NASA 1984 SBIR Phase 1 Solicitation
Project Title:
Computation of Tip Flow Field in Advanced Aircraft Propellers
01.01-0511A
Computation of Tip Flow Field in Advanced Aircraft Propellers
Scientific Research Associates Inc.
PO Box 498
Glastonbury
CT
06033
Levy
Ralph
NAS3-24881
Amount:
LeRC
NAS3-24532
Abstract:
The Phase I effort has established the feasibility of computing the tipflow field in advanced aircraft propellers using a forward-marching computation procedure.
The innovative effort has demonstrated the capability of the forward-marching procedure
to compute generation and roll-up the tip vortex in high subsonic Mach numbers and
in high Reynolds number turbulent flows. Additional tasks, beyond the scope of the
Phase I Statement of Work, have demonstrated capability in handling complex geometry
of advanced propeller blades.
The proposed Phase II effort would extend capabilities demonstrated by the Phase
I innovations. The objective of the Phase II study would be to provide a computer
code of verified accuracy capable of predicting the tip flow field in advanced propeller
blades. Such a computer code would be a valuable tool in the design of advanced
propeller blades and the analysis of propeller performance. In particular, such
a code would be valuable in computing the effects of details of propeller tip geometry
on tip vortex generation and suppression. Specific tasks have been identified in
the Phase II proposal to accomplish the above-mentioned objectives.
Project Title:
Optimization Procedure for Aerodynamic Design for Advanced Turbo Propeller
01.01-8500
Optimization Procedure for Aerodynamic Design for Advanced Turbo Propeller
Flow Industries Inc.
21414 68th Avenue South
Kent
WA
98032
Jou
Wen-Huei
NAS3-24855
Amount:
LeRC
NAS3-24533
Abstract:
In recent years, the turboprop propulsion system has received increasinginterest due to substantial savings that can be achieved in fuel consumption. Substantial
resources have been invested in developing new technologies for aerodynamic design,
aeroacoustic performance, aerodynamic structural design, power generation and power
transmission. In propeller design, prediction codes are available to assist design
engineers. However, optimization of the design requires manual manipulation of the
propeller configuration guided by experience and intuition. The objective of the
proposed Phase II work is to develop an automated aerodynamic design code by combining
a prediction code and a numerical optimization procedure. In Phase I, the feasibility
of using numerical optimization as a design tool was demonstrated by optimizing the
twist distribution of the blades for an incompressible flow. The objective was to
maximize the propeller at operating Mach numbers of approximately 0.8. In designing
the propeller, shock wave effects must be considered. The design objective for Phase
II will therefore include the requirements that choking be prevented near the hub
and that the strength of shock waves near the blade tip be as weak as possible to
increase efficiency and reduce noise.
Project Title:
Adiabatic Wankel Type Rotary Engine
01.03-5052
Adiabatic Wankel Type Rotary Engine
Adiabatics Inc.
630 South Mapleton Avenue
Columbus
IN
47201
Kamo
Roy
NAS3-24880
Amount:437,000
LeRC
NAS3-24533
Abstract:
The Phase I study of the turbocharged "Adiabatic Wankel-Type Rotary Engine"indicated progressive performance improvements in Wankel rotary engines when the
combustion chamber components were insulated. The adiabatic Wankel engine with the
advanced concepts: turbocompounding, higher compression ratio, reduced leakage,
and faster combustion could decrease the specific fuel consumption by 25% and increase
power output by 34%. The elimination of the cooling system can give another 5% reduction
due to cooling system components. A total possible improvement of 30% in performance
and a 15% reduction in specific weight on an installed basis could provide the next
spring-board for the adiabatic Wankel rotary engine to compete in the worldwide aircraft,
automotive, industrial, and other power plant markets.
Based on the Phase I incentive, a two-year program is proposed herein to design,
fabricate, procure, and assemble a prototype, adiabatic Wankel rotary engine with
50% adiabacity. The prototype engine will be extensively tested in the laboratory
to determine: (1) performance improvements, (2) integrity of the
ceramic coatings and components, (3) emissions characteristics, and (4) wear and
durability trend. Turbocompound performance improvements will be calculated from
the laboratory test data by simulating intake and exhaust mainfold pressures.
Project Title:
Rapidly Solidified Titanium Alloys by Melt Overflow
01.03-5444
Rapidly Solidified Titanium Alloys by Melt Overflow
Ribbon Technology Corp.
PO Box 30758
Gahanna
OH
43230
Gaspar
Thomas
NAS1-18288
Amount:
LaRC
NAS1-17978
Abstract:
The feasibility of casting rapidly solidfied aluminum alloys, magnesiumalloys and titanium alloys was demonstrated during Phase I research project. A mathematical
model of melt overflow was developed to predict cast dimensions from process parameters.
The model was verified by laboratory experiments. Microstructural analysis of the
foils cast by melt overflow led to estimates of cooling rates on the order of 105
K/s or greater. The proposed Phase II research project will be directed toward the
production of rapidly solidified titanium alloys having gine uniform microstructures,
minimum gaseous and foreign object impurities, dimensional and compositional uniformity
and reproducibility. A facility that combines transferred plasma arc melting and
melt overflow will be designed, constructed, operated and maintained at Ribbon Technology
Corporation. Mathematical and physical models of the Melt Overflow Process will
be developed. Processing experiments will be conducted to cast rapidly solidified
titanium alloy foils, filaments, and particulate. A
sample quantity of 10 kg will be delivered to NASA. The microstructures and compositions
of the rapidly solidified titanium alloys will be evaluated. The melt overflow process
will be evaluated for commercial scale operation.
Project Title:
New Perfluoroalkylether Fluids with Excellent Oxidative and Thermal Stabilities
01.05-3812
New Perfluoroalkylether Fluids with Excellent Oxidative and Thermal Stabilities
Exfluor Research Corp.
PO Box 7807
Austin
TX
78713
Bierschenk, Thomas
R.
NAS3-24856
Amount:
LeRC
NAS3-23896
Abstract:
The goal is to utilize direct fluorination technology to produce perfluoroalkyletherfluids and lubricants. The direct fluorination process involves the selection of
a hydrocarbon with the proper structure which is converted to fluorocarbon by a controlled
reaction with elemental fluorine. Since the starting material is a hydrocarbon,
numerous structures can be made due to the wide variety of monomers and synthetic
techniques available. In contrast, the synthesis of fluorocarbon polymers from fluorocarbon
monomers is costly and the types of reactions that can be carried out are extremely
limited. The perfluoro-
alkylethers produced will have a variety of uses in environments where extreme stability,
very low vapor pressure, low acute toxicity, high lubricity and very low pour points
are required. Nowhere is this demand so evident as in the aeronautical and space
industries.
Project Title:
Feasibility of Generating an "Artificial" Burst in a Turbulent Boundary Layer
02.02-8500A
Feasibility of Generating an "Artificial" Burst in a Turbulent Boundary Layer
Flow Industries Inc.
21414 68th Avenue South
Kent
WA
98032
Gad-el-hak
Mohamed
NAS1-18292
Amount:294,000
LaRC
NAS1-17930
Abstract:
It is generally agreed that the bursting phenomenon is the most significantdynamic event in a turbulent boundary layer. About 80% of the momentum transport
occurs during these bursts. Previous attempts to understand the physics and structure
of these events were frustrated by the fact that bursts occur randomly in space and
time and that successive bursts are not necessarily identical. During Phase I of
this study, "artificial" bursts were generated in laminar and turbulent boundary
layers. The burst-
like events were produced by withdrawing near-wall fluid from two minute holes separated
in the spanwise direction or by pitching a miniature delta wing that was flush-mounted
to the wall. Either of these actions generated stream-wise vorticity and a low-speed
streak that resembled a naturally occuring one. The resulting sequence of events
occurred at a given location and at controlled times, allowing detailed examination
and comparison with natural, random bursts by means of flow visualization and fast-response
probe measurement techniques. During Phase II of the investigation, the topological
properties of the artificial bursts will be deduced from phase-locked hot-film measurements
and from pattern recognition algorithms.
As part of this investigation, a new technique to reduce skin friction drag in a
turbulent boundary layer is proposed. The technique combines the beneficial effects
of suction and a longitudinally ribbed surface. The suction will be applied selectively
in space and time to minimize pumping energy requirements and to alleviate the need
for a porous wall. It is anticipated that net drag reduction using the proposed
method will far exceed the reduction attained using suction alone or longitudinal
grooves alone.
Project Title:
Magnetic Suspension and Balance System Advanced Study
02.03-5903
Magnetic Suspension and Balance System Advanced Study
Madison Magnetics Inc.
216 Walnut Street
Madison
WI
53705
Boom
W. Roger
NAS1-18279
Amount:
LaRC
NAS1-17931
Abstract:
The innovation investigated in Phase II is to achieve more powerful,more compact, less expensive and more reliable suspension systems by new design concepts
and by the experimental and theoretical development of new key components. The results
of the Phase I work are improvements over the previous 1984 Madison design as to
reductions in: cost (28%), weight (43%), conductor (38%), helium liquefier (33%),
power (68%), stored energy (55%); and increased pole strength (19%) and increased
wing permanent magnetization (40%). Costs for an MSBS for an 8' x 8' tunnel have
decreased from $89,000,000 in 1982 (G.E.) to $29,900,000 in 1984 (M.M.I.) to $21,400,000
in the Phase I study. The objectives of Phase II are to confirm and enhance the
new features of the Phase I design which are better persistent current superconducting
solenoids in the suspended airplane model, better permanent magnet wings, and better
designs. The planned efforts to develop new key components are to construct and
test a full-scale cryostat and solenoid wound on a holmium core, to experimentally
develop even
better solenoids with new NbTi wire and better epoxy potting, to test new permanent
magnet wing material, and to confirm better designs. The results expected are experimental
confirmations of the key component developments which substantiate the major MSBS
design improvements.
Project Title:
Shear Stress Development Using Surface Acoustic Waves
02.06-4037
Shear Stress Development Using Surface Acoustic Waves
Raman Aeronautics Inc.
734 Melville Avenue
Palo Alto
CA
94301
Raman
K. R.
NAS2-12481
Amount:
ARC
NAS2-12121
Abstract:
This project is concerned with the development of a small, reliable anduniversally acceptable surface shear stress (or skin friction) sensor for aerodynamic
boundary layer research at subsonic to supersonic speeds. The interdigital transducers
(IDTs) required by the surface acoustic wave (SAW) delay-line concept on the crystal
substrates have been generated and are being evaluated. The enclosure to house the
crystal cantilevered beam has been designed, all parts machined and two units assembled
to accept the crystal beam. After bench tests are completed, a more sensitive and
sophisticated SAW resonator (replacing the delay-line IDTs) on the crystal beam will
be designed. A pair of reflector gratings and IDT in the acoustic cavity that are
required for resonator concept will be designed and generated on the crystal surface.
The developed sensor will be extensively tested inthe laboratory prior to being
used in the wind tunnel.
Project Title:
Optical Technique to Study the Impact of Heavy Rain on Aircraft Performance
03.02-8477
Optical Technique to Study the Impact of Heavy Rain on Aircraft Performance
Spectron Development Laboratories Inc.
3303 Harbor Blvd., Suite G-3
Costa Mesa
CA
92626
Hess
Cecil F.
NAS1-18242
Amount:
LaRC
NAS1-17932
Abstract:
A technique to measure the size, velocity, and concentration of raindropsin very heavy rain is proposed. Studies conducted during Phase I show the feasibility
of this technique under simulated very heavy rain experiments. In Phase II, a working
prototype will be produced and demonstrated in the 4 x 7 m wind tunnel at NASA Langley.
The technique bases the size of the drops on the intensity of the light scattered
at a prescribed solid angle, and the velocity on the classical Doppler frequency.
The Phase I studies showed that spray interference had no significant effect on
the size distribution, and an accurate size obtained. The studies also include a
scattering model for nonspherical drops which helps establish the optical conditions
less sensitive to droplet shape.
These studies also point out that to measure the flows expected at NASA's facilities,
a more powerful laser and faster electronics are needed. These elements will be
incorporated in the advanced
prototype developed during Phase II.
Project Title:
Optimal Guidance with Obstacle Avoidance for NOE Flight
03.08-9191
Optimal Guidance with Obstacle Avoidance for NOE Flight
Theory & Applications Unlimited
10 Jackson Street, Suite 101
Los Gatos
CA
95030
Denton
Richard V.
NAS2-12402
Amount:
ARC
NAS2-12092
Abstract:
This project is developing automatic guidance for helicopter Nap-of-the-Earth (NOE) flight. The guidance technology uses information from the onboard
sensors combined with an onboard digital map, when the digital map is available,
to result in safe low-altitude flight corridors. The guidance technology makes a
digital map truly useful to the pilot, while affording acceptable workload levels.
Such an integrated digital map/optimal NOE guidance system will revolutionize low-level
helicopter operational performance and its impact on crew workload.
The applicability of the concept has been sucessfully demonstrated through analysis,
through simulations, and through delivery of a videotape showing how well the low-altitude
NOE algorithm can be made to operate in real time.
Engineering feasibility will be established. The work continues with the algorithm
refinements, particularly in relating the rotorcraft equations of motion to the NOE
trajectory computation scheme. Ride quality consideration and pilot-vehicle interfaces
will also be treated. The refined algorithm will be implemented in an engineering
testbed that emulates the eventual operation in an airborne flight computer. Appropriate
display advisories and the flight control coupler design requirements will also be
addressed. This will result in a prototype design that meets pilot acceptability
criteria, and that will operate in real time.
Project Title:
Decision Making Modeling for Theory of Human Error
03.09-2281
Decision Making Modeling for Theory of Human Error
Systems Technology Inc.
13766 S. Hawthorne Blvd
Hawthorne
CA
90250
Clement
Warren F.
NAS2-12540
Amount:
ARC
NAS2-12094
Abstract:
A quantitative theory of human error applicable to monitoring, decisionmaking, information processing, and control operations has been developed. The theory
comprises models for: (1) risk acceptance decision-making in the presence of uncertainty
and divided attention, and (2) operations in which slips, blunders, and control errors
become more prevalent as the level of divided attention is increased. Quantitative
measures such as risk acceptance functions, slip probabilities, and dwell fractions
for control and managerial tasks (to characterize divided attention) are sensitive
indicators of the susceptibility of system config-
ura-tions and procedures to human error.
The theory and measures will address a current critical problem in aeronautics:
the pilot decision to continue or go around in dangerous wind shear situations.
Competing possible content, format, and precision of wind shear advisory information
(ranging from tower communications to on-board precision guidance) will be assessed
using the theory and associated metrics. Exploratory
"Pilot" and "Validation" experiments are proposed to obtain the risk acceptance
and other functions for the most interesting set of advisory possibilities. The
experimental data will also permit refinement of the analytical models to a higher
confidence predictive form.
Project Title:
Ceramic Fiber/Ceramic Matrix Composites
04.05-5911
Ceramic Fiber/Ceramic Matrix Composites
Fiber Materials Inc.
Biddeford Industrial Park
Biddeford
ME
04005
Cox
M. K.
NAS2-12449
Amount:471,000
ARC
NAS2-12104
Abstract:
Various types of ceramic fiber/ceramic matrix composites have been successfullyfabricated using novel materials and processing methods. The material developed
is a durable and lightweight composite with temperature capability of 2000 deg F.
It consists of woven ceramic fibers impregnated with a preceramic polymer which
forms silicon carbide after pyrolysis. The material properties of these ceramic
composites are comparable to a four directional carbon-carbon while the resistance
to oxidation is much greater for the ceramic than the carbon-carbon.
Process development parts, which will undergo various processing schedules will be
screened to choose a candidate material for full scale fabrication to define the
mechanical and thermal properties along with studies concerning matrix formation.
Project Title:
Providing Structural Modules with Self-Integrity Monitoring
04.09-5050
Providing Structural Modules with Self-Integrity Monitoring
Anco Engineers Inc.
9937 Jefferson Blvd
Culver City
CA
90232-3591
Ibanez
Paul
NAS7-961
Amount:439,000
JPL
NAS7-937
Abstract:
An important aspect of having complex space structures, and any relatedoperations, function successfully is to be able to rapidly and remotely detect structural
damage. The Phase I research involved developing five approaches that can be used
for structural damage detection. They are all dependent on defining a substructure
transfer function matrix. The space structure would be divided into substructures.
The substructure being analyzed would be excited by an external load source and
changes in the transfer function matrix would be detected. Some of the "tools" used
for the detection are (1) Taylor series expansion of the transfer function (TF),
(2) phase shift of the TF, (3) modal strain energy distribution, and (4) nonlinear
parameter estimation. First cut validations of all the approaches are presented
in the final report. Overall, the results are good.
The Phase II work will involve an extension of the Phase I work, with there being
certain areas of concentration because of the
greater possibility of substantial success in those areas. The deliverables will
consist of benchmarked, final algorithms/ approaches to damage detection, together
with all the material used for validation. Also, all software needed for basic damage
detection will be provided.
Project Title:
Ultrasonic Correlator for Nondestructive Characterization of Materials
04.10-0332
Ultrasonic Correlator for Nondestructive Characterization of Materials
Industrial Quality Inc.
P.O. Box 2397
Gaithersburg
MD
20879-0397
Berger
Harold
NAS1-18258
Amount:
LaRC
NAS1-17937
Abstract:
A new cross-correlator has been developed and shown to be useful formaterials characterization. A simplified cross-correlator technique, originally
developed for work in the kilohertz frequency range, is the primary element in the
new ultrasonic cross-correlator. The cross-correlator output provides the same information
as the impulse response of a material. Therefore, the cross-correlator is an attractive
approach for ultrasonic characterization of materials. In the Phase I program the
range of the cross-correlator has been extended to meghertz frequencies, thereby
making the instrument useful for ultrasonic measure-
ments. A test made with the new system showed significant differences in frequency
versus time reponse for fatigued and fatigued aluminum samples. In addition, the
processing of the cross-correlator data has been adapted to an IBM personal computer
making the instrument more generally useful, and leading directly to a Phase II program.
In the new program the cross-correlator performance will be improved by electronic
changes such as an improved white noise generator, by compatible broadband transducers
and by software modifications leading to display of both frequency and phase. Further
work to understand the theoretical limits of cross correlation versus conventional
ultrasonic characterization problems will lead to the identifi-
cation of potential applications. A demonstration will be made of a prototype cross-correlator
instrument to be designed and fabricated as part of the Phase II program.
Project Title:
Space Structures Concepts and Materials
04.13-1504
Space Structures Concepts and Materials
DWA Composite Specialties Inc.
21119 Superior Street
Chatsworth
CA
91311-4393
Supan
Edward C.
NAS8-37257
Amount:
MSFC
NAS8-35264
Abstract:
The objective of the project is to expand the successful developmentof DWG (Grfiber/Al) end fitting and integrate the continuing work into a comprehensive
program designed to achieve a thermally stable truss structure using DWG end fittings
and tubes. Zero CTE end-fitting material, fabricability of DWG into complex geometry,
and end-fitting design concepts have been accomplished. The major objective is to
establish the design requirement for fittings, tubes and joints in terms of CTE,
load capability and weight; to optimize DWG materials used for fittings and tubes
over the intended temperature spectrum. The program will also consider innovative
DWG heat pipe for temperature control; cored panel with DWG face sheet; DWG-angle
structural members; and metal-matrix composite weldment. It is anticipated that
uses of DWG in the steady will spawn applications of this stiff, strong, low-density
MMC in aerospace structure, missile components, medical apparatus, and instrumentation.
Project Title:
Novel Oxygen Atom Source for Material Degradation Studies
04.14-9030
Novel Oxygen Atom Source for Material Degradation Studies
Physical Sciences Inc.
P.O. Box 3100, Research Park
Andover
MA
01810
Caledonia
George
NAS7-963
Amount:
JPL
NAS7-938
Abstract:
NASA requires a ground-based test facility to study material degradationresulting from impact of energetic oxygen atoms exhibiting velocities appropriate
to low earth orbit. Physical Sciences Inc. has demonstrated the ability to produce
a high flux pulse of oxygen atoms, with a characteristic velocity of 8 km/s, using
a laser breakdown technique. We propose in the Phase II effort to build an O-atom
material erosion facility utilizing this technique for the O-atom source. This facility
would have the capability of irradiating material specimens of area of up to 200
cm2 with an average high velocity O-atom of 5 x 1016 atm/cm2-s. Facility diagnostics
would include real time mass removal evaluation, mass spectrometry and target effluent
radiative signatures. This facility would provide the ability to provide material
aging simulations of interest to Space Shuttle and Space Station over relatively
short periods of time (1/2 day to 1 week).
Project Title:
Dead Reckoning Optoelectronic Docking System
05.04-4561
Dead Reckoning Optoelectronic Docking System
Energy Optics Inc.
224 North Camp Street
Las Cruces
NM
88001
Ward
Steven M.
NAS9-17603
Amount:
JSC
NAS9-17283
Abstract:
The feasibility of applying existing, military and commercial optoelectronicsystems to the problem of automating space proximity operations, particularly the
hard docking of two space vehicles has been evaluated. Although no specific system
was found adequate, existing optoelectronic components and technologies such as "time
of flight" laser ranging, "tone" ranging and "optical contrast" video tracking were
applied. The two specific problems of configuring a wide field, laser tracker with
no moving parts and precision target attitude sensing at ranges under three meters
were solved by innovating new optoelectronic techniques. Feasibility of the resulting
DROID system was predicted by simulation, by performance analysis and by constructing
rudimentary hardware.
The thrust of further studies is to solidify system requirements and to design and
construct operational prototypes of the three intelligent sensors; (1) pulsed array
LIDAR, (2) CW array LIDAR and (3) CCD TV LIDAR. In addition, the DROID Main CPU
will be
configured from a commercially available microprocessor system. The resulting DROID
system prototype will be extensively tested by both the contractor and NASA to determine
operational performance and measurement resolution.
Project Title:
Optimal Systolic Architectures for the Navier-Stokes Equations
06.01-3030K
Optimal Systolic Architectures for the Navier-Stokes Equations
Zeroone Systems Inc.
2431 Mission College Blvd
Santa Clara
CA
95054
Fok
Simon K.
NAS2-12444
Amount:
ARC
NAS2-12082
Abstract:
The objective is to construct a Systolic Navier-Stokes Attached Processor(SNAP) connected to a VAX computer for high speed NASA flow code computations. A
high level architecture for the SNAP has been designed. The architecture consists
of: (1) a narrow bandwidth linear solver which is currently under development for
NASA by ZeroOne Systems, Inc. and (2) fast Fourier transform modules and matrix-vector
multiplier modules which will be constructed using Sky Computers' Sky Warrior array
processors. All these processors will be integrated with the host computer through
the Apter DPS-2400 which is, in essence, a shared memory multiprocessor. The three
NASA flow codes already studied will be mapped into the SNAP. This involves restructuring
of the whole computational process in each code to facilitate systolic chaining;
the actual computational algorithm will not be changed. Software will also be developed
to coordinate the operations of multiple processors, shared memory and the host using
low-level interprocessor communication primitives to create
semaphores, critical regions and other synchronization primitives to ensure reliable
operations of the SNAP. Cost-effectiveness of the SNAP with respect to a range of
computers will be assessed.
Project Title:
A Floating-Point Computer Module for Array Processing on the FLEX/32 MultiComputer
06.03-1234
A Floating-Point Computer Module for Array Processing on the FLEX/32 MultiComputer
Flexible Computer Corp.
1801 Royal Lane, Bldg #8
Dallas
TX
75229
Matelan
Nicholas
NAS1-18241
Amount:
LaRC
NAS1-17939
Abstract:
The FLEX/32 MultiComputing Environment is a general-purpose, digitalmultiple-processor system that allows virtually any number of high performance, hetergeneous,
32-bit computer modules to compute in parallel together on one or more tasks.
The Phase I study has shown the feasibility of using the FLEX/32 MultiComputer in
floating-point array processing. This can be done through development of a new Floating-Point
Computer Module (FPCM) specifically adapted to floating-point arithmetic, vector
and array processing. Phase II will result in production of a new FPCM module and
library software that will be fully integrable into any FLEX/32 configuration, be
it all FPCM's or mixed as needed with already existing module types. FPCM software
would execute under UNIX System V used by other FLEX/32 modules.
A single FLEX/32 cabinet, equipped with the new modules, could give 32-bit computing
power in the 80 to 120 megaflops range. Since there is no inherent architectural
limitation to the number of cabinets that can be directly coupled together, there
is no theoretical limit to the size and processing power that such a machine can
attain. A five-cabinet FLEX/32 could offer performance in the 400-500 megaflops
range, for example, depending on use of suitable algorithms.
The availability of an FPCM would turn the commercially available FLEX/32 MultiComputer
into a lower cost array-processing supercomputer replacement.
Project Title:
Enhancement of Simulation/Animation Graphics System (Phase II)
06.04-1625
Enhancement of Simulation/Animation Graphics System (Phase II)
Lincom Corp.
18100 Upper Bay Rd, Suite 100
Houston
TX
77058
Voss
Mark J.
NAS9-17606
Amount:
JSC
NAS9-17277
Abstract:
The objective is to design and develop very high performance graphicssubsystem for use in simulation, animation and general graphics applications. The
system must provide real time dynamics for complicated scenes, realistic shading
models, and be commercially realizable.
Research will be conducted on graphics architectural concepts and VLSI implementation
to produce an expandable modular display system with the ability to render scenes
composed of over 10,000 patches in real time with realistic shading models and programmable
light sources. The system will have expandable performance by using parallel processing
techniques, and will have the ability to display infinitely complex scenes by using
incremental shading and hidden surface techniques with a frame buffer for output.
General purpose graphics capabilities are also included to allow the system to perform
a variety of duties.
Project Title:
Focal-Plane Processing of Visual Information
07.04-1112
Focal-Plane Processing of Visual Information
Q-DOT Inc.
1069 Elkton Drive
Colorado Springs
CO
80907
Roberts
Peter C. T.
NAS1-18287
Amount:
LaRC
NAS1-17940
Abstract:
A Phase II follow-on program is proposed based on the good results generatedin the Phase I program. An actual layout was performed in the Phase I program showing
that a 128 x 128 x 3 mil square focal-plane processor (FPP) chip is feasible. The
performance of that FPP and an improved hexagonal symmetry version will be studied
with actual test chip measured data from the Phase II tasks. Support hardware is
to be assembled using low-cost standard components and a full system definition developed
for the Phase III subsequent program. Optical performance will be determined by
a combination of test chip measurements and analytic and computer simulation method.
Reasonable expectations of device yield indicate that working versions of 32 x 32,
64 x 64, and 128 x 128 array FPP will be achieved. Throughput of the final optimized
FPP using the brick-wall architecture is expected to greatly outperform conventional
approaches to visual information acquisition and initial processing for computer
and/or robotic vision systems. Frame rate of 100 to 1,000 per second at grey-scale
(four to six bits) resolution are possible at > 1 GOPS throughput.
Project Title:
Low Power Spectrum Analysis and Real Time Data Compression
07.06-1000
Low Power Spectrum Analysis and Real Time Data Compression
Defense Systems Inc.
7903 Westpark Drive
Mclean
VA
22102
Starkey
Donald L.
NAS5-29432
Amount:
Center: GSFC
NAS5-28624
Abstract:
For deep space probes where the distance of the probe from the Earthlimits the communication bandwidth, there is a need to develop an on-board, low power,
spectrum analyzer signal processor with flexible and programmable post processor
capabilities to analyze three axis magnetometer data. Defense Systems, Inc. (DSI)
on Phase I designed and built such a "brassboard" Fourier transform programmable
spectrum analyzer that has the potential to meet all stated NASA requirements. While,
with the software supplied on Phase I, it handles only one channel inputs, it can
be remotely programmed according to an uplinked schedule through an RS-232 interface,
it has programmable resolution from 0.025 to 1.6Hz, 512 arbitrarily distributed frequency
bins, it can detect spectral clusters, track their peak frequencies and display the
spectral history on an IBM PC computer, CRT display and printer. With additional
effort the analyzer can be expanded to handle 3-
channel inputs, logarithmic spectral resolution, keep the I and Q components separate,
perform spectrum energy change detection,
spectral peak detection and tracking and other time and spectrum averaging statistical
operations NASA requires. It is proposed in Phase II to develop flight hardware
signal processor of approximately 1 watt power consumption, packaged to the required
configuration. The design maturity of the DSI processor enables the accomplishment
of these objectives in Phase II.
Project Title:
West Coast Storm Forecasting with SSMI
07.06-8911
West Coast Storm Forecasting with SSMI
Remote Sensing Systems
475 Gate Five Rd, Suite 211
Sausalito
CA
94965
Wentz
Frank J.
NAS5-29438
Amount:
GSFC
NAS5-28634
Abstract:
The first in a new generation of satellite microwave radiometers, theSSMI, will be launched in spring of 1986. Our SBIR project is a demonstration that
SSMI images of water vapor V, rain rate R, and wind speed W (VRW images) can improve
the forecasting of North Pacific storms coming into the West Coast of the United
States. The Phase I study established the feasibility of this project by determining
the accuracy and resolution of the SSMI products, the SSMI spatial coverage, and
the timeliness of the SSMI data. Also, VRW images of the severe storms that devastated
the California shoreline in 1982 and 1983 were produced using NIMBUS 7 SMMR data.
Phase II will be a demonstration of SSMI's forecasting capabilities. An image processing
system will be developed to overlay the SSMI VRW images onto NMC analyses and GOES
imagery. Advection forecasting of using SSMI products in techniques will be tested,
and the potential of using SSMI products in numerical forecast models will be investigated.
The Phase II project will end with a real-time demonstration in which actual forecasts
are
made using the SSMI data in conjunction with other meteorological information.
We expect that SSMI will have a significant impact on West Coast forecasting.
Project Title:
Radial Concentric Grating Ruling Engine
08.01-6882
Radial Concentric Grating Ruling Engine
Hyperfine Inc.
1930 Central Avenue
Boulder
CO
80301
Bach
Bernhard W.
NAS5-29415
Amount:
GSFC
Phase I Contract Number:
Abstract:
Future space astronomy missions propose new designs of in-plane and off-planegrating configurations. The new grating designs have been theoretically calculated
and two types have recently been test ruled at Hyperfine. A concentric grating of
600 1/mm, 50x50mm ruled area and nominal groove curvature radius of 400mm was ruled
for the Phase I effort for NASA. A radial fan groove grating was ruled for the University
of Colorado. Both ruling projects required extensive temporary modifications to
our existing ruling engines. For this Phase II effort, we propose to construct a
new ruling engine capable of accommodating the new ruling requirements. We will
add a circular motion to the grating carriage, allowing the various ruling commands
and its computing capability will calculate variable grating spacing positions.
Variable spaced, concentric and radial fan gratings will offer new performance possibilities
to the science community.
Project Title:
A TEOM Particulate Monitor for Comet and Planetary Atmospheres
08.03-4520
A TEOM Particulate Monitor for Comet and Planetary Atmospheres
Rupprecht & Patashnick Co Inc.
17 Maple Road, Box 330
Voorheesville
NY
12186
Rupprecht
George
NAS7-962
Amount:
JPL
NAS7-941
Abstract:
Future missions to comets and planetary atmospheres require particulatemonitoring instrumentation to fulfill a number of scientific and engineering measurement
needs. This project involves an investigation to characterize and expand the particulate
measurement capabilities of TEOM instrumentation. The results of the Phase I effort
demonstrated that vacuum compatible tapered elements (the mass detecting component
of the system) could be produced to achieve a mass resolution in the 10-12 g region.
The groundwork laid in Phase I will be extended in Phase II to further improve the
sensitivity of the instrument and to develop fabrication procedures to increase yield
and uniformity. A further objective is to test these devices under space simulated
conditions with controlled particulate fluxes.
To accomplish these objectives, additional work on the reduction of the electronic
noise is planned. Futhermore, the production of
these devices must be elevated from current laboratory fabrication techniques to
standardized manufacturing procedures. This also involves the definition of meaningful
test procedures and the establishment of a quality control program to insure consistent
and reliable performance levels. It is also planned to develop a facility to produce
a particulate flux in vacuum to provide test data for the instrument under a simulated
comet mission environ-ment.
Project Title:
Simultaneous Orbit Determination with Physical Connectedness
08.05-1590
Simultaneous Orbit Determination with Physical Connectedness
Applied Technology Associates Inc.
444 Castro Street, Suite 520
Mountain View
CA
94041
Wright
James R.
NAS5-29417
Amount:
GSFC
NAS5-28637
Abstract:
The innovation, called SIMULTANEOUS ORBIT DETERMINATION, refers to thesequential simultaneous estimation of the orbits of two spacecraft (TDRS and SPACE
SHUTTLE, or TDRS and SME, or TDRS and any low altitude "USER") when tracking measurements
depend simultaneously on both orbits. TDRS relay range measurements and TDRS relay
doppler measurements satisfy this tracking measurement condition.
Two Phase I objectives have been accomplished: (1) Live TDRS relay-doppler measurements
were collected for SHUTTLE Mission 41G, together with appropriate support data; (2)
A 200-page Experiment Design Report was written to define the development of a live
data engineering test-bed for Phase II.
The principal objective for Phase II is to demonstrate significant orbit determination
accuracy improvements for the TDRS and SHUTTLE (or SME) orbits using live TDRS relay
range and/or relay doppler tracking data; and using our innovation: SIMULTANEOUS
ORBIT DETERMINATION.
Planned Phase II efforts will consist of: (1) development and validation of the
ATA algorithm/software capability; (2) live tracking data demonstrations with TDRS/SME
and TDRS/SHUTTLE spacecraft combinations; (3) determination of predicted and post-
fit ephemeris accuracy performance.
We expect that a successful demonstration of SIMULTANEOUS ORBIT DETERMINATION will
enable the elimination of both the GSTDN and BRTS tracking network.
Project Title:
Implementation of an Integrated Receiver Using Programmable Charge Coupled Device
08.05-3220
Implementation of an Integrated Receiver Using Programmable Charge Coupled Device
Stanford Telecommunications Inc.
6888 Elm Street
Mclean
VA
22101
Weinberg
Aaron
NAS5-29416
Amount:
GSFC
NAS5-28638
Abstract:
The combination of concept development, theoretical analysis and computersimulation in Phase I demonstrated the technical feasibility of the Charge Coupled
Device/Pseudo-Noise Matched Filter (CCD/PNMF) concept towards achieving a unique,
integrated receiver processing capability that encompasses PN, carrier and symbol
synchronization. Its potentially significant application to TDRSS was established,
and other possible applications were identified. The principal goal of the proposed
Phase II effort is to again focus on the CCD/PNMF Integrated Receiver (CPIR) concept
and use the solid foundation provided by Phase I as the basis for an in-depth research
and development effort, to comprehensively demonstrate the viability of the CPIR.
This is to be accomplished by a carefully selected mix of concept development, theoretical
analysis, computer simulation and laboratory hardware/software model development.
Two hardware demonstrations are proposed for presentation to NASA during the course
of the Phase II effort. If this effort is successful, the Phase III basis for expanded
research and hardware development in multiple areas will have been established, especially
in regard to advanced signal processing for the Second TDRSS Ground Terminal. Representative
areas may include: Autonomous Integrated Receiver System (AIRS), interference detection/mitigation,
and advanced processing for hybrid spread-spectrum systems.
Project Title:
Technical Proposal to Develop Technology for a Space Qualifiable Carbon Dioxide Laser
08.06-1920
Technical Proposal to Develop Technology for a Space Qualifiable Carbon Dioxide Laser
System
Pulse Systems Inc.
139 Longview Drive
Los Alamos
NM
87544
McLellan
Edward J.
NAS5-29419
Amount:
GSFC
NAS5-28639
Abstract:
Global wind sensing using CO2 lasers is a prime NASA mission objective. Pulse Systems, Inc. (PSI) has analyzed its unique patented laser discharge design
in a Phase I SBIR grant to determine how it could best aid in the development of
a space-qualifiable CO2 laser remote-sensor system. This analysis combined with
test data accumulated during Phase I shows that, with the unique PSI discharge design,
it is feasible to design, construct and test a CO2 discharge module with performance
goals of greater than 108 sealed shot-life with total system volume of less than
0.01 m3 and weight of less than 8 kg including all electronics, optics and tube.
Additional goals for the proposed CO2 module when used as a laser are greater than
1.0 Joules per pulse at 10 Hertz with a wall-plug (total system including all electronics
losses) efficiency of greater than 10%. The objective of Phase II is to design,
fabricate and test a sealed CO2 laser using the unique PSI laser
discharge technology. This system will be used to conduct tests and accumulate
data which will be used to optimize far-field energy per pulse, efficiency and shot-life
while minimizing size and weight. Expected results from the proposed Phase II program
include meeting the above stated performance goals with minimal chirp in a rugged
thermally stable package suitable for spaceborne applications.
Project Title:
Adiabatic Demagnetization Refrigerator for Use in Zero Gravity
08.07-8629
Adiabatic Demagnetization Refrigerator for Use in Zero Gravity
Alabama Cryogenic Engineering Inc.
P.O. Box 2451
Huntsville
AL
35804
Hendricks
John B.
NAS5-29418
Amount:
GSFC
NAS5-28641
Abstract:
This study covers the design of an adiabatic demagnetization refrigeratorfor use in zero gravity. The most important element in the study is a combined precooler/heat
switch for cooling the paramagnetic salt during magnetization. The precooler reduces
the required magnetic field and simplifies the design of the system. The Phase II
effort is a demonstration of the concepts developed in Phase I.
Project Title:
A Solid State Tunable Laser for Remote Sensing Applications
08.08-0537
A Solid State Tunable Laser for Remote Sensing Applications
Lasergenics Corp.
P.O. Box 33010
Los Gatos
CA
95031-3010
Schlecht
Richard
NAS1-18303
Amount:
LaRC
NAS1-17941
Abstract:
During Phase I of our SBIR program, four titanium doped sapphire crystalswere evaluated. Two of the crystals from separate vendors proved to be of laser
quality, indicating that crystals can be produced by multiple vendors. Pumping configuration
and laser physics analyses indicated that a longitudinal pumping configuration should
be used. It was determined that at the near infrared laser lines, which are of interest,
for remote sensing, a large conversion efficiency of 50% is possible from the pump
lasers. There is little likelihood of optical damage occurring. Several techniques
for wavelength control were evaluated with two appearing attractive. It was determined
that relatively efficient crystals are available for second harmonic generation and
sum frequency generation which would extend its output from the fundamental band
of 650nm to 1000nm into the 90nm to 500nm region. System scaling issues were addressed,
indicating large energies per pulse are obtainable from a single aperture device.
Based on these results, we are proposing to develop a breadboard
laser to demonstrate the capabilities of this system for scaling to the 1 Joule
per pulse energy level. The specifications of the breadboard laser are 100mJ per
pulse at a 10 Hz repetition rate and 1 pM laser line width at 724,760 and 940nm.
Project Title:
Laser Spectrometer and Wavemeter
08.08-9030
Laser Spectrometer and Wavemeter
Physical Sciences Inc.
Dascomb Research Park, P.O. Box 3100
Andover
MA
01810
McKay
J. A.
NAS1-18243
Amount:
LaRC
NAS1-17942
Abstract:
The device to be built is a laboratory prototype of a combination high-accuracywavemeter and high-resolution spectrometer capable of real-time, pulse-by-pulse analysis
of laser pulses. This instrument will be built with attention to further development
into a rugged, flight-qualifiable, unattended-operation model with little redesign.
The device will be invaluable for numerous laboratory spectroscopic applications
as well as for the principal application, airborne/spaceborne DIAL for remote sensing
of the atmosphere.
The conceptual design of this wavemeter/spectrometer, completed in Phase I, incorporated
the innovative combination of a Snyder low-
finesse interferometer with a Fizeau high-finesse interferometer, yielding a dual-function
instrument well suited to compact, rugged construction.
The objective of Phase II is the construction of a working prototype of this instrument.
The system will be evaluated for accuracy, resolution, and speed capabilities.
The prototype will yield (1) an optical design, (2) an electronic system, and (3)
a software package, providing a high-confidence projection of the performance capabilities
of, and a solid foundation for the construction of, a next-generation, flight-ready
instrument. The prototype itself will be suitable for laboratory use.
Project Title:
Optimization of Silicon Carbide Production
08.09-6500
Optimization of Silicon Carbide Production
Aerodyne Research Inc.
45 Manning Road
Billerica
MA
01821
Warmhoudt
Joda C.
NAS3-23891
Amount:500,000
LeRC
NAS3-24531
Abstract:
Silicon carbide (SiC) is an advanced material which has significant technicaland economic potential in electronic and optical device applications. The high temperature
tolerance of SiC makes it particularly attractive in applications requiring active
electronics which operate at elevated temperatures. Progress toward realizing the
benefits provided by SiC devices has been limited by difficulties in growing semiconductor
quality material. Recently, however, a NASA research team has developed a two-step
CVD process, for producing epitaxial B-SiC on Si single crystal wafers. In this
process, buffer or initial layers deposited in the first step minimize lattice mismatches
so that high quality SiC can be deposited in the second or crystal growth step.
The objective of this program is to develop a mechanis-
tically accurate, predictive model which will provide the required basis for optimizing
the two-step process. Phase I of this program focused on the gas phase chemistry
and led to an evaluation of the impact of gas phase chemistry on deposition.
Phase II focuses on the surface chemistry of the deposition process and extending
current modeling capabilities. Provisions are included for additional gas phase
studies where warranted by the surface and modeling work.
Project Title:
Widely Tunable Gas Laser for Remote Sensing of Stratospheric Constituents
08.11-2227
Widely Tunable Gas Laser for Remote Sensing of Stratospheric Constituents
Rothe Technical Research
5205 Avenida Encinas, Suite E
Carlsbad
CA
92008
Rothe
Dietmar, E.
NAS7-970
Amount:
JPL
NAS7-935
Abstract:
The Phase I study has resulted in the definition of an advanced, compactmultigas TE laser for remote interrogation of the earth's atmosphere from a space
platform. Newly developed excimer laser and pulse power technology permit the design
of a laser with extended tunability in the UV and IR and with greatly increased efficiency.
Incorporation of these advances (e.g. prepulse-
assisted efficiency, impedance matching, constant-V,I PFL, X-ray preionization, magnetic
switching) lead to a doubling of the electric efficiency, longer system life, improved
discharge uniformity and higher beam quality.
The proposed system may be operated as a rare-gas halide (RGH) laser, a multi-atmospheric
CO2 laser, or as a DF laser. Narrowband, frequency-stabilized optical pulses are
tunable over the UV excimer bands and are continuously tunable from 9 to 11 um in
the IR. At 25 pulses per second, projected pulse energies are 2 to 5 J for CO2 and
0.2 to 2 J for RGH, with wallplug efficiencies of 4 to 7% and 2 to 3%, respectively.
Besides being ideally suited for the active sensing of upper atmospheric O3, H2O,
CH4, CO, N2O, NO2, SO2, HNO3, CH3Cl, LIF, the proposed system may be used for stratospheric
wind determinations by incoherent UV Doppler detection. Other NASA applications
are in aerosol monitoring, cloud-top mapping and mineral exploration.
Project Title:
Analysis of Atmospheric Aerosols with 0.3 Micrometer Spatial Resolution
08.12-7847
Analysis of Atmospheric Aerosols with 0.3 Micrometer Spatial Resolution
ST&E Technical Services Inc.
1214 Concannon Blvd.
Livermore
CA
94583
Klainer
Stanley M.
NAS1-18253
Amount:
LaRC
NAS1-17943
Abstract:
Raman spectroscopy is a non-destructive analytical technique that performsmolecular identification and characterization by the analysis of inelastically scattered
laser light. Commercial Raman instruments are available that can analyze individual
micro-
particles in the 1 micrometer ranges with difficulty. NASA, however, has identified
a problem area that requires molecular analysis of particles under 1 micrometer in
diameter. In Phase I the application of micro-Raman analysis to the NASA problem
area was established. The applicability of existing commercial and custom micro-Raman
to solve this problem was evaluated. These spectrometers were shown to have sensitivity
to selected particles no smaller than 1 micrometer in diameter and their potential
as a micro-particle analyzer was rejected. A first principal calculation was performed
on the feasibility of micro-Raman analysis of a representative 0.3-micrometer-diameter
particle. The results indicated that with spectroscopic innovation, a new-
generation, user friendly, automatic micro-Raman spectrometer with routine sensitivity
to 0.3 micrometer could be built. A preliminary design of this instrument is presented
in the Phase I final report.
In Phase II, the research and development to complete design, construction, and delivery
to NASA of a prototype of this new-
generation micro-Raman spectrometer is discussed. In addition, this spectrometer
will be used to generate a partial library of micro-Raman spectra using selected
particles in the 0.3 to 1.0 micrometer range. Analysis will also be performed on
particles provided by NASA.
Project Title:
Miniature Infra-Red Data Acquisition and Telemetry System
08.13-4561
Miniature Infra-Red Data Acquisition and Telemetry System
Energy Optics Inc.
224 North Campo Street
Las Cruces
NM
88001
Stokes
John H.
NAS1-18285
Amount:
LaRC
NAS1-17944
Abstract:
Phase I demonstrated a heretofore unavailable telemetry technology relyingon IR communications and hybrid miniaturization to allow data from small aircraft
models to be transmitted in realtime to a remote test console. The thrust of the
program was miniatur-iza-
tion of a Telemetry Transmitter Unit (TTU) which resides within the confines of the
model. The resulting two-way communications capability allows data acquisition commands
to be transmitted to the TTU and test data to be received from it, while the model
is magnetically suspended in a wind tunnel.
Phase II is designed to advance the Miniature Infra-Red Data Acquisition and Telemetry
(MIRDAT) system to the user. The miniature TTU developed in Phase I will be modified
to meet user production stage requirements for wind tunnel telemetry. The TTU will
be further miniaturized by means of advanced hybridization techniques to a total
volume of about one cubic inch. Telemetry transmitters will undergo extensive laboratory
testing and actual wind tunnel testing before the final design is released for
production. A small quantity of TTUs, along with the required MIRDATperipherals,
will be manufactured and delivered to user.
Project Title:
Modular Digital Holographic Fringe Data Processing System
08.13-8500
Modular Digital Holographic Fringe Data Processing System
KMS Fusion Inc.
3621 S. State Rd, P.O. Box 1567
Ann Arbor
MI
48106
Downward
James C.
NAS1-12531
Amount:
LaRC
NAS1-17945
Abstract:
Holographic and interferometric techniques are used routinely for measuringwind tunnel flow field density distributions and structural deflections. The goal
of this proposal is to develop a general purpose, modular, fringe analysis system
which will be able to use global and expert knowledge to control the processing of
fringe patterns into useful engineering data.
During Phase I of this proposal, the VAX/VMS software architecture for this system
was designed and critical components were prototyped to insure the implementation
method would meet the system design goals. In addition, existing in-house fringe
locating algorithms were applied to NASA wind tunnel fringe data and were shown to
semi-automatically locate the fringes.
Phase II of this proposal will implement the Phase I architecture in software to
produce a prototype Fringe Analysis System (FAS). Specifically, the FAS monitor,
core components of the Fringe Processing Command Language, and fringe locator modules
will be
developed. In addition, a prototype Expert Decision Module will be developed and
its use within the FAS environment evaluated.
Project Title:
Measurement of Chlorophyll, Related Pigments, and Productivity in the Sea
08.15-1315
Measurement of Chlorophyll, Related Pigments, and Productivity in the Sea
Biospherical Instruments Inc.
4901 Morena Blvd, #1003
San Diego
CA
92117
Booth
Charles R.
NAS7-969
Amount:
JPL
NAS7-942
Abstract:
The Phase I effort successfully demonstrated a new method of remotelymaking instantaneous measurements of the rates of primary production in phytoplankton
in the ocean. This approach avoids the manpower-intensive requirements of previous
methods and will allow NASA to make and correlate measurements of chlorophyll and
productivity with the optical signals sensed by spaceborne sensors at levels not
previously practical. As a result of this technique, the linkage between ocean color
and production will be further developed.
A series of models was developed that suggested that the rates of solar-stimulated
fluorescence from chlorophyll in plankton provided a good estimation of the concentration
of chlorophyll and a measure of the rates of carbon fixation of primary production.
A series of field tests verified these models and the agreement was excellent:
Natural fluorescence is readily measured and provides an accurate and rapid determination
of both the photosynthetic rate and pigment concentration. The small size and low
power consumption for the sensor would allow easy adaption to a variety of field
sampling. The biological and optical relationships fundamental to this new technique
will be refined and verified. This sensor will be designed and tested for validation.
Project Title:
Time-Resolved In-Situ Field Measurement of the Liquid and Frozen Water Contents of
08.15-1512
Time-Resolved In-Situ Field Measurement of the Liquid and Frozen Water Contents of
Snow
Ophir Corp.
7333 West Jefferson Ave, Suite 210
Lakewood
CO
80235
Nelson
Loren D.
NAS7-966
Amount:
JPL
NAS7-943
Abstract:
In Phase I of this SBIR research effort we have fabricated prototypehardware and demonstrated in the laboratory that is feasible to independently and
simultaneously sense the liquid (unfrozen) and ice (frozen) water content of in-situ
natural snowpack in real-time with an electronic sensor.
Such measurements are critical for "ground-truth" assessment of active and passive
satellite microwave sensors used in high-
latitude environmental research and military monitoring of arctic sea ice. Microwave
reflectivity and emissivity of snowpack are strongly dependent on its unfrozen water
content.
Phase I laboratory tests and theory indicate that we will be able to extend our preliminary
Phase I results to simultaneous real-
time volumetric measurement of liquid, air, and frozen water in natural snowpack
in Phase II development.
This will require refinements to our Phase I designs to eliminate interfering effects
such as space charge polarization, DC conductivity offsets, and insulation caused
artificial Debye dispersion.
We will then test our second generation snow-liquid-water-content sensor technology
in the field during cooperative field-trials sponsored by the Division of Ice Dynamics
of the U.S. Geological Survey.
Project Title:
Variable Emissivity Electrochromic Panels for Control of Radiant Energy Transfer
09.04-9450
Variable Emissivity Electrochromic Panels for Control of Radiant Energy Transfer
in Spacecraft
EIC Laboratories Inc.
111 Downey Street
Norwood
MA
02062
Rauh
David R.
NAS8-37259
Amount:
MSFC
NAS8-35267
Abstract:
Heat transfer in the space environment is largely a radiative process. The emissivities of the surface linking the payload to the space environment are
key to the problem of temperature stabilization and control in orbiting spacecraft.
The purpose of the proposed research effort is to develop thin film coatings which
have variable thermal emissivities and variable solar absorptivities. The development
of such coatings will provide a means of actively controlling heat transfer between
orbiting spacecraft and the space enviroment. Modulation of the emittance and absorptance
is achieved by the passage of a small DC electric current and is based on the concept
of electrochromism. The Phase I program was successful in demonstrating the principle
of variable thermal emittance (e = 0.06-0.75) and variable solar absorptance (as
= 0.32-0.98) switching in thin films of WO3. In addition, the concept of a solid-state
five-layer electrochromic coatings was formulated and optical switching experiments
showed
that variable emittance/absorptance coatings could undergo a large number of switching
cyles without degradation. The Phase II program is intended to develop electrochromic
coatings to the point of commercialization. To accomplish this objective, the Phase
II program will include: fabrication of variable emittance and variable absorptance
solid-state thin film coatings, demonstration of long-term optical switching, determination
of design parameters for thermal engineers, development of magnetron sputtering process,
and delivery to NASA of optimized variable thermal emittance and variable solar absorptance
electrochromic coatings.
Project Title:
Electronic Component Temperature Control Using Metal-Matrix Composites
09.05-1504
Electronic Component Temperature Control Using Metal-Matrix Composites
DWA Composite Specialties Inc.
21119 Superior Street
Chatsworth
CA
91311-4393
Supan
Edward C.
NAS3-24896
Amount:
LeRC
NAS3-24245
Abstract:
Research and development of high thermal conductivity metal-matrix compositeheat pipe for ???? will continue. The goal is to produce a metal-matrix composite
exhibiting thermal conductivity significantly higher than that of copper, and to
demonstrate performance of this "heat-pipe" material in controlling the temperature
of a demonstration electronic heat source. Variations of "DWG" composite material
(continuous graphite fiber in a metal matrix) tailored to optimize thermal conductivity
will be featured. The objectives are to optimize thermal conductivity; demonstrate
fabrication of generic shapes; develop joining methodology; assess performance of
the material used in real hardware; compile a beginning data base; and promote commercial
sector commitment to sponsor further ManTech programming. It is confidently expected
that DWG exhibiting more than 150% the thermal conductivity of copper can be demonstrated
and that several of the DWG composites will exhibit this high conductivity over the
temperature range -150C +150C. The potential applications for this unique and innovative
material concept are in controlling and dissipating heat from high-power-density
electronics as found in space, robotics, avionics, medical equipment, automative
components, computers, and advanced military systems. All these applications need
the reliability of solid-
state, superconducting "DWG" heat pipe.
Project Title:
Metallized Kevlar Space Tether System
09.06-5785
Metallized Kevlar Space Tether System
Material Concepts Inc.
666 North Hague Avenue
Columbus
OH
43204
Orban
Ralph F.
NAS8-37256
Amount:
MSFC
NAS8-35268
Abstract:
Metal coated Kevlar has been investigated as a space tether system. Several different tether samples were evaluated against atomic oxygen attack. A
pilot production unit capable of coating Kevlar was also designed and built. After
modification and improvement, the pilot production unit is capable of producing high-quality,
metal-coated Kevlar in a timely and economic manner. Samples were exposed to an
oxygen plasma, then evaluated. Results indicate that metal coating does not seriously
degrade strength. A copper undercoat, a nickel overcoat and an insulating polymer
overcoat over both metals appears to be a viable candidate.
The objective now is to produce a 2.5 kilometer metallized Kevlar tether which has
the required strength characteristics, the required electrical conductivity and the
required degree of protection against attack by atomic oxygen. Work will include
further production, exposure, and testing of selected candidate tether materials,
improvements in testing and process quality control, increasing production from the
pilot coating unit, examination of various tether constructions, preparation of processsing
and tether specifications, and production of a finished tether.
Project Title:
High Performance Ambient Temperature Heat Pipes
09.08-6551
High Performance Ambient Temperature Heat Pipes
Thermacore Inc.
780 Eden Road
Lancaster
PA
17601
Keddy
Michael D.
NAS8-37261
Amount:
Center: MSFC
NAS8-35269
Abstract:
The goal is to develop a 50 foot (15 m) long ambient temperature compositeheat pipe capable of transporting 5000 W. The aluminum/ammonia heat pipe will be
designed for operation in spec over the temperature range of 0-40C.
The concept selected for development was deemed the most desirable configuration
based on heat transport capability, mass, T, cost, ease of fabrication and integration
with the Thermal Bus. The design based on preliminary tests shows that the heat
pipe will be capable of transporting 8400 W on earth, and accepting a heat flux of
10 W/cm2 over the entire perimeter of the evaporator. The heat pipe as designed
has a 5.04 MW-in (12.8 MW-cm) figure of merit based on total pipe length which compares
to a 1.3 MW-in (3.3 MW-
cm) for the current state-of-the-art monogroove heat pipe.
The efforts will focus on developing full scale prototype heat pipes for ground testing
and space flight testing. The work will include fabricating and testing pre-prototype
heat pipes for the purpose of fully characterizing and optimizing their performance
as well as the development of a computer model to aid in predicting and evaluating
the performance of composite heat pipes. The hardware for coupling heat pipe components
having differing cross sections will be developed and the fabrication and testing
of scale prototype composite heat pipe(s) will be conducted.
Project Title:
Investigation of Metal Hydrides for Integration of Spacecraft Hydrogen Resources
09.09-0546
Investigation of Metal Hydrides for Integration of Spacecraft Hydrogen Resources
Hydrogen Consultants Inc.
P.O. Box 10454
Denver
CO
80210
Egan
Gregory J.
NAS8-37262
Amount:
MSFC
NAS8-35270
Abstract:
Metal hydride reversible hydrogen absorbers can manipulate hydrogen andheat in unique ways that may be useful in the Space Station Program. Preliminary
designs of hydride devices, which would interface with Space Station-related hydrogen
and thermal systems have been made. Realistic estimates of mass, power requirements,
volume and performance were derived for each potential application. Two applications
offer significant advantages over any known alternative: Hydrides can serve in heat
pumps or refrigerators with virtually no consumption of electric power. Hydrides
are also the lightest alternative for hydrogen storage when holding times are too
long for cryogenics. Additional work will carry both applications forward to demonstration
hardware. The limits of hydride refrigeration will be probed by studying desorption
dynamics in the low temperature region. Based on these results, the lowest temperature
refrigerator deemed feasible will be designed, constructed and tested. The long-term
hydrogen storage study has two parallel objectives: (1) investigate advanced lightweight
hydride materials and (2) construct a proof-of-concept demonstration tank, based
on state-of-the-art hydride materials.
Project Title:
A Reliable, Long-Lifetime Closed-Cycle Cryocooler for Space
09.12-3800B
A Reliable, Long-Lifetime Closed-Cycle Cryocooler for Space
Creare Inc.
P.O. Box 71
Hanover
NH
03755
Sixsmith
Herbert
NAS5-29436
Amount:
GSFC
NAS5-28642
Abstract:
This proposal describes Phase II of a program to develop a 5 watt, 70Kcryocooler based on rotating turbomachines in a reverse-
Brayton cycle. The recently completed Phase I of this program established the preliminary
design specifications for the cryocooler and showed that the proposed concept is
feasible. The objective of Phase II is to build and test a single stage, closed-
cycle cryocooler using miniature turbomachinery. The main component development
effort will center around the development of a high-speed motor/centrifugal compressor
unit. We will use existing designs/technology for the other cryocooler components.
The turboexpander design will be based on that of other expanders we have built
in the past to meet very similar specifications, and heat exchanger suitable for
demonstrating the cycle on earth will be built from commercially available finned
tubing. This effort will result in a working engineering model of a turbomachine-based
cryocooler which will be used to demonstrate the concept, validate the component
design methodologies, and establish the design for a
flight prototype cryocooler.
Project Title:
09.13-5000
Handheld Optical Radar
Odetics Inc.
1515 S. Manchester Avenue
Anaheim
CA
92802-2907
Drap
Robert P.
NAS9-17604
Amount:
JSC
NAS9-17289
Abstract:
The general system configuration and specifications for the HandheldLaser Radar in spaceborne proximity operation applications have been determined.
Detailed studies on the range processing electronics and optics were conducted.
Further research will encompass the development, fabrication and test of prototype
laser radar equipment aimed at space proximity operations, robotic manipulator control,
and precision measurement applications. The prototype equipment will feature high
accuracy, small size and lower power consumption and will be tested to demonstrate
the suitability for space applications.
Project Title:
Non-Azeotropic Spacecraft Cooling Systems
09.14-4942
Non-Azeotropic Spacecraft Cooling Systems
Frederick A. Costello Inc.
12864 Tewksbury Drive
Herndon
VA
22071
Costello
Frederick A.
NAS5-29439
Amount:
GSFC
NAS5-28643
Abstract:
We propose to design, build, ground test and flight test a small-scale, complete, working spacecraft temperature-control system that uses a non-azeotropic,
two-phase fluid as the working medium. The innovation lies in the use of the non-azeotropic
fluid. In Phase I we showed analytically that this novel system has great potential.
We resolved all of the previously identified problems. In addition, to resolve
the one potential problem that our analyses uncovered, we built a model of and ground
tested a complete system, not just the mixing section. This system will bring the
technology development to completion. All that will remain will be to implement
the concept in a full-scale application.
Non-azeotropic fluid mixture boils not at a fixed temperature but over a small range
in temperature (at a fixed pressure). Therefore, unlike conventional fluids, the
thermodynamic quality can be readily determined by sensing the easily measured temperature.
The following advantages result: simpler and more
reliable control systems; faster control system response; higher average evaporator
and condenser heat-transfer coefficients; smaller evaporators and condensers; reduced
fluid flow rates; lighter temperature-control systems, and less power practical means
for measuring quality. Quality sensors are heavy and costly and their response time
long. Instead, either the fluid is superheated and poor heat-transfer coefficients
are accepted or the platetemperature is measured and the control-system response
is long.
Project Title:
Modular Cold Plates For High Heat Fluxes
09.16-1227
Modular Cold Plates For High Heat Fluxes
Thermacore Inc.
780 Eden Road
Lancaster
PA
17601
Dussinger
Peter M.
NAS9-17610
Amount:
JSC
NAS9-35272
Abstract:
Full and effective use of the thermal bus on the space station will requireuniversal thermal/mechanical mounting plates for power dissipating experiments and
permanent equipment. The cold plates designed for this purpose will use heat pipe
technology to increase the thermal conductivity of the plates and to minimize the
contact resistance between the plates and the thermal bus.
Flexible heat pipes with a cold plate as an evaporator will also be developed. These
can then be coupled to the thermal bus and will increase the utility of the thermal
bus significantly.
The efforts will be directed at developing high performance modular cold plates with
an emphasis on system integration with the space station. Cold plates, flexible
heat pipe-cold plates, and thermal bus couplers will be designed, fabricated, and
tested in depth. The results of this developmental effort will aid designers in
system studies for the heat rejection system of the space station.
Project Title:
A Helium-3/Helium-4 Dilution Cryocooler for Operation in Zero Gravity
09.19-8629
A Helium-3/Helium-4 Dilution Cryocooler for Operation in Zero Gravity
Alabama Cryogenic Engineering Inc.
P.O. Box 2451
Huntsville
AL
35804
Hendricks
John B.
NAS8-37260
Amount:
MSFC
NAS8-35273
Abstract:
The proposed Phase II effort is an experimental program to demonstratethe concepts developed in the Phase I study. Three alternate approaches to the operation
of a zero gravity dilution refrigerator were developed in Phase I. The method selected
uses surface tension forces to separate and circulate the He-3 rich component in
a He-4 circulation dilution cycle. The absence of gravity means that the space refrigeration
cycle is quite different from the cycle used in earth based refrigerators. The Phase
II effort will demonstrate, in the earth laboratory, the principles of the zero gravity
machine.
Project Title:
Novel Electrodes for Hydrogen-Bromine Battery
10.01-7270
Novel Electrodes for Hydrogen-Bromine Battery
Giner Inc.
14 Spring Street
Waltham
MA
02154
Jalan
Vinod
NAS3-24878
Amount:
LeRC
NAS3-24394
Abstract:
Poisoning of the hydrogen electrode by ion, and intercalation of carbonbased bromine electrodes are life-limiting factors in state-of-the-art hydrogen/bromine
batteries. Electrocatalysts which have improved resistance to these limiting factors
were identified, prepared and evaluated. These electrocatalysts were evaluated in
half-cell configuration as well as in a complete hydrogen/bromine battery based on
a solid polymer electrolyte configuration. The complete battery was successfully
subjected to over 150 quick charge/discharge cycles. This technology, after optimization
will lead to stable and efficient hydrogen/bromine batteries for long-term applications
of NASA such as space stations.
Project Title:
High Efficiency Radiation-Resistant Indium Phosphide Solar Cells
10.03-6000
High Efficiency Radiation-Resistant Indium Phosphide Solar Cells
Spire Corp.
Patriots Park
Bedford
MA
01730
Spitzer
Mark
NAS3-24857
Amount:
LeRC
NAS3-24395
Abstract:
This Phase II proposal addresses radiation-resistant indium phosphide(InP) solar cells. Owing to unusual radiation damage annealing properties, (1-3)
such cells are of considerable interest for space applications. Research in Phase
II has as its primary object the development of innovative cell processing techniques
that may be applied to cell manufacture.
In Phase I, the feasibility of various InP cell fabrication techniques were evaluated.
A new cell fabrication process based on ion implantation was identified, and all
steps in the cell fabrication process were evaluated. Solar cells with efficiency
of 10% were fabricated with the techniques identified in this research. Concurrently,
modeling was carried out which indicates the manner in which efficiency of 20% may
be attained. The modeling and analysis of actual cells fabricated during Phase I
has identified areas requiring further research in Phase II. This Phase I research
has thus established the feasibility of the
proposed work.
In Phase II, research will be carried out that addresses specific problems in cell
design and fabrication that were identified in Phase I. This research will include
an investigation of improved junctions and junction formation techniques. Phase
II also includes research on the contact metallurgy. Various types of cells will
be fabricated for testing of radiation resistance.
Project Title:
Device to Measure Reversing Flow Pressure Drops in Stirling Engine Heat Exchangers
10.04-2221A
Device to Measure Reversing Flow Pressure Drops in Stirling Engine Heat Exchangers
Sunpower Inc.
6 Byard Street
Athens
OH
45701
Wood
J. Gary
NAS3-24879
Amount:
LeRC
NAS3-24396
Abstract:
The effect of oscillating flow on pressure drop and heat transfer isvery important to the design and optimization of Stirling engines. Even with all
the present work being done on Stirling cycle machines, very little is known about
oscillating flow. The purpose of this project is to generate the needed basic test
data on oscillating flow pressure drop.
A novel test rig has been designed for measuring pressure drop under oscillating
flow conditions. The unit is a dedicated piece of hardware and thus allows for the
measurement of pressure drop independent from the other processes and losses that
occur in Stirling cycle machines.
The rig is designed to operate at frequencies from less than 1 hertz up to greater
than 120 hertz, and at test pressures up to 150 bar. It is thus capable of testing
heat exchangers and regenerators for most existing and proposed engine designs including
those of the NASA SP-100 program.
Fabrication of the hardware will be completed and the operation of the unit tested.
The rig will then be used to generate basic test data on oscillating flow pressure
drop.
Project Title:
A Large Deployable Solar Concentrator with Receiver & Heat Storage
10.04-7039
A Large Deployable Solar Concentrator with Receiver & Heat Storage
Energy Science Laboratories Inc.
11404 Sorrento Valley Rd, #113
San Diego
CA
92121
Carroll
Joseph A.
NAS3-24882
Amount:
LeRC
NAS3-24397
Abstract:
We investigated designs for 2 key components of solar dynamic power systems: concentrator and receiver. Our concentrator stows compactly for launch, on the
unused 2nd Remote Manipulator System ledge. The receiver ??????? both concepts greatly.
The Phase I study led us to downsize the concentrator from 35 m to 14 m across.
This fits NASA's program needs better and also reduces production tooling cost.
We also discovered a better stowing geometry, which may allow 4 concentrators to
be stowed on one RMS ledge. We also fabricated small self-deploying models which
validated our stowage/deployment concept. The Phase II effort will revise the design,
fabricate 20% prototypes & sections of full-scale models, and test for performance
ruggedness.
The receiver evolved from separated-storage in liquid media to integral storage for
a Brayton cycle in solid media. This prevents contamination from leakage of condensible
volatiles. Several receiver features were discovered which raise system efficiency
for any given concentrator. The Phase II effort will revise the design, model the
system behavior, and fabricate & test critical components.
Project Title:
Thermally Stable Electrolytes for Rechargeable Lithium Batteries
10.08-1140
Thermally Stable Electrolytes for Rechargeable Lithium Batteries
Covalent Associates Inc.
52 Dragon Court
Woburn
MA
01801
Koch
Victor R.
NAS7-967
Amount:
JPL
NAS7-944
Abstract:
Phase I research has identified two organolithium salts that cycle wellin Li/TiS2 cells containing sulfolane. Of major importance was the discovery that
one organolithium salt, which failed as a supporting electrolyte, may be used as
a high energy cathode material. During Phase II, we will further characterize the
stability of organolithium salt/sulfolane electrolytes with Li via SEM/ESCA and a
new grazing angle FTIR technique. This technique allows for the in situ collection
of infrared data at the Li/electrolyte interface. Full Li/TiS2 cells incorporating
organolithium salt/sulfolane will be prepared and cycled. Particular attention will
be paid to cathode composition and electrolyte wettability thereof. Finally, the
new high energy density cathode material will be cycled in both cyclic ether and
sulfolane-based electrolytes. Both pressed and pasted cathode formulations will
be studied. The best combinations of electrolyte and cathode will be extensively
cycled in full cells with an emphasis on temperature, rate, and depth of discharge.
At the end of Phase II, hermetically sealed cells will be delivered to JPL for inhouse
evaluation.
Project Title:
Temperature Sensitive Variable Area Joule-Thomson Expansion Nozzles
11.03-1856A
Temperature Sensitive Variable Area Joule-Thomson Expansion Nozzles
General Pneumatics Corp.
7662 E Gray Road, Suite 107
Scottsdale
AZ
85260
Walker
Graham
NAS10-11322
Amount:
KSC
NAS10-11144
Abstract:
Gas liquefiers utilize isenthalpic (Joule-Thomson) expansion of cooled,compressed gas to generate refrigeration. Effective usage of the compressed gas
requires a variable mass flow rate: a high initial flow with progressive reduction
to the operating condition and intermittent flow thereafter according to load demand.
A common problem of fixed orifice nozzles is blockage by condensed contaminants
in the expanding fluid. Innovative Joule-Thomson expansion nozzles were investigated
experimentally. Materials having different coefficients of thermal contraction were
incorporated in a J-T nozzle--to achieve the load demand flow characteristic. The
problem of orifice blockage by condensed contaminants was resolved by design for
expansion of the compressed gas in a tappered annulus with the annular labyrinth
flow spoilers acting as catchment reserviors. The experimental prototype nozzles
were equipped with a screw flow adjustment capable of precise control over a wide
range, permitting the same
nozzle to be used in a variety of applications or in permitting the same application
for a wide variety of flow regimes.
Further work will extend the flow capacity of the new nozzle design to embrace most
of the potential space and non-space orientated J-T cryocoolers reliquefiers. A
critical design review will be carried out to achieve minimum production time and
cost for the new nozzles. Fabrication and test of prototype closed cycle Linde-Hampson
cryocooler liquefiers is proposed. These would incorporate the novel J-T nozzles
and an innovative diaphragm compressor with linear electric actuator.
Project Title:
Internal Fluid Mechanics of Liquid Propellant Rocket Thrust Chambers
11.06-0511
Internal Fluid Mechanics of Liquid Propellant Rocket Thrust Chambers
Scientific Research Associates Inc.
P.O. Box 498
Glastonbury
CT
06033
Gibeling
Howard J.
NAS8-37255
Amount:
MSFC
NAS8-35274
Abstract The multicomponent, multiphase, reacting flow inside a liquid propellant
rocket thrust chamber influences both the performance and life of the rocket engine.
A unique Lagrangian discrete particle transport model has been developed and combined
with an existing state-of-the-art, multidimensional, time-dependent, compressible
Eulerian Navier-Stokes computer code. The procedure was successfully used to compute
a gas/particle flow with strong interaction due to droplet evaporation. The effort
will continue the development of this computer code by investigating and implementing
an advanced turbulent dispersion model for particle motion, and a stochatic droplet
injection model. These models will be evaluated extensively and detailed comparisons
with available experimental data will be made. A sensitivity study will be conducted
to determine the applicability of the various models to liquid propellant rocket
thrust chamber flows. Also, the convergence of the Eulerian-Lagrangian coupling
procedure will be improved by use of matrix conditioning and other applicable techniques
in order to reduce code execution times signifi-
cantly. Both the Eulerian and Lagrangian analyses will be modified to include a
sufficient number of species to adequately model typical liquid propellant combustion
process. A turbulent flow combustion model will be developed, implemented and tested
by comparison with experimental data. Several axisymmetric reacting flow calculations
for rocket thrust chambers will be performed. Finally, the analysis will be extended
to treat three-dimensional thrust chamber flows, and will be demonstrated by a calculation
for a realistic chamber-injector configuration. Additional computer code variation
will be performed to decrease computer run time.
Abstract:
Project Title:
Reagentless Water Quality Monitor (Organic Content)
12.01-2484
Reagentless Water Quality Monitor (Organic Content)
Astro Resources International Corp.
100 Park Avenue
League City
TX
77573
Ejzak
Edward M.
NAS9-17612
Amount:
JSC
NAS9-17282
Abstract:
The innovation being investigated is a reagentless Total Organic CarbonAnalyzer that can determine quantitative TOC values on a wide variety of organic
inputs.
Based on all information available to date (including Phase I results), the best
way to analyze a water sample for TOC is still oxidation to carbon dioxide (CO2).
The chosen method of oxidation is high energy ultraviolet light irradiation at elevated
temperatures with subsequent gas sparing to remove CO2. This is followed by gas-liquid
separation and gas analysis for CO2 in a specialized Infrared Analyzer (IRA) which
is free of water interference.
The results and conclusions of Phase I efforts include: (1) "Delta" conductivity
analysis for quantitative CO2 measurement after oxidation is not acceptable. (2)
Added heat improves UV promoted oxidation. (3) Reagentless TOC analysis of typical
NASA water samples at 5PPM TOC or less is possible given enough UV energy, heat input,
and time.
Phase II approach is to characterize and improve the technique. Also, the specific
problems of sparging and gas-liquid separation at zero gravity, speed of response,
NASA water recovery system interface, computer interface/control, IRA response, power
consumption, and size will be investigated.
Project Title:
A Novel Membrane-Based Water Reclamation Post-Treatment Unit
12.01-4100
A Novel Membrane-Based Water Reclamation Post-Treatment Unit
Bend Research Inc.
64550 Research Road
Bend
OR
97701-8599
Ray
Roderick J.
NAS9-17611
Amount:
JSC
NAS9-17286
Abstract:
On future long-term space missions, launch and resupply penalties associatedwith the storage and one-time use of the required quantities of water will be prohibitive;
consequently, space craft wastewater recycle systems are now under development.
Most system configurations are hybrid in nature--i.e., they are a combination of
several technologies, each optimized for the specific waste-
water stream to be treated. At the heart of most systems is a phase-change subsystem
that produces distillate. Another source of relatively clean water is the dehumidification
of the space craft cabin, which produces a "humidity condensate." These condensate
and distillate streams must be "polished" by a post-
treatment subsystem typically consisting of expendable sorption beds.
The goal is to develop a hybrid post-treatment subsystem consisting of a combination
of conventional sorption beds and a membrane module. The membrane module will act
to reduce the level of contaminants in streams entering the sorption beds and thus
reduce the rate of use of the sorption beds and the corresponding resupply penalty.
The goal of the project is to deliver a breadboard hybrid post-treatment subsystem
to NASA-JSC for testing.
Project Title:
Tissue Fixation Apparatus for Flight Experimentation
12.02-8606
Tissue Fixation Apparatus for Flight Experimentation
Phyoresource Research Inc.
707 Texas Ave, Suite 202-d
College Station
TX
77840
SCHELD
H. W.
NAS9-17608
Amount:
JSC
NAS9-17291
Abstract:
The objective is the development of modular flight research hardwarewhich will meet the requirements of a broad range of plant and animal cell experiments
in the environment controlled growth and chemical treatment of cultured cells, tissues,
or organisms. A list of experiments has been developed in collaboration with a representative
group of NASA life sciences investigators and concepts for hardware configuration
developed and tested through use of mockups and breadboard models. In the continuing
effort, a previously used hardware item, the SO-15 cell culture system, will be prepared
for use in preliminary experimentation and a laboratory research effort will be carried
out to develop baseline data for guidance of culture chamber design. The final product
of this effort will be in a engineering development unit of hardware which incorporates
the requirements of the investigators into the space occupied by a single Shuttle
locker.
Project Title:
In-flight Acquisition of Engineering Data for Plant Growth System Design
12.04-8606
In-flight Acquisition of Engineering Data for Plant Growth System Design
Phytoresource Research Inc.
707 Texas Ave., Suite 202-d
College Station
TX
77840
Scheld
H. W.
NAS9-17609
Amount:
JSC
NAS9-17292
Abstract:
This project will undertake the development of a flight test system forroutine exposure for plants or plant models aimed at generation of engineering data
necessary for design and construction of space-rated plant culture systems for use
in Shuttle, Spacelab or beyond. The general data base on plant interaction with
its environment was evaluated and a set of test protocols and apparatus defined for
acquisition of flight data. Currently available and potential test support hardware
items have been evaluated. In the continuing effort, hardware will be fabricated
and tested and a series of routine data acquisition flight tests will be developed.
Project Title:
An Animal Development Habitat for Space Biology
12.05-3309
An Animal Development Habitat for Space Biology
Star Enterprises Inc.
3595 N. Hinkle Rd
Bloomington
IN
47401
Alberts
R. Jeffrey
NAS2-12476
Amount:
ARC
NAS2-12113
Abstract A full-size model of a life support system has been designed and constructed
to sustain a lactating rat and her offspring during a Shuttle mission. The configuration
of this burrow-like habitat meets the spatial and environmental requirements of the
Shuttle middeck. An innovative aspect of the design phase was a program of observational
and choice tests of animals, which was used to establish their needs and preferences.
The Habitat model includes: nest, den, passageway, waste and airhandling modules,
lighting and temperature control, regulated airflow, two video cameras and timelapse
recording capability, as well as food and water provisions for the full mission.
Further objectives are: (a) construction of a flight-type prototype of the Animal
Development Habitat, (b) provision of extensive bioengineering data on its functional
characteristics and the quality of animal life within it, (c) assembly drawings,
and (d) videographic documentation of Habitat structure and function. Use of the
Habitat by NASA and private interests is anticipated on the Shuttle and space station.
Components developed for the project have commercial potential.
Abstract:
Project Title:
An Open Path Diode Laser Flux Meter for Trace Gases
12.06-9500
An Open Path Diode Laser Flux Meter for Trace Gases
Aerodyne Research Inc.
45 Manning Road
Billerica
MA
01821
Stanton
Alan C.
NAS2-12433
Amount:
ARC
NAS2-12117
Abstract:
The purpose of this study is the development of instrumentation to measurefluxes of trace gases in order to determine their sources and sinks in the biosphere.
A tunable diode laser source combined with an open path multiple pass absorption
cell is used for trace species detection at sub-ppb levels. Absorption lines for
sensitive, interference-free atmospheric pressure detection of important trace gases
have been identified. Laboratory tests, including measurements of atmospheric nitrous
oxide at atmospheric pressure, demonstrated the feasibility of the multiple pass
diode laser approach. Preliminary evaluations of alternative cell designs and data
processing techniques have also been performed.
Phase II, an open path tunable diode laser monitor of trace gases will be interfaced
with a sonic anemometer and thermistor temperature sensor to permit simultaneous
measurements of trace species concentration, temperature, and fluctuating velocity
field. These measurements will be correlated to obtain fluxes of at least four trace
species, possibly including nitrous oxide,
methane, carbon monoxide, carbon dioxide, ammonia, carbonyl sulfide, or carbon disulfide.
The result will be a prototype instrument which will be delivered to NASA and tested
in field measurements of trace species fluxes.
Project Title:
Operational Forecasting of Florida Sea Breeze Thunderstorms Using a Mesoscale
13.05-1424
Operational Forecasting of Florida Sea Breeze Thunderstorms Using a Mesoscale
R*SCAN Corp., Business & Technology Center
511 Eleventh Avenue South
Minneapolis
MN
55415
Lyons
Walter A.
NAS10-11321
Amount:
KSC
NAS10-11142
Abstract:
Sea breeze convection (SBC) thunderstorms are a major impediment to SpaceShuttle operation at KSC, and are notoriously difficult to forecast. A mesoscale
numerical model (MNM), previously used as a research tool [Pielke, 1974], shows a
great potential for improving forecast guidance in the "mesoscale forecast gap,"
extending from T+1 to T+12 hours. Three case studies with similar synoptic conditions
but distinctly different SBC storm patterns were simulated. A hybrid thunderstorm
potential index, combining model predicted mesoscale maximum vertical motion fields
and the perturbations of thermodynamic stability due to localized moisture convergence,
yielded very encouraging results when compared to thunderstorm distributions (determined
by a lightning tracking system). The model physics will be upgraded by (1) incorporating
the Fritsch-Chappell convective parameterization scheme to forecast cloud tops and
wind gusts, (2) improving the initialization schemes for cloudiness and non-homogeneous
and non-
stationary synoptic situations, and (3) developing a fine mesh grid (2.5 km) version
to account for the local convergence effects of Cape Canaveral. A two-year test
and evaluation program (up to 100 simulations) is proposed, with the second year
generating real-time forecasts transmitted for use on an experimental basis. Other
model uses (evaluating dispersion regimes and providing input to the MIDDS and MARSS
systems) will be tested experimentally.
Project Title:
Space Flight Gas Temperature Probe
13.08-8581C
Space Flight Gas Temperature Probe
Remtech Inc.
2603 Artie Street, Suite 21
Huntsville
AL
35805
Bender
R. L.
NAS8-37258
Amount:
MSFC
NAS8-35277
Abstract:
A double-shielded, multi-sensor gas temperature probe with a thermalsink base is proposed to provide accurate measurement of the Orbiter base region
gas temperature during Shuttle ascent. This component of the ascent environment
was not successfully measured during Shuttle development flights. Research established
the technical feasibility of the multi-sensor concept and provided preliminary design
data for a probe configuration which meets the thermal responsiveness and accuracy
requirements. Measurements of base gas temperatures of 3450R at high altitude (low
density) can be achieved. The design will be finalized based upon the results of
thermal and structural development tests to be performed by REMTECH. Two flight
qualified probes will be fabricated and deliverable for acceptance tests. The flight
probe will be flown on a future Shuttle flight and provide gas temperature data which,
in conjunction with the heating rate measurement, will define heat transfer coefficients
at critical base locations. Knowledge of the heat transfer coefficient is essential
to complete understanding of the flowfield and for scaling of test data to future
designs of Shuttle derivative launchvehicles.
Project Title:
Advanced Low-Cost Universal 20 GHz Monolithic Receiver Front-End
14.01-6642
Advanced Low-Cost Universal 20 GHz Monolithic Receiver Front-End
Microwave Monolithics Inc.
465 E. Easy Street
Simi Valley
CA
93065
Peterson
Wendell C.
NAS3-24894
Amount:
LeRC
NAS3-24246
Abstract:
A program to fabricate all components of a low cost universal monolithicreceiver front end covering the 17.7 to 20.2 GHz band has been undertaken. Key components
of the front end, the low noise amplifier (LNA) and the local oscillator (LO), have
been designed to establish feasibility of the proposed approach. Results indicate
that a front end with 3.5 dB noise figure and in excess of 30 dB gain is feasible,
with a projected production cost under $1,000 after fabrication of the first 10,000
units.
The designs of the LNA and LO will be finalized and the mixer and intermediate frequency
amplifier designs completed. Following fabrication utilizing proprietary "flash
annealing" techniques, the chips will be evaluated and modified as required, resulting
in a monolithic "chip set" applicable to a wide range of advanced communications
systems. Revised cost estimates will then be generated. Final component integration
to form a complete receiver front end is the ultimate objective.
The approach will permit adaption to neighboring frequencies with minor mask modifications,
further enhancing the utility of the proposed MMIC receiver front end.
Project Title:
Advanced GaAs Monolithic 20 GHz RF Switch Matrix
14.02-6642
Advanced GaAs Monolithic 20 GHz RF Switch Matrix
Microwave Monolithics Inc.
465 E. Easy Street
Simi Valley
CA
93065
Ch'en
Daniel R.
NAS3-24895
Amount:
LeRC
NAS3-24248
Abstract:
Fabrication and evaluation of a novel advanced GaAs monolithic 20 GHzRF switch matrix for satellite communications applica-tions has been accomplished.
The feasibility of the RF switch matrix approach has been verified by detailed study
of a proprietary crosspoint switching element design and the analysis of its performance
in large arrays. Passive FET switches are used for signal steering, while FET buffer
amplifiers provide an overall insertion loss of 0 dB, allowing two dimensional cascading
to form larger arrays (up to 100 X 100), also with 0 dB insertion loss. A proprietary
packaging concept initially conceived for a monolithic IF switch matix was extended
to 20 GHz to facilitate modular construction of large crosspoint matrices and interfering
to other systems components.
The next level of effort will concentrate on demonstration of the monolithic RF matrix
switch concept by building a complete 3 X 3 switch matrix. Following a second design
iteration of the matrix and its associated package and test fixture, a 10 X 10 or
TBD size
monolithic switch matrix will be designed, complete with on-chip buffer amplifiers
and partial drive electronics.
Project Title:
Facility for Integrated System Testing (FIST) of Space Station Communication and
14.03-3220
Facility for Integrated System Testing (FIST) of Space Station Communication and
Tracking System
Stanford Telecommunications Inc.
6888 Elm Street
Mclean
VA
22101
Zakrzewski
NAS9-17607
Amount:
JSC
NAS9-17281
Abstract:
The development and delivery of a prototype facility for integrated simulation,modeling and analysis of potential space station multi-access communication options
has been accom-
plished. The new hybrid modeling technique for the RF link analysis combines the
inherent time benefits of analytic modeling extensions (such as importance sampling
and extreme value theory) with the flexibility of a Monte Carlo direct simulation
approach. An agenda-based expert system is proposed to take outputs from the RF
link analysis and assess potential impacts on the multi-access technique. Run time
control of this library of modeling tools and the innovative approaches to chaining
data flow through the communication link components is performed by a master executive
also to be implemented with Artificial Intelligence techniques. The goal is to provide
JSC with a fully optional prototype which will reduce the time it takes a system
engineer to evaluate a communication system and thus increase the number of options
he can consider in Real Time. The results validated the technical feasibility of
all module and user interfaces and demonstration CPU time savings of multipleorders
of magnitude.
Project Title:
Low Power Digital Controller for Laser Communications
14.07-3319
Low Power Digital Controller for Laser Communications
The Navitrol Company Inc.
9204 Markville Drive
Dallas
TX
75243
Brown
Richard J.
NAS5-29437
Amount:
GSFC
NAS5-28645
Abstract:
The objective of this research is the development of a Low Power DigitalController (LPDC), for providing the overall control electronics functions for a
highly accurate and stable laser pointing and tracking system to be applied to laser
inter-
satellite communication system. Reductions in system power, size and weight are
to be achieved while increasing performance by application of the latest technology
in CMOS VLSI, computer architecture and advanced control system theory. The computational
load for a control system processor to meet laser pointing and tracking requirements
is considerable and, without severe design compromises cannot be handled in conventional
microprocessors. With the LPDC system it can.
The LPDC is a highly modularized multi-processor system, expandable or contractable
to fit many and varied applications. Results clearly demonstrate the feasibility
of such a system. The same technology applied to processing will be applied to reduce
size, weight and power of the interface electronics, as well.
Simulation and test results indicate that considerable gains can be made in power
usage reduction by applying new system techniques to cutting on and off the motors
and encoders.
Project Title:
A Color Schlieren System for Large Scale Low-Gravity MPS Fluids Experiments
15.01-7307
A Color Schlieren System for Large Scale Low-Gravity MPS Fluids Experiments
E/Erg Inc.
2030 E. Speedway #214
Tucson
AZ
85719
Poteet
Wade M.
NAS8-37254
Amount:
MSFC
NAS8-35278
Abstract:
A number of low-gravity materials processing experiments, such as crystalgrowth studies, require a specialized optical system capable of flow visualization.
A small prototype color schlieren imaging system has been developed and tested for
application to materials processing in space (MPS) programs. The system was successfully
constructed and subsequently tested on the NASA KC-
135 low-gravity aircraft. Design, construction and testing of a protoflight system
based on the prototype experience will begin. This will include applications of
improved filtering, real time image acquisition and temperature monitoring of the
experiment sample. This work will provide a foundation for the flight hardware development.
Project Title:
Ultrafine Particle and Fiber Production in Micro-Gravity
15.03-7039
Ultrafine Particle and Fiber Production in Micro-Gravity
Energy Science Laboratories Inc.
11404 Sorrento Valley Rd #113
San Diego
CA
92121
Webb
George W.
NAS8-37253
Amount:
MSFC
NAS8-35279
Abstract:
Results show that ultrafine particles and ultrafine fibers can be preparedby the evaporating material into an inert gas where it subsequently condenses. The
results also show that the floating material can be connected by techniques appropriate
to micro-
gravity. Here ultrafine particles and fibers are defined to have characteristic
diameters of less than 1000 angstroms. The growth process was found to be dominated
in its later stages by coales-
cence processes between particles and that the coalescence is made much worse by
convection in the inert gas. These results suggest that the technique will produce
smaller particles and fibers in microgravity.
The objectives are: to determine optimum growth parameters for smallest diameter
particles and fibers, to determine optimum heating methods for use in microgravity
and to determine optimum collection methods for use in microgravity. Experimental
test of the concept and methods in KC 135 reduced gravity flights will be conducted.
Preliminary design of orbital hardware and procedure
will begin. If the project is successful it will be possible to produce significant
quantities of ultrafine particles and fibers of a wide range of materials.
Project Title:
Lunar Oxygen Production from Ilmenite/Fluid Particle Processing Technology in Space
15.04-7840
Lunar Oxygen Production from Ilmenite/Fluid Particle Processing Technology in Space
Carbotek Inc.
2916 West T.C. Jester, Suite 101
Houston
TX
77018
Gibson
M. A.
NAS9-17605
Amount:
JSC
NAS9-17288
Abstract:
A primary objective is to measure extensive fluidized-bed characterizationdata for simulated lunar ilmenite reactor feedstock at simulated lunar gravity conditions.
These data will be combined with kinetics and solid reactivity studies already begun--a
second major ojective. This information then will be used to plan the explicit design
of a prototype lunar ilmenite reactor.
Another major objective is to extend the fluid-particle characterization data to
low, controlled gravity conditions characteristic of the space shuttle and space
station for commercial space processing applications.
The early work has shown that 1000 metric tonnes/year of oxygen can be produced using
an 8 ft. O.D. x 6 ft. I.D. x 20 ft. tall refractory-lined, stainless steel reactor.
The metal shell weight is 7 tons; internal insulation (firebrick) weight is 30 tons;
total 37 tons. Process conditions are the 1000C, 150 psia and equilibrium H2 conversion.
Ilmenite conversion is 90%; the reduction appears to follow a shrinking-core, chemical
reaction-
rate-controlled mechanism. Reduced-gravity fluid bed behavior and internal insulation
designs were identified as areas where additional study could result in higher solids
conversions and/or weight savings.
Project Title:
The Large Format Camera: Novel Analyses of Sensor Applications
15.05-7606
The Large Format Camera: Novel Analyses of Sensor Applications
Autometric Inc.
5205 Leesburg Pike, Suite 1308, Skyline 1
Falls Church
VA
22041
Lucas
Carroll
NAS8-37263
Amount:
MSFC
NAS8-35280
Abstract:
The capability of Large Format Camera products to support analyses ina variety of user disciplines has been documented. Comple-
mentary and competitive present and future imaging systems and their products were
compared with LFC cartographic and multispectral properties to demonstrate the potential
for LFC commercialization. Based upon the results of the earlier work it will be
shown how LFC acquisitions and products can be profitably commercialized. The main
goals are to refine procedures for exploiting LFC products, produce a prototype workstation
for such exploitation, compile procedures and manuals for using LFC materials, and
provide a training plan, a prototype training system, and training course materials.
A market analysis will be conducted and a commercialization plan will be established
working with the LFCIWG.