NASA 1994 SBIR Phase 1 Solicitation

Project Title:

HYBRID FLOATING BRUSH SEAL FEASIBILITY STUDY FOR THE HIGH TEMPERATURE ADVANCED GAS TURBINE APPLICATIONS

94-1	01.01	0051

HYBRID FLOATING BRUSH SEAL FEASIBILITY STUDY FOR THE HIGH
TEMPERATURE ADVANCED GAS TURBINE APPLICATIONS

Abstract:

The present proposal offers the possibility of a technological
jump in the use of Brush Seals, which in themselves represent a
novel technology presently being incorporated in the new
generation of jet engines. Turbine efficiency is strongly
associated with the blade tip clearance, and it can decrease
significantly through the unloading of the blade due to leakage
over its tip, and subsequent increase in the flow area over the
tip. The most basic cause resides with the radial displacements
of the rotor and the case when the clearance generally becomes
larger than the desired operating conditions.
A significant contribution towards the solution of the problem
has been the introduction of the brush seals. These types of
seals provide a principally compliant buffer between the blades
and the case, or at compressor and turbine interstages. While
these seals work relatively well, the brush wear at the
rotor/brush interface as well as its overheating seem to still be
a major obstacle to long term reliability. As the problem stems
in part from the large relative velocity and heat flux production
at the interface, the solution proposed here, the hybrid Floating
Brush Seal aims at reducing considerably (80%-90%) the relative
velocity thus completely eliminating this class of problems. To
further reduce overheating, be that from friction at the
interface, or from the extremely hot gases coming from the
combustor, a new procedure of combined film and transpiration
cooling is also incorporated within this new type of floating
brush.

Brush seal development is a specific technology that has been
identified by Government organizations(Air Force, Army), as well
as by private industry jet engine manufacturers (General
Electric, Textron Lycoming, Allied Signals, Pratt & Whitney,
Rolls-Royce) and seal manufacturers (Technetics, EG&G Sealol,
Cross Mfg), as very promising in the area of enhanced engine
primary and secondary stream management and SFC. Successful
conclusion of the undertaking proposed here will offer a new
class of brush seal devoid of the problems exhibited by the
present generation of brush seal. Such a brush could be used with
newly found reliability not only in the turbine and compressor
interstages but also as very efficient and reliable blade tip
seals. Its added transpiration cooling feature will possibly make
this brush usable even in the first stage of the high pressure
turbine.

Key Words

B&C Engineering Associates, Inc.
P.O. Box 2384
Akron, OH 44309

Project Title:

Experimental Simulation of Buoyancy Effects using Two Liquids inTurbo machinery Components

94-1	01.01	0333

Experimental Simulation of Buoyancy Effects using Two Liquids in
Turbo machinery Components

Abstract:

An innovative experimental technique is proposed which would allow
simulation of flows where buoyancy effects are important but
compressibility is not. The technique uses two liquids of different
density and seeds one of the two with fluorescent dye. Velocity
measurements are obtained using Laser Velocimetry (LV) with a
Refractive Index Matched (RIM) liquid. Use of the liquids allows
matching Rotation and Reynolds numbers with those of the engine
while maintaining a low rpm, thus providing distinct cost and cycle
time benefits in assessing and developing design alternatives.
Laser Induced Fluorescence (LIF) is used to track species diffusion
which can be related to temperature diffusion. The ability to use
acrylic models, when coupled with RIM fluid, provides complete
optical access. The technique would be demonstrated by obtaining
benchmark velocity and species diffusion (which can be related to
temperature diffusion) data in a compressor drum rotor which is a
critical component in stall line management. The program would
provide a novel concept for instrumentation and flow visualization
and would gather benchmark experimental data. The technique would
provide a new tool for NASA in obtaining data in a cost-effective
and timely manner.

The technique would have very significant advantages for
experimental investigation for flows where buoyancy is important
but compressibility is not. Such situations are common in gas
turbine components where secondary flow is used for cooling
purposes. In rotating machinery, it would allow matching of mass-
flow and tangential Reynolds numbers at lower rpm than possible
with a gas flow and would allow use of an acrylic model allowing
maximum optical access for laser-based measurement. Applications
other than turbomachinery would be found in the chemical process
industry and industrial power generation industry. Development of
this technique would provide SRA with an important
commercialization opportunity in its support service operation.

Key Words

Scientific Research Associates, Inc.
50 Nye Road, P.O. Box 1058
Glastonbury, CT 06033-6058

Project Title:

An Innovative Fuel Atomization Device for Gas Turbine Combustors

94-1	01.01	1600

An Innovative Fuel Atomization Device for Gas Turbine Combustors

Abstract:

This proposal introduces an innovative fuel atomization device,
the "smart nozzle", for gas turbine combustors. It consists of a
conventional fuel atomizer and an innovated piezoelectric driver.
It generates the spray through the fuel atomizer and modulates
the spray structure through the piezoelectric driver. By adopting
a conventional atomizer, the "smart nozzle" retains the basic
characteristics of the current fuel atomization system but adds
the controllability to spray structure. One will be able to
adjust and optimize combustor performance by control of the fuel
spray through the "smart nozzle".
An analytical model describing the spray cone angle and nozzle
discharge coefficient will be developed. The model will be
verified with experimental data. Open loop response of the smart
nozzle to control signal, such as the variation of cone angle
under different driving conditions, will be measured. Laser
Induced Fluorescence (LIF) will be used to measure spray
patternation. As a result of the proposed work, a database about
the smart nozzle operation will be compiled and used for flow
tests and combustor performance verification in Phase-II. The
acquired knowledge will lead to proper control of spray structure
for satisfactory combustor performance.

Smart nozzle enables on-line control of fuel spray and combustor
performance in a wide range of operating conditions. Concurrent
improvement in efficiency, and emissions reduction can be
achieved as a result of improved combustor performance. Such a
device can have a great market in gas turbine industry as well as
other liquid spray related industries.

Key Words

Berkeley Applied Science and Engineering
5 Third Street, Suite 530
San Francisco, CA 94103

Project Title:

Coupled Flow and Heat Transfer Analysis using Hybrid Structured-Unstructured Grids.

94-1		01.01	3304			AMOUNT REQUESTED $

Coupled Flow and Heat Transfer Analysis using Hybrid Structured-
Unstructured Grids.

Abstract:

A new CFD software technology is proposed for the simultaneous
analysis of fluid flow and wall heat conduction in propulsion
systems components. In gas turbine engines, the proposed software
will be particularly useful for analyzing turbine blades. Using the
proposed software, designers will be able to design better
turbine blade cooling techniques which will increase engine
efficiency by allowing higher turbine entry temperatures and/or
by requiring less compressed air. The design of other hot gas
section components will similarly benefit. The proposed software
will be unique in that it will simultaneously solve for
combusting flow within the hot gas section, coolant flow in the
geometrically complex coolant passages, and heat conduction
through the wall. Also unique will be the use of hybrid
structured/unstructured grids, which will simplify the generation
of grids for complex geometries. Implicit solution procedures
will be used for all modules. During Phase I, a 2D wall heat
conduction module will be developed and coupled with the existing
hybrid structured-unstructured modules, and time preconditioning
will be added to accelerate Navier-Stokes solver convergence for
low Mach number flows.

The new analysis system will allow designers to quickly analyze
flow and heat transfer for propulsion system components. The code
will be marketable to the aerospace industry and other industries.

KEY WORDS

Amtec Engineering, Inc.
3075 112th Ave N.E. Suite 106
PO Box 3633
Bellevue, WA 98009-3633

Project Title:

Intelligent Parallel Task Partitioning for Workstation Clusters

94-1	01.01	5601

Intelligent Parallel Task Partitioning for Workstation Clusters

Abstract:

Since workstation clusters are becoming more prevalent for
executing "production" parallel programs, we propose to develop
"intelligent" techniques for partitioning the parallel tasks of a
parallel program among workstations grouped in a cluster. Current
parallel programming environments (e.g.,PVM) enable the
programmer to view the workstation cluster as a single entity but
thrust upon the programmer the responsibility for determining how
to partition the various parallel tasks of the parallel program
among the workstations. Although programmers may relatively
easily specify an arbitrary partitioning, they may not so easily
specify an efficient partitioning. Our innovation will be to
employ artificial intelligence techniques to perform the
partitioning: the Intelligent Parallel Task Partitioning System
(IPTPS) will "learn" from past executions how of a particular
parallel program to modify accordingly the partitioning of the
current execution. We anticipate that for production runs of
internal fluid mechanics codes (i.e., ones needing to execute
several hundred or more times for parametric analyses), after
some learning curve, the IPTPS will allocate the program's tasks
among the workstations in a near optimal manner. After the
initial demonstration on internal fluid mechanics computations,
production codes of other application domains should be amenable
to being efficiently executed on workstation clusters with IPTPS.

The IPTPS will be useful in any industrial application
(computational fluid dynamics, structural mechanics, fluid flow,
thermal analyses, computational chemistry, numerical weather
prediction, etc.) in which workstation clusters can provide the
necessary computational power. Additionally, the IPTPS
methodology will also find application in other domains, such as
automobile traffic control, in which efficient, effective,
automated "load balancing" is useful.

Key Words

SYSTRAN Corp.
4126 Linden Avenue
Dayton, OH 45432

Project Title:

Enhanced Cooling of Turbine Blades with Perforated Ribs

94-1	01.02	0017

Enhanced Cooling of Turbine Blades with Perforated Ribs

Abstract:

Gas turbines are required to operate with gas flows at temperatures
more than 1400@C, much higher than the melting temperatures of
blade material. Ribs cast in internal passages of blades for
cooling, result in exorbitant pressure drops and extremely uneven
heat transfer distribution. This is mainly due to the rib-induced
"separation reattachment of cooling air". Perforated ribs are
proposed for heat transfer augmentation. It is anticipated that the
interaction between the flow through perforations and the main flow
over the rib, can increase turbulence intensity near the wall,
yielding enhanced and uniform heat transfer. The additional flow
path provided by perforated ribs can also lower the penalty in
pressure drops. The present investigation aims at obtaining the
distribution of local heat transfer coefficients by using liquid
crystal thermometry and understanding the complex interaction
between two flows. The local distributions obtained will determine
the extent of uniformity and enhancement of heat transfer. A square
channel with ribs on two opposite walls simulating internal
passages of blades will be employed. A wide number of operating and
geometrical parameters for perforated ribs will be examined.
Lynntech Inc., intends to adopt a dual-use approach for advanced
cooling techniques, rendering them available for aircraft engines
and industrial consumer-oriented applications.

The potential commercial applications for perforated ribs include
gas turbine blades employed in aircraft engines and power plant
utilities, heat exchangers for process and petrochemical
industries, fuel rods in nuclear reactors, evaporator and
condensers in refrigeration industries, tubes in boilers and heat
recovery units, etc.

Key Words

Lynntech, Inc.,
7610 Eastmark Drive,
Suite 105,
College Station, TX 77840.

Project Title:

The Variable Flow Number Pressure Fuel Nozzles

94-1	01.02	1322

The Variable Flow Number Pressure Fuel Nozzles

Abstract:

The performance of the traditional simplex pressure atomizer design
is limited/undesirable for its low Turn-Down Ratio(TDR) in its
application to the practical engines. An innovative variable
geometry/Flow-Number pressure nozzle concept is proposed to remedy
the defect of the current design. The program goal is to be
achieved by introducing a pressure activated fuel swirler plug into
the nozzle spin chamber. With this modification, at low
flow/pressure conditions, the swirl plug slots are to be partially
blocked and result in a smaller cross-section low Flow Number(FN)
fuel passage. At this mode, the fuel nozzle will effectively
increase the off-set of the fuel slots relative to the center of
the spin chamber. Thus at a given flow rate condition, the nozzle
will be operated at a much higher liquid velocity (due to low FN)
and angular momentum (due to the increased slot off-set). It will
then achieve a much better atomization performance at low flow
conditions as well as higher TDR for the entire nozzle operation
range.

This innovative nozzle design will achieve a much better nozzle
performance than me traditional counterpart. It will be widely used
in the gas turbine industry and industrial oil burner applications.
The improved nozzle performance can also be used in spray
atomization application at large.

Key Words

Sun Valley Technology Inc.
26700 Emery Industrial Parkway, Unit 4
Warrensville Heights, OH 44128

Project Title:

AIR ASSISTED FUEL ATOMIZATION SYSTEM

94-1	01.02	1535	A

AIR ASSISTED FUEL ATOMIZATION SYSTEM

Abstract:

This Phase I SBIR proposal will evaluate an innovative method for
obtaining a more uniform dispersion of smaller fuel droplets and
prevent droplet coalescing in order to reduce flame hot spots by
several hundred degrees. If successful, this SBIR program has the
potential to ease stage I turbine nozzle design and reduce NOx
formation during high power engine operation.
The basic Air Assist Fuel Atomization system operating principle is
to (1) extract a small amount of compressor discharge air, (2)
further compress it by approximately 25% in a engine mounted
turbocompressor, and then (3) insert the compressed air into the
fuel nozzle upstream of the exit orifice in an innovative mixing
chamber.
The test apparatus to be used in the Phase I test program will be
fabricated to Grey Fox Technologies' specifications. The proposed
Phase I work plan will be centered on two test segments. The first
test segment will be comprised of simple, understandable tests
using different air/water ratios and mechanical mixing
configurations. The second test segment will consist of a more
precise measurement of the actual droplet sizes for the most
promising air/fuel ratios and mechanical mixing configuration.
The Air Assisted Fuel Atomization system has a significant world
wide commercial and military market potential for advanced high
compressor pressure ratio and turbine inlet temperature aircraft
engine applications. This innovative system also has a substantial
marine and industrial gas turbine market potential.

o Advanced Subsonic Transports
o Advanced Supersonic Transports
o Marine and Industrial Gas Turbine Applications

Key Words

GREY FOX TECHNOLOGIES, Inc.
33 DASCOMB ROAD
ANDOVER, MA. 01810

Project Title:

An Innovative Variable Geometry Advanced Dual-Lip Airblast Fuel Nozzle

94-1	01.02	4138

An Innovative Variable Geometry Advanced Dual-Lip Airblast Fuel
Nozzle

Abstract:

An innovative variable geometry dual-lip airblast fuel nozzle for
current and future gas turbine combustors is proposed for
development in this SBIR. The proposed nozzle design, which is a
new propulsion system component, will control the nozzle effective
flow area (ACd) over a wide range of engine power conditions
resulting in a high quality fuel atomization particularly at start-
up and ground idle conditions. The proposed nozzle has a dual-lip
design, which offers high turndown fuel/air ratios (10 to 1), and
provides for a premixing capability of fuel and air prior to
admission into the combustor primary zone. These design features
will optimize the combustor performance in terms of producing lower
NOx, CO, HC and satisfying the combustor performance and life
goals. In this phase I SBIR, 2D and /or 3D CFD analysis will be
performed to predict the effective flow area (ACd) of each air flow
passage and compute the flow velocity and pattern for a number of
designs concepts configurations. The best design(s) concepts
screened by Phase I will further be optimized, designed, fabricated
and tested in Phase II at Fuel Systems Textron Inc. Proof of best
design concept in an engine sector under high pressure conditions
will also be included in Phase II. The final product of this SBIR
will be an advanced fuel nozzle that will have both commercial ar
government applications in particular for the Advanced Subsonic
Technology program.

The proposed airblast dual-lip fuel nozzle in this SBIR will
improve the performance of gas turbine combustors such as light-up
characteristics, lower NOx and CO, higher turndown fuel-air ratios
and combustion efficiency. Such an improved nozzle design is always
of great interest to government and commercial aviation firms.

Key Words

Engineering Research & Analysis Company
4810 Mulford St., Suite # 1-E
Skokie, IL 60077-3146

Project Title:

Advanced Subsonic Engine High Efficiency Combustor

94-1	01.02	5215	A

Advanced Subsonic Engine High Efficiency Combustor

Abstract:

Overall engine efficiency can be dramatically improved with a high
inlet velocity, low pressure drop, high heat release rate combustor
which reduces diffuser losses and combustor pressure drop losses,
improves turbine nozzle performance, and minimizes size and weight.
For natural gas fuel, PCI has demonstrated a novel catalytic
combustor design with very low pressure drop, high inlet duct
velocity, high turndown and stability, and low NOx at pressure.
With appropriate design modifications for liquid jet fuel
operation, this combustor design should be suitable for integration
into the advanced subsonic gas turbine engine program. In the Phase
I, the important design issues for conversion to liquid jet fuel
will be addressed for proof-of-concept testing leading to high
pressure combustor testing in a Phase II.

This proposal offers a high efficiency, low emissions subsonic
combustor technology which has substantial attractiveness for
NASA's advanced subsonic gas turbine engine program.

Key Words

Precision Combustion, Inc.
25 Science Park
New Haven, CT 06511

Project Title:

Lean Direct Fuel Injector for Low NOx Advanced Subsonic Technology (AST) Gas Turbine Combustors

  94-1	01.02	6576

  Lean Direct Fuel Injector for Low NOx Advanced Subsonic
  Technology (AST) Gas Turbine Combustors

Abstract:

The high combustor inlet pressures and temperatures required to
meet Advanced Subsonic Technology (AST) goals will put critical
demands on the fuel injector design. This SBIR project proposes
to develop an innovative Lean Direct Injector (LDI) concept that
enhances fuel-air mixing to reduce NOx emissions, yet is free
from durability problems associated with Lean, Premixed~
Prevaporized (LPP) fuel injectors.
In Phase I, at least five configurations of the proposed LDI
concept will be studied. Different types of axial and radial
fuel staging techniques used within the nozzle will be examined,
including partial premixing in some designs. Selected designs
will be analyzed using 2-D and 3-D turbulent, reacting CFD
analysis. The analysis will include multi-step, finite-rate
chemistry and prescribed pdf modeling for turbulence-combustio
n interaction. General Electric Aircraft Engines, the selected
subcontractor, will assist in the review/ assessment of result
s. In Phase II, the most promising designs will be optimized
using a combined numerical/experimental approach. Experimental
tests will be performed using existing experimental rigs at GEAE
or General Applied Science Laboratories (GASL). LDI fuel
injector concepts that are successfully demonstrated in Phase II
have strong potential for future transition into commercial and
military low NOx combustors.

The final product of this project will be a staged LDI fuel
injector capable of durable and reliable operation with very low
NOx emissions for the full range of anticipated AST operating
conditions. This product is of significant interest to
manufacturers of gas turbine engines.

Key Words

CFD Research Corporation
3325 Triana Blvd.
Huntsville, AL 35805

Project Title:

Adaptive Closed-Loop System for Control of Combustor Pattern Factor (71 14-940)

  	  94-1	01.03	0003

  	  Adaptive Closed-Loop System for Control of Combustor Pattern
  Factor
  	  (71 14-940)

Abstract:

This proposal describes a program to experimentally
demonstrate an
adaptive closed-loop control system for real-time control of
the
exit temperature distribution in gas-turbine combustors. The

proposed concept takes advantage of new technologies
associated
with adaptive signal processing and flow control to create
a
completely new engine control system. The system is based on
a
multi-input/output controller using an adaptive neural
network.
Demonstration experiments will be performed in an existing
small-
scale spray combustion facility modified to accommodate
dilution
air actuators and temperature sensors. Proof-of-principle
experiments to control the combustor exit temperature profile will
be demonstrated in this simplified geometry. Conclusions drawn from
these experiments will be used to identify control system
requirements for full scale gas-turbine applications. The Phase II
program will then design, fabricate, and test a scaled-up control
system on a larger combustor with eventual testing to be performed
on a designated NASA gas-turbine combustor sector rig.

The proposed innovation is applicable to both commercial and
military gas-turbine combustion systems including both stationary
and propulsion related applications. The system will increase gas-
turbine service life by controlling the thermal stress associated
with turbine blade wear. Successful implementation of the proposed
system in commercial aircraft propulsion units will represent a
significant savings to the airline industry by reducing turbine hot
section service and maintenance costs.

Key Words

Physical Sciences Inc.
20 New England Business Center
Andover, MA 01810-1077

Project Title:

Durable "Fly-by-Light" Jet Engine Temperature Probe

  94-1		01.03	5130

  Durable "Fly-by-Light" Jet Engine Temperature Probe

Abstract:

We proposed to utilize out innovative, proprietary, pollution-free,
JET VAPOR DEPOSITION process to fabricate high quality, durable,
oxidation-resistant, noble-metal aluminide intermetallic coatings
for use in an advanced "fly-by- light" jet engine temperature
probe. This SBIR project will be carried out with Allison Gas
Turbines, a major jet engine manufacturer, and Land Infrared Co.,
a leader in fiber-optic pyrometer systems for engine control
applications. The University of Pennsylvania will advise us on the
development of the intermetallic coatings. In Phase I, we will
develop and demonstrate advanced sensor coating materials able to
withstand the extreme high temperature oxidizing environment of an
advanced gas turbine. We will calibrate and test the performance of
the sensor in simulated engine conditions. If Phase I is
successful, we will collaborate in Phase II to optimize the sensor
design and qualify it for actual engine control applications. We
will also improve and automate the sensor manufacturing processes.
In Phase II commercialization, we will produce and sell these high-
value sensors for advanced, multi-channel, "fly-by-light" gas
turbine engine temperature control systems for both new engines and
retrofit applications for both military and commercial aircraft.

This R&D will result in an innovative, low cost manufacturing
method for high performance "fly by light" jet engine control
sensors for the DOD/NASA Integrated High Performance Turbine Engine
Technology Initiative.

Key Words

Adr

Project Title:

Large-area SiC-on-insulator (SiCOI) Substrates for High-temperature Electronics

94-1	01.03	6000

Large-area SiC-on-insulator (SiCOI) Substrates for High-
temperature Electronics

Abstract:

This Phase I program will fabricate low-defect, high-quality SiC
(using carbonized ultrathin silicon-on-insulator (SOI) structures)
as a lattice-matched buffer layer for CVD growth of SiC device
structures. Recently, Spire demonstrated for the first time the
fabrication of ultrathin Si on SiO2 (140 A) by using the low-energy
Separation by IMplantation of OXygen (SIMOX) process. SiC thin
films will be fabricated by carbonizing the ultrathin Si top layer
of SIMOX wafers. The carbonization technique has produced the
lowest defect density in epitaxial SiC on Si; however, due to the
different lattice constants, a strained layer exists at the
interface which limits the usefulness of this material for device
applications.
Ultrathin Si films will allow rapid conversion of the entire Si
layer to SiC, since the SiC only contacts SiO2, which is amorphous
and softens at the carbonization temperature. In the absence of a
lattice mismatch, the source of stress is eliminated (as in SIMOX),
thus paving the way for formation of a high-quality SiC layer.
Phase I will produce SiC buffer layers under varying material and
processing conditions, and epitaxial SiC layers, by CVD, on the
lowest-defect material. Phase II would include optimization of the
processing parameters and fabrication of device structures for
material evaluation.

Fabrication of large-area, inexpensive, Si-based substrates for
growth of low-defect SiC and GaN films will enable for radiation-
hard, high-temperature electronics. These substrates are essential
for integration of LEDs, lasers, detectors, and a variety of other
devices into Si microelectronic chips.

silicon carbide (SiC), carbonization, gallium nitride (GaN), atomic
layer epitaxy (ALE), silicon-on-insulator (SOI)

Spire Corporation
One Patriots Park
Bedford, MA 01730-2396
Phone number: (617) 275-6000

Project Title:

Computer-Aided Design Software for Integrated Flight/Propulsion Control System Design

94-1	01.03	7569

Computer-Aided Design Software for Integrated Flight/Propulsion
Control System Design

Abstract:

The importance of integrated flight/propulsion control systems in
enhancing the performance of STOVL aircraft and the future
hypersonic aircraft has been recognized by researchers at NASA
and other aerospace research centers. Proposed research will
identify the role of integrated flight/propulsion control systems
for improving the performance existing transport and high
performance aircraft. Design algorithms for integrated
flight/propulsion system control will be set up to form the basis
for a computer-aided design software. Robust linear control
techniques based on centralized control design followed by
controller partitioning technique pioneered at NASA LeRC,
together with decentralized design methods, and methods based on
multiple time-scale analysis and feedback linearization will be
included. During Phase II, these algorithms will be used for
synthesize a computer-aided design package useful for integrated
flight/propulsion control system development by the aerospace
industry.

Integrated flight/propulsion control systems have the potential
for improving the performance and safety of existing aircraft,
and will also find significant use in high angle of attack
aircraft, high speed civil transport, and in the hypersonic
aircraft program. Design methods and software developed under the
proposed SBIR program will contribute towards the continued
leadership of the U. S. aircraft industry.
The software developed under the present research will find
extensive use in the design of control systems containing several
complex subsystems. Semiconductor process control and, control of
flexible manufacturing systems are two typical examples of such
systems.

KEY WORDS

Optimal Synthesis
450 San Antonio Road, Suite 15
Palo Alto, CA 94303

Project Title:

"High Temperature Fiber Optic Imaging Apparatus"

  94-1	01.03	9014

  "High Temperature Fiber Optic Imaging Apparatus"

Abstract:

It is proposed to develop a high temperature imaging fiber
optic system as a means for non-intrusive diagnosis of high
temperature and high pressure engine components and combustion
systems, and as a research tool for system development.
Current fiber optic imaging systems provide invaluable access
for remote sensing in many applications but are relatively
limited in temperature range. The development of imaging
sapphire fiber optics and high temperature fiber cladding
processes under other NASA programs have led to the
possibility of fiber optic imaging at temperatures in excess
of 1000@C. This would enable simple, non-intrusive diagnosis
of jet combustors and turbines, rocket engines, and furnace
processing. A sapphire fiber optic video system will be
designed, fabricated and tested for basic performance in a
furnace as a Phase 1 feasibility demonstration. A prototype
system will be developed in Phase 2 for delivery to NASA.

High temperature imaging fiber optics will be used extensively
for diagnosis of engine and combustion processes at high
temperature and high pressure manufacturing processes, and
with 2-D laser excited flow and combustion diagnostics. Future
applications include intelligent multipoint combustion system
control and fault detection.

sapphire, fiber optic, imaging, high temperature, optical
access.

Thoughtventions Unlimited
P.O. Box 1310
Glastonbury, CT 06033

Project Title:

Fiber Optic Sensors for Long Wavelength Pyrometry andThermometry

  94-1    01.03     9806

 Fiber Optic Sensors for Long Wavelength Pyrometry and
Thermometry

Abstract:

Radiation pyrometry and thermometry combined with fiber optics
provide powerful sensors for determining surface and gas
temperatures in otherwise unaccessible locations. However,
several applications require that temperature measurements be
made in the long-wavelength infrared (LWIR) where widely-used
silica fibers are non-transmissive. For example, gas turbine
engines components are being fabricated from ceramic materials or
are often coated with ceramic thermal barrier coatings which have
low, variable emissivities at shorter wavelengths. Therefore,
temperature measurements would be more accurate and reproducible
in the LWIR where the emissivities are typically high and stable.
A second example is measurement of gas temperatures where the
dynamic range must be extended to lower temperatures. In this
case, shorter wavelength sensors suffer as the peak of the Planck
function shifts to longer wavelengths. This program will involve
the development and testing of novel fiber optic radiometric
temperature sensors that operate in the LWIR. The key innovation
is the use of hollow sapphire waveguides to carry radiation from
the sensing point to the detector. Hollow sapphire waveguides are
suitable for use at high temperatures and transmit in the LWIR;
no currently available solid-core fibers offer this combination
of features.

The development of hollow sapphire waveguide-based radiometric
temperature sensor would extend the applicability of LWIR
pyrometry to applications where limited optical access would
otherwise preclude this type of measurement. This will be of
particular benefit to measuring temperatures of turbine engine
components coated with ceramic thermal barrier coatings which
have low and variable emissivities at shorter wavelengths. The
proposed technology will also extend the capabilities of fiber
optic gas thermometers by providing an increased dynamic range
with a single sensor.

Key Words

Advanced Fuel Research, Inc.
87 Church Street
East Hartford, CT 06108

Project Title:

Regenerated Engines for General Aviation Propulsion

  94-1    01.04     2637

 Regenerated Engines for General Aviation Propulsion

Abstract:

A new type of lightweight, highly efficient, diesel engine is
currently being developed under a joint Navy - Caterpillar
program. The ReJen Company is the originator of this new
regenerated engine approach and is a major partner in its R&D.
Current programs are directed toward large, four stroke, marine
engines. However, there is reason to believe that smaller and two
stroke versions of these regenerated engines can be developed. If
so, they would be a new type of powerplant for general aviation
aircraft that would provide: (1) fuel efficiency superior to the
best current diesel engines, (2) very much smaller size and
weight engines, (3) an air cooled engine, (4) an engine that
utilizes cheap and readily available fuel, and (5) the potential
for reduced emissions. The objective of this Phase I SBIR program
is to determine the feasibility of applying this regenerated
engine technology to general aviation propulsion. This will be
accomplished by (1) analytically investigating the performance of
two stroke regenerated engines, (2) analytically investigating
the scalability of the regenerated engine, and (3) experimentally
and analytically investigating the structural integrity and
thermal performance of the most critical new component of these
engines, the regenerator. Ultramet, Inc., is a major
subcontractor in this Phase I program.

Regenerated engines could replace other powerplants in many
applications, including general aviation propulsion. The improved
performance, greatly reduced operating cost, lower weight, air
cooling, and smaller volume of these engines could have
substantial impact on the general aviation industry. If this SBIR
program successfully demonstrates the applicability of the
regenerated engine to general aviation propulsion applications,
then it will initiate a new area of aircraft engine R&D with very
high payoff.

Key Words

The ReJen Company
Rt. 2, Box 394
Mountain View Dr.,
Swall Meadows
Bishop, CA 93514

Project Title:

Single Lever Power Control for General Aviation and Unmanned Aircraft

  94-1	01.04	3633

  Single Lever Power Control for General Aviation and Unmanned
  Aircraft

Abstract:

Powerplants of general aviation and lightweight aircraft are
generally controlled through various levers by the pilot. It is
upon the pilot to select speed setting for the propellor through
direct throttle setting on the engine to obtain a desired flight
condition. Therefore, the selected operating conditions can be far
off from best performance and sometimes even far off from safe
operating conditions. The innovation proposed herein is a single
lever flight controller in the form of a single command from the
pilot to the entire powerplant system and which enables the PCU
(Powerplant Control Unit) to select optimum performance for any
desired flight condition. The pilot is now free to concentrate on
navigation and the control of the aerodynamic surfaces, if not done
by the autopilot.
The work proposed consists of implementing a single lever power
controller into the existing hard- and software of a high-altitude
UAV (Unmanned Air Vehicle) turbocharged powerplant controller.
ú Anticipated results: The most efficient combination of engine MAP
(Manifold Air Pressure) and engine rotational speed to find desired
power output independent of flight conditions
ú Applications:General Aviation Aircraft, UAV (Unmanned Air
Vehicles), High-Altitude Aircraft
ú Benefits:	Safety due to reduced pilot work, Performance,
Simplification of pilot-autopilot interface (reliability),
Increased TBO (Time Between Overhaul), Comfort (ergonomics)

ú General Aviation
ú UAV'S (Unmanned Air Vehicles)
ú HALE aircraft (High-Altitude Long-Endurance)
ú General motorized vehicles.

Key Words

Aurora Flight Sciences Corporation
10601 Observation Rd. Manassas, VA 22111
Phone: (703) 369-3633

Project Title:

Computation of Aircraft Trailing Vortices

  94-1		02.01	0631

  Computation of Aircraft Trailing Vortices

Abstract:

A new numerical algorithm, "Vorticity Confinement" is proposed
to economically and accurately compute the generation and
evolution of trailing vortices in realistic conditions,
including shear, ground effect, turbulence, and
stratification. Completely Eulerian, the method involves the
addition of a self-interaction term to the momentum equations
which depends only on local computed velocity. This term
eliminates numerical diffusion and prevents concentrated
vortices from spreading due to numerical discretization error,
even if the vortices are resolved over only 2-3 grid cells. As
such, Vorticity Confinement combines the generality and ease
of use of Eulerian fixed-grid methods with the efficiency of
Lagrangian methods in treating concentrated, convecting and
possibly merging vortices. This capability will make it
possible to include computations of interacting, trailing
vortices under realistic conditions. Neither Lagrangian
markers nor external vorticity specifications are used, so
complex flows with changing topology can be computed.
Vorticity Confinement allows the use of simple, efficient
second-order methods on coarse, regular computational grids
rather than very fine grids, computationally intensive higher-
order methods, or complex grids that other Eulerian methods
require. Use of the method will allow the design of aircraft
with lower vortex-wake hazard and the development of better
safety standards and better trailing vortex sensors.
Objectives include demonstration of the technique for several
realistic, 3-D trailing vortex problems, and development of a
preliminary code for use in the Phase II effort.

The efficiency and accuracy of the computational tools
developed will be unique. Commercial applications will
include: (i) the design and utilization of wake vortex ad
visory systems; (ii) the design of wake vortex sensors; (iii)
the determination of aircraft wake vortex characteristics; and
(iv) the design and utilization of crop dusting equipment. In
addition, agencies responsible for planning air transport
systems and setting aircraft separation standards will use the
computational tools to aid their decision making. It is
anticipated that a version will be installed at each major
airport for wake simulation in addition to versions sold to
aircraft and wake-sensor manufacturers, since no other
computational method will have the capability.

Key Words

Flow Analysis, Inc.
256 93rd Street
Brooklyn, NY 11209-6806

Project Title:

Optimization of Suction for Laminar Flow Control Applications

94-1	02.01	0818

Optimization of Suction for Laminar Flow Control Applications

Abstract:

We propose to make available a transition prediction code which
incorporates recently developed techniques for efficient
optimization of suction distribution on swept wings for achieving
larger regions of laminar flow. The objectives will be achieved
through a two-phase project.
In phase I, a code developed at HTC which computes the mean flow
and stability characteristics of three-dimensional flow will be
modified to incorporate recent optimization techniques also
developed at HTC. Phase I results in a code which computes
efficiently the optimal suction distribution for user provided
total mass flux and flow conditions. The code also handles user-
provided constraints on parameters such as the maximum suction
velocity.
The project will result in a design tool for efficient optimization
of suction distribution for the purpose of delaying laminar-
turbulent transition onset on aerodynamic surfaces and achieving
larger regions of laminar flow with minimum suction power.

Development of a transition prediction code that efficiently
determines the optimal suction distribution for laminar flow
control on aircraft wings is valuable for reducing the project time
needed to design such surfaces. Such a code is also expected to
achieve larger regions of laminar flow with less suction power.

Key Words

High Technology Corp.
28 Research Drive
Hampton, VA 23666

Project Title:

Active Control/Alleviation of Trailing (Streamwise) Vortices

94-1	02.01	0818	B

Active Control/Alleviation of Trailing (Streamwise) Vortices

Abstract:

Destabilization and dissipation of wing tip vortices is the
dominant issue for reducing wake hazard and increasing airport
productivity. The wake hazard problem exists due to the longevity
of trailingline vortices and their associated high rotational
energy. An innovative control strategy is proposed for the
enhancement and premature aging of the vortex system. This research
is focused on an active excitation/energization of large scale
instability modes and inducement of bursting in tip vortices via
acoustic and non-acoustic forcing. The technique is innovative for
its simplicity, i.e., it is easy to add on to current wing design
and it has no adverse effects on the aerodynamic characteristics of
the generating wing. The effort is directed at modeling the
receptivity of tip vortices to acoustic/external excitation and
manipulation of sound-induced large-scale turbulence for tip vortex
disablement.

Control and alleviation of the wake vortex of commercial and
military aircraft to increase safety and airport productivity,
efficient aerial spraying of agricultural chemicals, prevention of
helicopter blade vibration/fatigue, aircraft (submarine) stealth,
and mixing enhancement.

Key Words

High Technology Corp.
28 Research Drive
Hampton, VA 23666

Project Title:

A New Approach to the Prediction of Transition in Gas Turbines

94-1		02.01	2600			AMOUNT REQUESTED $

A New Approach to the Prediction of Transition in Gas Turbines

Abstract:

The objective of this proposal is to develop advanced analysis
software based on three-dimensional computational fluid dynamic
(CFD) methods to support the design and optimization of gas
turbines.
In fact, due to the process of transition from a laminar to a
turbulent boundary layer on the blade, great uncertainty presently
exists in predicting convective heat transfer rates from the blade.
Current CFD techniques using inadequate transition criteria, based
on local pressure gradient and boundary-layer thickness parameters,
fail to address the fact that the competing effects of high
external stream turbulence and severe streamwise acceleration can
lead to the boundary layer being in an intermediate state between
laminar and turbulent over much of the blade surface. We propose to
use a well-validated procedure, based on state-of-the-art
turbulence modeling, for predicting momentum and heat transfer
rates in boundary layers with especial reference to the transition
from laminar to turbulent (or semi-turbulent) flow induced by high
levels of external stream turbulence.
Phase I will focus on demonstrating the innovative technology and
assessing our turbulence models in the design of gas turbines. This
will be accomplished by modeling the development of a boundary
layer on the blade surface under the influence of various free
stream turbulence energy levels. The state-of-the-art in turbulence
modeling will include the use of low-Reynolds number RNG-based
eddy-viscosity models, non-linear k-e, explicit algebraic stress
models and other alternatives to a full low-Re second-moment
closure.
Phase II will focus on improving and enhancing physical models as
deemed necessary in Phase I, as well as employing the use of
sophisticated full Reynolds-stress closures that incorporate
sufficiently general sub-models of the different processes at work
for there to be good prospects of it predicting transition with
reasonable accuracy.

The proposed work employs many basic features that will find wide
usage in industry. The code developed may be used for modeling
blade-cascade flows over a wide range of operating conditions and
will be a valuable tool for the design and optimization of gas
turbines.

KEY WORDS

Fluent Inc.
10 Cavendish Ct.
Lebanon, NH 03766

Project Title:

From Design to Analysis: A Synergistic Approach to Grid and Model Geometry

94-1		02.01	6660	A		AMOUNT REQUESTED $

>From Design to Analysis: A Synergistic Approach to Grid and Model
Geometry

Abstract:

We propose designing the structured grid generator GRIDGEN's
geometric basis so that grid geometry and CAD model geometry are
treated identically: as rational, n-th degree polynomial curves and
surfaces.  We also propose adding CAD-style curve and surface
creation tools to the grid generator.  This unique approach to
the challenge of accurate transfer of product geometry from the
designer to the analyst will: 1) provide the analyst with a
single code for geometry repair and grid generation, 2) enable
the analyst to effectively repair or idealize the geometry for
gridding, 3) enhance the grid generation process by providing
new, CAD-style tools for grid creation, and 4) improve the
efficiency of the grid generation software and its user
interface.  Since grid generation is a necessary step prior to
any CFD analysis and since complex aerospace vehicle geometry
usually arrives at the grid generator in a form not amenable to
analysis, the proposed work is essential to the continued use of
CFD in aerospace design.  Since GRIDGEN is widely used at several
NASA centers the results of the proposed research will be
immediately useful.

Adding the proposed grid-CAD geometry engine to the GRIDGEN
structured grid generator would have considerable commercial
applications for any firm that obtains analysis models from CAD
systems. Many firms are turning to computer aided engineering
(CAE) analysis software as a means of improving their
international competitiveness, especially in light of the recent
downsizing trend. CAE software helps these firms decrease the
time to market for new products and improve product quality
through improved analyses. However, before the grid can be made
and the analysis performed, the geometry must be changed to a
usable form. It is this need that the proposed program fulfills.
An aerospace application may call for editing the trailing edge
of a wing so that is sharp. The CAD model may be of a wind tunnel
model that purposely defined a blunt trailing edge for ease in
milling the model. An automotive engineer may wish to fair over
the wheel wells of a vehicle prior to an external aerodynamics
calculation. A biomedical engineer may have to edit the curves in
an arterial model (curves that originated from a magnetic
resonance imaging scan). Finally, as a result of incorporating
curve and surface creation tools, analysts without access to any
CAD system may create a model from scratch in GRIDGEN.

KEY WORDS

MDA Engineering, Inc.
Suite 401
500 E. Border St.
Arlington, TX 76010

Project Title:

An Object-Oriented Scientist's Workbench for Parallel Vector and Tensor Field Analysis

94-1		02.01	7442			AMOUNT REQUESTED $

An Object-Oriented Scientist's Workbench for Parallel Vector and
Tensor Field Analysis

Abstract:

We propose to investigate the feasibility of a scientist's
workbench based on the vector bundle visualization model and the
Linda(R) and ParadiseTM programming systems. The vector bundle
model provides a theoretical basis for high-level integration of
analysis, visualization, and verification of vector and tensor
field datasets, while Linda and Paradise provide transparent,
scalable parallel or distributed execution on both massively
parallel machines and workstation networks. The union of these
technologies into a single environment will provide a parallel
computation and visualization workbench with specific knowledge of
vector and tensor fields, capable of handling the extremely large,
heterogeneous datasets associated with computational fluid dynamics
and other applications based on partial differential equations.
The specific Phase I objectives are to
(i)		investigate the mappings of fields and other data types
in the vector bundle model into objects in the virtual
shared memories provided by Linda and Paradise;
(ii)		investigate heuristics for adjusting the granularities
used to decompose vector bundle objects and map them to
available processors; and
(iii)	identify the most suitable operations in the vector
bundle model for parallelization.
These investigations will lead to a design specification from which
a full prototype workbench can be developed in Phase II.

The proposed scientist's workbench would give scientists, in
computational fluid dynamics and a wide range of other disciplines,
convenient access to parallel processing for analysis and
visualization of extremely large vector and tensor field datasets.
The ability to transparently distribute large computation and
visualization problems over heterogeneous networks of workstations
and other machines would provide a level of computational power not
currently available to most scientific and engineering
organizations.

KEY WORDS

Scientific Computing Associates
One Century Tower
265 Church Street
New Haven, CT 06510-7010

Project Title:

Turbulence Model with Enhanced Physics and Neural Network Closure Modeling

94-1	02.01	9457

Turbulence Model with Enhanced Physics and Neural Network Closure
Modeling

Abstract:

The objective of the work is to develop a new multi-equation,
eddy-viscosity turbulence model. Significant advances in the
analytical and empirical aspects of turbulence modeling will be
employed. The model will be derived from exact equations
representing the critical physics in most turbulent flows, rather
than dimensional analysis. An artificial neural network, trained
on turbulence data and constrained by universal laws of
turbulence, will provide the empiricism needed to "close" the
turbulence model equations. The proposed work represents a
fundamentally new concept in modeling, not just an incremental
improvement. If this modeling concept is successful, the model's
accuracy can be increased, without inherent limits, by enlarging
the turbulence data base use to train the neural net. The concept
provides a means of applying turbulence simulation results to
realistic, full-scale problems. This turbulence model will be
useful for solving many problems in aerodynamics within NASA and
in the commercial sector.

Inadequate turbulence modeling is a major obstacle to improved
accuracy in many flow simulations, and improved modeling accuracy
is needed to help solve some critical design issues in
aeronautical systems. All companies which employ CFD in the
design of aircraft, engines, and automobiles, for example, are
potential customers of a significantly improved turbulence model.

Turbulence modeling, artificial neural networks, computational
fluid dynamics

Nielsen Engineering & Research, Inc.
526 Clyde Avenue
Mountain View, CA 94043-2212

Project Title:

Electronic Knowledge Exchange System for CFD Validation Concepts

94-1	02.01	9457	A

Electronic Knowledge Exchange System for CFD Validation Concepts

Abstract:

The transition of state-of-the-art Computational Fluid Dynamics
(CFD) methods from the code research and development community to
the vehicle design community is an important goal for the aerospace
industry. However, the success of this technology transfer effort
is dependent upon the active participation of both communities,
particularly in the area of CFD code validation. The objective of
this work is to combine knowledge systems and electronic
communication tools into a hypermedia system for exchanging
information among multiple users. This system will document CFD
code validation efforts in a knowledge base and will allow the user
community to provide comments and feedback to the code development
community. The proposed technique takes advantage of the ability of
electronic networks to facilitate communications among a
distributed group of participants and of the applicability of
knowledge systems to technology transfer tasks. The merging of
these two technologies will benefit NASA and the aerospace industry
by increasing the participation factor in code validation user
communities.

The knowledge exchange system can be used to document test cases
and results, provide feedback, and implement multiple communication
channels for any application that involves testing of complex
hardware or software systems by a distributed group of users. One
such application is the technology transfer of CFD to the
aerospace, ship building, or turbomachinery industries. This system
also has commercial potential in the validation and testing of any
software product, and therefore can be marketed to the U.S.
software industry.

Key Words

Nielsen Engineering & Research, Inc.
526 Clyde Avenue
Mountain View, CA 94043-2212

Project Title:

Application of Degenerate Four-Wave Mixing for Diagnostics of High-Enthalpy Test Facilities

94-1	02.02	0688

Application of Degenerate Four-Wave Mixing for Diagnostics of High-
Enthalpy Test Facilities

Abstract:

The innovation proposed in this small business innovative research
proposal is the application of degenerate four-wave mixing (DFWM)
to the measurement needs of high enthalpy test facilities. DFWM
provides a means of simultaneously measuring species concentration
and gas temperature in such facilities. The resonant and spatially
coherent characteristics of DFWM make it suitable for trace species
detection in luminous environments. We propose to make simultaneous
measurements of the OH concentration and temperature in NASA's
counter-flow diffusion flame (CFDF) facility. We anticipate that
this work will enable us to develop a strategy for performing
similar DFWM measurements in other NASA facilities such as the
scramjet combustor test facility, TC-2, at Langley. DFWM
measurements in the CFDF will meet two of NASA's needs. First, the
data collected in the CFDF will provide an experimental database
for direct comparison with NASA's combustion modeling efforts.
Second, the work performed in the CFDF will enable the development
of a general DFWM measurement strategy, providing NASA with a
diagnostic tool applicable to many test facilities.

The technique of degenerate four-wave mixing is applicable to a
number of measurement needs in both the public and private sector.
The Phase I effort proposed here will result in the design of a
prototype diagnostic tool for use in combustion environments. An
existing MetroLaser product, the FlameMap, can easily be modified
to incorporate the designed DFWM tool.

Key Words

MetroLaser
18006 Skypark Circle #108
Irvine, CA  92714-6428

Project Title:

An Adaptive Probability Density Function (PDF) Method for Turbulent Supersonic Combustion Simulations

94-1		02.02	6576			AMOUNT REQUESTED $

An Adaptive Probability Density Function (PDF) Method for Turbulent
Supersonic Combustion Simulations

Abstract:

An innovative adaptive PDF methodology will be developed in this
project to improve the predictability and efficiency of turbulent
supersonic combustion. Previous attempts at developing an analysis
approach of this type suffered from one or more of the following
problems: inefficient use of computer resources, inaccurate
modeling, and limited geometric flexibility. A new and unique
approach based on adaptive modeling techniques is proposed which
provides the foundation for resolving these problems.
In the proposed Phase I study, the feasibility of coupling an
adaptive Monte Carlo solution procedure for the composition
probability density function (PDF) with an advanced structured,
unstructured, and hybrid CFD code will be addressed. The PDF will
account for the interaction between turbulent fluctuations and
finite-rate chemical kinetics. The proposed PDF algorithm will
incorporate adaptive table generation for chemical kinetics and
adaptive particle distribution. Without an adaptive approach,
accurate and efficient use of PDF modeling as a design tool is not
possible.
The feasibility of the combined method will be shown by solving
several two- and three-dimensional problems on structured,
unstructured, and hybrid grids. The planned Phase II work includes
extending the adaptive modeling principles for efficient spray,
radiation, and soot formation models. Additionally, the developed
PDF models will be useable with NASA Langley's CFL3D and USM3D
codes.

The adaptive PDF technology will be packaged as a module into
existing commercial CFD software as part of Phase III. The software
will allow efficient and accurate evaluation of supersonic
combustion systems. This capability will have direct application to
hypersonic vehicles such as NASP, HSCT, Hypersonic Transport
Aircraft, and Advanced Launch Systems.

KEY WORDS

CFD Research Corporation
3325 Triana Blvd.
Huntsville, AL 35805

Project Title:

A Novel Pneumatic Vortex Control Technique for Lift and Maneuverability Enhancement of Highly-Swept Configurations.

	  94-1		02.03	1400

	  A Novel Pneumatic Vortex Control Technique for Lift and
	  Maneuverability Enhancement of Highly-Swept Configurations.

Abstract:

A pneumatic technique for vortex augmentation and breakdown
control on highly-swept wings is proposed. The technique
relies on chordwise blowing tangentially from wing upper-
surface slots that are located directly below the vortex
paths. The entrainment effect of the wall jets is utilized to
accelerate the downwash in the symmetry plane thus
strengthening the rotational energy of the vortex cores and
also moving them closer to the upper surface. The resulting
increase of vortex suction on the wing enhances lift, and may
also be applied nonsymmetrically to generate roll control. A
low-speed wind tunnel feasibility study will be performed on
generic delta and arrow wing configurations. Six-component
force/moment and pressure measurements and supporting flow
visualizations will be conducted to evaluate the vortex
control effectiveness as functions of jet flux and momentum,
and its potential benefits to the lift and lateral control
characteristics of the two wing configurations.

The proposed research is aimed towards development of a new
aerodynamic technology of direct relevance to the next-
generation advanced supersonic aircraft. It is anticipated
that its potential for improving the cranked-arrow low-speed
lift capability will of great interest to the industry in the
context of the High Speed Civil Transport program.

Key Words

ViGYAN, Inc.
30 Research Drive
Hampton, VA 23666-1325

Project Title:

BATSCAN System - Acoustic Tomographic Array Monitoring for Wind Tunnels

94-1	02.03	1886

BATSCAN System - Acoustic Tomographic Array Monitoring for Wind
Tunnels

Abstract:

The BATSCAN project has the potential to significantly improve wind
tunnel productivity and reduce test program costs. BATSCAN measures
three dimensional noise fields within any wind tunnel, measuring
both source intensity and directivity. BATSCAN uses tomographic
detector arrays and acoustic passive tomography imaging. BATSCAN is
an innovative extension of three dimensional, acoustic noise
location/measurement systems developed for use in nuclear power
plants and costing many millions of dollars to develop, validate
and demonstrate. Application of a BATSCAN system to NASA's wind
tunnel programs will result in significant savings in operation,
model preparation and data analysis costs. For example; the BATSCAN
system:
* Measures the absolute noise intensity (pressure fluctuation
intensity) at all points on surfaces of models or open jets in a
wind tunnel.
* Reduces number of, or precludes need for dynamic pressure
monitors built into models.
* Extracts the intensity of local internal noise sources from
reverberant noise fields. Acoustic energy absorbing duct linings
are not required to minimize reflected sound.
* Increases technical content of a test.
Phase 1 will provide a practical demonstration of BATSCAN's
capabilities for a wind tunnel environment.

There is a large number of wind tunnels in operation in NASA, and
a very large number in use throughout the world. Successful
demonstration of this technology will lead to adoption of this
monitoring technique on many of the NASA and commercially operated
facilities. BATSCAN's significant increase in monitoring technology
is potentially an enabling technology for significant design
enhancements in fixed wing and rotor aircraft. The BATSCAN system
has a wide potential in process and manufacturing industries. These
include petrochemical and process plant applications such as
monitoring of loose parts in large vessels, boiler monitoring, and
monitoring a furnace's combustion efficiency. Other potential
applications include aircraft engine fault detection, geological
exploration, submarine surveillance, and corona discharge in high
voltage transformers.

Key Words

GREENE R&D International, Inc.
1101 S. Winchester Blvd., Suite A-107
San Jose, CA 95128

Project Title:

Aircraft Drag Reduction using Distributed Suction and Adaptive Control Techniques

  94-1		 02.03  	4151



  Aircraft Drag Reduction using Distributed Suction and Adaptive

  Control Techniques

Abstract:

Implementing laminar flow control (LFC) for airplanes using

suction through slotted or perforated surfaces, promises two

to three times the current achievable range (full chord

laminar flow is achieved over aircraft wings). Because of

variations in surface pressure, several suction compartments

are necessary under the wing surface. The maximum benefit of

LFC is dependent on using minimum suction rates in the various

suction panels and compartments.

The proposed innovation is to design an LFC controller to

optimize the flow in various suction panels to keep the

transition at a predetermined location on the wing. This

innovative monitoring and flow control system will measure the

boundary layer state, i.e. transition location in real time, and

use this to adjust the suction flow rates to continuously vary

and maintain extensive region of laminar flow on LFC airplanes.

A key component of the innovation is the use of a non-intrusive

method to measure the boundary layer state on the wing using

several flush mounted miniature microphones, buried under the

suction surface. Flow control based on the microphones is non-

intrusive, more sensitive, and rugged than the other more

conventional methods.


An adaptive boundary layer control system will provide high pay-

off in terms of requiring minimum required power to run the

suction system, and could be highly beneficial to commercial

subsonic and supersonic transports and military airplanes

designed for extremely long ranges. The proposed innovation will

also be useful in applications such as reducing the high-speed

buffet fatigue loads on high-speed transport airplanes, which

will be possible by supplying boundary layer suction in and

downstream on the shock region. Real-time feedback transition

control system proposed will be necessary for every flying LFC

airplane in the future.


Key Words


Innovative Aerodynamic Technologies

534-C Wythe Creek Road

Poquoson, Virginia  23662

Project Title:

Fast Prediction Method for Transonic Aerodynamics

94-1	02.04	5412

Fast Prediction Method for Transonic Aerodynamics

Abstract:

In the design of modern aircraft it is essential to incorporate as
much information as possible in the conceptual design phase;
decisions made in this phase can "lock in" as much as 90% of the
costs of the project. It is becoming increasingly important to
incorporate unsteady aerodynamic criteria into the design at an
early stage; this is the topic in the Solicitation. There may be
many iterations of the design and this has led to the need for
modeling tools that are accurate and computationally fast. This
proposal is concerned with the fast prediction of the loads in
unsteady transonic flow. Frequently the transonic flow regime is
where the most critical unsteady loads occur. The innovation
proposed in Phase 1 is the development of a method that allows
sufficiently fast estimation of the aerodynamic loads for
conceptual design. This technique will be coupled in Phase 2 with
other techniques developed by the author and others to provide a
comprehensive prediction capability that can be used for conceptual
or preliminary design.

If successful the research will lead to the development of
commercially viable software for the prediction of unsteady
transonic flow. This method will be sufficiently fast for use in an
optimizer; there is a market for this type of product in the
aerospace industry.

Key Words

NWING Inc.
427 Monroe Drive
Palo Alto, Ca. 94306

Project Title:

A Universal Indicial Function for Unsteady Transonic Flow

  94-1	02.04 	5412 	B



  A Universal Indicial Function for Unsteady Transonic Flow

Abstract:

In the design of modern aircraft it is essential to incorporate

as much information as possible about unsteady aerodynamic

criteria into the conceptual design phase. This is the topic in

the Solicitation. This has led to the need for modeling tools

that are both accurate and computationally fast. One such model

is the use of indicial response functions. However, in the

transonic flow regime, where the most critical unsteady loads

occur the indicial response functions are very dependent on the

wing geometry and hence a new indicial function has to be

computed for every geometry change. This removes most of the

benefit when used in a design optimization. The innovation

proposed in Phase 1 is the development of a "universal indicia

l function" for transonic flows which will allow an extremely

fast estimation of the loads for conceptual design. This

technique will be extended in Phase 2 and coupled with other

techniques to provide a comprehensive prediction capability that

can be used for conceptual or preliminary design.


If successful the research will lead to the development of

commercially viable software for the prediction of unsteady

transonic flow. This method will be sufficiently fast for use in

an optimizer; there is a market for this type of product in the

aerospace industry.


Key Words


NWING Inc.

427 Monroe Drive

Palo Alto, CA 94306

Project Title:

UNSTEADY AERODYNAMIC AND AEROELASTIC SIMULATION USING PANEL METHODS COUPLED TO A FINITE ELEMENT STRUCTURES METHOD AND INCLUDING AEROELASTIC EFFECTS

94-1	02.04	9090

UNSTEADY AERODYNAMIC AND AEROELASTIC SIMULATION USING PANEL METHODS
COUPLED TO A FINITE ELEMENT STRUCTURES METHOD AND INCLUDING
AEROELASTIC EFFECTS

Abstract:

The proposed program of work will show that it is possible to
predict the behavior of flight vehicles in response to external
stimuli such as microbursts or wake-vortex encounters, using
tractable high-speed computational methodologies. In the Phase I
work outlined in this proposal, computational tools, based on well
tried configuration modeling methods and
structural analysis techniques, will be applied in the time domain, and their
performance demonstrated modeling typical aircraft in representative
situations. Certain extensions to the numerical flow method would be
investigated with a view to speeding up the calculations when treating the
complex vortex wake/surface interactions. In a subsequent Phase II, the
method would be formalized and implemented, and its performance validated
through comparison between the calculated results and results obtained from
flight and wind-tunnel tests of representative aircraft.

Reduced reliance of wind-tunnel testing of scale models
Reduced prototype development time
Reduced prototype development costs
Reduced technical risk during development
Reduced overall program cost for new aircraft

Key Words

ANALYTICAL METHODS, INC.
2133 -152nd Avenue N.E.
Redmond, WA 98052
(206) 643-9090

Project Title:

Advanced Computational Techniques for Rotorcraft Aerodynamics and Interaction

94-1	02.05	2600

Advanced Computational Techniques for Rotorcraft Aerodynamics and
Interaction

Abstract:

The objective of this proposal is to develop computational
techniques for the analysis of rotorcraft aerodynamics and
interaction that are significantly faster than those currently
available. We propose to use unstructured meshes for discretization
of the complex geometries and sliding and deforming mesh concepts
for accommodating the rotor motion along all its degrees of
freedom, including tiltrotor configurations. We also propose to use
MIMD parallel processing on dedicated architectures as well as
networks of heterogeneous workstations to enable routine use of
these techniques for analysis and design purposes. Phase I of the
proposed work will concentrate on rotor aerodynamics and
demonstrate the feasibility of using sliding unstructured grids to
resolve all the flow features and performance characteristics of
interest. The methodology will be validated against available
experimental/computational data for a rotor in isolation. Phase II
will include the capability of studying interactions between the
rotor, airframe and other rotorcraft components as well as rotor-
ground interaction. Solution adaption techniques and rotor blade
dynamics will be incorporated. Procedures for parallel processing
will also be implemented.

The software developed here will find widespread use not only in
the rotorcraft industry but also in many other industrial
applications. Vertical and horizontal axis wind turbines represent
a growing area of interest. Many internal flow applications also
involve rotating blades and interaction between moving components;
examples include mixing tanks, food and materials processing
equipment and turbomachinery. Potential uses in the automotive
industry are for design of components such as gear pumps, gerotors
and torque converters.

Key Words

Fluent Inc.
10 Cavendish Ct.
Lebanon, NH 03766

Project Title:

Downloads and aeroacoustics of tilt-rotor aircraft

  941     02.05     3880

 Downloads and aeroacoustics of tilt-rotor aircraft

Abstract:

JAI Associates, Inc. proposes to develop an innovative hybrid
computational fluid dynamics (CFD) method for accurately
calculating aerodynamics and aeroacoustics of V-22 configuration.
In particular, the complex downloads problem will be addressed in
the Phase I research effort. A multi-block Navier- Stokes
numerical method that is capable of resolving the flowfield by
using Chimera overset grids will be used. An accurate turbulence
model will be utilized to capture the massively separated
flowfield associated with the downloads problem. A rotating
Kirchhoff formulation will be coupled to the flow solver. The
Navier-Stokes upwind scheme called TURNS, developed by the
Principal Investigator, will be the heart of the proposed
numerical scheme. This method has been demonstrated to be
accurate, robust, and computationally efficient.
Phase I effort is a 6-month study to obtain a demonstration
calculation of the downloads for a V-22 tilt rotor configuration
in hovering flight. A successful demonstration of this will
provide a solid foundation for realistic calculations on a full
V-22 tilt rotor aircraft in hover and axial flight in Phase II
research. The individual items to be completed for the success of
Phase I research are 1) identification and gridding of a V-22
rotor and wing using several body-conforming overset grids; 2)
implementation of Chimera or Pegasus schemes in to the Navier-
Stokes upwind numerical code; 3) a demonstration calculation of
V-22 tilt rotor downloads; 4) implement rotating Kirchhoff
formulation for calculating farfield noise accurately will begin
in Phase I; and 5) compare results with experiments and prepare a
final report. Phase II and the follow-on efforts will provide
additional man-years to complete the task generated by Phase I
and proposed for Phase II. JAI Associates, Inc. personnel and the
proposed consultant are uniquely qualified to undertake this work
since they are recognized leaders in the field of rotorcraft
research.

Commercial applications include the design of advanced
technology tilt rotors for better aerodynamic and aeroacoustic
performance. The method could also be used for designing
efficient rotor blades for helicopters and tilt rotors. Other
important applications include the interaction of multiple moving
bodies relative to each other such as the main rotor and tail
rotor of helicopter, tandem rotors, turbines and compressors in
engines, and store separation etc.

Key Words

JAI Associates, Inc.
P. O. Box 293
Mountain View, CA 94042-0293

Project Title:

Fast Modeling Technology for General Rotor/Surface Interaction

  94-1	02.05	9282

  Fast Modeling Technology for General Rotor/Surface Interaction

Abstract:

Predicting the behavior of surface-bounded vortical flows is
critical for a variety of aeronautical problems. This proposal
involves the development and application of new, efficient
approaches to modeling such complex flows that will not only
provide a predictive capability including wall or fuselage effects
but also provide a unified model of rotor wake behavior for
arbitrary advance ratios. This will be accomplished by building on
existing work in non-time-domain analyses of vortex wake dynamics
while applying innovative numerical approaches, including reduced-
memory free wake relaxation methods, an O(N) fast vortex method,
and fast boundary element calculations. The coupling of these
methods to an existing comprehensive rotor code will produce a
general analysis of rotor aerodynamics at arbitrary advance ratio
for application to cases both with and without boundary effects.
Applications include the assessment of ground effect, rotor/body
interaction, and the correction of wind tunnel data to free air
conditions, in particular rotors in low-speed. The analysis
technology developed here will be extensible to a wide range of
aeronautical and nonaeronautical applications.

A combined Phase I / Phase II effort would produce software capable
of efficient modeling of a wide range of enclosed and unenclosed
rotor/body combinations, supporting design, analysis, and testing
work in the rotorcraft community. This technology would be
applicable to essentially any design task for incompressible fixed
wing aerodynamics, while also being extensible to compressible
flows. The highly efficient surface panel modeling would also
benefit the whole class of boundary element methods, both within
and outside aeronautical disciplines.

Key words

Continuum Dynamics, Inc.
J.O. Box 3073
Princeton, NJ  08543-3073

Project Title:

Thin Film Sensing Elements for Skin Friction Imaging Arrays (7 124- 570)

  	  94-1	02.08	0003

  	  Thin Film Sensing Elements for Skin Friction Imaging Arrays
  (7 124-
  	  570)

Abstract:

Physical Sciences Inc. (PSI) herein proposes to continue
engineering development of a new skin friction imaging
measurement
technique suitable for aerodynamic and hydrodynamic flow
fields. A
previous NASA-sponsored effort has demonstrated the key
component
technologies for a new approach to skin friction and surface

contamination measurement which offers the potential of high

resolution readout and display in real time for wind tunnel
instrumentation and aeronautical applications. The Phase I
program
will demonstrate the feasibility of manufacturing integrated

sensing elements. A single prototype skin friction sensor
with
integrated thin film transistor, i.e., a "unit cell" of the
proposed arrays, will be developed, and tested in the Phase I
program. Ultimately, the device would consist of an array of a skin
friction sensors integrated into a thin, flexible sheet or "skin".
High sensitivity, flexible pyroelectric sensors which accumulate
charge in proportion to local temperature changes, can monitor
local surface cooling rates after known heat pulses are delivered
by heating films. This cooling rate has a simple relationship to
the skin friction. In principle, temperature changes, and thus the
skin friction, can be sampled and read out with hard-wired dynamic
and analog shift registers, similar to CCD arrays. As a
prerequisite to actual TFT switch fabrication, the ability to
deposit semiconductor grade amorphous hydrogenated silicon on
polymers such as polyimide has been previously demonstrated. Such
a sheet could be readily attached to any surface and the skin
friction monitored and displayed continuously in, for example, RGB
video format.

A non-intrusive skin friction `camera' has the potential to become
a commercial product usable on commercial aircraft and in fluid
dynamics laboratories around the world including several NASA
facilities. These distributed sensor arrays could be installed on
aircraft wings with outputs coupled to control system which improve
aerodynamic performance. Because they readily detect surface ice
contamination, such sensors could also serve as the basis for
efficient, adaptive anti-icing techniques with significant
commercial potential.

Key Words

Physical Sciences Inc.
20 New England Business Center
Andover, MA 01810-1077

Project Title:

X-Ray Backscatter Measurements for Defining Scramjet Combustor Flowfield Characteristics

94-1	02.06	2458

X-Ray Backscatter Measurements for Defining Scramjet Combustor Flowfield
Characteristics

Abstract:

Understanding of combustor flow fields is of great importance for the design
and performance analysis of static and installed propulsion systems. One of
the major drivers in combustor design is losses due to the fuel-air mixing
and combustion inefficiencies. The combustor loss calculations and flow field
structure (static and dynamic) for simple designs are normally retrieved from
published data but for complex combustor flows, model testing is required.
The major objective of these tests are to determine the flow structure and
mixing efficiency along the entire length of the combustor, especially at the
area of fuel injection. We propose an innovative non- intrusive technique to
measure the internal combustor flow field density distribution and possibly
the time averaged velocity through an unaltered combustor case. The technique
is based on X-ray Compton backscatter and the resultant frequency shift of
the scattered photons. This novel diagnostic approach has many advantages
over similar scattering techniques and holds tremendous potential for
commercialization. The technique requires absolutely no seeding, no special
windows or access ports, uses basic physics and simple instrumentation, and
will provide a portable, field useable tool for planar flowfield diagnosis.

The XRD approach to flow field diagnostics will have unlimited applications
to all systems with exposed or enclosed flowing gases or liquids. These could
include aircraft propulsion systems, fluid transfer systems, hydrodynamic
structures and industrial cooling systems. We believe that this system
approach will be simple, easy to apply to a variety of diagnostic
requirements. Additionally, there is a significant possibility that the
system be commercialized to broader applications.

Key Words

Micro Craft Inc
Applied Science and Engineering Group
3050 Pacific Highway
San Diego, CA 92101-1127

Project Title:

Micron and Submicron Sized High Temperature Polymer Spheres

  94-1		02.06		3200

  Micron and Submicron Sized High Temperature Polymer Spheres

Abstract:

The aerospace community is in the process of designing
vehicles for high supersonic flight regimes for programs such
as High Speed Research, the High Speed Civil Transport and the
National Aerospace Plane. Current particles employed for flow
pattern and velocity determinations do not meet the
requirements of these and similar high speed programs. Foster-
Miller proposes to generate high temperature polymeric
particles by the rapid and complete conversion of a soluble
precursor polymer to an insoluble polymer; resulting in
formation of spherical and monodispersed polymeric particles
whose average size can be selectively varied from 0.2 to 2.0
~m. High temperature particles have been produced from polymer
systems like poly(aryl ketones), poly(aryl sulfides) and
poly(aryl ketone sulfones). Foster-Miller will refine and
expand this concept to produce high temperature polymeric
particles suitable for supersonic flow visualization.
In Phase 1, we will demonstrate the feasibility of generating
high temperature micron and submicron sized particles by
rapidly converting soluble precursor to insoluble polymers. We
are working in conjunction with Dr. J.S. Riftle of VPI&SU,
whose research has demonstrated this concept, Boeing and Bangs
Laboratories, a commercial firm currently producing particles
for special applications. In Phase II, two systems will be
selected for col-version process optimization. One polymer
system will then be scaled-up to produce sufficient quantities
for wind tunnel testing.

The intensifying high supersonic flight research is being
carried out in civilian and military sectors both inside and
outside this country. Substantial quantities of particles will
be required to support this research. Alternative commercial
applications such as powder coated prepreg tows for
composites, molding, painting and coating would benefit
significantly from this research. The use of powders rather
than systems containing solvents or dispersants in these areas
would also limit emmisions of Volatile Organic Compounds and
thus make these processes more environmentally acceptable.

Key Words

Foster-Miller, Inc.
350 Second Avenue
Waltham, MA 02154-1196

Project Title:

Optical Limiter for Eye Protection

  94-1    02.06     6890

 Optical Limiter for Eye Protection

Abstract:

This laboratory has demonstrated a passive optical filter that
transmits low-intensity light with little or no attenuation, but
limits the transmission of high-intensity light to an intensity
tolerable to the human eye, thus, protecting the eye from injury
from intense radiation such as from lasers, high--power lamps or
sunlight while still providing good see-ability in normal light
levels. It responds all across the visible spectrum and is
expected to be fast enough to protect against pulsed lasers. The
proposed program is to optimize the performance of the prototype
filter and to incorporate it into practical protective eyewear.

The commercial applications of a successful limiter exceed
government applications by a wide margin. Limiter eyewear will
replace all current laser-protective eyewear since it will handle
all laser wavelengths rather than merely selected wavelengths,
and a single unit will replace an entire set of specific goggles.
The market will include industrial and academic research
laboratories and industrial operations as well as NASA and
military laboratories and military combat equipment. We will
pursue commercialization vigorously in Phase III in strategic
partnership with one or more commercial eyewear manufacturers
such as American Optical or Glendale.

Key Words

JOHN BROWN ASSOCIATES INC
329 Main Avenue
Stirling, NJ 07980

Project Title:

Error Reduction for Pressure-Sensitive Paint Applications

94-1 02.06-9431

Error Reduction for Pressure-Sensitive Paint Applications

Abstract:

Pressure Sensitive Paint (PSP) technology has the promise of developing into a technique that could revolutionize aerodynamic testing. Although PSP is currently being used for measurements and qualitative assessment at transonic and low supersonic Mach numbers, its usefulness is hampered by the many sources of error to which it is subject. Reducing the errors can result in improved accuracy at current testing conditions in conventional and cryogenic wind tunnels, and may even allow testing with PSP at much lower speeds. In either case, the increased usefulness and possible simplification of the technique would result in applications performed by a much larger group than at present.
An innovative approach for improving the accuracy and the applicability of PSP technology is offered. The Phase I proposal objective consists of performing a systematic and comprehensive identification, characterization and estimation of the sources of error associated with the PSP technology. It is anticipated that methods to significantly reduce or circumvent the errors will be found. Since NASA performs many tests in wind tunnels, an improved PSP technology would be of direct benefit in providing more accurate global surface pressure measurements.

The Phase I research that is proposed here has as its goal the reduction of errors in the PSP technique and can lead to significant enhancement of the PSP capabilities, and thus to wider commercial usage. A mature PSP technology will lead to improved global pressure measurements on test articles, and will reduce the costs and time required to complete a design cycle. Error reduction will improve the utility of PSP technology, even when it is applied at current transonic and low supersonic Mach numbers. If error reduction succeeds in a PSP technology that is applicable at low speeds, many more commercial applications become viable, from the design and testing of subsonic and general aviation aircraft, propellers, automobiles and bicycles to certain types of sports equipment. A low speed PSP technology would also greatly widen the group of users as well as the scope of the applications.

Applied Sciences, Inc.
P.O. Box 8134
Hampton, VA 23666

Project Title:

Kirchhoff Code - a Versatile CAA Tool

94-1	02.07	1464

Kirchhoff Code - a Versatile CAA Tool

Abstract:

A very attractive, innovative method that has been used for the
evaluation of aircraft noise is the "Kirchhoff method". This is a
nonlinear CFD solution plus Kirchhoff's integral for the farfield.
A Kirchhoff's integral formulation allows the radiating sound to be
evaluated based on quantities on an outside the control surface S,
when the linear wave equation is assumed valid technique for
coupling CFD and aeroacoustic calculations. The main advantages of
the method are its ability to evaluate the nonlinear acoustic
effects (e.g. shock wave and compressibility effects), and its
efficiency. A background study and historical notes are included.
We propose here the development of a simple set of portable
Kirchhoff subroutines for the calculation the farfield noise from
comprehensive and versatile computer program (i.e. Kirchhoff code)
will be developed and tested under phases I and II of this project.

We expect to develop a versatile, user-friendly comprehensive tool
for the evaluation of acoustic signals at arbitrary positions, when
the input is CFD code. The code has been developed with rotorcraft
noise in mind, but we will not be limited by this. We expect wide
variety of aeroacoustic applications, e. g. airplanes, rotorcraft,
propeller, fans, etc. We estimate that Kirchhoff's code will have
a high commercial application potential, as a cheap postprocessor
device to usual CFD codes. The potential enhancement of FlightLab
and 2GCHAS with this aeroacoustic code will provide them with noise
prediction and analysis capabilities.

Key Words

Advanced Rotorcraft Technology, Inc.
1685 Plymouth St. Suite 250
Mountain View, CA 94043

Project Title:

A Numerical Method to Predict Airframe Noise

	  94-1	02.07	3600



	  A Numerical Method to Predict Airframe Noise

Abstract:

The objective of the work proposed here is to develop software

to be used to predict the unsteady airflow around an airframe at

subsonic speeds and thus the airframe noise . This software will

combine the advantages of inherently stable implicit time

integration methods, the use of unstructured grids and the

ability to solve both incompressible and compressible flows. The

core of the work is the Galerkin/Least-Squares (GLS) method based

on the non-conservative form of the Navier-Stokes equations

written in terms of the "primitive" variables. The GLS

formulation is conservative by itself up to the convective terms

in the momentum and energy equations and can be made to satisfy

conservation through the use of an additional term. The

perturbation used is within the accuracy of the method and does

not degrade the accuracy of the overall scheme. An additional

Least-Squares operator gives the additional stability required

to complete the method. The software will be made available on

parallel computers and systems of work stations so that realistic

"design scale" problems can be solved. Comparison of analysis

results with experimental data will guide development in the

important flow regime from Mach 0.1 to 0.4.


Potential applications of this product are in the design of

aircraft, automobiles, trucks and high speed trains where the

prediction of both interior and exterior noise is important.

Other applications are in the design of ducting systems, the wake

effects of buildings and similar applications.


Key words


Centric Engineering Systems, Inc.

3801 East Bayshore Road

Palo Alto, CA 94303

Project Title:

Reduction of Turbulence-induced Noise in Aircraft Cabins

94-1	02.07	4973

Reduction of Turbulence-induced Noise in Aircraft Cabins

Abstract:

The purpose of the proposed project is to learn to reduce aircraft
cabin noise stemming from turbulence generated at the aircraft's
boundary layer, using a new patented technique of multi-channel
noise cancellation proprietary to Signal Separation Technologies.
NASA has already made substantial progress in applying active noise
cancellation to the reduction of cabin noise stemming from engine
vibration. On the other hand, eliminating the noise coming from the
turbulent boundary layer is somewhat more complicated. Here, the
required multiple noise reference sensors and multiple actuators
necessitate the use of a multi-channel noise cancellation procedure
which will reliably remove the always-present redundancies from the
corresponding correlation matrices. The classical procedure for
performing multichannel noise cancellation contains no provision
for the elimination of these redundancies, but Signal Separation
Technologies' patented method using singular-value decomposition
(SVD) to eliminate them is robust and a prime candidate method for
solving this problem.

The immediate application of the multi-channel active noise
cancellation cancellation system to be developed will be the
suppression of aircraft cabin noise coming from multiple sources
such as the turbulence induced along the aircraft surface. The
market for this innovation will include makers of military and
civilian aircraft. Such manufacturers will be solicited for the
formation of joint ventures to develop and market a noise canceller
for use in aircraft.
Other potential markets for a successful multi-channel active noise
cancellation system such as this will be the automobile industry,
which also has shown considerable interest in noise cancellation
techniques for use in cars. Automobile companies might provide an
additional source of funding, based on the availability of a
working prototype noise canceller for aircraft.

Key Words

Signal Separation Technologies
4020 Iva Lane
Annandale, VA 22003

Project Title:

Design of Optimized Nacelle Acoustic Liners based on Mode Cut-OffRatio Method

94-1	02.07	8533

Design of Optimized Nacelle Acoustic Liners based on Mode Cut-Off
Ratio Method

Abstract:

A research program is proposed to develop the technology to provide
a unique direct acoustic treatment design method for the inlet and
exhaust ducts of the nacelle of advanced high bypass turbofan
engines based on the mode cut-off ratio concept developed by E. J.
Rice. An innovative new wall acoustic impedance model will be
developed and combined with the cut-off ratio liner model to study
the acoustic merit of a proprietary linear liner having superior
structural integrity compared to existing linear liners. The
workplan is divided into four principal tasks consisting of (1)
improving Rice's existing direct liner design method for inlets,
(2) verifying that it can be extended to the fan aft-duct, (3)
developing an advanced liner impedance model and (4) using the
liner design method to evaluate proprietary linear liner designs.
A successful Phase I program offers NASA the opportunity to develop
(1) an optimized impedance direct liner design method for aft-duct
exhaust fan applications, (2) efficient linear liners superior to
current fine mesh screen linear liner designs and (3) hybrid
active/passive nacelle treatments.

A successful Phase I research program will demonstrate the
feasibility of providing the technology to permit engine
manufacturers to design efficient sound absorbing nacelle
treatments for the control of inlet and aft-duct engine noise of
existing and future high bypass commercial and military engines.
The technology will be licensed or sold to manufacturers of (1)
commercial and military aircraft engines, (2) HVAC equipment and
(3) liquid rocket engines, ramjets and industrial furnaces.

Key Words

Hersh Acoustical Engineering, Inc.
780 Lakefield Rd, Unit G
Westlake Village, California 91361

Project Title:

"Aircraft Drag Reduction Using Boundary Layer Heating"

  94-1	02.08	8228	A

  "Aircraft Drag Reduction Using Boundary Layer Heating"

Abstract:

The benefits of reducing the drag of either a new or existing
aircraft configuration are obvious. An aircraft's endurance is
directly proportional to it's lift to drag ratio. Decreased drag
also translates into faster top speed, quicker acceleration,
shorter take-off distances and lower direct operating costs in
the form of fuel savings. In order to project military air power,
or on the commercial side, receive better range and fuel economy,
reducing drag during the cruise portion of a flight is the most
critical. During cruise, the drag of the aircraft primarily comes
from profile drag (skin friction), induced drag (drag due to
lift), compressibility drag, separation drag and interference
drag. Of these, skin friction (from the "wetted" elements of the
aircraft) typically accounts for more than 50% of the total. The
proposed innovation uses active surface heating in the turbulent
regions of the aircraft's boundary layer. When heat is added to
the turbulent boundary layer, the skin friction is reduced as a
function of the ratio of the skin temperature to the ambient
temperature. The result is an effective drag reduction method
that can be retrofitted to existing aircraft.

The proposed innovation has wide reaching significance for
reducing fuel consumption and increasing the range of new and
existing commercial and military aircraft.  A successful
demonstration of this technology could lead to a massive retrofit
campaign of the world's transport type aircraft in order to
captitalize on the greatly reduced operating costs due to fuel
savings.

Key Words

Aircraft, Inc.
3415 Lomita Blvd.
Torrance, CA 90505

Project Title:

Similarity Principles to Enable Heavy Gas Testing of High-Lift Systems at Flight Reynolds Numbers

  94-1	02.08	9457

  Similarity Principles to Enable Heavy Gas Testing of High-Lift
  Systems at Flight Reynolds Numbers

Abstract:

High-lift systems testing at flight Reynolds numbers can only
be achieved in current tunnels by substitution of cryogens or
heavy gases for the tunnel air. Productivity problems
associated with cryogenics make heavy gases an attractive
alternative, but because these gases are not ideal, a reliable
method is needed for transforming viscous, compressible non-
ideal flows to their air equivalents. Nielsen Engineering
proposes to develop the similarity principles that would make
possible reliable transformation of test results between heavy
gas and air. This will be achieved through application of Lie
group methods to the compressible Navier-Stokes equations.
Establishing these similarity laws would enable the
development of this commercially important testing technology,
advance the pace and accuracy of high-lift system design in
the US, and could save both NASA and the US aircraft industry
hundreds of millions of dollars in new facilities money.

The technology developed here would enable the development of a
new, commercially important testing methodology for the US
aircraft industry. Its application would advance the pace and
accuracy of high-lift system design in the US, an area where
European efforts are believed superior. It could also save NASA
and the aircraft industry hundreds of millions of dollars in new
facilities money, by allowing the conversion of existing tunnels,
or the construction of smaller ones, to obtain flight Reynolds
number testing ability.

Key Words

Nielsen Engineering & Research, Inc.
526 Clyde Avenue
Mountain View, CA 94043-2212

Project Title:

"Improved Vortex Generators for Maximum Lift and Minimum Cruise Drag on G/A Airfoils"

  94-1	02.09	8228

  "Improved Vortex Generators for Maximum Lift and Minimum Cruise
  Drag on G/A Airfoils"

Abstract:

Significant performance gains for single-engine business
airplanes can be realized if the wing loading can he matched with
cruise performance requirements, realizing potential range and
cruise speed improvements as high as 100%. To achieve this
requires a wing with minimum cruise drag hut still having
sufficient maximum lift to meet the FAA-imposed stall speed
regulations. One means of providing higher lift, particularly to
increase CLmax, is to use vortex generators (VG's) on the wing
to delay flow separation with angle of attack. While VG's can he
very effective for increasing maximum lift, typical designs
impose a large cruise drag penalty. The focus of this Phase I
effort is to demonstrate that VG's of non-standard design can
provide either significant increased maximum lift or presently
achievable levels of maximum lift enhancement but with a greatly
reduced drag penalty. This improved VG could provide significant
benefits to enhance the performance and safety characteristics
of existing airfoils as a retrofit on today's G/A airplanes, and,
it might lead to a new airfoil design methodology where the use
of VG's is integrated into the design from the beginning. There
is a potential demand in the GA industry for the benefits of both
approaches.

New VG's that improve the performance levels of GA aircraft by
increasing maximum lift and/or decreasing the cruise drag penalty
will have direct applications to existing GA airfoils to reduce
stall speeds and stall/spin problems. Improved VG's may also lead
to the development of a new methodology for VG/airfoil/flap
designs where VG performance is integrated into the design. The
potential benefits are higher performance at reduced cost, lower
stall speeds, higher cruise efficiency, improved ride quality,
simplified high-lift flap systems and improved flight safety.

Key Words

Eidetics Aircraft, Inc.
3415 Lomita Blvd.
Torrance, CA 90505

Project Title:

Affordable de-ice system which preserves laminar flow on NLI~ airfoils

  94-1		03.01		2233



  Affordable de-ice system which preserves laminar flow on NLI~

  airfoils

Abstract:

Lancair International, Inc. proposes an integrated de-ice/anti-

ice protection system which does not degrade laminar flow on the

natural laminar flow (NLF) wings for general aviation. When the

TKS ice protection is not in use during cruise flight, the air

flow enters through the laser drilled holes of the TKS system in

the stagnation region, where the accelerating flow decreases the

local pressure, destabilizes the boundary layer and so disrupts

the NLF of the airfoil. The effort includes development and

testing of the new TKS ice protection systems to control and

eliminate the boundary layer destabilizing effects. Innovative

manufacturing approaches will be developed to integrate

dissimilar materials involved while maintaining laminar flow.

This will innovatively integrate manufacturing/installation

techniques coupled with new TKS de-ice systems that when

combined will produce a system which maintains laminar flow when

the TKS is not in the active de-ice mode.


Commercial applications are enormous and immediate for both high

performance kit airplanes, which now far outsell high

performance, production general aviation aircraft, as well as

for virtually all newly emerging certified versions of kit

airplanes, all of which utilize highly laminar flow wing

technology. Application would be available to many other

certified. production general aviation aircraft.


Key Words


Lancair International, Inc.

2244 Airport Way

Redmond, OR  97756

Project Title:

A Low Cost Passive Infrared Sensor in the Remote Detection of Ice

94-1	03.01	2820

A Low Cost Passive Infrared Sensor in the Remote Detection of Ice

Abstract:

Visidyne proposes to develop a novel low cost uncooled passive
infrared sensor system to detect remotely ice accretion on
propellers and rotors for all-weather operations. The ability to
measure ice accretion through the latent heat released as
supercooled water freezes on a rotor has been demonstrated using
passive infrared (IR) thermometry. The latent heat release causes
a characteristic temperature profile with increased temperature on
the iced leading edge of the propeller/rotor compared with the
uniced trailing edge. Preliminary tests have been conducted on both
static and dynamic rotor models for a variety of wet (glaze) and
dry (rime) ice conditions. The anticipated surface temperature
profiles were observed and the passive IR system successfully
detected the ice accretion remotely. This approach represents the
first practical technique to obtain direct measurements of ice
accretion without resorting to contact methods which are
unreliable. Visidyne will explore the feasibility of using a low
cost uncooled infrared detector in the development of an
operational system using this passive technique for the remote ice
detection of propellers and rotors.

Potential commercial applications include helicopter rotor ice
detection systems for both military and civil operations, ice
detectors for propellers on general aviation aircraft and
helicopter tail rotors, integrated ice protection system
controller, wind turbine ice detection (e.g. windmills).

Key Words

Visidyne, Inc.
10 Corporate Place
South Bedford Street
Burlington, MA 01803

Project Title:

Highly Sensitive, Low Profile, Microwave Phase Based Icing Detection System

	  94-1	03.01	3161

	  Highly Sensitive, Low Profile, Microwave Phase Based Icing
	  Detection System

Abstract:

Dedicated Electronics proposes to develop a dual-use, innovative
aircraft icing detection system consisting of conformable
microwave sensors. Our technology is based on phase measurements
of a low power microwave signal that passes through a sensor
designed to exhibit large phase shifts as ice begins to form, as
opposed to existing resonance shift-based microwave ice
detectors. Evidence of our technology to unambiguously
distinguish between ice, water, and deicing fluids is presented.
The sensor is a transmission line, whose electrical delay depends
on the medium to which it is exposed. The associated microwave
hardware is very simple, and is contained in a small, rugged
module beneath the sensors. The system is compatible with
aircraft surfaces including wings, fuselage, propellers, and
rotor blades; unlike more fragile icing detectors. Data
transmission from the sensors to the cockpit can be accomplished
through RF techniques. The sensor shows great promise to meet
NASA's need to detect icing and to measure ice thickness and
accretion rate, on the ground and in flight.
In Phase I we will develop the icing sensor, calibration methods,
and processing algorithm. We will also fabricate and test a
complete prototype system. The icing detection system will be
fully developed in Phase II.

This system has commercial potential because it offers a major
improvement in aviation safety. Maintenance costs from deicing
will be reduced without sacrificing safety. Undesirable
environmental effects from unnecessary use of deicing fluids will
be reduced.
This technology is also applicable to detecting ice or other
foreign materials on roadways, electrical distribution wires,
ship masts and structures, and antennas.

Key words

Dedicated Electronics, Inc.
96 Lane Road
Chester, NH 03036-4022

Project Title:

AN INNOVATIVE AIRPORT WEATHER AND WAKE-VORTEX MONITORING SYSTEM.

94-1	03.02	4545

AN INNOVATIVE AIRPORT WEATHER AND WAKE-VORTEX MONITORING SYSTEM.

Abstract:

Flying aircraft generate a pair of trailing vortices which can pose
a hazard to following aircraft. Aircraft separations have been
increased behind large aircraft in order to prevent hazardous wake
vortex encounters. This has resulted in reduced airport capacity.
We will apply an acoustic-radar weather monitoring and aircraft
wake-vortex tracking system, which has been developed under a
previous SBIR, to measure the two-dimensional wind and turbulence
field in a cross-section of the flight path. The innovation is that
it can simultaneously measure meteorological conditions and track
the motion of aircraft trailing vortices, and integrate the data
with air traffic control. We can explore how the meteorological
conditions cause the vortices to decay and then implement a "Vortex
Hazard Monitoring System". This will notify air traffic controllers
if the timing constraints for wake vortex avoidance can be relaxed.

There are three applications of a wake vortex weather radar:
detection and analysis of wake vortex incidents, research data on
stalled wake vortices in the approach corridor, and as prototype
enhanced vortex advisory system. The first clients will be
government agencies studying the problem so as to enhance airport
safety and capacity. The apparatus ultimately will be used at
airports to warn pilots of vortices in the landing corridor.

Key Words

Technology Integration Inc.
54 Middlesex Turnpike
Bedford Ma 01730

Project Title:

An Integrated Weather/Autonomous Landing Radar System

  94-1	03.02	9755

  An Integrated Weather/Autonomous Landing Radar System

Abstract:

Subtopic 03.02 addresses the requirement to develop on-board
sensors to detect environmental hazards along an aircraft flight
path. These sensors may have widely disparate functions and
requirements. The innovation proposed is to integrate two radar
frequency bands (X and K,) performing complementary functions
into a single dual purpose radar in a manner that is low cost,
light weight, and low volume. The system uses the two
frequencies to optimally perform weather/wind shear detection
and mapping of the airport runway area for the purpose of
autonomous landing in near zero visibility conditions. The
solution proposed is to incorporate a Ka-band
antenna/transmitter/receiver into an existing X-band weather
radar, and to employ innovative monopulse processing to improve
map quality.
The key technical issues to be researched include(l) the antenna
scanning technique to be used by the Ka -band mapping radar,
(2)the integrated transmitter/receiver technology to be used,
and (3) the performance to be expected from the Ka-band sensor
for detection of environmental hazards and autonomous landing
including a unique monopulse processing technique to improve
mapping quality. The design approach will be validated in Phase
I. The NASA application is the modification of commercial
weather radars for aircraft systems.

The approach promises to provide enhanced autonomous enroute and
landing ability in next-generation commercial weather radars.
The X-band function of the commercial weather radars will be
retained without degradation. The Ka-Band promises to enhance
detection of some environmental hazards such as vortex and hail
and therefore complements the X-Band functionality.
The concept of radar-supported autonomous landing systems is a
recent development that is undergoing continuous refinement. Our
technique, of a dual frequency, multi-function radar system,
will be less expensive, lighter and will occupy less volume than
alternate multi-frequency radar systems.
In addition to commercial aircraft, helicopters have a similar
requirement for detection of fixed and moving hazards in the
vicinity of a heliport. The Civil Tilt Rotor program has a
specific requirement for this capability. Our proposed
integrated system meets their severe packaging and weight
constraints.

KEY WORDS

Technology Service Corporation
2950 31st Street, Suite 200
Santa Monica, CA 90405

Project Title:

Advanced Flight Control Diagnostics and Reconfiguration

  	  	03.03	0686

  	  Advanced Flight Control Diagnostics and Reconfiguration

Abstract:

The objective this effort is to demonstrate a robust, fault
tolerant, prototype diagnostic and reconfiguration system
for
aircraft flight control using AbTech's abductive modeling
tool. The
resulting system will demonstrate the feasibility of
developing an
evolutionary control and diagnostic capability which can
model
flight control at the system level detect failures and
automatically adapt the control system parameters to
compensate for
failures. AbTech has developed an innovative network
approach,
called abductive networks, based on over a decade of
research in
neural networks and advanced statistics. Abductive networks
are
simply networks of very powerful high-order polynomial
equations.
This proposal first introduces a practical supervised learning tool
for synthesizing abductive networks from databases of examples. It
discusses how networks can be applied to substantially increase the
control and diagnostic capabilities of systems in a practical and
very cost-effective manner. AbTech proposes training abductive
networks to recognize degraded or failed flight control system
characteristics, and to adjust the flight control system parameters
to compensate in real time. AbTech proposes using it's PC-hosted
high-fidelity NASA F-18 High Alpha Research Vehicle (HARV)
simulation as a basis for this effort.

Phase I technology will apply to a broad range of commercial
systems where robust control is required. Potential commercial
applications include autonomous systems, factory automation,
equipment diagnostics, robotics, aids for the handicapped, weather
prediction, and economic forecasting.

Key Words

AbTech Corporation
508 Dale Avenue
Charlottesville, VA 22903

Project Title:

Real-Time Code Generation for a Passive Range Estimation Algorithm

94-1	03.04	1500



Real-Time Code Generation for a Passive Range Estimation Algorithm

Abstract:

Passive range estimation based on tracking features using images

taken in real-time is a very time consuming task to execute on

typical computer architecture's. Major modifications to the

algorithm are required to efficiently use the target hardware

executing the algorithm.

Previous work to meet real-time processing needs has focused on the

following options:

*  Designing a special hardware architecture to execute the

algorithm in real-time.

* Designing a parallel computing architecture using available

processors.

The first option proves to be very expensive and applies only to

the particular algorithm it is designed for. The second option has

the advantage of being usable for other implementations but is

difficult to code effectively, still requires some special purpose

designs, and is yet to satisfy a need to execute the algorithm in

real-time.

An alternative solution is to have a tool that can automatically

generate executable code that can be executed in real-time on

available computer hardware. This solves the problem of having to

design special hardware architecture's, and makes it easy to

efficiently modify and test.


This technique has commercial applications in the field of robotics

and automation, automatic landing of aircraft, and aid pilots under

minimum visibility conditions using infrared (IR) sensors.


Key Words


Integrated Systems, Inc.

3260 Jay St.

Santa Clara, Ca 95054

Project Title:

Metal-Coated Optical Fiber-Based Temperature and Pressure Sensors for Aerospace and Dual-Use Applications

  94-1	03.05	7556

  Metal-Coated Optical Fiber-Based Temperature and Pressure
  Sensors for Aerospace and Dual-Use Applications

Abstract:

Fiber and Sensor Technologies (F&S) proposes to research,
develop, manufacture and market temperature and pressure sensors
for advanced aerodynamic, propulsion and structural evaluation
at temperatures up to 950 C using specialized metal-coated
optical fibers. This work will be based largely on basic optical
fiber sensor and high temperature optical fiber coating research
funded by NASA Virginia Tech, and on patented and licensed fiber
strain sensor technology already commercialized by F&S. Such F&S
sensors have been used at low temperatures on structural
systems, including an F15 fatigue test frame, as well as in the
High Reynolds Number Facility at Wright Laboratory. Commercial
opportunities for such sensors exist in the flight research and
aerospace systems instrumentation areas, as well as in dual-use
applications including high temperature electric power
generation and processing systems, and in advanced materials
manufacturing. An even broader market exists for the high
temperature and high-strength metal-coated optical fiber which
would be of general use for aerospace instrumentation and dual-
use industrial systems, as well as for high performance
communication systems. Cost sharing and Phase III non-Federal
product commercialization funding, similar to that on existing
F&S R&D programs, are pledged.

Potential commercial applications include 1) flight research
instrumentation, 2) flight vehicle instrumentation, 3) dual-use
sensors for high temperature power generation and materials
manufacturing systems, and, for metal-coated fiber, 4) high
speed fiber communications and networking. Non-federal Phase III
commercialization funding has been committed for products
resulting from this SBIR program.

KEY WORDS

Fiber & Sensor Technologies, Inc.
P. O. Box 11704
Blacksburg, VA   24062- 1704

Project Title:

Multi-Degree-of-Freedom Reaction Force Sensors Simplify theDetermination of Aircraft Weight, Balance and Inertia Properties

94-1		03.06	0001

Multi-Degree-of-Freedom Reaction Force Sensors Simplify the
Determination of Aircraft Weight, Balance and Inertia Properties

Abstract:

Accurate, six degree-of-freedom (DOF) measurement from new reaction
force sensors will allow for precise estimation of a flight
vehicle's rigid body properties (RBP's): mass, center of gravity
and inertial properties. By exciting one setup of an aircraft and
measuring all the forces involved, as well as the resulting rigid
body motions, the RBP's can be estimated from a single measured
data set using Newton's first and second law.
The key to determining the RBP's through this simplified method is
the accurate determination of each force or moment DOF. The
summation of the reaction forces can already be measured by wiring
different cuts of piezoelectric crystals in series to produce a
single output signal. Recent advances in array calibration indicate
that this force sensor can be completely calibrated for it's six
sensitivities by attaching an instrumented mass of known RBP's.
Technical issues relating to selection of crystal cuts, physical
configuration, calibration fixturing and calibration methodology
will be examined. Application of the new sensor for RBP
determination will also be developed. Applications for a six DOF
force sensor include simplification of aircraft, automotive and
component RBP measurement, more accurate force
measurement for modal analysis and machine tool cutting force
dynamics.

The ability to accurately measure force in all six DOF
immediately benefits the scientific community by reducing
measurement error introduced through previously unmeasured
DOF's. More accurate models, and modifications resulting in
better structural performance will result. Specific
applications for rigid body properties are widespread and
extended from aerospace to automotive including component
modeling and dynamic analysis.

Key Words

PCB Piezotronics, Inc.
3425 Walden Avenue
Depew, NY  14043-2495

Project Title:

Simple Low Cost Laser Diode Vibration Sensor

94-1	03.06	0688

Simple Low Cost Laser Diode Vibration Sensor

Abstract:

This proposal describes a photonic device that can act as a
versatile sensor of the vibratory characteristics of flight
vehicles and engines. It is compact, robust and low cost; requiring
only a standard, single mode laser diode, power supply and FM
demodulation electronics. The device is based on the recently
discovered self mixing and current-frequency modulation phenomena
found in laser diodes. Driving a laser diode with a sawtooth
current and reflecting a small portion of the light off a target
back into the laser cavity produces a beat frequency at the monitor
photodetector usually integrated with the diode package. The
vehicle's position is measured as a beat frequency and its
vibration as an FM demodulation of the side-lobes. This type of
coherent detection is extremely sensitive and works with back
reflections lower than -100 dB. Using commercially available
diodes, the device can measure vibration up to MHz. In preparation
of this proposal, MetroLaser conducted preliminary experiments
proving the concept to be highly promising.Phase I will demonstrate
a prototype device and analytically determine capabilities and
limitations. Phase II will produce a complete system including
signal processing electronics which should be of significant value
to the NASA program.

The device, in addition to its application to the measurement of
the vibratory characteristics of flight vehicles and engines in
ground or flight testing has many potential applications,
particularly in the area of early fault detection and failure
prevention in rotating machinery and other structures. Such devices
would compete favorably in a large existing commercial market for
such products because they are inexpensive and interruptable.

Key Words

MetroLaser
18006 Skypark Circle #108
Irvine, CA  92714-6428

Project Title:

A GPS-Based Attitude Determining System to Aid High Dynamic Flight Test Data Analysis

  94-1	03.06	2900

  A GPS-Based Attitude Determining System to Aid High Dynamic Flight
  Test Data Analysis

Abstract:

NASA needs a moderate cost system that can provide accurate
attitude and time information to assist with flight test data
analysis. A GPS based attitude determining system offers
significant advantages over traditional inertial sensors in that it
provides attitude that does not drift over time, accurate time
information for time synchronization of data, as well as position
and ground velocity (speed and track). Time can be determined to
the nanosecond level. Adroit Systems, Inc., (ASI) is proposing to
develop a GPS-based attitude determining system that is capable of
operating reliably on a high dynamic aircraft platform. To achieve
the high-dynamic performance capability required in NASA's flight
test environment, ASI proposes to slightly modify an existing GPS
ADS and integrate the GPS based sensor with an inexpensive inertial
attitude device. This augmentation will improve system integrity,
increase achievable attitude rates, and compensate for occasional
GPS signal shading.
During Phase I, ASI will develop the design for the integrated
system in order to assure a low-risk prototype design and
integration in Phase II. The system requirements and an aircraft
integration plan will be developed in Phase I, and hardware and
software design analysis will be performed. From this, the ADS
specifications will be determined.

Potential applications of a robust, high-performance GPS-based
attitude determining system are: photogrammetry, commercial and
military aircraft navigation, marine navigation, Intelligence
Vehicle Highway Systems (IVHS), remotely piloted Unmanned Aerial
Vehicles (UAV) and Unmanned Ground Vehicles (UGV).

Key Words

Adroit Systems, Inc.
209 Madison Street, Suite 500
Alexandria, VA 22314

Project Title:

A Practical Real-Time Wavelet Analysis Tool

94-1	03.06	3800

A Practical Real-Time Wavelet Analysis Tool

Abstract:

Our innovation is a practical, real-time wavelet analysis tool specifically
designed for the analysis of engineering test data. Wavelet transform
techniques offer significant advantages over traditional techniques such as
the Fourier transform for certain types of signals. The infinite wavetrain
assumed in Fourier analysis cannot adequately describe non-periodic or
intermittent data. Wavelet transforms provide an alternative analysis tool
with a localized waveform. A wavelet has limited extent both in time and in
frequency and is characterized by three features: its shape, size (duration
or 'frequency') and location. The latter is missing from traditional Fourier
analysis; variants such as windowing offer a measure of localization, but
still rely on local periodicity. In Phase I of this project we will implement
a real-time wavelet analysis algorithm and several useful wavelet post-
processing techniques in IDARS/Scanalyzer, an engineering test data
acquisition and analysis software package marketed by Creare and currently in
use at numerous commercial and government installations. The utility of the
algorithms will be demonstrated through the analysis of selected engineering
data sets. One focus of the Phase I effort will be to prepare a tutorial
which describes the wavelet transform technique and useful processing
techniques for the practicing engineer.

The result of this SBIR project will be a suite of software products which
bring