NASA 1991 SBIR Phase 1 Solicitation

Project Title:

Compressor Stall Avoidance and Alleviation

01.03-0333
910417
Compressor Stall Avoidance and Alleviation
Scientific Research Associates, Inc.
P.O. Box 1058
Glastonbury
CT
06033
John P.
Kreskovsky
203-659-0333
LeRC
NAS3-26334
005

01.03-0333
910417

Abstract:

Compressor Stall Avoidance and Alleviation
This project addresses development of a system for avoiding and controlling compression
system instabilities in gas turbine engines. Phase I will assess the feasibility
of analyzing engine data to identify a stall precursor in the time scales required
for real-time corrective action. The precursor is a growing small-amplitude traveling
wave. When no precursor is identified, a backup stall detection system and active
control system would be used. Phase I will include a feasibility assessment, development
of real-time software, demonstration of the procedure on existing data for stall
without inlet distortion, and a plan for high-speed component testing. Phase II will
develop the hardware and software for stall avoidance and demonstrate and evaluate
the innovation through an existing component test program. The project will demonstrate
that real-time, stall precursor detection and active control can be used for stall
avoidance to significantly improve engine operability.
A detection/control system for use in avoiding compressor instabilities will significantly
reduce current compressor stall margins and requirements thereby providing a important
gas-turbine technology that will be marketed to gas-turbine manufacturers. The signal
analysis technology will be marketed for other applications.
compressor instability, compressor stall, precursor, real-time, software

Project Title:

Turbomachinery Temperature Measurements Using an Oxygen-Laser-Induced Fluorescence

01.03-9500
911809
Turbomachinery Temperature Measurements Using an Oxygen-Laser-Induced Fluorescence
Aerodyne Research, Inc.
45 Manning Rd
Billerica
MA
01821
Kurt D.
Annen
508-663-9500
LeRC
NAS3-26600
007

01.03-9500
911809

Abstract:

Turbomachinery Temperature Measurements Using an Oxygen-Laser-Induced Fluorescence
Recent progress in designing advanced turbomachinery includes the use of numerical
models of compressors, turbines, and combustors to guide new designs. However, further
advancements in the accuracy of numerical models are needed. Improvements in these
models will depend significantly on the availability of quality experimental data
against which the models can be judged. Velocity data currently being acquired in
compressor and turbine test facilities needs to be accompanied by temperature measurement
to improve the utilization of the data by numerical modelers and to allow the determination
of the heat transfer coefficient and Stanton number from heat flux measurements.
This project will develop a diagnostic tool using 02 laser-induced fluorescent (LIF)
and 02 Raman scattering to perform linear-imaging gas temperature measurements in
turbomachinery. The ratio of the 02 LIF signal to the 02 Raman signal is a function
of temperature only, and is independent of the laser power and the cleanliness of
the optics. Seeding is not required. Single pulse measurements of the temperature
profile can be performed with good precision. Phase I will determine the optimum
laser excitation wavelengths for measurements in compressor and turbine test facilities.
The temperature sensitivity of the technique will be measured and compared with theoretical
predictions. A system for turbomachinery applications will be designed and the accuracy
and precision of the temperature measurement system will be calculated.
The turbine temperature measurement system will have commercial applications for
temperature and heat transfer coefficient measurements in turbomachinery test facilities
of jet engine and stationary power turbine manufactures.
turbomachinery, 02 LIF, 02 Raman, temperature diagnostic

Project Title:

Advanced Photochemical Techniques for Relight and Combustion Enhancement of Supersonic

01.04-7970
911526
Advanced Photochemical Techniques for Relight and Combustion Enhancement of Supersonic
Transport Aircraft Systems
ML Energia, Inc.
P.O. Box 1468
Princeton
NJ
08542
Moshe
Lavid
609-799-7970
LeRC
NAS3-26331
008

01.04-7970
911526

Abstract:

Advanced Photochemical Techniques for Relight and Combustion Enhancement of Supersonic
Transport Aircraft Systems
Successful operation of future supersonic aircraft propulsion systems depends on
the attainment of significant advances in combustion technology. The conditions of
high flight-speed and high altitudes cause severe strains on ignition reliability,
stability, and overall combustion efficiency. A novel photochemical technique to
alleviate these problems and selectively irradiate combustion species will be developed.
The ensuing photodissociative reactions generate highly reactive radicals that modify
the gas-phase kinetics and lead to ignition and enhancement via chain-branching paths.
The overall objective of Phase I will be to determine, experimentally, the feasibility
of using this technique to obtain reliable relight of Jet A fuel. Specific tasks
in this effort include investigating minimum ignition energy, power requirements,
flow conditions, radiant frequency, and reliability. The effect of this technique
on ignition-delay-time may also be investigated.
This innovation might lead to a breakthrough in gas turbine combustion technology
by substantially improving the performance of engines to extend the range and speed
of supersonic aircraft for commercial and military applications.
relight, radiative ignition, ignition-delay-time, combustion enhancement, supersonic
transport (SST), photochemical dissociation

Project Title:

Fuzzy Grid Methods for Computational Fluid Dynamics

02.01-1515
910919
Fuzzy Grid Methods for Computational Fluid Dynamics
Cambridge Hydrodynamics, Inc.
P.O. Box 1403
Princeton
NJ
08542
Ilya
Staroselsky
609-683-1515
ARC
NAS2-13514
009

02.01-1515
910919

Abstract:

Fuzzy Grid Methods for Computational Fluid Dynamics
Grid generation for computational fluid dynamics (CFD) is a critically important
field of technology. The fuzzy grid method is a novel way to generate simple and
robust unstructured grids for the solutions of equations in very complex geometries.
In comparison with the current state-of-the-art unstructured grid methods such as
Delaunay/Voronoi grids, fuzzy grids are easier to apply to higher dimensional problems
and have better stability properties. Many of the most important research questions
today in computational fluid dynamics involve strongly inhomogeneous velocity fields,
compressible turbulent flows, and shock waves. Such occurrences are found in regions
of relatively smooth velocity fields interspersed with regions of high vorticity
and high pressure gradients. This causes conventional structured grid techniques
such as spectral element methods to be very wasteful in terms of computer time and
storage. Unstructured grid techniques are a more efficient approach but have proven
difficult to implement in high dimensions. Also, the complexity induced by the nonlocal
interactions in the grid makes the analysis of their mathematical properties difficult.
This innovative fuzzy grid technique is easy to implement on both vector and parallel
supercomputers and its simplicity enables mathematical verification of important
stability and convergence properties.
The development of efficient, easy-to-use software is key to enabling the accurate,
efficient solution of complex engineering problems in many areas. The fuzzy grid
technique will have commercial interest because it will allow robust, accurate simulations
of the most complex flows of industrial interest.
grid generation, unstructured grid, Voronoi grid, Delaunay tringulation, nearest
neighbor algorithms, CFD, parallel computing

Project Title:

A Mathematically Based Reynolds-Stress Model of Turbulence

02.01-9457A
911876
A Mathematically Based Reynolds-Stress Model of Turbulence
Nielsen Engineering & Research, Inc.
510 Clyde Avenue
Mountain View
CA
94043-2287
Robert E.
Childs
415-968-9457
ARC
NAS2-13515
010

02.01-9457A
911876

Abstract:

Turbulence modeling is a critical element in most computational fluid dynamics calculations
in all speed ranges, from subsonic to hypersonic. However, existing models are inadequate
for large classes of flows. An example of this would be flows with large regions
of separation and three-dimensional flows. The inadequacy of these turbulence models
can be attributed to the heuristic reasoning that is used in the model derivation.
The goal of this project is to develop a mathematically (as opposed to heuristically)
based model that is self-consistent and from which error bounds can be deduced. The
approach will use Duhamel's equation to derive an expression for the terms which
must be modeled in normal Reynolds-stress transport models.
Improved turbulence models will benefit aircraft and automobile manufacturers and
chemical and food processors.
fluid flow, turbulence modeling

Project Title:

Suction Laminarization of Junctures in Laminar-Flow-Control Airplanes

02.02-7093
911115
Suction Laminarization of Junctures in Laminar-Flow-Control Airplanes
Analytical Services & Materials, Inc.
107 Research Drive
Hampton
VA
23666
Werner
Pfenninger
804-865-7093
LaRC
NAS1-19518
012

02.02-7093
911115

Abstract:

Suction Laminarization of Junctures in Laminar-Flow-Control Airplanes
The range of transport airplanes has increased during the past years. When laminar
flow is achieved over most of the aircraft surface, they will have even longer range.
This is because laminar-flow-control (LFC) will substantially raise the lift/drag
ratio in cruise.  This project will use distributed suction to maintain laminar flow
in the particularly critical juncture region between the wing and fuselage. In Phase
I, the feasibility of this approach will be evaluated computationally. For a given
wing-fuselage juncture configuration, boundary layer development and stability calculations
will be used to determine suction requirements to maintain laminar flow runs in the
juncture region. Configuration geometry tailoring in the juncture near the wing trailing
edge will achieve fuselage laminarization downstream of the wing trailing edge. Phase
I will evaluate the performance improvement due to suction and Phase II will conduct
a wind tunnel experiment to demonstrate the innovation.
This novel approach can be used to design junctures between various components in
LFC airplanes.
body-wing combination, LFC, Suction, L/D ration, aircraft range, high subsonic flow

Project Title:

Navier-Stokes Technique for Aerobraking Orbital-Transfer Vehicles

02.03-2036
911594
Navier-Stokes Technique for Aerobraking Orbital-Transfer Vehicles
VRA, Inc.
P.O. Box 50
Blacksburg
VA
24063
Clark H.
Lewis
703-953-2036
LaRC
NAS1-19551
013

02.03-2036
911594

Abstract:

Navier-Stokes Technique for Aerobraking Orbital-Transfer Vehicles Applications
Upon atmospheric entry, proposed aerobraking orbital-transfer vehicles (AOTV) configurations
will experience large heat loads. Accurate prediction of these complex flow fields
is necessary for designing appropriate heatshields. Thermal-chemical nonequilibrium,
nonequilibrium radiation, and surface-ablation effects will be important under these
conditions. This project will develop and demonstrate a new space-marching Navier-Stokes
scheme that will be computationally fast and efficient and will also be able to address
these flow-field effects. Phase I will focus on axisymmetric perfect-gas flow over
a typical AOTV forebody, and will use a space-marching approach with Van Leer flux
splitting. The project will demonstrate this new numerical capability by predicting
hypersonic flow over a 70-degree sphere-cone under typical AOTV conditions, and provide
a detailed engineering report. Phase II will address the extensions to include three-dimensional
flows, a wide range of nonequilibrium-to-equilibrium flows, radiation and surface-ablation
effects, and will include near- as well as far-wake flow field regions. The developed
code(s), user's manual(s), and a final engineering report will be provided at the
end of Phase II.
Commercial applications include the design and analysis of various hypersonic penetration
aids and decoys, NASP, TAVs, AOTVs and aerobrakes, and AFE configurations. In the
absence of sufficient flight data, these computational fluid dynamics capabilities
will help generate the data base for such advanced design concepts.
space marching, Navier-Stokes, aerobrake, nonequilibrium, ablation, radiation

Project Title:

Numerical Simulation of Hypersonic, Shock-Separated Flows in a Turbulent Medium

02.03-3844
911782
Numerical Simulation of Hypersonic, Shock-Separated Flows in a Turbulent Medium
DCW Industries, Inc.
5354 Palm Drive
La Canada
CA
91011
David C.
Wilcox
818-790-3844
LaRC
NAS1-19524
014

02.03-3844
911782

Abstract:

Numerical Simulation of Hypersonic, Shock-Separated Flows in a Turbulent Medium
Using the multiscale model of turbulence devised by Wilcox, an analytical/numerical
method will be applied to investigate hypersonic shock-separated flows in a turbulent
medium. This project will incorporate the multiscale model in a NASA Langley three-dimensional
thin-shear-layer computer program known as CFL3DE and provide for high Mach number
corrections for the turbulence model using a combination of physical reasoning aided
by analytical and numerical tools. A key phenomena pertinent in hypersonic flows,
viz, strong compressibility effects, compressible viscous sublayer and defect layer
structure, and heat-transfer effects will be addressed. Hypersonic viscous-inviscid
interactions will then be numerically simulated.  The computations will determine
how well the multiscale model predicts properties of such flow and if it is feasible
to use a second-order-closure model for three-dimensional computations with today's
computer resources.
This project may lead to a greatly improved capability to predict properties of turbulent
flow in incompressible through hypersonic speed ranges. This could help reduce fuel
consumption for airplanes, ships, automobiles, etc.
turbulence, hypersonics, CFD

Project Title:

Basic Governing Equations and Physical Models for Highly Nonequilibrium Hypersonic

02.03-3921
912538
Basic Governing Equations and Physical Models for Highly Nonequilibrium Hypersonic
Flows
BSA Services
4010 Tidewater
Houston
TX
77045
Jong-Hun
Lee
713-433-3921
ARC
NAS2-13554
015

02.03-3921
912538

Abstract:

Basic Governing Equations and Physical Models for Highly Nonequilibrium Hypersonic
Flows
This project will investigate the use of a four-temperature concept for highly nonequilibrium
hypersonic flows. The development of hypersonic space vehicles for future NASA missions
involves knowledge of complex aerothermodynamic phenomena such as thermal and chemical
nonequilibrium. Since it is extremely difficult to simulate the thermochemically
complex flow field around vehicle models in a ground-based experimental facility,
it is highly desirable to obtain accurate numerical computations of the flow field.
To do so, it necessary to have a physically valid set of conservation equations in
the flow regimes of interest. The objective of this project is to develop a basic
set of governing equations and physical models based on the concept of four independent
temperatures (translational, rotational, vibrational-electronic, and electron temperatures),
for the highly nonequilibrium hypersonic flows around future space vehicles. A phenomenological
approach will be taken to clarify the technical issues to be resolved and to examine
possible engineering methods to attack the issues. This comprehensive analysis of
expected thermochemical nonequilibrium phenomena proposed for Phase I will provide
the basis for further development of the detailed  physical models. Phase II will
incorporate these models into the required set of basic governing equations.
This work will establish the theoretical feasibility of phenomenological models in
the highly nonequilibrium hypersonic flow around future space vehicles and planetary
probes. The governing equations and physical models obtained may become the basis
for future development of computational fluid dynamics codes that will be used in
the design of proposed space vehicles and planetary probes.
nonequilibrium, aerothermodynamics, hypersonic, aeroassist entry, space vehicle,
planetary probes

Project Title:

High-Speed Velocity Diagnostic for Arc Facilities

02.03-6100
911581
High-Speed Velocity Diagnostic for Arc Facilities
Deacon Research
2440 Embarcadero Way
Palo Alto
CA
94303
Anthony
O'Keefe
415-493-6100
ARC
NAS2-13560
016

02.03-6100
911581

Abstract:

High-Speed Velocity Diagnostic for Arc Facilities
Thermal protection of the outer structure of a space vehicle during atmospheric re-entry
is crucial to the success of that vehicle's mission. The effects of spacecraft heating
due to gas in the earth's upper atmosphere can be simulated in the laboratory using
an arc jet flow. The need for accurate analysis of such data is critical since the
amount of thermal shielding loaded onto a spacecraft directly impacts the payload.
Laser induced fluorescence techniques are being developed to probe for species content
and temperature in these flows. The goal of this project is to develop a fast (kHz)
remote probe of flow velocity in arc-flow research facilities. This innovation will
permit the velocity field to be mapped out with both spatial and temporal resolution,
allowing detailed analysis of turbulence and shock front effects. Preliminary physical
and optical measurements will be used to evaluate the potential of this approach.
This project will establish the feasibility of making high speed flow velocity measurements
with a non-intrusive laser probe. Applications include use in the development of
advanced air frames, high speed jet engines and rockets and in the remote measurement
of engine thrust.
velocity, remote sensing, frequency modulation

Project Title:

A Novel Coupling Technique for Solving the Euler Equations Over Complete Aircraft

02.04-9090
912370
A Novel Coupling Technique for Solving the Euler Equations Over Complete Aircraft
Analytical Methods, Inc.
P.O. Box 3786
Bellevue
WA
98009
David M.
Tidd
206-643-9090
ARC
NAS2-13553
017

02.04-9090
912370

Abstract:

A Novel Coupling Technique for Solving the Euler Equations Over Complete Aircraft
To increase the design throughput of complex full aircraft configurations, a method
which is both computationally efficient and has minimal setup time is required. This
project will develop a new procedure for coupling a cartesian, multigrid Euler code
with a second Euler technique using a body-filled mesh. The method, coupled with
an iteration scheme, combines the advantages of two different gridding techniques
to produce a resulting scheme which will facilitate rapid model setup. The research
is aimed at providing a practical Euler method for complete aircraft configurations
including nozzle afterbody and inlet integration studies.
This novel technique would lead to an improved design capability for complex aircraft,
including a faster throughput of design and reduced amount of wind tunnel testing.
Euler, multigrid, cartesian, body-fitted, complete aircraft

Project Title:

A Prediction Method for High-Angle-of-Attack Aerodynamics

02.05-9457A
910193
A Prediction Method for High-Angle-of-Attack Aerodynamics
Nielsen Engineering & Research, Inc.
510 Clyde Avenue
Mountain View
CA
94043-2287
Patrick H.
Reisenthel
415-968-9457
LaRC
NAS1-19529
018

02.05-9457A
910193

Abstract:

A Prediction Method for High-Angle-of-Attack Aerodynamics
The occurrence of structural failures of the vertical tails on aircraft such as the
F-15, F-18, and possibly the F-22 is a problem of extreme importance. These failures
are due to aerodynamic interaction between the vertical tail and the unsteady vortical
flow. In order to avoid this adverse interaction it is necessary to predict the flow
in the early design stages so that appropriate steps can be taken. The key element
in predicting the unsteady airloads on the tail of an aircraft at high angles-of-attack
is a model of the vortex that emanates from the forebody, inlet, or leading edge
extension. This model should be capable of representing a burst vortex. The overall
model of the flow field could then be used to analyze the loading on the tails. Predicting
the unsteady flow that causes the failure of the tails will be explored. The goal
of this project is to produce an engineering tool for high angle-of-attack flows
significantly beyond the onset of stall by applying the simplest possible physical
models.
This engineering methodology and a prediction tool would help designers ensure that
the fatigue problems occurring on twin-tail tactical fighters do not arise in future
aircraft designs. This will be of considerable benefit to the federal government
and to the aerospace industry.
unsteady aerodynamics, unsteady separated flow, vortex breakdown, buffeting, aeroelasticity,
mathematical modeling, potential flow, computational fluid dynamics

Project Title:

Simulation of Helicopter Rotor-Body Interaction Flow Fields by Navier-Stokes Method

02.06-7722
910805
Simulation of Helicopter Rotor-Body Interaction Flow Fields by Navier-Stokes Method
JAI Associates, Inc.
465 Fairchild Drive, Suite 111
Mountain View
CA
94043
G.R.
Srinivasan
415-967-7722
ARC
NAS2-13534
019

02.06-7722
910805

Abstract:

Simulation of Helicopter Rotor-Body Interaction Flow Fields by Navier-Stokes Method
A three-dimensional, unsteady Navier-Stokes numerical methodology to calculate economically
and accurately the flow field of multi-bladed helicopter rotor and fuselage in hover
and forward flight will be developed. Ad hoc wake models will not be used to model
the vortex wake; instead, the complete vortical wake will be captured as a part of
the overall flow field solution. A Navier-Stokes upwind scheme will be used in conjunction
with a Chimera grid for preserving and convecting concentrated vortices. Phase I
will demonstrate a calculation for a rotor-body combination in hover which would
provide a solid foundation for realistic calculations in hover and forward flight
in Phase II. The individual items to be completed in Phase I are the gridding of
a two-bladed rotor and fuselage for a Chimera scheme; implementation of Chimera and
Pegasus schemes into the Navier-Stokes numerical method; and a demonstration calculation
of rotor-body flow in hover and comparing the results with experiments.
Commercial applications include the design of advanced technology helicopters with
efficient aerodynamics and aeroacoustics performance, including the selection process
of rotor blade shapes and planforms and the interaction of multiple moving bodies
relative to each other such as the main rotor and tail rotor and engine turbines
and compressors.
viscous flow, Navier-Stokes equations, unsteady, hover, forward flight, helicopter
rotor, wake, interaction flow, transonic, three-dimensions

Project Title:

Long-Wavelength, Infrared, Detection System for Wind Tunnel Design and Experimental

02.07-6621
911178
Long-Wavelength, Infrared, Detection System for Wind Tunnel Design and Experimental
Techniques
Amber Engineering, Inc.
5756 Thornwood Drive
Goleta
CA
93117-3802
John D.
Blackwell
805-683-6621
LaRC
NAS1-19517
020

02.07-6621
911178

Abstract:

Long-Wavelength, Infrared, Detection System for Wind Tunnel Design and Experimental
Techniques
Infrared detection and imaging systems are required for measuring temperature profiles
along the surface of models in a cryogenic environment, down to 100 K or less. Staring
infrared arrays offer advantages over scanned arrays presently used for this application.
This project will demonstrate the feasibility of installing a closed-cycle infrared
camera system in a wind tunnel. The firm has successfully demonstrated gallium-doped
silicon (Si:Ga) 128x128 element, long-wavelength infrared (LWIR) staring focal plane
arrays (FPAs), with spectral coverage from 3-17 micrometers. A Si:Ga based LWIR imaging
system will be used to image airplane models. A sensitivity of 0.02mK or better is
predicted for Si:Ga at temperatures down to 100 K. The system's video electronics
features variable frame rates (up to 217Hz) and integration times, and furnishes
both raw digital data and RS-170 outputs for data recording purposes. It is anticipated
that project results will show Si:Ga staring FPA technology is the optimal solution
for test and research applications in cryogenic windtunnels. This project offers
the near-term prospect of retrofitting wind tunnels with low-cost, high-performance
LWIR camera systems.
Commercial applications would apply in leak detection and imaging or similar low
background scenes including satellite detection, detection of clear-air turbulence
(commercial aircraft), discovery of leaks in pipelines (e.g., Alaska oil pipeline),
constituent determination of earth and planetary atmospheres, and remote sensing
of atmospheric and weather conditions.
wind tunnel, LWIR, cryogenic, Si:GA, FPA, infrared, imaging, airplane

Project Title:

A Quantitative Skin Friction Imaging Sheet

02.08-0003
912284
A Quantitative Skin Friction Imaging Sheet
Physical Sciences, Inc.
20 New England Business Ctr
Andover
MA
01810
R. Daniel
Ferguson
508-689-0003
LaRC
NAS1-19534
022

02.08-0003
912284

Abstract:

Optical techniques have been employed in attempts to gain a qualitative picture of
the skin friction distribution over surfaces. The methods based upon coatings which
exhibit shear-stress-sensitive properties have limited dynamic range. They require
external imaging systems that render them less suitable for aeronautical applications.
New thermal-type imaging approach offers the potential of high-resolution, CCD-style
readout and display of skin-friction data in real time without the need for external
optical diagnostics, and will be developed for large-area (1 m2) wind-tunnel instrumentation
and aeronautical applications. The proposed device would consist of an array of a
new type of thermal, shear-stress sensor integrated into a thin, flexible skin. High-sensitivity,
flexible, pyroelectric sensors that accumulate charge in proportion to local temperature
changes can monitor local surface cooling rates after known heat pulses are delivered
by underlying heating films. This cooling rate has a simple relationship to the skin
friction. Standard "V"-type sensor configurations can separate the wall shear stress
components in cross-flow conditions. The skin friction would read out in a manner
similar to CCD-array cameras. Such a sheet could be readily attached to any surface
and the skin friction monitored and displayed continuously in, for example, standard
RGB video format.
A non-intrusive, skin-friction CCD 'camera' has the potential to become a commercial
product usable in fluid dynamics laboratories around the world. These distributed
sensor arrays can be installed on aircraft wings with outputs coupled to control
system which improve aerodynamic performance. Active control strategies can be developed
for turbulence, flow separation and cross-flow problems, where rapid assessment of
extended flow-field topology is critical.
skin friction, imaging, turbulence, instrumentation, diagnostics

Project Title:

Methods for Computational Aeroacoustics

02.09-9457
910568
Methods for Computational Aeroacoustics
Nielsen Engineering & Research, Inc.
510 Clyde Avenue
Mountain View
CA
94043-2287
Robert E.
Childs
415-968-9457
LaRC
NAS1-19530
024

02.09-9457
910568

Abstract:

Methods for Computational Aeroacoustics
Computational aeroacoustics (CAA) is an emerging discipline in which numerical solutions
of the partial differential equations governing compressible flow are employed to
make predictions of the noise generated by unsteady and turbulent flows. Methods
required for CAA are somewhat similar to those used in computational fluid dynamics
(CFD); however, two major differences are that CAA requires significantly better
far-field boundary conditions and higher accuracy solution algorithms than are typically
employed in CFD. Innovative boundary conditions which employ superposition of numerically
generated solutions for the exterior of the computational domain will be developed
to treat difficult outflow problems. A high-order-of-accuracy shock-capturing algorithm
will be constructed to be consistent with the laws of thermodynamics, unlike many
shock capturing schemes. Improvements in computational efficiency (interpreted as
the range of scales resolved per computational cost) as large as two orders of magnitude
when compared to existing second order methods may be achieved.
This project will improve accuracy and/or reduce cost for computational methods,
both CAA and CFD. These methods are employed by a range of businesses that are as
diverse as aircraft, automobile, and ship manufacturing, food processing, and biomechanics
firms. All of these areas, especially the aerospace industry, could benefit.
computational fluid dynamics, aeroacoustics, boundary conditions, high accuracy algorithms.

Project Title:

Aeroacoustic Diffraction and Dissipation by a Short Propeller Cowl in Subsonic Flight

02.10-1421
910079
Aeroacoustic Diffraction and Dissipation by a Short Propeller Cowl in Subsonic Flight
Cambridge Acoustical Associates, Inc.
80 Sherman Street
Cambridge
MA
02140
Rudolph
Martinez
617-491-1421
LeRC
NAS3-26598
025

02.10-1421
910079

Abstract:

Aeroacoustic Diffraction and Dissipation by a Short Propeller Cowl in Subsonic Flight
This project will investigate two concerns of the propfan noise research program:
 the beneficial effect of placing the new propulsion system within a short, diffractive
cowl and whether practical variations in the configuration of the acoustic liner
on such a cowl would significantly affect the character of the noise emerging from
its ends. A ducted-propeller theoretical model will be developed incorporating the
following physical features:  an idealized cowl of finite length, open-ended, unflanged,
and thin-walled; an axisymmetric liner that will cover parts of its interior surface
with variable material properties along the cowl's short axial extent; the effects
of a subsonic freestream (the flight speed) on the coupled phenomena of edge diffraction
and liner dissipation and on the propagation of the predicted radiated field; and
an insonifying aeroacoustic field due to a realistic distribution of modeled propeller
sound sources.
The design of acoustic liners specially tailored to short-ducted propellers will
address, respectively, the problems of cabin noise during flight (near-field radiation
patterns) and community environmental noise (far-field radiation patterns).
ducted propeller, linear optimization, diffracting cowl

Project Title:

Noise Reduction by the Dynamical Entrainment of Aircraft Engine Acoustics

02.10-2585
910289
Noise Reduction by the Dynamical Entrainment of Aircraft Engine Acoustics
Advanced Projects Research, Inc.
5301 North Commerce Avenue, Suite A
Moorpark
CA
93021
James D.
Sterling
805-523-2585
LeRC
NAS3-26326
026

02.10-2585
910289

Abstract:

Noise Reduction by the Dynamical Entrainment of Aircraft Engine Acoustics
A novel method for the reduction of noise in propulsion systems will be developed.
Pressure oscillations associated with engine internal flow dynamics will be analyzed
using nonlinear dynamical systems theory to determine the effective number of degrees
of freedom that participate in the oscillations. Reduction of this dimension can
be achieved by nonlinear forcing of the system to achieve "mode-locking" or "entrainment"
of the oscillations so that low-dimensional deterministic dynamics are obtained.
Both linear and nonlinear control techniques may then be applied to the system to
reduce or modify the attractor. Phase I will demonstrate the entrainment of high-dimensional
dynamics onto low-dimensional attractors for known mathematical constructs; apply
dimension-determination techniques to the results of acoustic models to characterize
"noisy" data; and investigate the application of dimension reduction techniques to
acoustic oscillations associated with rotor-stator interactions, nozzle acoustic-entropy
interactions, combustion chamber acoustic modes, and compressor surge.
The reduction of noise by nonlinear entrainment of the high-dimensional dynamics
may prove beneficial for many engineering systems. Application to propulsion systems
requires hardware that can influence the fluid flow to reduce noise. It is anticipated
that commercial implementation of the methods will first be applied to minimize pressure
oscillations in combustors of aircraft engines.
noise, acoustics, dynamical systems, fluid mechanics, propulsion

Project Title:

Surface Roughness Features Formulation for Aircraft Icing

03.01-8581
910250
Surface Roughness Features Formulation for Aircraft Icing
Remtech, Inc.
3304 Westmill Drive
Huntsville
AL
35805
Robert D.
Kirchner
205-536-8581
LeRC
NAS3-26322
027

03.01-8581
910250

Abstract:

Surface Roughness Features Formulation for Aircraft Icing
A theoretical model will be devised to define icing surface roughness features in
detail. The establishment of such a roughness model is crucial to the development
of all future ice accretion models and ice scaling laws, and it is vital in efforts
to gain a full understanding of the ice accretion process. The model will be derived
from an analysis of physical mechanisms that govern the icing process, and it will
define the texture of accreting ices in terms of the size, shape, and surface density
of individual roughness elements that form during icing processes. One goal of this
project is to provide the aviation industry with a tool that can be used to model
the effects of roughness in surface heat transfer studies. Another is to help define
the aerodynamic penalties associated with icing processes and so serve as an indispensable
key in the development of all future ice accretion models and ice scaling laws.
This project will provide a significant advancement in efforts to develop ice accretion
models and ice scaling laws that can be used to establish the extent, growth rate,
and effects of icing processes on aircraft surfaces in all icing conditions.
icing roughness features, ice accretion processes

Project Title:

Ice-Accretion Prediction on Massively Parallel Computers

03.01-9457A
910458
Ice-Accretion Prediction on Massively Parallel Computers
Nielsen Engineering & Research, Inc.
510 Clyde Avenue
Mountain View
CA
94043-2287
Steven C.
Caruso
415-968-9457
LeRC
NAS3-26321
028

03.01-9457A
910458

Abstract:

Ice-Accretion Prediction on Massively Parallel Computers
This project addresses the use of massively parallel computers for the prediction
of time-dependent ice accretion on two- and three-dimensional aerodynamic bodies.
Currently, the LEWICE computer code is being developed at NASA's Lewis Research Center
for the prediction of aircraft aerodynamic performance under icing conditions. There
are several distinct components to the LEWICE program, including water droplet trajectory
calculations and airfoil aerodynamics predictions. These components can require large
amounts of CPU time. The extension of this computer code to three-dimensional geometries
will be severely restricted by the computational power of present-day single- or
serial-processor computers. The goal of this project is to demonstrate the feasibility
of using massively parallel processing techniques to gain significant computational
efficiencies for typical calculations performed in time-dependent icing analyses.
In Phase II, the complete LEWICE code will be ported to a parallel computer.
An accurate and efficient tool that can perform three-dimensional aircraft icing
analyses could be used by both government and industry to further understand aircraft
icing problems, decrease development time and costs of ice protection systems, and
aid in the qualification and certification of aircraft to operate under icing conditions.
icing analysis, parallel processing, computational fluid dynamics

Project Title:

Eclectic, Mixed H-Infinity and Mu-Synthesis Procedures for Practical Flight-Control-System

03.03-2281A
911090
Eclectic, Mixed H-Infinity and Mu-Synthesis Procedures for Practical Flight-Control-System
Design
Systems Technology, Inc.
13766 South Hawthorne Boulevard
Hawthorne
CA
90250
Peter M.
Thompson
213-679-2281
LaRC
NAS1-19547
030

03.03-2281A
911090

Abstract:

Eclectic, Mixed H-Infinity and Mu-Synthesis Procedures for Practical Flight-Control-System
Design
Modern aerospace vehicles require highly integrated multidisciplinary control systems
and the use of numerous control effectors, including thrust vecturing. The resultant
complexities motivate a need for improved synthesis methods and a re-examination
of conventional control design criteria. The h-infinity optimal control approach
is a promising candidate because performance and robustness specifications can directly
be included in the cost function. As it now stands, h-infinity is not yet useful
for flight control design and, indeed, has as many deficiencies for such purposes
as it has promises. To overcome the major deficiencies, an eclectic and complementary
mix of control synthesis procedures that utilize h-infinity and -synthesis as core
techniques will be developed. The approach will address and rectify the deficiencies
and evolve a practical composite technique for flight control purposes. The project
will investigate the mixture of techniques and apply them to advanced stability augmentor
and autopilot designs for a high-performance, high-angle-of-attack aircraft.
The advanced practical synthesis methods developed could become universal in the
design of advanced, highly integrated, robust flight control and similar automated
systems in air, space, and ground transportation. Near-term possibilities include
experiments on the NASA HARV, or applications to the X-30 or HSCT. Some of the techniques
and procedures developed could be incorporated as upgrades in existing commercially
available software design programs ("Program CC").
h-infinity, mu-synthesis, robustness, flight control design

Project Title:

Parallel Implementation of Image Correspondence Algorithms for Rotorcraft

03.04-1567
912258
Parallel Implementation of Image Correspondence Algorithms for Rotorcraft
Innovative Configuration, Inc.
9053 Soquel Drive, Suite 203
Aptos
CA
95003
Vason
Srini
408-688-1567
ARC
NAS2-13524
031

03.04-1567
912258

Abstract:

Parallel Implementation of Image Correspondence Algorithms for Rotorcraft
The operation of rotorcraft in high-threat environments requires assistance from
on-board computers, image sensors, and automation tools so that nap-of-the Earth
flight mode can be used to carry out a specified mission. The goal of this project
is to evaluate four parallel architectures for their ability to provide real-time
obstacle detection, range estimation, image correspondence, and other near-field
guidance calculations. The first architecture uses Datacube's MaxVideo 20 pipeline
image processing system, containing multiple functional units interconnected by a
32 x 32 crossbar. The second architecture uses Intel/CMU's iWarp chip interconnected
in a systolic manner. The third architecture involves general purpose microprocessors
such as Sparc interconnected using a shared bus to form a shared memory multiprocessor.
The fourth architecture employs special purpose, high-performance VLSI chips interconnected
in a systolic manner. The four architectures will be evaluated using the algorithms
and C programs available from NASA and other agencies during Phase I. These evaluations
will determine what portion of the parallelism present in the algorithms can be turned
into speedup by the architecture. The features of each of the four architectures
such as communication network, speed of ALU and multiplier, and pipelining that can
facilitate the exploitation of parallelism into speedup will be analyzed and documented.
Based on these evaluations, one of the architectures will be selected for implementation
in Phase II. The implementation will result in a board that can be plugged into the
SBUs slots of SparcStation 2 and experimented at NASA facilities.
The compact and low-cost board can be used in spacecraft and ships. The system can
also be used in full-motion video processing systems. The range estimation and image
correspondence algorithms will be applicable in controlling robots, monitoring flow
of materials in factories, and manufacturing.
rotorcraft flight, range estimation, image correspondence, kalman filters, digital
signal processor, video image processing, parallel system, systolic architectures

Project Title:

A Three-Component, Optical, Doppler Air Velocity Sensor

03.05-2100
912229
A Three-Component, Optical, Doppler Air Velocity Sensor
Optra, Inc.
66 Cherry Hill Drive
Beverly
MA
01915
Geert
Wyntjes
508-921-2100
ARC
NAS2-13439
032

03.05-2100
912229

Abstract:

A Three-Component, Optical Doppler Air Velocity Sensor
This project will assess the feasibility of a novel approach to a non-intrusive measurement
of the relative, with respect to the vehicle, air velocities in the forward, pitch,
and yaw directions using a radically different implementation of a laser Doppler
anemometer. Unique to this design is a single beam for illumination with three interferometric
receivers to measure the phase shift of the backscattered light in three vector directions.
The combination of these will provide a measurement of air velocity in the forward,
pitch, and yaw directions at a single point in space. Key to the design are the uses
of a complex spatial filter to enhance fringe contrast and an efficient signal processor
operating in the polar or phase domain to recover accumulated phase shift (proportional
to the product of vector air velocity and time) with a low probability of error even
when fringe signal-to-noise is low. The interferometric design can be implemented
at any wavelength from the UV to well into the near-IR and makes only moderate demands
on temporal and spatial coherence of the illuminating source, permitting consideration
of both relatively broadband sources and spatial, multi-mode laser sensors. As envisioned,
the sensor would be compact, weigh little, and require minimum electrical power.
The sensor concept will satisfy many long-standing needs, including the measurement
of air motions under extreme flight conditions. It will also extend the stand-off
distance for the premonitory detection of low-altitude windshear.
laser, doppler, airborne

Project Title:

A Non-Intrusive, Solid-State, Angle-of-Attack Instrument

03.05-7093
911989
A Non-Intrusive, Solid-State, Angle-of-Attack Instrument
Analytical Services & Materials, Inc.
107 Research Drive
Hampton
VA
23666
S. M.
Mangalam
804-865-7093
LaRC
NAS1-19519
033

03.05-7093
911989

Abstract:

A Non-Intrusive, Solid-State, Angle-of-Attack Instrument
A new technique for indicating the angle-of-attack (AOA) based on accurately locating
the leading-edge stagnation point in flight will be developed. Advanced flow diagnostics
techniques and instrumentation developed recently by the company will be used for
the flight application. The stagnation point location will be determined by identifying
the phase reversal signatures, and the clearly identifiable fundamental and higher
harmonic dither frequencies in signals from micro-thin, multi-element, hot-film sensors.
The multi-element, hot-film sensors will be operated by a high sensitivity constant
voltage anemometer. Signals from 16 anemometers will be simultaneously acquired by
the company's data acquisition and analysis system. Flight tests will be made on
an experimental-class airplane to evaluate the feasibility of determining angle-of-attack
over the entire flight envelope through the identification of the leading-edge stagnation
point.
Existing AOA devices are relatively high cost and/or intrusive. A low-cost, non-intrusive,
digital relative angle-of-attack display suitable for general aviation aircraft as
well as for transport and military aircraft has market viability, and could also
be made available in a more sophisticated form to measure absolute AOA for research
and flight test aircraft. The measurement technique can also be used to provide yaw
or side slip angle displays as well as provide tail downwash or sidewash angles.
angle-of-attack, non-intrusive, multi-element, hot-film, sensors

Project Title:

Optical-Fiber Velocimeter for Flows in Hypersonic and Supersonic Flight

03.05-7637
910802
Optical-Fiber Velocimeter for Flows in Hypersonic and Supersonic Flight
Candela Laser Corporation
530 Boston Post Road
Wayland
MA
01778
Rafael A.
Sierra
508-358-7637
LaRC
NAS1-19520
034

03.05-7637
910802

Abstract:

Optical-Fiber Velocimeter for Flows in Hypersonic and Supersonic Flight
A new airborne instrument for velocimetry of the external and internal flows of re-entry,
hypersonic, and supersonic vehicles will be developed. This technique may also prove
useful for temperature measurement. Based on the time-of-flight approach, the instrument
uses laser-generated N2 ions as tracers and delayed laser-induced fluorescence for
imaging. Two recent advances make this innovation possible:  the identification of
an efficient photo-ionization of N2 and the development of a new burst-mode, Q-switched,
frequency-doubled, Ti:Sapphire laser. The new laser can deliver two high-energy,
tunable laser pulses using a single flashlamp pulse. The first pulse is used to write
a tracer line by tuning it to the ionizing transition of N2. The second pulse is
used, after a preset delay, to induce fluorescence that is detected by a solid-state
digital camera. The all-solid-state system is robust and may be made into a low-volume,
low-power, minimally intrusive, highly accurate, and reliable device.
This instrument will also be useful for wind tunnels and combustion diagnostics.
In addition, the UV laser will find use as a resonance ionization source for mass
spectrometric analysis of ultra trace elements in biological samples in medical research.
Other applications of the laser include spectroscopy and materials research.
optical velocimeter, tunable Ti:Sapphire laser, photo-ionization, Q-switched laser

Project Title:

Synthetic, Moire-Fringe Surface Metrology

03.05-8775A
911446
Synthetic, Moire-Fringe Surface Metrology
Bauer Associates, Inc.
177 Worcester Road, Suite 101
Wellesley
MA
02181
Paul
Glenn
617-235-8775
ARC
NAS2-13440
035

03.05-8775A
911446

Abstract:

Synthetic, Moire-Fringe Surface Metrology
A new surface contour measurement will be developed. Because of its remote, non-contacting
nature, it will be able to measure a wide variety of structural deformations, including
those induced by high Mach number airflows over aerodynamic surfaces. The approach
is an innovative variation on Moire fringe techniques. It replaces the physical,
periodic viewing mask with specific digital image processing algorithms, making the
approach easy to implement and extremely flexible. The result is accurate measurement
data on a regular rectangular grid, with meaningful horizontal resolution equal to
that of the viewing system. Sensitivities to deflections of several micro-inches
and absolute accuracies better than one hundred micro-inches appear to be achievable.
Objectives are to define a baseline system and to develop calibration algorithms
and a comprehensive performance prediction model. Phase II will provide a breadboard
instrument to characterize and demonstrate its capabilities. NASA applications include
flight research sensors and instrumentation, as well as generalized surface metrology.
Benefits include real-time, non-contacting, accurate measurement of surface shapes
and deflections.
Applications include in-process surface and deflection mapping of complex parts,
including aerodynamic surfaces. The instrument can also be used for pre-weld shape
and orientation inspection, mold inspection, part alignment in a robotic manufacturing
cell, and measurement of human back shape for scoliosis screening.
contour measurement, deflectometry, Moire, non-contact

Project Title:

Smart-Skin Technology for Vortex Flow Detection

03.06-0533
911288
Smart-Skin Technology for Vortex Flow Detection
Innovative Dynamics
Cornell Research Park, 244 Langmuir Labs
Ithaca
NY
14850-1296
Gail A.
Hickman
607-257-0534
ARC
NAS2-13458
036

03.06-0533
911288

Abstract:

Smart Skin Technology for Vortex Flow Detection
Innovative methods for measuring and controlling vortex-dominated flows will be developed
to achieve enhanced mission performance of advanced technology fighters. The primary
objective of this project is to define and quantify experimentally techniques for
measuring surface flow patterns and vortex structures. Phase I will demonstrate an
innovative concept based on "smart skins" to measure vortex flow fields on a delta
wing using sensor arrays integral with the airfoil skin. The basic concept is to
measure pressure and shear forces at the surface with thin-film arrays and construct
three-dimensional vortex fields using digital signal processing techniques. Laboratory
experiments and wind tunnel flow visualization tests will be conducted to demonstrate
embedded solid-state transducers in an open-loop mode of operation. The most promising
sensors/actuators will be integrated into a thin boot design for Phase II developmental
and Phase III in-flight testing on NASA's F/A-18 high-angle-of-attack (AOA) research
vehicle. This work will help researchers verify the accuracy of computational fluid
dynamics calculations to predict accurately the aerodynamics and behavior of an aircraft
maneuvering at high AOA. Successful development of smart skins could produce advanced
control mechanisms that will extend fighter aircraft performance envelopes without
the complexity and weight penalties of pneumatic control systems.
Fundamental knowledge of the spatial and temporal structure of vortex flows would
have important uses in boundary layer management, high-angle-of-attack aerodynamics,
separated flows, rotor wake interactions, and vane-type vortex generators. The USAF/NASA
AFTI Mission Adaptive Wing program and the Advanced Tactical Fighter would directly
benefit from this technology.
vortex sensor array, vortex manipulator, smart skin, piezoelectric

Project Title:

A Design Method for the Calculation of Supersonic and Hypersonic Flow Fields

03.07-2900
912434
A Design Method for the Calculation of Supersonic and Hypersonic Flow Fields
Adroit Systems, Inc.
209 Madison Street
Alexandria
VA
22314
Thomas R.A.
Bussing
703-684-2900
LaRC
NAS1-19513
037

03.07-2900
912434

Abstract:

A Design Method for the Calculation of Supersonic and Hypersonic Flow Fields
The specific innovation in this project results from a desire to increase speed and
reduce computer memory requirements for the computation of internal and external
hypersonic flows. The approach is to reduce problems involving three-dimensional,
embedded elliptic flow regions that require the full Navier-Stokes (FNS) equations
to problems for which only the parabolized Navier-Stokes (PNS) equations, coupled
with innovative fluid and chemistry models, are required. The innovation involves
building analytical models for various embedded elliptic fluid flows, i.e., transverse
fuel injection, parallel fuel injection, base flows, and so on, for which the extent
of the embedded elliptic flow is small compared to overall flow field. Current FNS
methods require one or two orders of magnitude more CPU time and computer memory
as compared to PNS methods. In addition, an evaluation of the optimization techniques
that could be coupled with these PNS methods will be performed. These new, efficient
codes could be run on super workstations to enhance their availability to the design
community. This innovation will lead to a new, highly efficient class of design methods
applicable to a wide variety of hypersonic problems.
The new design method could be applied in the areas of missile design, supersonic
aerodynamics analysis, hypersonic vehicle design, and scramjet development.
parabolized Navier-Stokes (PNS), fuel injector, hypersonic, design methods, elliptic
flow, computational fluid dynamics (CFD), fluid model, supersonic

Project Title:

Improving Access and Use of Graphical Information in Commercial Air Transport

03.09-1457
911903
Improving Access and Use of Graphical Information in Commercial Air Transport
Search Technology, Inc.
4725 Peachtree Corners Circle Suite 200
Norcross
GA
30092
Paul R.
Frey
404-441-1457
LaRC
NAS1-19545
039

03.09-1457
911903

Abstract:

Improving Access and Use of Graphical Information in Commercial Air Transport
This project addresses an effort to improve the accessibility and use of computer-based
graphical information in the cockpits of commercial transport aircraft. This improvement
derives from the use of principled approaches in both the presentation design and
the ease of access of the graphical information. Two unique and innovative aspects
are the application of recent research results on the use of an information "abstraction-aggregation
space" to the design of computer-based graphics, and the transfer of recent research
and development experience on military fighter aircraft information management to
management of graphical information in commercial air transport. The results of this
effort hold promise for directing and managing the anticipated expansion of computer-based
graphical information in the cockpit.
Information management systems have wide commercial application in civil air transport
as well as in many other industries. In the near term, the most likely commercial
application of this project is the development of electronic library systems (ELS)
for new commercial transport aircraft. It may prove useful in ELS retrofits as well.
information management, graphical information, commercial air transport, electronic
library system

Project Title:

Configurable, Icon-Based Expert System for On-Line Documentation

03.10-0655
911111
Configurable, Icon-Based Expert System for On-Line Documentation
American Research Corporation of Virginia
P.O. Box 3406
Radford
VA
24143-3406
John A.
Neal, III
703-731-0655
ARC
NAS2-13447
040

03.10-0655
911111

Abstract:

Configurable, Icon-Based Expert System for On-Line Documentation
NASA has identified a need for a user-configurable presentation of system functional
overviews and detailed system documentation. To address this need, this project proposes
the innovative application of computer-based expert systems and high-resolution graphics
in a diagrammatic (iconic) environment for the presentation of user-configurable
on-line documentation of aircraft and ground test systems. The project's technical
objectives include evaluation of documentation presentation methodologies, design
of an interactive iconic environment, development of an expert system architecture,
integration of high-resolution computer graphics, and testing and verification of
the expert system. This effort will demonstrate a proof-of-concept system for on-line
graphical presentation of overview and detailed aircraft and test systems. The results
anticipate the development of an expert system architecture and graphical user interface
that is flexible enough to be used in a variety of complex system documentation applications.
Expected NASA application will initially occur in the design, modification, and testing
of aircraft systems; benefits will be realized from an increase in design accuracy,
system reliability, and safety, and a decrease in man-hours spent on documentation
searches.
This intelligent interface will be capable of application to a variety of complex
system documentation needs. It can be used to provide more efficient and more accurate
access to large volume design, performance, and test documentation databases, such
as those found in the aerospace and shipbuilding industries.
expert system, on-line documentation, iconic interface, computer graphics

Project Title:

A Parallel Computing Environment for Probabilistic Response Analysis of High-Temperature

04.01-0018
911218
A Parallel Computing Environment for Probabilistic Response Analysis of High-Temperature
Composites
Applied Research Associates
6404 Falls of Neuse Road, #200
Raleigh
NC
27615
Robert H.
Sues
919-876-0018
LeRC
NAS3-26576
042

04.01-0018
911218

Abstract:

A Parallel Computing Environment for Probabilistic Response Analysis of High-Temperature
Composites
A parallel processing environment consisting of software strategies and optimal hardware
configurations for probabilistic simulation of the response of high-temperature composite
structures will be developed. Probabilistic composite mechanics (PCM) problems have
many inherent levels of both coarse- and fine-grained parallelism. However, the software
strategies needed to achieve large-scale parallelism do not exist. Moreover, current
parallel processor configurations may not be efficient for all cases. Developing
an efficient parallel processing environment for PCM problems will make these computationally
intensive methods practical for tailoring high-temperature structural composites.
The ability to tailor these composites and meet reliability-based design criteria
will contribute to making application of high-temperature composites in aerospace
propulsion structures possible. Phase I will identify the multiple levels of parallelism
in PCM problems and investigate innovative software strategies that can exploit this
parallelism while minimizing parallel processing overhead. Two sample problems will
then be executed on two different parallel architectures. The results will be used
to formulate recommendations for developing optimal parallel processing environments
(software and hardware) for PCM problems.
This hardware-software package will be used to reduce the need for costly testing
of numerous possible composite design configurations to many different load environments.
Commercial application would be in aerospace, automotive, offshore oil, nuclear power,
and construction industries.
parallel processing, probabilistic mechanics, high-temperature composites, structural
reliability

Project Title:

Advanced Area Detector for Real-Time Radiography of Aeropropulsion Materials

04.03-7780
911480
Advanced Area Detector for Real-Time Radiography of Aeropropulsion Materials
Advanced Research & Applications Corporation
425 Lakeside Drive
Sunnyvale
CA
94086
Christopher R.
Mitchell
408-733-7780
LeRC
NAS3-26507
045

04.03-7780
911480

Abstract:

Advanced Area Detector for Real-Time Radiography of Aeropropulsion Materials
The objective of Phase I is to quantify the effect of x-ray scatter on radiographic
image quality, test scatter rejection approaches, and generate a conceptual design
of a system that will provide better resolution, contrast sensitivity, and dynamic
range than is currently available with commercial real-time radiography systems.
Presently, real-time radiography systems do not reject scatter and this has a significant
effect on the performance of these systems. X-ray systems with enhanced resolution,
contrast sensitivity, and dynamic range are needed for the imaging of advanced aeropropulsion
materials that are now being developed. Information gathered from such a system will
be useful in developing accurate models to predict material behavior. Incorporation
of such a system with a load frame will allow information to be gathered on how these
materials behave under mechanical load. The system will also be designed to be compatible
with a future upgrade to a volumetric computed tomography (CT) system, providing
even greater information on advanced material behavior. NASA will be able to use
both the near real-time radiographic and volumetric computed tomography systems to
study advanced aeropropulsion material behavior and provide information to guide
the modeling of these material systems.
The construction of a real-time radiographic system with enhanced resolution, contrast
sensitivity, and dynamic range over currently available systems will extend the use
of these systems, open up many new applications of x-ray imaging, and lead the way
to volumetric computed tomography (CT) systems that will greatly increase the throughput
and utility of CT technology.
radiography, real-time, aeropropulsion, materials, scatter, processing, computed
tomography, models

Project Title:

Process Optimization by Visualization Technology for Composites Manufacturing

04.04-8080
911783
Process Optimization by Visualization Technology for Composites Manufacturing
Technical Research Associates, Inc.
410 Chipeta Way, Suite 222
Salt Lake City
UT
84108
William R.
Hughes
801-582-8080
LeRC
NAS3-26568
046

04.04-8080
911783

Abstract:

Process Optimization by Visualization Technology for Composites Manufacturing
Performance of advanced composite materials for use in aeropropulsion depends to
an extent on the complex processes required for their fabrication. There is a need
to better understand and control such processes through numerical simulation and
process optimization techniques. The goal of this project is to develop new visualization
technology with capabilities that can be directed toward process optimization for
advanced composite manufacturing and improving the understanding of cause and effect
relationships among fundamental process parameters. Further significance of the innovation
resides in the generic capability as a model to show complex relationships of large
numbers of variables, and to add or change any of the variables while observing effects
on all the other variables. Phase I objectives include demonstration of this solution
relative to the basic manufacturing methodologies of filament winding, RTM, and pultrusion.
Anticipated results include demonstration that performance of a composite material
can be optimized by balancing one variable against another in the overall process.
Understanding of how variables relate to other variables will be gained by analysis
of multi-dimensional displays.
Space programs will benefit from higher performance materials made possible by process
optimization. Process optimization for composites will benefit aircraft, automotive
and truck, marine, sports, electrical and construction, and medical applications.
Cost savings through improved yields could be quite impressive.
visualization, processes, composites, multi-dimensional display optimization, modeling

Project Title:

Lightweight, SiC-Ceramic-Foam, Mirror Structures

04.05-0236
912393
Lightweight, SiC-Ceramic-Foam, Mirror Structures
Ultramet
12173 Montague Street
Pacoima
CA
91331
Brian E.
Williams
818-899-0236
LaRC
NAS1-19550
047

04.05-0236
912393

Abstract:

Lightweight, SiC-Ceramic-Foam Mirror Structures
Projected NASA civil and commercial space missions will require power systems capable
of greater versatility and higher power levels than those currently available. Advanced
solar dynamic (ASD) power systems offer the potential for efficient, lightweight,
survivable, relatively compact, long-lived space power systems. The solar concentrator,
a key component of the ASD power system, must be lightweight, dependable, and resistant
to chemical attack. State-of-the-art mirrors for concentrator panels are too heavy
and the surface slope error is too high. In a recently concluded program, the company
has developed a mirror fabrication process in which six inch-diameter optical quartz
(Si02) faceplate mirror surfaces, fabricated by chemical vapor deposition (CVD),
were bonded to lightweight ceramic foams fabricated by chemical vapor infiltration
(CVI). The resulting mirrors were shown to withstand exposure over the temperature
range (from -330 to +250F) without deviating from a surface slope error of 1.0 mrad
over a 72" radius of curvature and a surface roughness of <20.0 A RMS. Phase I will
develop a lightweight SiC mirror structure, composed of a CVI ceramic foam structural
material to which a CVD SiC mirror surface will be deposited. CVD SiC is highly polishable
and has the potential of reducing a real density to <0.20 g/cm2, a 40 percent reduction
from the previous study.
The successful completion of this program will result in a significant advance in
the technology of ultra-lightweight stiff mirror structures. Potential commercial
applications include space optical devices such as telescopes and fast-response laser
pointing mirrors, as well as structural and power system components for the Space
Station.
mirrors, lightweight, silicon carbide (SiC0, solar concentrator, advanced solar dynamic
(ASD), space power systems, foam

Project Title:

Producing Foils from Direct-Cast, Titanium Alloy Strip

04.06-5444
911895
Producing Foils from Direct-Cast, Titanium Alloy Strip
Ribbon Technology Corporation
Box 30758
Gahanna
OH
43230
Thomas A.
Gaspar
614-864-5444
LaRC
NAS1-19541
049

04.06-5444
911895

Abstract:

Producing Foils from Direct-Cast, Titanium Alloy Strip
A promising new technique for direct-casting rapidly solidified titanium alloy strip
was developed by the firm with NASA support. The plasma melt overflow process combines
transferred plasma-arc, skull melting techniques, and melt overflow rapid solidification
technology to direct-cast ribbons and strip. A wide range of alloys can be cast by
the process. After casting a near-net-shape strip, there is still sufficient thickness
to break up the cast microstructure and develop the mechanical and metallurgical
properties by thermal and mechanical processing (TMP) to result in high-quality foils.
This project focuses on the development of techniques to produce TiAl and Ti3Al foils
from direct-cast strip using TMP. The techniques that will be investigated include
direct casting of strip, heat treatment, wet grinding, and pack rolling.
Applications would be in honeycomb panels, metal-matrix composites, turbine exhaust
nozzle flaps, and superalloy foils.
aluminides, titanium, foils, rapid solidification, pack rolling

Project Title:

An Advanced Carbon-Carbon Composite with Improved Interlaminar and Flexure Properties

04.07-1980
911713
An Advanced Carbon-Carbon Composite with Improved Interlaminar and Flexure Properties
and Oxidation Resistance
Materials & Electrochemical Research
7960 South Kolb Road
Tucson
AZ
85706
J. C.
Withers
602-574-1980
LaRC
NAS1-19528
050

04.07-1980
911713

Abstract:

An Advanced Carbon-Carbon Composite with Improved Interlaminar and Flexure Properties
and Oxidation Resistance
Carbon-carbon composites have significant potential for use in airframes, hot structural
applications on advanced hypersonic vehicles, spacecraft, and engines, but have not
reached their potential due to limiting properties of interlaminar and flexure strength
and oxidation resistance. An innovative approach that overcomes these difficulties
utilizes a SiC conversion coating, without or with whiskers, on the graphite reinforcements;
doping of the carbon matrix with a gradation to the surface to inhibit oxidation
and match CTE of a coating system that encompasses a bridge coating; and a proven
oxidation resistant layer and a moisture resistant glaze. A composite-coating system
integrally designed will have substantial increased mechanical and oxidation resistant
properties over current systems.
A carbon-carbon composite with substantially improved interlaminar and flexure properties,
and oxidation resistance will have broad usage in airframes, space structures, engines,
brakes, dies, and so on.
carbon-carbon composites, coatings, plasma deposition, SiC coatings.

Project Title:

Real-Time Monitoring and Analysis of Thermal Spray Processes Using Machine Vision

04.08-7900
910998
Real-Time Monitoring and Analysis of Thermal Spray Processes Using Machine Vision
Automatix, Inc./Control Vision, Inc. - Joint Venture
755 Middlesex Turnpike
Billerica
MA
01821
John
Agapakis
508-667-7900
MSFC
NAS8-39306
051

04.08-7900
910998

Abstract:

Real-Time Monitoring and Analysis of Thermal Spray Processes Using Machine Vision
The objective of this project is to develop innovative vision-sensing and processing
techniques that can be used for real-time visual monitoring and analysis of thermal
spray processes. Process R&D and real-time control for high-temperature material
coating processes are the main applications of the project. The same monitoring and
analysis technology can also find use in spray forming applications. The innovative
viewing system suppresses the intense light of the flame or plasma in the video image
and allows direct observation of the traveling coating particles. The advanced image
processing and analysis schemes will allow in-process determination of important
quantitative measures such as the pattern and gross velocity of the particle stream,
the velocity of individual particles, the powder mass flow rate, the geometry and
turbulence of the plasma or flame, and possibly the temperature of particle populations.
Phase I will include a brief review of related work, and analysis of application
requirements, particularly focusing on NASA needs, an investigation and prototyping
of the proposed vision sensing approaches, and investigation and prototyping of vision
processing approaches. On the basis of the above, needs for future R&D will be identified
and the Phase II effort will be planned.
In addition to direct benefits to NASA and the aerospace industry, where thermal
coatings are widely used in advanced propulsion system components, the project has
immediate applications in jet engine manufacture, overhaul, and repair in which thermal
spray coatings are also widely applied.
thermal spraying, monitoring, control, vision sensing, image processing

Project Title:

A Unique Silicon-Carbide Reusable Thermal Protection Material

04.09-1980
912063
A Unique Silicon-Carbide Reusable Thermal Protection Material
Materials & Electrochemical Research
7960 South Kolb Road
Tucson
AZ
85706
Raouf O.
Loutfy
602-574-1980
JSC
NAS9-18691
052

04.09-1980
912063

Abstract:

Novel Thermal Protection Materials
A new and unique process, chemical vapor reaction (CVR), to convert graphite structures
to low-density SiC structures will be investigated to produce high-temperature thermal
protection materials. Available heat shield materials have temperature limitations
of about 2500F and extremely low mechanical properties. In this project net-shape,
low-density SiC with excellent strength, excellent thermal shock resistance, high
emissivity, high-temperature capability, and low thermal conductivity will be developed.
The properties of the SiC will be optimized by investigating the effect of the graphite
precursor's density and microstructure and the effect of CVR process operating parameters.
The CVR-SiC materials will also be CVD SiC coated to improve ablation resistance.
Test specimens will be fabricated and fully characterized, and samples will be delivered
to NASA for evaluation.
In addition to a structural insulation for use on the Space Shuttle and other re-entry
vehicles, a high-temperature structural insulation will have commercial applications
as thermal barrier coatings in gas turbine engines, spark ignition and diesel engines,
furnace insulation, and so on.
insulation, composites, 3000F, SiC

Project Title:

Ion-Beam-Modified, Atomic-Oxygen-Resistant Lubricious Surfaces

04.12-2437
910260
Ion-Beam-Modified, Atomic-Oxygen-Resistant Lubricious Surfaces
First Omega Group, Inc.
10205 West Exposition Avenue
Lakewood
CO
80226-3912
Ronghua
Wei
303-986-2437
MSFC
NAS8-39317
056

04.12-2437
910260

Abstract:

Ion-Beam-Modified, Atomic-Oxygen-Resistant Lubricous Surfaces
Lubricous wear surfaces will be developed for use on mechanisms exposed to low-Earth
orbit environment for extended periods. Such lubricous surfaces are expected to have
long wear and excellent resistance to atomic oxygen degradation. The wear surfaces
are created by ion-deposited, diamond-like carbon film and/or ion-implanted chromium
or chromium plus oxygen. The ion-beam processing and implantation equipment to be
used for this work is unique in that it employs large-diameter ion-beams of very
high current density. A novel controlled environment tribotester, capable of providing
simulated atomic oxygen environment around the wear tested surfaces, will be used
for evaluations. Expected Phase I and II results are surface modification process
and evaluation techniques sufficiently developed that NASA may confidently specify
the process to create lubricous surfaces on mechanical elements for use in long-duration,
low-earth orbit applications such as Space Station Freedom.
A surface treatment process that makes surfaces long wearing, lubricous, and resistant
to oxygen degradation will provide superior performance in critical civilian and
government terrestrial applications.
ion, deposition, implantation, atomic-oxygen, lubricous, DLC

Project Title:

Solid Lubricants for Aeronautics and Space Applications

04.12-3200
912096
Solid Lubricants for Aeronautics and Space Applications
Foster-Miller, Inc.
350 Second Avenue
Waltham
MA
02154-1196
Philip
Stark
617-890-3200
MSFC
NAS8-39320
057

04.12-3200
912096

Abstract:

Solid Lubricants for Aeronautics and Space Applications
This project investigates the use of improved cubic boron nitride (CBN) thin-films
as solid lubricants for long-term NASA space missions. The improved films are deposits
using the novel technique of laser ablation. The benefit expected is a new solid
lubricant film with significantly greater atomic oxygen resistance and longer life
than currently available in commercial products. CBN exhibits exceptional durability,
hardness second only to diamond, ultrahigh resistance to wear, and relatively low
coefficient of friction. Its resistance to attack by atomic oxygen should be better
than diamond. In addition, CBN thin-films can be deposited at temperatures significantly
lower than diamond films and on a greater variety of substrates. This unique combination
of properties makes CBN a prime candidate for use as a solid lubricant in long-term
space applications. Phase I will demonstrate the effectiveness of CBN as a solid
lubricant for NASA space applications. Commercially available, polycrystalline CBN
(pCBN) will be characterized in terms of its tribiological properties in the as-received
condition and after being subjected to atomic oxygen exposure. Simultaneously, pCBN
thin films will be fabricated by laser ablation and their performance compared to
bulk pCBN and commercially available (non-laser ablated) pCBN films.
Commercial applications would exist in the areas of aerospace structural components,
automotive engine components, machine tools, and fossil fuel recovery, and would
include solid lubricant coatings for a variety of mechanisms including gears, bearings,
pistons, actuators, and the like.
cubic boron nitride, solid lubricants, atomic oxygen protection, thin-films, friction
and wear

Project Title:

Space Welding Power Control Unit

04.14-9500
911880
Space Welding Power Control Unit
Space Power, Inc.
621 River Oaks Pkwy
San Jose
CA
95134
See-Pok
Wong
408-434-9500
MSFC
NAS8-39341
061

04.14-9500
911880

Abstract:

Space Welding Power Control Unit
Space welding capability will be needed for maintaining, repairing, or constructing
spacecraft in space. The former Soviet Union has already performed welding in space
successfully. Furthermore, future spacecraft will have enough power on board for
welding. A cost-effective approach to obtain a space-use welding power control unit
by adapting a power conditioning unit (PCU) from an arcjet electric propulsion system
for spacecraft will be pursued. Arcjet and welding are both gaseous discharge with
very similar load characteristics and power source requirements. The firm, a developer
for high-power arcjet PCUs, is currently working on an Air Force program to develop
a flight-qualified arcjet system. Welding has been performed successfully with an
arcjet PCU breadboard without any modification. The efficiency of this breadboard
is well above 96 percent; the specific mass is less than 1.5 kg/kw. In Phase II,
a flight-prototype space welding control unit will be built and will be ready for
full space qualification. This will enable NASA to perform welding in space.
Welding in space can be used to repair or construct military spacecraft as well as
commercial satellites. The compact, lightweight, and high-efficiency space welding
system could also be modified to an attractive portable welding system for hard to
reach areas in nuclear reactors or, other field applications.
space welding, use arc PCU technology, cost-effective

Project Title:

Graphite-Magnesium, Metal-Matrix-Composites for Space Structural Joints with Built-In

04.15-3200
912106
Graphite-Magnesium, Metal-Matrix-Composites for Space Structural Joints with Built-In
Metallic Inserts
Foster-Miller, Inc.
350 Second Avenue
Waltham
MA
02154-1196
Uday
Kashalikar
617-890-3200
MSFC
NAS8-39319
062

04.15-3200
912106

Abstract:

Graphite-Magnesium, Metal-Matrix-Composites for Space Structural Joints with Built-In
Metallic Inserts
A low-cost MMC fabrication method for net-shape fabrication of space structural joints
with built-in metallic inserts will be developed. Two innovations will be demonstrated
during Phase I: low-cost, reusable tooling to pressure cast Gr-Mg components to net
shape, and "built-in" metallic inserts in the component to produce strong and reliable
MMC joints using conventional metal joining. The firm has pressure cast Gr-Al and
Gr-Mg components exhibiting a complete preform infiltration and a controlled fiber-matrix
interface chemistry. The MMC specimens have shown rule-of-mixtures modulus and a
high strength (>100 ksi). The major issues that need to be resolved to encourage
widespread utilization of MMCs in space systems are reducing the cost of tooling
and processing, and developing joining techniques for MMC parts by virtue of its
reusability. Incorporation of metallic inserts will enable assembly of the MMC components
using existing techniques such as welding, bolting, brazing, and so on. A complex
shaped Gr-Mg joint component with metallic fittings will be selected, fabricated,
and evaluated during Phase I. The process will be optimized to demonstrate repeatability
in component properties during Phase II.
The successful development of low-cost, easily "joinable" Gr-Mg components will open
up commercial applications in automotive and aircraft engines, avionics and electronic
packages as well as in high-performance sporting equipment. Phase I will identify
candidate commercial applications that will be further investigated during Phase
II.
The successful development of low-cost, easily "joinable" Gr-Mg components will open
up commercial applications in automotive and aircraft engines, avionics and electronic
packages as well as in high-performance sporting equipment. Phase I will identify
candidate commercial applications that will be further investigated during Phase
II.
pressure casting, Gr-Mg, metal-matrix composites, space structures, joints, built-in
inserts, fittings, tooling

Project Title:

Laser-Based Detection of Contamination on Adhesive Bonding Surfaces

04.17-0003
911269
Laser-Based Detection of Contamination on Adhesive Bonding Surfaces
Physical Sciences, Inc.
20 New England Business Ctr
Andover
MA
01810
Victor
Dicristina
508-689-0003
LaRC
NAS1-19535
065

04.17-0003
911269

Abstract:

Laser-Based Detection of Contamination on Adhesive Bonding Surfaces
The use of lightweight metallic and composite materials in structures that must function
under extremes of temperature, pressure, and loading presents new challenges to design
engineers. These materials range from common metals to metal-matrix composites as
well as carbon- and silica-based composites. In the joining of these multilayer materials
and the welding of advanced metals, the cleanliness of the interface can play a large
role in the strength of the resulting bond. Through the excitation of fluorescence
in the contaminants by UV light and photoelectric detection methods, a non-destructive
imaging technique for the detection of contaminants that hinder surface bonding will
be developed. Unlike previous applications of this method, a commercially available
UV laser coupled to an image-intensified TV camera to obtain rapid real-time images
of large structures, regardless of shape, will be applied. In addition to inspection,
the system can be employed to remove contaminants via laser ablation and/or vaporization
without damage to the underlying material. Phase I will test the sensitivity of the
detection method for contaminants of interest on aluminum substrates, demonstrate
laser removal of contaminants, and define a prototype system for development in Phase
II.
Applications would be in inspection and preparation of metals prior to welding or
brazing; contamination detection in the manufacture of layered composite structures,
adhesive bonding of composites, and surfaces prepared for film deposition; and detection
of contaminants on optical surfaces, semiconductor wafers, and magnetic storage media.
contamination, bonding, welding, imaging, process control, manufacturing, non-destructive
evaluation

Project Title:

Nondestructive Analysis of Graphite-Reinforced Materials

04.17-1167
911460
Nondestructive Analysis of Graphite-Reinforced Materials
Radiation Monitoring Devices, Inc.
44 Hunt Street
Watertown
MA
02172
Michael R.
Squillante
617-926-1167
LaRC
NAS1-19539
066

04.17-1167
911460

Abstract:

Non-Destructive Analysis of Graphite-Reinforced Materials
The advent of graphite-reinforced composites has led to major advances in aerospace
technology. Such composite materials are becoming essential to modern flight technology
due to their exceptionally high strength-to-weight ratios when compared to metals
and alloys. Many aircraft and rocket components are currently made from these new
materials and many new developments require their unique properties. The use of graphite-reinforced
materials (GRM) in aerospace applications has resulted in higher quality materials
to meet more demanding performance specifications. As a result, there is a requirement
for advances in non-destructive inspection equipment to provide accurate, real-time
composition analysis of these composites. Since the properties of these composites
are strongly dependent on the ratio of graphite filler to binding resin, a reliable
non-destructive technique for the determination of the resin to graphite ratio of
GRM in both prepreg and cured forms is essential. To ensure that GRM are suitably
made, a radiometric non-destructive instrument allowing the accurate determination
of resin constant in both prepreg and final composites will be developed. The instrument
will be useful not only for quality assurance but also for failure analysis of key
components and structures.
The graphite composite analyzer will find numerous applications in the manufacturing
of composites. It will not only improve component performance but will reduce the
manufacturing cost by reducing the number of rejected parts.
non-destructive testing, graphite, composites, radiography

Project Title:

New Digital Radiography System for Nondestructive Testing

04.17-2701
911473
New Digital Radiography System for Nondestructive Testing
Quantex Corporation
2 Research Court
Rockville
MD
20850
Peter K.
Soltani
301-258-2701
LaRC
NAS1-19538
067

04.17-2701
911473

Abstract:

New Digital Radiography System for Non-Destructive Testing
This project addresses a new technology for the digital radiography employing a patented
storage-phosphor material. Planar screens fabricated from this material can acquire
radiation images in much the same way as radiographic film, with the key exception
that the images are obtained digitally. This innovative technology will be superior
to radiographic film, in that it exhibits a linear response over a radiation exposure
range of 100,000:1, exhibits potentially greater exposure sensitivity, and can be
re-used. Because of these properties, the storage-phosphor imaging screens can be
calibrated to allow quantitative analysis of structural changes in engineering materials
and components, as well as precise flaw detection and characterization. The objective
of this project will be to demonstrate the specific characteristics of the technology
in radiographic imaging. These will include quantification of performance characteristics
relative to film and current digital radiography systems, such as fluoroscopy and
related scintillator-based system. These will lead to the development of a prototype,
digital radiography system during Phase II that can be used by NASA to perform quantitative
non-destructive evaluation of structural components.
A digital radiography system is expected to be useful in aerospace applications (e.g.,
inspection of aircraft structures), power generation facilities, inspection of composite
and electronic components, and generally in any industry that currently employs radiography
as an inspection method.
radiography, digital imaging, non-destructive testing

Project Title:

Low Outgassing Marking Inks

04.18-4334C
910215
Low Outgassing Marking Inks
Utility Development Corporation
112 Naylon Avenue
Livingston
NJ
07039
Harry S.
Katz
201-994-4334
GSFC
NAS5-31885
068

04.18-4334C
910215

Abstract:

Low-Outgassing Marking Inks
Low-outgassing marking inks that can be applied by silk screen, spray, brush, or
stamping and possess good chemical and abrasion resistance will be developed. This
objective will be achieved by formulating cationic UV-curable epoxies in combination
with photoinitiators, flow control agents, reactive monomers and oligomers, fillers,
and pigments that will be tested for abrasion resistance, chemical resistance, gloss,
flexibility, cure characteristics, and adhesion. Outgassing will be investigated
by determination of weight loss versus time under vacuum at various temperatures.
The solvent-free inks and coatings will have superior abrasion resistance adhesion
to various substrates, low odor, low toxicity, and rapid cure. These products will
be especially useful for packaging industries and printers.
epoxy, abrasion, chemical resistance, cationic, gloss, UV-curable, solvent-free

Project Title:

Adaptive Materials Using Magnetostrictive Actuation

04.21-0540
911677
Adaptive Materials Using Magnetostrictive Actuation
Satcon Technology Corporation
12 Emily Street
Cambridge
MA
02139-4507
Ralph C.
Fenn
617-661-0540
LaRC
NAS1-19542
072

04.21-0540
911677

Abstract:

Adaptive Materials Using Magnetostrictive Actuation
A new class of adaptive materials will be developed using magnetostrictive actuation.
These will provide a superior alternative to piezoelectric materials now under development.
A unique characteristic of magnetostrictive materials is the contactless transfer
of power to the material through magnetic fields. This freedom to separate the electrical
components physically from the actuator material has the advantages of eliminating
both bulky and unreliable embedded power or sensor leads and shorting by conductive
laminations. Physical continuity and integrity of the actuator lamination is unnecessary,
and there is greater shape flexibility by using magnetic field alterations. Many
magnetostrictive materials have the additional benefits of favorable physical properties
that are often lacking in piezoelectric materials, such as toughness, ductility,
and stable properties. Phase I will identify magnetostrictive materials, and various
magnetrostrictive material and field producing geometries will be analyzed. Proof-of-concept
samples will be fabricated and tested for properties of importance to adaptive materials.
Phase II will characterize, validate, and integrate magnetostrictive adaptive materials
into a structure for evaluation of damping, motion, and shape control. Adaptive materials
based on magnetostrictive actuation offer improved reliability, maintainability,
and flexibility over existing materials.

Potential Commercial Application:

Potential Commercial Applications:  Commercial uses of the adaptive materials include
active vehicle suspension, active structural control, vibration and noise isolation,
precision industrial position systems, and ultra-precision machining applications.
adaptive materials, smart materials, magnetostriction, intelligent structures

Project Title:

Novel Design for Lunar-Magma Electrolysis Cell

04.23-8899
910187
Novel Design for Lunar-Magma Electrolysis Cell
Carbotek, Inc.
16223 Park Row, Suite 100
Houston
TX
77084
Michael A.
Gibson
713-578-8899
JSC
NAS9-18685
076

04.23-8899
910187

Abstract:

Novel Design for Lunar-Magma Electrolysis Cell
The firm will develop a new configuration for an electrolytic cell to produce oxygen
and metal by-products from lunar soil. This design uses ideas adapted from industrial
experience in alumina electrolysis, coal gasification, and ferrosilicon alloy production.
The design addresses most of the severe operability issues raised by such a cell.
These include melt containment, low-melt conductivity, anode-gas blanketing, control
of levels and temperature, and the continuous removal of waste heat and molten, corrosive
by-products. The new cell design features are coolant passages in the refractory
walls to provide a thin, frozen layer protecting removal; platinum screen anodes
tilted slightly from the horizontal to promote oxygen bubble removal while still
minimizing anode-cathode distances; local heating/cooling at the molten spent magma
taphole to regulate outflow rates by local temperature/viscosity control rather than
valves; a sliding refractory gate valve for molten ferrosilicon layer level control.
Phase I will identify the power/volume needs of the new cell and will complete the
design of a benchscale experimental cell for testing in Phase II.
Materials and techniques found successful in a magma electrolysis cell may be applied
in alumina electrolysis, refractory  manufacture, metals processing, and other processes
requiring corrosive, high-temperature conditions.
lunar oxygen, magma electrolysis, refractory selection

Project Title:

Fast Three-Dimensional Imaging

05.01-2407
910097
Fast Three-Dimensional Imaging
Intelligent Automation, Inc.
1370 Piccard Drive, Suite 210
Rockville
MD
20850
Leonard S.
Haynes
301-990-2407
MSFC
NAS8-39325
077

05.01-2407
910097

Abstract:

Fast Three-Dimensional Imaging
Today's robots use cameras to capture images of the objects to be manipulated by
the robots, and attempt to use that image data to learn the exact position of parts,
identify problems, inspect parts, detect proximity, and perform other tasks. One
of the factors that limits the use of machine vision in manufacturing environments
is that camera images are two-dimensional, and the objects to be manipulated are
three-dimensional. Three-dimensional information is essential in most realistic applications;
hence numerous techniques have been tried to generate depth information from two-dimensional
camera images. None of these techniques are acceptable for factory application because
they are slow, costly, unusable where objects are specular, and\or inaccurate. This
project addresses how to implement a "smart camera" that will generate a full-range
map of a manufacturing scene in real time with virtually no computation required.
The same camera will also continue to function as a normal intensity-based camera
and can be switched from intensity to range mode by switching a single binary line.
This new type of camera is named the FAST 3-D Imaging Camera (F3DI).
F3DI will provide an entirely new capability not possible with any other technology
at any cost. There are obvious applications for robotics, in situations in which
a robot uses visual information for sensory feedback, and for automatically guided
vehicles.
range image, Fast 3D Imaging, F3DI, depth perception, robot visions

Project Title:

Adaptive Wavelet Image Processing

05.01-2577
912031
Adaptive Wavelet Image Processing
Fastman, Inc.
1414 Millard Street
Bethlehem
PA
18018
Michael
Tucker
215-691-2577
MSFC
NAS8-39316
078

05.01-2577
912031

Abstract:

Adaptive, Wavelet Image Processing
The firm has recently developed the adaptive wavelet transform (AWT) and has shown
that the AWT is very adept at extracting features from complex one-dimensional signals
even in the presence of noise. This project will determine the ability of the AWT
to extract features from images in the presence of noise and variable lighting conditions.
Phase I will assess the feasibility of utilizing the AWT for robust image feature
detection by extending the current one-dimensional AWT software code to two dimensions;
by demonstrating the ability of the AWT to decompose images into basis elements highly
related to the images' features; by determining how to combine currently used pattern
classification and neural networks with an adaptive wavelet preprocessor to detect
object regions; and by investigating real-time operation of the AWT.
This research will lead to advances in real-time spectral analysis for many commercial
and NASA applications, including image processing and speech processing monitoring
of machine vibration signals. It can also provide high-ratio data compression for
telephone answering machines, voice mail systems, cellular phones, fax machines,
teleconferencing equipment, and other equipment.
wavelet transform, image processing, feature detection

Project Title:

Tactile Displays for Whole-Arm Manipulators

05.02-5042
912315
Tactile Displays for Whole-Arm Manipulators
Begej Corporation
5 Claret Ash Road
Littleton
CO
80127
Stefan
Begej
303-973-5042
JSC
NAS9-18704
083

05.02-5402
912315

Abstract:

Tactile Displays for Whole-Arm Manipulators
The use of tactile sensory data for the control of whole-arm manipulators (WAMs)
is hampered by a lack of suitable devices capable of providing tactile feedback to
the operator. The objective of Phase I is to address this problem by undertaking
the development of an innovative tactile display specifically designed for application
to WAM systems. The work scope includes the formulation of design specifications
for a WAM forearm display; performance of advanced development upon tactile display
technology previously developed at the firm; development of a thin, flexible matrix
in which the tactile display elements ("tixels") are to be embedded; fabrication
of a 5x12 tactile display array for a lower WAM forearm; fabrication of an advanced
display driver; assembly and testing of the display system; preparation of the final
report; and delivery of the WAM forearm tactile display prototype to the sponsor
for further evaluation. Phase II will deliver a complete tactile display system (upper
and lower forearms, chest, and stomach) to NASA in support of ongoing WAM programs.
Important markets are foreseen in industries involving remote manipulation of large
objects in toxic, pressurized, or thermally extreme environments, e.g., space operations;
handling of toxic chemical or biological materials; undersea mining or salvage operations;
hot-object handling during manufacturing operations; and operations in extreme cold-weather
regions.
whole-arm manipulators, tactile displays, tactile sensors, tactile telepresence,
telerobotics

Project Title:

Advanced Induction Servomotor

05.03-0540
911676
Advanced Induction Servomotor
Satcon Technology Corporation
12 Emily Street
Cambridge
MA
02139-4507
Richard L.
Hockney
617-661-0540
JSC
NAS9-18673
086

05.03-0540
911676

Abstract:

Advanced Induction Servomotor
This project will design, fabricate, and demonstrate an advanced induction servomotor
and control system concept having high positioning precision coupled with outstanding
electrical noise characteristics. The concept will incorporate a unique multi-disk,
axial air-gap induction motor driven by a resonant converter operating at 20 kHz.
The resonant converter uses pulse-population-density modulation to both operate the
induction motor as an extremely power-dense and efficient, four-quadrant, variable-speed
actuator and to actively suppress output shaft torque ripple. The pulse-population-density
modulation approach provides inherent suppression of electromagnetic interference
(EMI) while minimizing required filtering and shielding. The control system will
be sensorless, providing feedback control based on estimated motor state. The project
will result in a space-certifiable design having a combination of small size, low
EMI, and low harmonic levels not previously possible with brushless servomotors.
Phase I will provide a preliminary design and detailed planning for Phase II. Phase
II will construct a prototype unit for testing based on the preliminary design developed
in Phase I.
The project's goal is to reduce the weight of robotic systems by improving the efficiency
and reducing the weight of the electrical distribution and drive system. In addition,
the development of improved electro-mechanical drives will have application to aircraft,
commercial ships, and industrial controls.
electromagnetic, resonant converter, actuator, induction motor, control

Project Title:

Magnetostrictive Bi-Directional Linear Actuator

05.03-2407
910096
Magnetostrictive Bi-Directional Linear Actuator
Intelligent Automation, Inc.
1370 Piccard Drive, Suite 210
Rockville
MD
20850
Leonard S.
Haynes
301-990-2407
LaRC
NAS1-19526
088

05.03-2407
910096

Abstract:

Magnetostrictive Bi-Directional Linear Actuator
This project involves the conceptual design of a hydraulic bi-directional linear
actuator. A "hydraulic actuator" built using the firm's concept would require no
separate hydraulic power source, no hydraulic valves of any kind, would have much
higher frequency response and resolution than conventional technology, would be fast,
and able to exert large forces. Resolutions of .00002 inches with velocities of 100
inches per second are achievable with bandwidths exceeding 1000 hertz. There is no
other linear actuator technology that can come even close to this performance.
This system represents an entirely new class of hydraulic actuator that could also
be used as a pump. If optimized for resolution, it could be used to meter fluids
or gases at high resolution. If built larger and optimized for flow rate, it could
be used as an ultra-quiet (no propeller and no moving parts) propulsion system for
torpedoes or similar ordnance.
linear actuator, pump, hydraulic actuator, naval propulsion system

Project Title:

A Fault-Tolerant, Intelligent, Robotic Control System

05.05-4717
911689
A Fault-Tolerant, Intelligent, Robotic Control System
Sohar, Inc.
8421 Wilshire Boulevard, Suite 201
Beverly Hills
CA
90211-3204
Kam Sing
Tso
213-653-4717
JPL
NAS7-1172
091

05.05-4717
911689

Abstract:

A Fault-Tolerant, Intelligent Robotic Control System
The goal of this project is to develop the application of a distributed fault-tolerant
system architecture for robot control in order to tolerate hardware and software
faults, and a knowledge-based diagnosis and recovery system to tolerate faults due
to operational errors. The underlying architecture to support this research is the
extended distributed recovery block (EDRB). Fault-tolerance provisions already implemented
in the architecture include protection against failures in application software,
system software, hardware, and networks. The knowledge-based system will use the
expert system shell, CLIPS, developed at the NASA Johnson Space Center. Advanced
automation techniques such as rule-based and model-based reasoning will be utilized
to monitor, diagnose, and recover from unexpected events. The two-level design provides
tolerance of two or more faults occurring serially at any level of command, control,
sensing, or actuation. The potential benefits of such a fault-tolerant, robotic control
system include a minimized potential for damage to humans, the work site, and the
robot itself; continuous operation with a minimum of uncommanded motion in the presence
of failures; and more reliable autonomous operation, providing increased efficiency
in the execution of robotic tasks and decreased demand on human operators for controlling
and monitoring the robotic servicing routines.
Fault-tolerant techniques building dependable robotic systems can be used in applications
that require a high degree of reliability and safety, such as servicing tasks in
Space Station Freedom, waste cleanup tasks in nuclear facilities, and patient-tending
tasks in medical facilities. The knowledge-based fault diagnostics and recovery system
can also be used in industrial robots to cope with various unexpected events occurring
during the manufacturing process.
recovery blocks, knowledge-based system, robotic systems, fault-tolerant, fault-diagnosis,
error recovery

Project Title:

Miniature, Fiber-Optic-Coupled Range Scanner

05.06-9200
910854
Miniature, Fiber-Optic-Coupled Range Scanner
Coleman Research Corporation
5950 Lakehurst Drive
Orlando
FL
32819
Dana
Simonson
703-719-9200
LaRC
NAS1-19521
093

05.06-9200
910854

Abstract:

Miniature, Fiber-Optic-Coupled Range Scanner
This project will develop a robust, miniature three-dimensional laser radar for measurement
of steps, gaps, and contours of the Space Shuttle's thermal protection system (TPS).
The approach is a miniature, fiber-optic-coupled, range scanner designed to function
as a three-dimensional, coherent, laser-radar topographical measurement system. This
will result in a robust miniature three-dimensional laser radar suitable for use
with robotic end-effectors. The innovative merger of laser radar technology with
a fiber-coupled GaAs integrated optical solid-state scanner provides a realistic
solution to the problem of TPS measurements. This measurement system will also provide
reflectance data that is independent of background illumination.
Commercial applications include robotic measurement and inspection in confined environments.
laser radar, lidar, inspection, integrated optics

Project Title:

Piranha Parallelism: Distributed Self-Management of Computing Resources in a Network

06.01-7442
912118
Piranha Parallelism: Distributed Self-Management of Computing Resources in a Network
Environment
Scientific Computing Associates, Inc.
One Century Tower, 265 Church St
New Haven
CT
06510-7010
Robert D.
Bjornson
203-777-7442
ARC
NAS2-13556
100

06.01-7442
912118

Abstract:

Piranha Parallelism:  Distributed Self-Management of Computing Resources in a Network
Environment
At the present time, typical large-scale computations may comprise at least three
major steps: input preparation, possibly on modest, text-oriented workstations; numerical
calculation on a large vector or parallel supercomputer; and output examination,
most likely on high-performance graphics workstations. Unfortunately, this entails
very unbalanced utilization of computer hardware. All the workstations are largely
unused (at least in terms of compute-power), and the parallel supercomputer can be
so oversubscribed that users have long waits for available time slots. The goal of
this project is to alleviate this situation. It will exploit networks of workstations
to provide additional supercomputer power through the development of software to
dynamically allocate unused workstation cpu cycles to fill the computational demands
of large jobs. This will be achieved in the framework of a simple and powerful scheduling
model called piranha parallelism. Users will generate parallel tasks following a
fixed format, and the tasks will be released into a network-wide task pool. These
tasks are guaranteed to be attacked by as many computational piranhas (aka workstations)
as have available idle cycles. Phase I will focus on the design and implementation
of a prototype piranha system.
Commercial and government users will see greatly enhanced output on important applications
and will incur far lower hardware acquisition costs, since it will make more effective
use of in-place computers in situations where local area networks of workstations
are rapidly becoming the standard computing environment.
parallel programming, network operating systems, Linda, distributed computing

Project Title:

A Plug-Compatible Architecture for Integrating Heterogeneous, Distributed, Software

06.02-3633
910756
A Plug-Compatible Architecture for Integrating Heterogeneous, Distributed, Software
Development Tools
Symbiotics, Inc.
725 Concord Avenue
Cambridge
MA
02138
Robert C.
Paslay
617-876-3635
GSFC
NAS5-31920
103

06.02-3633
910756

Abstract:

A Plug-Compatible Architecture for Integrating Heterogeneous, Distributed, Software
Development Tools
A multitude of useful tools exist for designing, testing, operating, maintaining,
and managing large software systems. Unfortunately, tools that support particular
system development tasks (e.g., requirements specification and traceability analysis)
are typically implemented independently by different vendors with little consideration
for the life-cycle process as a whole. Accordingly, these tools are implemented with
idiosyncratic data models and with data and control interfaces using different programming
languages and running on heterogeneous processors. An innovative architecture for
nonintrusively integrating disparate program tools into a unified software engineering
and management environment will be designed. Specific technical innovations will
be the application of object-oriented technologies to conceal tool-specific interfaces;
to map transparently across incompatible data mode; to integrate tools transparently
across heterogeneous computing environments; and to obtain plug-compatibility, wherein
any tool, once integrated, can interact freely with any other tool connected to the
framework as full peers. The resulting architecture will enable NASA to unify disparate
software tools in domains such as software development, scientific data analysis,
and decision support.
The technology can be used to integrate new and previously isolated software applications
in domains such as concurrent engineering, software engineering and management, office
automation, and automated operations support of complex systems (e.g., communications
networks).
object-oriented programming, software engineering, system integration, plug compatibility,
distributed systems

Project Title:

Intelligent Pen-Based Engineering Notebook

06.03-3370
911928
Intelligent Pen-Based Engineering Notebook
Software Productivity Solutions, Inc.
122 North 4th Avenue
Indialantic
FL
32903
Vincent J.
Kovarik
407-984-3370
LaRC
NAS1-19546
105

06.03-3370
911928

Abstract:

Intelligent Pen-Based Engineering Notebook
Systems engineering is a highly complex technical skill. Yet, the process of developing
a successful system design is very informal. The engineer often shifts between technical
research, mathematical analysis, group coordination, end-user interface, and other
activities. Because of this highly fluid work style, the engineering notebook has
remained the primary means for the engineer to capture and to retain analyses, decisions,
and rationale for projects. Unfortunately, the notebook is an extremely inefficient
method for transferring the information captured to the work products. For example,
requirements specifications must still be entered into a word processor to obtain
a requirements document. This project will investigate the development of an intelligent
assistant for the systems engineer within a pen-based computer. This assistant will
employ knowledged-based technology to perform tasks such as hypertext link formation
between requirements penciled in the notebook and the presentation of those requirements
in a document. In the software development domain, this will allow the engineer to
develop pencil sketches of a relational database organization, to move that to a
specification document and by external interface with an expert system on a workstation,
transform the graphical notation into data definition statements.
Virtually any domain that involves shifts between modes of operation, informal capture
of technical information, mobility can benefit from this technology. Civil engineers,
research scientists, software developers, process control designers can apply this
technology.
systems engineering, knowledge-based systems, pen-based computers, intelligent assistant

Project Title:

A Software Engineering Approach Towards Validation of Knowledge-Based Systems

06.04-1400
911831
A Software Engineering Approach Towards Validation of Knowledge-Based Systems
Vigyan, Inc.
30 Research Drive
Hampton
VA
23666-1325
Mala
Mehrotra
804-865-1400
JSC
NAS9-18706
107

06.04-1400
911831

Abstract:

A Software Engineering Approach Towards Validation of Knowledge-Based Systems
Currently, most expert-system shells do not address software engineering issues for
developing, maintaining, and verifying expert systems. As a result, large expert
systems tend to be incomprehensible, difficult to debug or to modify, and almost
impossible to verify or to validate. Partitioning rule-based systems into rule groups
that reflect the underlying subdomains of the problem should enhance the comprehensibility,
maintainability, and reliability of expert-system software. The firm will automatically
structure a given rule base so that verification-aid tools can test the behavior
of each of these subunits individually, as well as in relationship to each other.
Preliminary studies of rule-based structuring have provided insight into the various
parameters that affect the grouping process and have shown the feasibility of this
approach. More analysis will need to be done to understand the interplay of distance
metrics, clustering strategies, various objective functions to be optimized for grouping,
and evaluation criteria used to judge the quality of the resultant groups. A significant
secondary benefit of this approach will be the formulation of software engineering
guidelines to aid the grouping process. Such an environment would help in the verification
and validation of knowledge-based systems, allowing them to be used in commercial
and critical applications with more confidence.
Currently, expert systems cannot be used in critical applications since they are
not amenable to existing verification and validation techniques. An integrated environment
for expert system verification and validation can overcome this barrier thus opening
up a wide range of important applications.
rule groups, verification, validation, knowledge-based systems, clustering, pattern-matching

Project Title:

Realistic Virtual Environment Workstation

06.05-8500A
912222
Realistic Virtual Environment Workstation
KMS
P.O. Box 1567
Ann Arbor
MI
48106-1567
Frederick S.
Schebor
313-769-8500
JSC
NAS9-18696
111

06.05-8500A
912222

Abstract:

Realistic Virtual Environment Workstation
Recently developed virtual-world, heads-on displays have significantly increased
the potential of using computer-generated graphical environments for training and
operational scenarios. To enter a virtual-world environment, an operator wears a
head-mounted, stereo video display that provides a view of the objects and backgrounds
of the virtual-world environment as generated by a color graphics workstation. Head
motion is monitored and is used to control the operator's view within the environment.
Unfortunately, current virtual-world environments are far from realistic, providing
only rudimentary graphical representations of objects. This project plans to dramatically
increase the fidelity, usability, and cost-performance of virtual world simulations
by designing a real-world scanning system, REALVIEW, that will optimize the "feel"
of a virtual world by importing real objects and backgrounds into virtual world environments.
Specifically, the firm will design object grabber, background grabber, and world
editor/viewer subsystems that will allow existing objects and scenes to be captured,
stored, modified, and rendered in a virtual world. With these tools, an operator
will be able to easily create or modify virtual world simulations by manipulating
the objects and backgrounds acquired by REALVIEW.
The fidelity, usability, and cost-performance of virtual-world simulation make it
suitable for substantial commercial applications in such areas as teleoperated and
telerobotic systems that depend on realistic simulations.
computer graphics, virtual world, virtual reality, heads-on display, data glove

Project Title:

A CASE Tool for Intelligent Diagnosis of Space Flight System Faults

06.07-3474
911761
A CASE Tool for Intelligent Diagnosis of Space Flight System Faults
Charles River Analytics, Inc.
55 Wheeler Street
Cambridge
MA
02138
Alper K.
Caglayan
617-491-3474
GSFC
NAS5-31938
114

06.07-3474
911761

Abstract:

A CASE Tool for Intelligent Diagnosis of Space Flight System Faults
Since computing systems are crucial components of space flight systems, the detection
and the isolation of flight software and hardware faults are critical in space-flight
data systems. Although modest progress has been made in improving hardware and software
reliability, there is currently a need for intelligent, fault-diagnosis in space-flight
data systems to allow for increased reliability, availability, and maintainability.
What is needed is a computer-aided software engineering (CASE) tool for intelligent
fault-diagnosis that incorporates the practical techniques from software fault-tolerance
in a knowledge-based expert system framework. The goal of this project is to develop
a CASE tool for intelligent fault-diagnosis using an in-house expert system shell.
The approach will allow the incorporation of software fault-tolerance techniques
into a knowledge-based expert system and demonstrate the feasibility of developing
a CASE tool for building an intelligent fault-diagnosis system in space-flight data
applications.
Commercial application would be a CASE tool assisting the implementation of intelligent
fault-diagnosis systems targeted to aerospace, electrical, mechanical, and chemical
engineering markets by federal contractors, government, and university research laboratories.
intelligent systems, fault diagnosis, expert systems, space, data

Project Title:

Bacteriorhodospin, Spatial Light Modulators for Optical Processing

06.08-4100
910813
Bacteriorhodospin, Spatial Light Modulators for Optical Processing
Bend Research
64550 Research Road
Bend
OR
97701-8599
Dwayne T.
Friesen
503-382-4100
ARC
NAS2-13529
115

06.08-4100
910813

Abstract:

Bacteriorhodopsin, Spatial Light Modulators for Optical Processing
This project addresses the need for better spatial light modulators (SLMs) for use
in robotic vision, autonomous lander guidance, and spectral data analysis. An improved
SLM based on bacteriorhodopsin (BR), an organic material of biological origin with
unusual photochromic properties, will be developed. This will be optically addressable
and will offer the potential for high-resolution, high-speed updatability, and high
contrast. To demonstrate the potential of these BR-SLMs, it will be necessary to
fabricate high-optical-quality films of BR. Phase I will be focused on making and
optically testing films of BR. Phase II will demonstrate a prototype BR-SLM that
has high resolution, high-speed updatability, high contrast and the capability of
these devices in an optical-processor application.
High-quality BR-SLMs will be broadly useful in constructing optical computing devices
that are programmable in real time. Such devices could be used for pattern recognition,
synthetic aperture radar, and optical processors and also to implement artificial
neural networks. Holographic elements based on BR could be used for reconfigurable
optical interconnects, associative holographic memory, manufacturing-processing monitoring,
and dynamic-phase conjugate filters.
spatial light modulator, photochromic, bacteriorhodopsin, optical processor

Project Title:

Universal Spatial Light Modulator

06.08-8933
912065
Universal Spatial Light Modulator
Displaytech, Inc.
2200 Central Avenue
Boulder
CO
80301
Mark A.
Handschy
303-449-8933
ARC
NAS2-13530
117

06.08-8933
912065

Abstract:

Universal Spatial Light Modulator
The proposed work aims to develop "smart" spatial light modulators (SLMs) that integrate
photodetectors, light modulators, and electronic intra- and intercell processing.
These SLMs exploit a hybrid optoelectronic technology that places ferroelectric liquid
crystal (FLC) light modulators directly atop silicon VLSI circuitry. A small, prototype
FLC-VLSI SLM will be designed and fabricated implementing an innovative "universal"
function: it would be addressed either electrically or optically, and it would provide
programmable image thresholding, subtraction, memory, and inversion. The Phase I
prototype SLM should have an array size of 16 x 16 or greater and a frame update
rate greater than 1 kHz. This prototype will include pixel circuit design and simulation,
VLSI layout, silicon integrated circuit (IC) fabrication, fabrication of FLC modulators
atop the IC, and characterization of the resulting SLM. Phase II should result in
arrays sizes of 256 x 256 or greater with contrast better than 200:1 and frame rates
in excess of 10 kHz. The resulting SLMs will be no larger than a packaged integrated
circuit like a microprocessor and will require no specialized driver circuitry beyond
a standard logic-level interface.
The SLMs should find use in myriad optical processing applications such as correlators
and morphological processors. Foreseen commercial applications include use as input
devices in optical digital memory systems and as miniature displays suitable for
projection or head-mounted virtual reality environments.
spatial light modulator, ferroelectric liquid crystal, optoelectronics, optical signal
processing, image processing, optical computing

Project Title:

Extraction of Design Information from Three-Dimensional, Computerized Tomography

06.09-7780
911136
Extraction of Design Information from Three-Dimensional, Computerized Tomography
Data
Advanced Research & Applications Corporation
425 Lakeside Drive
Sunnyvale
CA
94086
Nicolas J.
Dusaussoy
408-733-7780
MSFC
NAS8-39301
118

06.09-7780
911136

Abstract:

Extraction of Design Information from Three-Dimensional, Computerized Tomography
Data
An innovative approach for generating computer-automated design (CAD) and computer-automated
manufacturing (CAM) models from volumetric computerized tomography (CT) data will
be developed. This innovation relies on novel image processing algorithms for meshing
surfaces and on advanced CT techniques for extracting subpixel surface information.
This project addresses important deficiencies currently precluding the automation
of stress analysis, model replication, and failure analysis of flawed parts from
CT data. Such methods that have been shown to be applicable to advanced composites
rely on coupling an accurate three-dimensional geometric description of the part
inspected (CAD/CAM) and the associated material information extracted from the CT
data into an appropriate finite element model (FEM). The project will enable the
execution of both of these critical functions in an adaptive fashion.
The availability of an accurate, adaptive data link between the unique quantitative
nature of volumetric CT data bases and CAD/CAM and FEM modeling capabilities should
have a significant impact on the fields of industrial stress analysis and design,
reverse engineering and model replication, and failure analysis. A commercial software
package would allow users to take better advantage of the installed and growing base
of industrial CT systems.
computerized tomography (CT), computer-automated design (CAD), computer-automated
manufacturing (CAM), finite-element method (FEM), computer graphics

Project Title:

Adaptive Ray-Tracing of Time-Dependent Flows on Massively Parallel Computers

07.02-1400
911832
Adaptive Ray-Tracing of Time-Dependent Flows on Massively Parallel Computers
Vigyan, Inc.
30 Research Drive
Hampton
VA
23666-1325
P.
Sundaram
804-865-1400
GSFC
NAS5-31919
120

07.02-1400
911832

Abstract:

Adaptive Ray-Tracing of Time-Dependent Flows on Massively Parallel Computers
A robust and adaptive ray-tracing algorithm for visualizing the volumetric data obtained
from time-varying numerical or experimental simulation will be developed. The ray
tracer will be adapted based on a neighborhood model of a suitable function for color
and opacity determination. The algorithm is attractive for a massively parallel computer.
The method is voxel-based and suitable for arbitrarily shaped lattices. In this method
the rendering pipeline is divided into two independent shading and classificate segments
in order to eliminate the inaccuracies in opacities that adversely influence the
color, and vice versa. The voxel value of color and opacity are approximated in a
trilinear fashion to obtain these values inside the lattice along the ray's path.
Phong shading and empirical illumination models are also incorporated into the method.
The adaptive ray tracer will be implemented on the SIMD-architecture MarPar's MP-1
computer. An unsteady Navier-Stokes solver will be used to yield the temporal change
of the data to test the present adaptive visualization algorithm. The actual task
of integrating the time-accurate numerical computation and the visualization on the
MPC will be attempted during Phase I and implemented in Phase II.
Commercial applications would be a very powerful software that is applicable for
state-of-the-art parallel computers and vital for research involving time-dependent
simulation.
ray tracer, parallel algorithm, adaptive algorithm, Navier-Stokes solver, volume
visualization

Project Title:

Auto-Vectorization of Areal- and Linear-Raster Image Features

07.03-1813
910778
Auto-Vectorization of Areal- and Linear-Raster Image Features
Delta Data Systems, Inc.
131 Third Street
Picayune
MS
39466
Andrew A.
Rost
601-799-1813
SSC
NAS13-481
122