and sensor networks for the Networked Sensors for the Future
Force (NSfFF) and Future Combat System (FCS). With the emphasis being shifted to lighter and more mobile forces, ARL
and NVESD have been collaborating and exploring various mobile platforms such as robotic vehicles and aerial platforms
such as unmanned aerial vehicles (UAVs) and balloons. Our most immediate collaboration focuses on the use of acoustic
sensors on small balloons and/or aerostats at several elevations and on the ground with the primary goals of: (i) investigate
the acoustic sensing and detection ranges; (ii) acoustically cue IR imagers and/or video cameras; and (iii) explore the
networking of elevated sensors and ground sensors for NSfFF. In this paper, we only focus on the first goal, the acoustic
detection portion of the collaborative effort.
DTIC
Balloon-Borne Instruments; Balloons; Drone Vehicles; Flying Platforms; Sound Detecting and Ranging
20050173464 University of Central Florida, Orlando, FL USA
Collaborative UAV Exploration of Hostile Environments
Luotsinen, Linus J.; Gonzalez, Avelino J.; Boeloeni, Ladislau; Dec. 2004; 7 pp.; In English; Original contains color
illustrations
Report No.(s): AD-A432922; No Copyright; Avail: Defense Technical Information Center (DTIC)
Unmanned Aerial Vehicles are frequently used for the exploration of a hostile environment. UAVs can be lost or
significantly damaged during the exploration process. Although employing multiple UAVs can increase the chance of success,
10
their efficiency depends on the collaboration strategies used. We present a cooperative exploration strategy for UAVs
controlled by autonomous agents. The agents are sharing information, coordinate their short-term goals and path choices,

while each agent uses state of the art algorithms for its individual path planning and obstacle avoidance. The overall goals are
to minimize the exploration time, avoid damage by sharing information about threats, and be robust to the failures of
individual UAVs. Extensive simulation results prove the validity of the approach and provide ways to determine the optimal
number of UAVs for different exploration tasks.
DTIC
Algorithms; Autonomous Navigation; Combat; Data Systems; Drone Vehicles; Pilotless Aircraft; Surveillance
20050173475 Army Aeromedical Research Lab., Fort Rucker, AL USA
Flexible Display Technologies Do They Have a Role in the Cockpit?
Rash, Clarence E.; Harris, Eric S.; McGilberry, William H.; Mar. 2005; 12 pp.; In English
Report No.(s): AD-A432947; USAARL-2005-07; No Copyright; Avail: CASI;
A03, Hardcopy
The 21st century promises a new ‘holy grail’of display technologies. With the long-promised arrival of the plasma display
allowing ‘hang-on-the-wall?’ television, the display community has moved on to the promise of fully conformable displays,
known as flexible displays. This touted new class of displays is not actually unique in itself but is actually an assortment of
novel subclasses of existing display technologies. These technologies include liquid crystal, light emitting diode (LED) and
electrophoresis. Flexible displays based on these technologies are advertised as thinner (almost paper thin), lighter weight,
stronger (extremely rugged and durable), cheaper, super efficient and conformable, as compared to current rigid, mounted
displays. Currently, organic LED (OLED) and electrophoretic displays are examples of flexible displays that have entered the
commercial market. The aviation community may find these displays highly desirable for cockpit applications. However, care
must taken to ensure that good human factors engineering principles are adhered to in such applications.
DTIC
Cockpits; Display Devices
20050173535 BMH Associates, Inc., Norfolk, VA USA
Air Virtual at Sea (VAST) Platform Stimulation Analysis
Jan. 2005; 22 pp.; In English; Original contains color illustrations
Contract(s)/Grant(s): N00014-04-M-0074
Report No.(s): AD-A433025; No Copyright; Avail: Defense Technical Information Center (DTIC)
Information included in this report is outlined as follows: 1) VAST/LVC integration Concept; 2) VAST/LVC Integration
Architecture; 3) Demonstration Concept; 4) Schedule and Cost; and 5) Engineering Management Topics.
DTIC

Avionics; Flying Platforms; Seas; Stimulation; Training Devices; Virtual Reality; Weapon Systems
07
AIRCRAFT PROPULSION AND POWER
Includes primary propulsion systems and related systems and components, e.g., gas turbine engines, compressors, and fuel systems;
and onboard auxiliary power plants for aircraft. For related information see also 20 Spacecraft Propulsion and Power; 28 Propellants
and Fuels; and 44 Energy Production and Conversion.
20050169930 NASA Lewis Research Center, Cleveland, OH, USA
Effect of Tabs on a Rectangular Nozzle Studied
[2005]; 3 pp.; In English; No Copyright; Avail: CASI;
A01, Hardcopy
In a continuing research program, jets from nozzles of different geometries are being investigated with the aim of
increasing mixing and spreading in those flows. Flow fields from nozzles with elliptic, rectangular, and other more complex
cross-sectional shapes are being studied in comparison to circular nozzles over a wide Mach number range. As noted by
previous researchers, noncircular jets usually spread faster than circular jets. Another technique being investigated to increase
jet spreading even further for a given nozzle is the use of ‘tabs’ to generate vortices. A typical tab is a triangular-shaped
protrusion placed at the nozzle exit, with the base of the triangle touching the nozzle wall and the apex leaning downstream
at 45 to the stream direction. This geometry was determined by a parametric study to produce the optimum effect for a given
area blockage. The tabs can increase jet spreading significantly. The underlying mechanism traces to a pair of counter-rotating
11
streamwise vortices originating from each tab. These vortex pairs persist in the flow; and with the appropriate number and
strength, they can increase spreading.
Author
Nozzle Geometry; Nozzle Design; Supersonic Nozzles; Rectangles; Nozzle Flow; Jet Flow
08
AIRCRAFT STABILITY AND CONTROL
Includes flight dynamics, aircraft handling qualities, piloting, flight controls, and autopilots. For related information see also 05 Aircraft
Design, Testing and Performance and 06 Avionics and Aircraft Instrumentation.
20050173306 Massachusetts Inst. of Tech., Lexington, MA USA
Small Polarimetric Adaptive Array for Airborne GPS Jammer Suppression
Blejer, Dennis; Ngai, Eugene C.; Phuong, Tri T.; Mar. 2004; 6 pp.; In English; Original contains color illustrations

Report No.(s): AD-A432593; No Copyright; Avail: Defense Technical Information Center (DTIC)
MIT Lincoln Laboratory has designed, built, tested, and analyzed a small polarimetric adaptive array for airborne GPS
jammer suppression. The array has 7 channels and is configured as a square array. The array consists of a right-hand circularly
polarized (RHCP) reference element and 3 dual-linearly polarized elements. The rationale for the design was to create a
7-channel array with 1 RHCP reference element that had acceptable levels of mutual coupling and fit within a 7 inch by 7 inch
footprint. The approach taken was to convert 3 of the 4 elements of a 4-element RHCP array to 3 dual-linearly polarized
elements. This modification actually simplifies the construction of the array by eliminating 3 hybrid couplers. This
modification results in up to 6 degrees of freedom for the polarimetric array. The concept of using dual-polarized elements
in an adaptive array was considered by R.T. Compton, Jr. and presented in his text, Adaptive Antennas. He showed that using
dual-polarized elements allows a polarization null to be directed towards an interfering source while receiving a desired signal
that is co-linear with the interferer and the receiver, provided the desired signal and the interfering signal have somewhat
different polarizations. He also showed that using an array with different element patterns can have better performance than
an array of isotropic elements under certain conditions. This paper will concentrate on the measured performance of the small
polarimetric adaptive array. The complex element patterns of the array were measured on a small ground plane in an MIT
Lincoln Laboratory indoor chamber, and a few azimuthal patterns were measured with the array on a Falcon 20 aircraft in the
Patuxent River Chamber.
DTIC
Adaptation; Antenna Arrays; Global Positioning System; Jammers; Polarimetry
09
RESEARCH AND SUPPORT FACILITIES (AIR)
Includes airports, runways, hangars, and aircraft repair and overhaul facilities; wind tunnels, water tunnels, and shock tubes; flight
simulators; and aircraft 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).
20050171029 NASA Lewis Research Center, Cleveland, OH, USA
Laser Sheet Flow Visualization Developed for Lewis’ Icing Research Tunnel
Research and Technology 1995; March 1996; 2 pp.; In English; No Copyright; Avail: CASI;
A01, Hardcopy
A new flow-visualization technique has been developed for use in the NASA Lewis Research Center’s Icing Research
Tunnel (IRT). This technique uses a sheet of light shining across the wind tunnel to illuminate a mist of water droplets in the
air and display any organized flow patterns. Since the IRT already has the special water spray system required for aircraft icing

experiments, no special visualization seeding material is required. The system has been used to visualize the changes in tip
and leading edge vortices caused by ice accretion. Because the IRT’s icing spray is used as part of the visualization technique,
changes in the flow patterns about a wing can be observed and measured during the ice accretion process.
Author
Flow Visualization; Laser Applications; Flow Measurement; Aircraft Icing
12
12
ASTRONAUTICS (GENERAL)
Includes general research topics related to space 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.
20050173384 RAND Corp., Santa Monica, CA USA
USA Air and Space Power in the 21st Century: Strategic Appraisal
Khalilzad, Zalmay; Shapiro, Jeremy; Jan. 2002; 495 pp.; In English
Contract(s)/Grant(s): F49642-01-C-0003
Report No.(s): AD-A432766; RAND/MR-1314; No Copyright; Avail: Defense Technical Information Center (DTIC)
Aerospace power has become the archetypal expression of the U.S. ability to project force in the modern world.
Throughout the world, U.S. aerospace power and thus, the U.S. Air Force (USAF) plays a critical, and often primary, role in
securing U.S. interests, in promoting American values, and in protecting human rights. While the USAF has had significant
success in employing aerospace power in the recent past, emerging trends in international relations, in technology, and in our
own domestic society will create a wide variety of new challenges and new opportunities for U.S. aerospace power. Meeting
these challenges and exploiting these opportunities will require careful planning, wise investments, and thoughtful training,
as well as difficult cultural adaptations within the USAF. This book identifies many of these challenges and opportunities in
a wide variety of issue areas and assesses the degree to which the USAF is prepared to meet them. While the work was carried
out under the auspices of the Strategy and Doctrine program of RAND’s Project AIR FORCE, which is sponsored by the U.S.
Air Force, this volume draws on the expertise of researchers from across RAND in a variety of related disciplines. The primary
audience of this work consists of Air Force leaders and planners, but it should be of interest to others concerned about national
security issues.
DTIC

Aerospace Systems; Education; Military Operations; United States
20050173391 National War Coll., Washington, DC USA
Mahan’s Elements of Sea Power Applied to the Development of Space Power
France, Martin E.; Jan. 2000; 15 pp.; In English
Report No.(s): AD-A432784; No Copyright; Avail: Defense Technical Information Center (DTIC)
As of today, no definitive work on space power theory, comparable to the writings of Clausewitz, Mahan, Mitchell (and
others in their respective fields), is recognized by military theorists. Though most preliminary space power writing in the USA
has centered on space as a logical extension of air power theory (if for no other apparent reason than the organizational
location of most space forces within the U.S. Air Force), such treatment is akin to early Army characterizations of aircraft as
a tool of the artillery or signal corps, restricted to supporting ground operations. While space is certainly a unique operational
setting that has yet to be fully exploited, it shares many characteristics with the sea as an arena for commerce, transport,
observation and conflict. In fact, because of the distances involved, the importance of constantly safeguarding the free flow
of global commerce (e.g. information) in both peace and war, and the more or less permanent basing of key civil and military
assets in orbit, space power, missions and responsibilities have many analogs to the sea. Therefore, one would do well to
consider first the earlier work of sea power theorists, specifically A.T. Mahan, when attempting to develop a theory of space
power and to develop strategies for space control.
DTIC
Seas; Space Missions
20050173472 Science Applications International Corp., San Diego, CA USA
Spacecraft Potential Control
Davis, Victoria A.; Gardner, Barbara M.; Jungeward, G. A.; Mandell, Myron J.; Jul. 2004; 70 pp.; In English; Original
contains color illustrations
Contract(s)/Grant(s): F19628-98-C-0074; Proj-2822
Report No.(s): AD-A432938; SAIC-04/2040; AFRL-VS-HA-TR-2004-1152; No Copyright; Avail: Defense Technical
Information Center (DTIC)
The objective of this contract is to develop improved numeric algorithms for the computation of spacecraft charging on
Earth-orbiting spacecraft. This work is part of the Nascap-2k program, which is a joint program with the Space Environment
13
Effects (SEE) Program at NASA/MSFC. The end result of the program is a user friendly computer code that computes
spacecraft charging in dense and tenuous plasma environments. The primary focus of the SEE Program’s contribution was

funding development of the graphical user interface and user documentation, as well as a related program to measure relevant
material properties.
DTIC
Algorithms; Computerized Simulation; Earth Orbits; Spacecraft Charging; Spacecraft Control
20050173489 Bari Univ., Italy
A Model For Ammonia Solar Thermal Thruster
Capitelli, Mario; Colonna, G.; Dec. 2004; 16 pp.; In English; Original contains color illustrations
Report No.(s): AD-A432967; EOARD-SPC-03-3072; No Copyright; Avail: Defense Technical Information Center (DTIC)
This reports results from a contract tasking University of BARI as follows: The kinetics of nozzle expansion flow is a
topic of large interest- due to its linking with technological applications. Usually one can treat the problem by using two
approaches. The first one is to use complicated 2D fluid dynamics codes with poor kinetics, second one is to use ID nozzle
codes emphasizing the role of chemical kinetics in affecting the whole fluid-chemical problem. The second approach has been
used by our group to characterize simple gases such as H2, N2, 02 and their mixtures. The peculiarity of our approach is to
describe each vibrational level of the molecule as a new species thus avoiding the concept of vibrational temperature. This
approach could be in principle extended to polyatomic molecules even though in this case the state tot state kinetics becomes
a very difficult problem. These concepts will be developed in the present proposal which deals with the characterization of
the kinetics of NH3 through nozzles of different geometries. Our proposal consists of different steps including: 1) development
of a realistic kinetics for ammonia decomposition, 2) development of a realistic macroscopic model for vibrational
deactivation of polyatomic molecules, 3) evaluation of the dependence of rates on vibrational temperature 4) insertion of
points 1-3 in the nozzle equations and 5) examination of results for different nozzle geometries.
DTIC
Ammonia; Propulsion System Configurations; Propulsion System Performance; Solar Energy
13
ASTRODYNAMICS
Includes powered and free flight trajectories; orbital and launching dynamics.
20050173192 Naval Postgraduate School, Monterey, CA USA
Aerosol Scattering Phase Function Retrieval From Polar Orbiting Satellites
Wunder, Daniel P.; Mar. 2005; 97 pp.; In English; Original contains color illustrations
Report No.(s): AD-A432338; No Copyright; Avail: Defense Technical Information Center (DTIC)
The retrieval of an aerosol scattering phase function using a multi-satellite technique is proposed. A total of 33 phase

functions were derived from 18 smoke cases and 15 dust cases. Each case was interrogated using four to nine satellite passes
over the aerosol in a two to four hour time frame. The radiance values for the Red and Near-Infrared (NIR) channels were
combined with backscattering angles to determine the shape of the scattering phase function. The radiance values were input
into the Naval Postgraduate School (NPS) aerosol model to determine optical depths and sample phase functions. A
comparison was made between the actual phase functions retrieved and the NPS model phase functions. It was found that the
phase functions for the smoke cases more closely matched the model phase functions than in the dust cases. Some conclusions
could be drawn about the actual aerosol size and density distribution based on how well it matched the model phase function.
Further analysis is necessary to define the exact size and number of the aerosol particles. Fully understanding the aerosol
composition is crucial in determining its effects on military sensors and impacts to operations.
DTIC
Aerosols; Artificial Satellites; Near Infrared Radiation; Polar Orbits; Scattering; Scattering Functions; Trajectories
14
14
GROUND SUPPORT SYSTEMS AND FACILITIES (SPACE)
Includes launch complexes, research and production facilities; ground support equipment, e.g., 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).
20050171025 NASA Lewis Research Center, Cleveland, OH, USA
INTEX Ka-Band Experiment Ground Terminal
Research and Technology 1995; March 1996; 1 pp.; In English; No Copyright; Avail: CASI;
A01, Hardcopy
The INTEX (interference experiment) Ka-Band Experiment Ground Terminal was developed by NASA Lewis Research
Center’s Advanced Space Communications Laboratory to enable space communications experiments that use the Advanced
Communications Technology Satellite (ACTS). INTEX is used for a wide range of ACTS technology validation and
investigation experiments as well as application demonstrations. It also supports experiments for other organizations within
and outside of NASA.
Author
ACTS; Extremely High Frequencies; Space Communication; Ground Stations
20050171036 NASA Lewis Research Center, Cleveland, OH, USA
Mach 6 Integrated Systems Tests of Lewis’ Hypersonic Tunnel Facility

Research and Technology 1995; March 1996; 2 pp.; In English; No Copyright; Avail: CASI;
A01, Hardcopy
A series of 15 integrated systems tests were conducted at the NASA Lewis Research Center’s Hypersonic Tunnel Facility
(HTF) with test conditions simulating flight up to Mach 6. Facility stagnation conditions up to 3050 R and 1050 psia were
obtained with typical test times of 20 to 45 sec.
Author
Hypersonic Wind Tunnels; Systems Integration; Wind Tunnel Tests
20050171038 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 1995; March 1996; 2 pp.; In English; No Copyright; Avail: CASI;
A01, Hardcopy
The NASA Lewis Research Center has a prime role in the Mars Pathfinder mission, the first in the series of
Discovery-class missions, sponsored by NASA Headquarter’s Office of Space Science. Mars Pathfinder is an engineering
proof-of-concept mission intended to demonstrate the successful deployment of scientific instruments, including a small rover,
on a planetary body and to gain engineering design information for follow-on systems. The mission was launched in December
1996 and will land on Mars on July 4, 1997.
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.
20050173154 Aerospace Corp., El Segundo, CA USA
Life Modeling for Nickel-Hydrogen Batteries in Geosynchronous Satellite Operation
Zimmerman, A. H.; Ang, V. J.; Mar. 2005; 26 pp.; In English; Original contains color illustrations
Contract(s)/Grant(s): FA8802-04-C-0001
Report No.(s): AD-A432256; TR-2005(8555)-2; SMC-TR-05-13; No Copyright; Avail: Defense Technical Information Center
(DTIC)
A model for predicting nickel-hydrogen battery lifetime in LEO applications has been extended to the conditions

encountered in GEO orbiting satellites. The model has been found to accurately reproduce the lifetimes observed from
available accelerated GEO tests, and is also consistent with the existing orbital performance data. The model has been used
to predict how properly designed and operated nickel-hydrogen battery lifetimes should depend on the operating environments
15
and charge control methods typically used in GEO operation. Lifetime is found to be strongly dependent on DOD (particularly
at high operating DOD levels), amount of overcharge, trickle-charge rate, and operating temperature. In addition, the model
finds a strong coupling between these wear-controlling parameters. The model suggests that with an optimized charge control
system and optimized operating conditions, properly designed nickel-hydrogen batteries are capable of reliably providing over
30 years of GEO operation at a DOD of 70-75%. The results also indicate that careful optimization of charge control, operating
temperature, and the maximum required DOD are needed to guarantee reliable operation beyond 10 years.
DTIC
Artificial Satellites; Electric Batteries; Models; Nickel Hydrogen Batteries
20050173262 Naval Postgraduate School, Monterey, CA USA
Fuel Optimal Low Thrust Trajectories for an Asteroid Sample Return Mission
Rust, Jack W.; Mar. 2005; 75 pp.; In English; Original contains color illustrations
Report No.(s): AD-A432514; No Copyright; Avail: Defense Technical Information Center (DTIC)
This thesis explores how an Asteroid Sample Return Mission might make use of solar electric propulsion to send a
spacecraft on a journey to the asteroid 1989ML and back. It examines different trajectories that can be used to get an asteroid
sample return or similar spacecraft to an interplanetary destination and back in the most fuel-efficient manner. While current
plans call for keeping such a spacecraft on the asteroid performing science experiments for approximately 90 days, it is
prudent to inquire how lengthening or shortening this time period may affect mission fuel requirements. Using optimal control
methods, various mission scenarios have been modeled and simulated. The results suggest that the amount of time that the
spacecraft may spend on the asteroid surface can be approximated as a linear function of the available fuel mass. Furthermore,
It can be shown that as maximum available thrust is decreased, the radial component of the optimal thrust vector becomes
more pronounced.
DTIC
Asteroid Missions; Electric Propulsion; Fuel Consumption; Low Thrust; Sample Return Missions; Trajectories
20050173372 Air Force Inst. of Tech., Wright-Patterson AFB, OH USA
Engineering Tools for Variable Stiffness Vibration Suppression and Isolation
Winthrop, Michael F.; Dec. 2004; 211 pp.; In English; Original contains color illustrations

Report No.(s): AD-A432732; AFIT/DS/ENY/05-02; No Copyright; Avail: Defense Technical Information Center (DTIC)
With the advent of smart materials, the concept of semi-active control or dynamic control of stiffness and/or damping for
vibration control of structures has become practical and has seen limited use. Semi-active control has advantages over active
and passive control methods, since it provides almost as much capability as active control while requiring much less power.
Its main disadvantage is its inherent nonlinearity, greatly complicating engineering design. The purpose of this research is to
extend semi-active control vibration isolation tools and methods considering space launch and on-orbit systems.
DTIC
Damping; Nonlinearity; Spacecraft Components; Stiffness; Vibration Isolators
20050173426 Rice Univ., Houston, TX USA
Robust Constrained Optimization Approach to Control Design for International Space Station Centrifuge Rotor Auto
Balancing Control System
Postma, Barry D.; Apr. 2005; 134 pp.; In English; Original contains color illustrations
Report No.(s): AD-A432849; CI04-1040; No Copyright; Avail: Defense Technical Information Center (DTIC)
This thesis discusses application of a robust constrained optimization approach to control design to develop an Auto
Balancing Controller (ABC) for a centrifuge rotor to be implemented on the International Space Station. The design goal is
to minimize a performance objective of the system, while guaranteeing stability and proper performance for a range of
uncertain plants. The performance objective is to minimize the translational response of the centrifuge rotor due to a fixed
worst-case rotor imbalance. The robustness constraints are posed with respect to parametric uncertainty in the plant. The
proposed approach to control design allows for both of these objectives to be handled within the framework of constrained
optimization. The resulting controller achieves acceptable performance and robustness characteristics.
DTIC
Approach Control; Balancing; Centrifuges; International Space Station; Optimization; Rotary Wings
16
20050173461 Air Force Inst. of Tech., Wright-Patterson AFB, OH USA
Impact of a Military Reusable Launch Vehicle on Dominant Maneuver and Focused Logistics
Williams, Nanette M.; Jun. 2000; 58 pp.; In English; Original contains color illustrations
Report No.(s): AD-A432917; AFIT/GMO/ENS/00E-13; No Copyright; Avail: Defense Technical Information Center (DTIC)
This study analyzes the role of a next-generation reusable launch vehicle (RLV) as a potential defense mobility platform
for the future. RLV prototypes offer rapid transportation anywhere on the globe within one hour, with a significant cost
reduction from today’s $10,000 per pound to $1,000 per pound of cargo through space. Unfortunately, extremely complex and

time-consuming infrastructure and ground handling requirements hinder the usefulness of the RLV in a military environment.
Joint Vision 2020 (JV2020) outlines operational concepts that mold warfighting capabilities to achieve full spectrum
dominance in the future. Two of the operational concepts, dominant maneuver and focused logistics, shape mobility
requirements and are used to evaluate the need for a military RLV. This project seeks to answer the question: ‘Could the
next-generation RLV be a viable tool to support JV2020’s operational concepts of dominant maneuver and focused logistics?’
Based on this analysis, current RLV prototypes do not meet the majority of criteria established by JV2020’s dominant
maneuver and focused logistics. However, if a military RLV were designed and produced specifically for defense
transportation, it could potentially overcome the reliability and flexibility obstacles and become a key enabler toward full
spectrum dominance.
DTIC
Launch Vehicles; Logistics; Military Technology; Reusable Launch Vehicles; Transportation
20050173466 University of Central Florida, Orlando, FL USA
A Scale MOUT Facility for Studying Human-Robot Interaction and Control
Jentsch, Florian; Evans, Arthur W., III; Feldman, Moshe; Hoeft, Raegan M.; Rehfeld, Sherri A.; Curtis, Michael; Dec. 2004;
8 pp.; In English; Original contains color illustrations
Contract(s)/Grant(s): DAAD19-01-C-0065; N61339-04-C-0034
Report No.(s): AD-A432924; No Copyright; Avail: Defense Technical Information Center (DTIC)
The Human Research and Engineering Directorate (HRED) of the US Army Research Laboratory (ARL) is involved in
a 5-year program to understand the implications of introducing new technology and procedures to enhance human robotic
interactions (HRI) for the Objective Force Warrior (OFW) and Future Combat Systems (FCS). An important component of
the HRI research is the study of the collaborative requirements for human robotic teams. The Team Performance Laboratory
(TPL) at the University of Central Florida (UCF) has been contracted to conduct research whose purpose is to understand and
enhance the interaction of multiple soldiers with multiple robotic systems that vary in size from small unmanned ground
systems (SUGVs), to medium sized unmanned aerial vehicles (UAVs) , to six-ton armored robot vehicles (ARVs).
DTIC
Military Vehicles; Robot Control; Robotics
16
SPACE TRANSPORTATION AND SAFETY
Includes passenger and cargo space transportation, e.g., shuttle operations; and space rescue techniques. For related information see
also 03Air 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.
20050169563 NASA Stennis Space Center, Stennis Space Center, MS, USA
SMARR (Safety and Mission Assurance Readiness Review)
Failla, David P.; April 20, 2005; 4 pp.; In English; SMARR, 20 Apr. 2005, Stennis Space Center, MS, USA
Report No.(s): SPPT-8600-0001; No Copyright; Avail: CASI;
A01, Hardcopy
This document from the Stennis Space Center Office of Safety and Mission Assurance rates flight preparation elements
for Space Shuttle mission STS-114. 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-114.
Author
Aerospace Safety; Flight Safety; Safety Factors; Space Shuttles; Space Transportation System 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.
20050171032 NASA Lewis Research Center, Cleveland, OH, USA
Low-Complexity, Digital Encoder/Modulator Developed for High-Data-Rate Satellite B-ISDN Applications
Research and Technology 1995; March 1996; 2 pp.; In English; No Copyright; Avail: CASI;
A01, Hardcopy
The Space Electronics Division at the NASA Lewis Research Center is developing advanced electronic technologies for
the space communications and remote sensing systems of tomorrow. As part of the continuing effort to advance the
state-of-the-art in satellite communications and remote sensing systems, Lewis developed a low-cost, modular, programmable,
and reconfigurable all-digital encoder-modulator (DEM) for medium- to high-data-rate radiofrequency communication links.
The DEM is particularly well suited to high-data-rate downlinks to ground terminals or direct data downlinks from near-Earth
science platforms. It can support data rates up to 250 megabits per second (Mbps) and several modulation schemes, including
the traditional binary phase-shift keying (BPSK) and quadrature phase-shift keying (QPSK) modes, as well as higher order
schemes such as 8 phase-shift keying (8PSK) and 16 quadrature amplitude modulation (16QAM). The DEM architecture also
can precompensate for channel disturbances and alleviate amplitude degradations caused by nonlinear transponder
characteristics.

Author
Spacecraft Electronic Equipment; Coders; Satellite Communication
18
SPACECRAFT DESIGN, TESTING AND PERFORMANCE
Includes satellites; space platforms; space stations; spacecraft systems and components such as thermal and environmental controls;
and spacecraft control and stability characteristics. For life support systems see 54 Man/System Technology and Life Support. For
related information see also 05 Aircraft Design, Testing and Performance; 39 Structural Mechanics ; and 16 Space Transportation and
Safety.
20050169874 NASA, Washington, DC, USA
Beyond the Baseline: Proceedings of the Space Station Evolution Symposium, Volume 2, Part 2, Space Station Freedom
Advanced Development Program
May 1990; 344 pp.; In English; First Annual Space Station Evolution Symposium: Beyond the Baseline, 6-8 Feb. 1990,
League City, TX, USA
Contract(s)/Grant(s): UPN 488-00-00
Report No.(s): NASA-CP-10044-Vol-2-PT-2; S-606-Vol-2-Pt-2; No Copyright; Avail: CASI;
A15, Hardcopy
This report contains the individual presentations delivered at the Space Station Evolution Symposium in League City,
Texas on February 6, 7, 8, 1990. Personnel responsible for Advanced Systems Studies and Advanced Development within the
Space Station Freedom program reported on the results of their work to date. Systems Studies presentations focused on
identifying the baseline design provisions (hooks and scars) necessary to enable evolution of the facility to support changing
space policy and anticipated user needs. Also emphasized were evolution configuration and operations concepts including
on-orbit processing of space transfer vehicles. Advanced Development task managers discussed transitioning advanced
technologies to the baseline program, including those near-term technologies which will enhance the safety and productivity
of the crew and the reliability of station systems. Special emphasis was placed on applying advanced automation technology
to ground and flight systems. This publication consists of two volumes. Volume 1 contains the results of the advanced system
studies with the emphasis on reference evolution configurations, system design requirements and accommodations, and
long-range technology projections. Volume 2 reports on advanced development tasks within the Transition Definition
Program. Products of these tasks include: engineering fidelity demonstrations and evaluations on Station development testbeds
and Shuttle-based flight experiments; detailed requirements and performance specifications which address advanced
technology implementation issues; and mature applications and the tools required for the development, implementation, and

support of advanced technology within the Space Station Freedom Program.
Author (revised)
Space Station Freedom; Aerospace Systems; Spacecraft Design; Systems Engineering; Automation
18
20050173425 Army Aviation and Missile Command, Redstone Arsenal, AL USA
Non-Line-Of-Sight Launch System - A Lethal Combination
Haynes, Greg; Hyman, Elizabeth; Dec. 2004; 3 pp.; In English; Original contains color illustrations
Report No.(s): AD-A432847; No Copyright; Avail: Defense Technical Information Center (DTIC)
The Non-Line-of-Sight Launch System (NLOS-LS) will provide enabling lethality for the Army’s Future Combat System
(FCS). The NLOS-LS, one of 19 FCS Core Systems, will consist of a family of missiles and a highly deployable,
platform-independent Container Launch Unit (C/LU) with self-contained tactical fire control electronics and software for
remote and unmanned operations.
DTIC
Launching; Line of Sight; Missiles
19
SPACECRAFT INSTRUMENTATION AND ASTRIONICS
Includes the design, manufacture, or use of devices for the purpose of measuring, detecting, controlling, computing, recording, or
processing data related to the operation of space vehicles or platforms. For related information see also 06 Avionics and Aircraft
Instrumentation; for spaceborne instruments not integral to the vehicle itself see 35 Instrumentation and Photography; for spaceborne
telescopes and other astronomical instruments see 89 Astronomy.
20050169831 Jet Propulsion Lab., California Inst. of Tech., Pasadena, CA, USA
Monitoring Floods with NASA’s ST6 Autonomous Sciencecraft Experiment: Implications on Planetary Exploration
Ip, Felipe; Dohm, J. M.; Baker, V. R.; Castano, B.; Chien, S.; Cichy, B.; Davies, A. G.; Doggett, T.; Greeley, R.; Sherwood,
R.; Lunar and Planetary Science XXXVI, Part 9; [2005]; 2 pp.; In English; See also 20050169816; Original contains color
illustrations; Copyright; Avail: CASI;
A01, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent
document
NASA’s New Millennium Program (NMP) Autonomous Sciencecraft Experiment (ASE) [1-3] has been successfully
demonstrated in Earth-orbit. NASA has identified the development of an autonomously operating spacecraft as a necessity for
an expanded program of missions exploring the Solar System. The versatile ASE spacecraft command and control, image

formation, and science processing software was uploaded to the Earth Observer 1 (EO-1) spacecraft in early 2004 and has been
undergoing onboard testing since May 2004 for the near real-time detection of surface modification related to transient
geological and hydrological processes such as volcanism [4], ice formation and retreat [5], and flooding [6]. Space autonomy
technology developed as part of ASE creates the new capability to autonomously detect, assess, react to, and monitor dynamic
events such as flooding. Part of the challenge has been the difficulty to observe flooding in real time at sufficient temporal
resolutions; more importantly, it is the large spatial extent of most drainage networks coupled with the size of the data sets
necessary to be downlinked from satellites that make it difficult to monitor flooding from space. Below is a description of the
algorithms (referred to as ASE Flood water Classifiers) used in tandem with the Hyperion spectrometer instrument on EO-1
to identify flooding and some of the test results.
Derived from text
Space Exploration; Spacecraft Control; Aerospace Engineering; Floods; Image Processing; Real Time Operation
20
SPACECRAFT PROPULSION AND POWER
Includes main propulsion systems and components, e.g., rocket engines; and spacecraft auxiliary power sources. For related
information see also 07 Aircraft Propulsion and Power, 28 Propellants and Fuels, 15 Launch Vehicles and Launch Operations, and 44
Energy Production and Conversion.
20050169740 NASA Lewis Research Center, Cleveland, OH, USA
Advanced Power Regulator Developed for Spacecraft
[2005]; 2 pp.; In English; No Copyright; Avail: CASI;
A01, Hardcopy
The majority of new satellites generate electrical power using photovoltaic solar arrays and store energy in batteries for
use during eclipse periods. Careful regulation of battery charging during insolation can greatly increase the expected lifetime
of the satellite. The battery charge regulator is usually custom designed for each satellite and its specific mission. Economic
competition in the small satellite market requires battery charge regulators that are lightweight, efficient, inexpensive, and
modular enough to be used in a wide variety of satellites. A new battery charge regulator topology has been developed at the
19
NASA Lewis Research Center to address these needs. The new regulator topology uses industry-standard dc-dc converters and
a unique interconnection to provide size, weight, efficiency, fault tolerance, and modularity benefits over existing systems. A
transformer-isolated buck converter is connected such that the high input line is connected in series with the output. This
‘bypass connection’ biases the converter’s output onto the solar array voltage. Because of this biasing, the converter only

processes the fraction of power necessary to charge the battery above the solar array voltage. Likewise, the same converter
hookup can be used to regulate the battery output to the spacecraft power bus with similar fractional power processing. The
advantages of this scheme are: 1) Because only a fraction of the power is processed through the dc-dc converter, the single-
stage conversion efficiency is 94 to 98 percent; 2) Costly, high-efficiency dc-dc converters are not necessary for high
end-to-end system efficiency; 3) The system is highly fault tolerant because the bypass connection will still deliver power if
the dc-dc converter fails; and 4) The converters can easily be connected in parallel, allowing higher power systems to be built
from a common building block. This new technology will be spaceflight tested in the Photovoltaic Regulator Kit Experiment
(PRKE) on TRW’s Small Spacecraft Technology Initiative (SSTI) satellite scheduled for launch in 1996. This experiment uses
commercial dc-dc converters (28 to 15 Vdc) and additional control circuitry to regulate current to a battery load. The 60-W,
87- percent efficiency converters can control 180 W of power at an efficiency of 94 percent in the new configuration. The
power density of the Photovoltaic Regulator Kit Experiment is about 200 W/kg.
Author
Power Effıciency; Regulators; Small Satellite Technology; Electric Power
20050170454 NASA Lewis Research Center, Cleveland, OH, USA
High-Aspect-Ratio Cooling Channel Concept Tested in Lewis’ Rocket Engine Test Facility
1995; 2 pp.; In English; No Copyright; Avail: CASI;
A01, Hardcopy
Rocket combustion chamber walls are exposed to the high-temperature environment caused by the combustion of
propellants. Even with the walls actively cooled by the fuel, the hot gases can deteriorate the walls severely and limit any
possibility for reusing the combustion chamber. For many years, the NASA Lewis Research Center has performed subscale
investigations of potential improved cooling concepts to extend the life and reliability of the combustion chamber. Results
from previous subscale tests have shown that, by increasing the coolant channel height-to-width aspect ratio, the rocket
combustion chamber hot gas side wall temperature can be reduced by as much as 28 percent, without an increase in the coolant
pressure drop. Recently, a series of experiments were completed in Lewis’ Rocket Engine Test Facility (RETF) to validate the
benefits of high aspect ratio cooling channels with a high-pressure, contoured rocket combustion chamber.
Author
Liquid Propellant Rocket Engines; Engine Tests; Engine Parts; Engine Coolants
20050172127 NASA Lewis Research Center, Cleveland, OH, USA
Advanced Power Regulator Developed for Spacecraft
Research and Technology 1995; March 1996; 2 pp.; In English; No Copyright; Avail: CASI;

A01, Hardcopy
The majority of new satellites generate electrical power using photovoltaic solar arrays and store energy in batteries for
use during eclipse periods. Careful regulation of battery charging during insolation can greatly increase the expected lifetime
of the satellite. The battery charge regulator is usually custom designed for each satellite and its specific mission. Economic
competition in the small satellite market requires battery charge regulators that are lightweight, efficient, inexpensive, and
modular enough to be used in a wide variety of satellites. A new battery charge regulator topology has been developed at the
NASA Lewis Research Center to address these needs. The new regulator topology uses industry-standard dc-dc converters and
a unique interconnection to provide size, weight, efficiency, fault tolerance, and modularity benefits over existing systems. A
transformer-isolated buck converter is connected such that the high input line is connected in series with the output. This
‘bypass connection’ biases the converter’s output onto the solar array voltage. Because of this biasing, the converter only
processes the fraction of power necessary to charge the battery above the solar array voltage. Likewise, the same converter
hookup can be used to regulate the battery output to the spacecraft power bus with similar fractional power processing.
Author
Voltage Regulators; Electric Batteries; Battery Chargers; Spacecraft Power Supplies; Photovoltaic Cells
20050173427 Army Research Lab., Aberdeen Proving Ground, MD USA
Development of Advanced Rocket Engine Technology for Precision Guided Missiles
Nusca, Michael J.; Michaels, R. S.; Dec. 2004; 9 pp.; In English; Original contains color illustrations
Report No.(s): AD-A432850; No Copyright; Avail: Defense Technical Information Center (DTIC)
20
The Army is developing hypergolic, liquid and gelled bipropellants for a small, selectable-thrust, liquid rocket engine
(LRE) that can power tactical missiles for both current and future combat systems. The use of gel propellants brings the
advantages of selectable thrust and the promise of small engine size but also introduces new challenges in combustion control.
One of these challenges is the efficient mixing of gelled oxidizer and fuel to obtain maximum performance from the LRE
combustor without increasing the size of the engine. The Army’s impinging stream vortex engine, ISVE, offers an efficient
alternative to increasing the combustion chamber volume of a LRE and has already generated excellent performance test data.
Since the ISVE is a new concept, analytical models that relate engine performance to engine design parameters are just
beginning to emerge. In order to fully exploit the performance that have been realized for the ISVE, it is desirable to
understand the underlying flow physics of the engine. This paper describes the Army s effort to use multidimensional,
multiphase computational fluid dynamics, combined with high-performance computers to generate simulations of the ISVE
that reveal combustion patterns as well as predict chamber pressure and thrust levels for the engine. The goal is to utilize this

computational tool to optimize the ISVE performance for a host of strategic Army missions.
DTIC
Liquid Propellant Rocket Engines; Missiles; Rocket Engines
23
CHEMISTRY AND MATERIALS (GENERAL)
Includes general research topics related to the composition, properties, structure, and use of chemical compounds and materials as they
relate to aircraft, launch vehicles, and spacecraft. For specific topics in chemistry and materials see categories 25 through 29. For
astrochemistry see category 90 Astrophysics.
20050169742 Missouri Univ., Rolla, MO, USA
Low Temperature Cathode Supported Electrolytes. Report for April 1, 2001-September 30, 2001
Anderson, H. U.; Huebner, W.; 2001; 156 pp.; In English
Report No.(s): DE2004-834069; No Copyright; Avail: Department of Energy Information Bridge
This project has three main goals: Thin Films Studies, Preparation of Graded Porous Substrates and Basic Electrical
Characterization and testing of Planar Single Cells. In this portion of study we have focused on producing YSZ films on porous
LSM substrates. When using the polymer precursor there are a number of obstacles to overcome in order to form dense
electrolyte layers on porous substrates (cathode or anode). Probably the most difficult problems are: (1) Extreme penetration
of the polymer into the substrate must be prevented. (2) Shrinkage cracking must be avoided. (3) Film thickness in the 1 to
5(micro)m range must be achieved. We have demonstrated that cracking due to shrinkage involved during the elimination of
solvents and organic matter and densification of the remaining oxide is not a problem as long as the resulting oxide film is
\h (approx) 0.15 (micro)m in thickness. We have also shown that we can make thicker films by making multiple depositions
if the substrate is smooth (roughness (le) 0.1 (micro)m) and contains no surface pores \g 0.2 (micro)m.
NTIS
Yttrium Oxides; Zirconium Oxides; Cathodes; Annealing
20050169792 California Univ., Lawrence Berkeley National Lab., Berkeley, CA, USA
Surface Engineering of Glazing Materials and Structures Using Plasma Processes
Anders, A.; Monteiro, O. R.; 2004; 10 pp.; In English
Report No.(s): DE2004-834933; No Copyright; Avail: Department of Energy Information Bridge
A variety of coatings is commercially produced on a very large scale, including transparent conducting oxides and
multi-layer silver-based low-emissivity and solar control coatings. A very brief review of materials and manufacturing process
is presented and illustrated by ultrathin silver films and chevron copper films. Understanding the close relation between

manufacturing processes and bulk and surface properties of materials is crucial for film growth and self-assembly processes.
NTIS
Metal Films; Plasmas (Physics); Surface Properties; Thin Films; Glazes
20050169847 California Univ., Lawrence Berkeley National Lab., Berkeley, CA, USA, Leipzig Univ., German Democratic
Republic, National Renewable Energy Lab., Golden, CO, Argonne National Lab., IL
Distribution and Chemical State of Cu-rich Clusters in Silicon
Buonassisi, T.; Istratov, A. A.; Weber, E. R.; Marcus, M. A.; Heuer, M.; Aug. 2004; 12 pp.; In English
Report No.(s): DE2004-15009893; NREL/CP-520-36748; No Copyright; Avail: Department of Energy Information Bridge
21
The chemical state and distribution of Cu-rich clusters were determined in four different silicon-based materials with
varying contamination pathways and degrees of oxygen concentration, including as-grown multicrystalline silicon. In all four
samples, Cu3Si was the only chemical state observed. Cu3Si clusters were observed at structural defects within all four
materials; XBIC measurements revealed that the presence of Cu3Si corresponds to increased recombination activity. Oxidized
Cu compounds are not likely to form in silicon. The +1 eV edge shift in the -XAS absorption spectrum of Cu3Si relative to
Cu metal is believed to be an indication of a degree of covalent bonding between Cu atoms and their silicon neighbors.
NTIS
Copper; Metal Clusters; Oxygen; Silicon
20050169853 National Renewable Energy Lab., Golden, CO
Commercial Status of the PV Industry in 2004-Identifying Important and Unimportant Factors
von Roedern, B.; Aug. 2004; 12 pp.; In English
Report No.(s): DE2004-15009891; NREL/CP-520-36681; No Copyright; Avail: Department of Energy Information Bridge
This paper reviews the current status of the commercial PV Industry. It assesses the current status of commercially
available modules, most of which use silicon wafers or ribbons. My analysis will show that the choice of Si wafers or
substrates, once deemed to be the most important aspect, ended up making only negligible differences for commercial
products, as long as cells are prepared by diffusion and screen printing. I will also address the prospects and requirements for
both next generation thin-film modules and super-high (\g20%) efficient commercial crystalline Si cells. It is shown that
traditional recombination loss analyses provide a poor tool for understanding limitations of cell and module performance,
because those analytical schemes ignore dominating interactions between different loss mechanisms (e.g., of surface and bulk
recombination).
NTIS

Commerce; Polymers
20050169869 Organisatie voor Toegepast Natuurwetenschappelijk Onderzoek, Rijswijk, Netherlands, Netherlands School
for Advanced Studies in Construction, Delft, Netherlands
HERON, Volume 48, No. 4, 2003
Sluys, L. J.; 2003; 72 pp.; In English
Report No.(s): PB2005-102997; No Copyright; Avail: CASI;
A04, Hardcopy
Contents include the following: Three-dimensional microstructure simulation model of cement based materials;
Ultrasonic underside inspection for fatigue cracks in the deck plate of a steel orthotropic bridge deck; and Measuring spatial
correlation of soil properties.
NTIS
Three Dimensional Models; Microstructure; Metal Fatigue
20050169882 Missouri Univ., Rolla, MO, USA
Low Temperature Cathode Supported Electrolytes
Anderson, H. U.; 2004; 48 pp.; In English
Report No.(s): DE2004-834065; No Copyright; Avail: Department of Energy Information Bridge
This project has three main goals: Thin Films Studies, Preparation of Graded Porous Substrates and Basic Electrical
Characterization and Testing of Planar Single Cells. During this time period substantial progress has been made in developing
low temperature deposition techniques to produce dense, nanocrystalline yttrium-stabilized zirconia films on both dense oxide
and polymer substrates. Progress has been made in the preparation and characterization of thin electrolytes and porous LSM
substrates. Both of these tasks are essentially on or ahead of schedule. In our proposal, we suggested that the ZrO(sub 2)/Sc
system needed to be considered as a candidate as a thin electrolyte. This was because microcrystalline ZrO(sub 2)/Sc has a
significantly higher ionic conductivity than YSZ, particularly at the lower temperatures. As a result, some 0.5 micron thick film
of ZrO(sub 2)/16% Sc on an alumina substrate (grain size 20nm) was prepared and the electrical conductivity measured as
a function of temperature and oxygen activity.
NTIS
Cathodes; Electrolytes; Thin Films
22