PROJECT TITLE : A Wireless MEMS Instrument for Flow Measurements in Turbomachinery

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Nielsen Engineering & Research (NEAR) is proposing to develop a wireless, flow measurement system for application to turbomachinery testing. This novel system will integrate a variety of microelectromechanical systems (MEMS) based sensors, required signal conditioning electronics, memory, communications circuitry, and power onto a single, thin, flexible substrate.

High quality MEMS-based sensors are currently available for measuring quantities such as shear stress, flow direction, temperature, surface pressure, acceleration, and structural vibration. Data generated by an array of these sensors will be filtered, amplified, and digitized by onboard electronics and then either transmitted to a remote data acquisition computer while the test is in process, or stored in memory and downloaded once the run is complete. All of the components in the integrated system are on the order of 10-microns thick and thus can noninvasively quantify the boundary layer flow. Because the device eliminates the need for power and data transfer wires, it can be easily adhered to any fixed or rotating component within the machine under test.

During the Phase I effort, NEAR will investigate different design options and generate a specification document for the complete system. The Phase II program will focus on fabricating and testing an operational system.

The proposed system can be used for basic research and product development in any field where nonintrusive aerodynamic measurements are needed. This includes aeropropulsion systems development, airframe development, basic wind tunnel and flight test research, and automobile design.

Daniel A. Pruzan, Ph.D.
Nielsen Engineering & Research
526 Clyde Ave.
Mountain View, CA 94043

PROJECT TITLE : Visualization of High-NOx Regions in Combustors for Design Cycle Time Improvement

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

A chemiluminescent tracer has been identified which is predicted to closely track the production rate of NO under gas turbine combustion conditions. It provides a unique, simple means of identifying and visualizing locations of high NO production and for providing an instantaneous indication of NOx formation rates in a model or full scale combustor. This diagnostic will aid the understanding of flow and mixing processes in aeropropulsion combustion systems and provide an easy means for refining combustor designs to minimize NOx production. This directly addresses the requirement of Topic 01.01 for novel measurement techniques that substantially reduce design cycle time and that measure the formation of gaseous emissions. The objectives are an experimental demonstration of the diagnostic in a simple turbulent jet diffusion flame, and development of a detailed mechanism for the chemiluminescence process, coupled with a diffusion flame model to verify similarity of boron chemiluminescence and NO production over a range of operating conditions applicable to aeropropulsion systems. Quantitative correlation of chemiluminescence with NO production level and spatially resolved intensity distribution will be demonstrated experimentally, and diagnostic utilization requirements under gas turbine conditions defined, including the definition of a high temperature viewing device. The proposed diagnostic will be highly effective in developing combustor technology to meet stringent NOx emission limits in the NASA HSCT and SASS programs.

Virtually all combustion systems are required to operate with limited NOx emission, resulting in extensive development of innovative low emission burners for the entire civil sector. The immediate chemiluminescence visualization applications include NOx formation measurement for decreased emission from aircraft and stationary gas turbines, as well as industrial and electric utility burners.

Kurt D. Annen
Aerodyne Research, Inc.
45 Manning Road
Billerica, MA 01821

Aerodyne Research, Inc.
45 Manning Road
Billerica, MA 01821

PROJECT TITLE : Catalytic Combustor for Aeropropulsion Engines

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Considerable improvements in combustion efficiency, emissions reduction, and heat release rate, as well as elimination of pattern factor and utilization of low-grade fuels, can be achieved using catathermal, or catalytically enhanced (surface-catalyzed), combustion. The use of catalytic combustion allows combustion systems to operate at improved efficiencies outside conventional air/fuel mixture ratios and combustion temperatures, and can speed the combustion process, increasing heat release rates and allowing complete combustion to occur while minimizing detrimental byproducts such as CO and NOx. In this Phase I project, Ultramet proposes to demonstrate the feasibility of a catalytic combustion system constructed around a ceramic foam-supported platinum group metal/rare earth oxide catalyst system.

Subscale combustor performance and emissions will be characterized, and a catalyst/support system will be demonstrated that is structurally and thermally compatible with catalytic combustion systems, has sufficient life and temperature capabilities, and is immune to thermal poisoning effects.

A catalytic combustion system has applications for reducing pollution and increasing efficiency ranging from domestic heating to natural gas-powered pumps and turboelectric generators to efficient utilization of low-grade byproduct gases in the petrochemical, metals processing, and waste incineration industries.

In aerospace, commercial uses include the High Speed Civil Transport and future turbojet/turboshaft engines, while military uses include high-speed tactical missiles, unmanned aerial vehicles, and rotorcraft engines.

Andrew J. Sherman
Ultramet
12173 Montague Street
Pacoima, CA 91331

Ultramet
12173 Montague Street
Pacoima, CA 91331

PROJECT TITLE : Transonic Micro-Turbojet Propulsion System

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

NASA currently has a need for an airbreathing propulsion system capable of providing advanced sub-scale demonstration aircraft with sufficient thrust to explore high-subsonic and transonic flight. SWB Turbines; with support from McDonnell Douglas Aerospace and Orbitec, proposes to develop a 70 lb. thrust micro-turbojet engine with integrated inlet and exhaust system capable of achieving transonic flight speeds. The transonic micro-turbojet propulsion system will include an enhanced-performance, growth-version of SWB Turbines' existing 35 lb thrust turbojet specifically configured for transonic applications.

This new engine will be installed in an integrated nacelle incorporating a 2-D ramped inlet, bypass/bleed system, and 2-D single expansion ramp nozzle (SERN) with ejector. Advanced aircraft currently being investigated by NASA will be evaluated during the Phase I study to provide realistic size and performance objectives. The primary goal of the proposed Phase I effort will be to conduct a thorough technical analysis of this propulsion system to demonstrate the feasibility of propelling supersonic-capable, sub-scale aircraft to Mach 1.0 using a micro-turbojet engine. A combustor rig test will also be performed during Phase I to reduce program risk. Phase II will include fabrication, static testing, and flight testing of the propulsion system installed on a NASA sub-scale aircraft.

The transonic micro-turbojet propulsion system would be applicable to atmospheric/environmental research aircraft, glider boost power modules, refuse incineration power generators, and ground-mapping remotely piloted vehicles. Additional areas of use may include advanced cruise missiles, target drones, decoys and other Unmanned Aerial Vehicles (UAV's) currently under study in the Department of Defense.

Thomas J. Sierocuk
SWB Turbines
2418 Industrial Drive, Unit F
Neenah, WI 54956

SWB Turbines
2418 Industrial Drive, Unit F
Neenah, WI 54956

PROJECT TITLE : Design of a High Performance External-Compression Inlet for Cruise at Mach 2.4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

This proposal identifies a revolutionary new supersonic cruise inlet. It introduces a unique "external-compression" inlet concept that provides very high performance at Mach 2.4. cruise conditions without the large cowl drags normally associated with external compression inlets. A viable external compression inlet offers increased safety by providing "unstart free" operation. Inlet unstart is a critical issue for the mixed-compression inlets that are currently being considered for high Mach number cruise aircraft. This proposal responds to the SBIR subtopic by proposing a new invention in inlet design that will enable the development of a commercial supersonic aircraft. The objective of the effort is to provide a preliminary aerodynamic design of the inlet, an initial conceptual layout of the inlet and a preliminary evaluation of the inlets aerodynamic characteristics. It is expected that this Phase I effort will identify a revolutionary new inlet that will be selected for both experimental and analytical validation in a follow-on SBIR Phase II. This revolutionary advance in inlet technology will enable the development of an efficient and safe propulsion system for a US supersonic transport (HSCT). This type of enabling technology is the goal of NASA's HSR program.

The commercial application of the proposed new inlet design is based on the expectation of achieving very high performance while maintaining low external cowl drag. External compression inlets inherently provide increases safety (unstart free) and offer reduced complexity and weight. The increased efficiency and versatility provided by the new inlet concept will enable the development of a propulsion system for a supersonic aircraft that offers increased range, payload/profit, and safety. Commercial applications include aircraft used for transportation of people and packages throughout the world.

City/State/Zip
Bobby W. Sanders
Techland Research
Box 605
North Olmsted, OH 44070

PROJECT TITLE : Adaptive Control of Air Turbo Ramjet

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Accurate Automation proposes to develop an innovative adaptive propulsion system controller for Air Turbo Ramjet (ATR) Engines. One such engine is the Japanese ATREX [Tanatsugu, Sato, et al., 1994]. This poses a unique configuration with heat exchangers ahead of and behind the compressor. A Neural Network Controller will provide the required precise regulation of engine operating parameters. The precise gain scheduling required would make a conventional control system design difficult and costly; time consuming empirical studies would be necessary. We propose a direct adaptive algorithm to maintain precise control during changes in Mach number, altitude, angle of attack, throttle setting, and in the presence of parameter uncertainties and unforeseen circumstances. We also propose to develop a preliminary design of an unmanned flying testbed based on the LoFLYTE waverider. It will feature an innovative flowpath which may be reconfigured to allow integration of a range of engine designs. It will have the potential for low cost demonstration of new engine developments.

The Neural Network Adaptive controller will advance the state of the art in propulsion system control and will ensure that the United States stays commercially competitive with other nations. This technology will be applicable to hypersonic aircraft, including cruise missiles, tactical aircraft, strategic aircraft, and reconnaissance aircraft.

Lindley A. "Al" Carlton
Accurate Automation Corporation
7001 Shallowford Road
Chattanooga, TN 37421

Robert M. Pap
Accurate Automation Corporation
7001 Shallowford Road
Chattanooga, TN 37421

PROJECT TITLE : Near-IR Diode Laser Sensors for Combustor Emissions Monitoring and Control (7117-080)

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Physical Sciences Inc. (PSI) proposes to develop a compact, robust diode laser-based sensor for simultaneous measurements of CO, CO2, OH, H2O, and temperature in combustion gases. The sensor will use a custom-fabricated room-temperature diode laser operating near 1.575 æm in the near-IR and will join a suite of fiber-coupled sensors currently being developed and integrated with large scale combustor test facilities. Using previously demonstrated techniques, velocity, mass-flux, and momentum-flux capability will be included. The ultimate goal of this suite of sensors is the gasdynamic characterization of the inlet and exhaust flows of an aeropropulsion engine, allowing for real-time thrust determination and emissions control. In the Phase I portion of the program, surveys of the high temperature combustion gases will be conducted between 1.5 and 1.6 æm using a combination of FTIR, external-cavity diode laser, and distributed feedback diode laser. Two-line thermometry will be demonstrated on OH. These measurements will be used to determine the detection limits and accuracy of a prototype sensor configuration to be integrated with larger scale test facilities in the Phase II portion of the effort.

Significant commercial applications of the sensor suite for environmental, emissions, and process monitoring exists and have been realized through the development of a $7M commercial subsidiary. Direct commercial development of related sensors for aeropropulsion applications has already begun with AlliedSignal Engines and will continue in parallel through the Phase I and Phase II efforts. Discussions are continuing with Allison Engines Company and the Boeing Aircraft Company for further development. The proposed sensors will join this developing suite.

Dr. Mark G. Allen
Physical Sciences Inc.
20 New England Business Center
Andover, MA 01810-1077

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

PROJECT TITLE : Thick Intrinsic 4H-SiC Epitaxial Layers

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Silicon Carbide (SiC), with its wide bandgap, high breakdown field, and thermal conductivity, is an ideal material for high temperature and high power electronic devices. Commercially viable SiC devices require epitaxial growth processes that produce very smooth surface morphologies, low background impurity concentrations, polytype purity, and controlled, uniform, and reproducible layer thicknesses, n-type doping, and p-type doping. Current growth techniques suffer from process variabilities that make it difficult to reproducibly grow thick epitaxial layers with good surface morphologies and uniform background carrier concentrations, required for power devices. In Phase I we will develop, through careful process control and reactor technology, novel growth techniques that will greatly reduce the process variability in SiC CVD processes. The new growth techniques will permit reproducible growth of very thick, low background impurity epitaxial layers for high voltage devices. Undoped layers will first be examined, followed by initial intentional doping studies using the new techniques. In Phase II we will expand the technology to include the full range of intentional epilayer doping to form device structures, and the complete evaluation of high power devices. In Phase III we will commence commercialization of the epitaxial layers and devices generated by this process.

The development of a commercially viable, reproducible process for the growth of thick, lightly-doped SiC epitaxial layers will permit fabrication of devices for controlling power at levels unobtainable in any other commercial material system. These devices will be used in engine sensors and controls for automotive and jet engines, aerospace and advanced avionics systems, and electric cars.

Barbara Landini
Advanced Technology Materials, Inc.
7 Commerce Dr.
Danbury, CT 06810

Advanced Technology Materials, Inc.
7 Commerce Dr.
Danbury, CT 06810

PROJECT TITLE : Compressor Stall Warning System

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Compression systems are subject to aerodynamic instabilities that limit the stable operating range of the compressor. Recent research have shown that the Hynes-Greitzer model accurately predicts the mass flow at which a compressor stalls, and that a traveling wave, predicted by the model, is present prior to stall. Currently no stall warning system is available and aircraft are being flown with an unnecessarily large margin of safety at the expense of lower efficiency. SSCI proposes a compressor stall warning system that combines existing flight data, a priori information, and the compressor map with the Hynes-Greitzer model to give a stall warning indicator whenever the compressor is approaching the stall point.

The objective of Phase I is to show that currently available flight data and a priori information are sufficient to provide a reliable stall indicator. The concept will be extended in Phase II to include measurements of flow perturbations. The addition of this instrumentation will allow monitoring of engine degradation with time and allow appropriate maintenance steps to be taken on a timely basis.

Prof. James D. Paduano from MIT, who has done pioneering work on control and identification of these fluid dynamic instabilities, will provide consulting support. A collaboration with the engine manufacturers will be developed in Phase II.

Both current and future commercial and military aircraft will benefit enormously from the proposed stall warning indicator as this would allow more efficient operation with smaller stall margins. The savings in cost and safety are enormous leading to a very high commercial potential for the proposed innovation.

Dr. Christiaan van Schalkwyk
Scientific Systems Company, Inc.
500 West Cummings Park Suite 3000
Woburn, MA 01801

Scientific Systems Company, Inc.
500 West Cummings Park Suite 3000
Woburn, MA 01801

PROJECT TITLE : MONTE CARLO MODELING OF SURFACE MORPHOLOGY DURING SiC FILM GROWTH

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The technological usefulness of a material is determined in part by the compositional and morphological uniformity attained during growth. When films are deposited on a surface, the resulting morphology can change drastically depending on the operating parameters of the reactor and the preparation of the surface to be altered. Although the resulting morphologies give insight as to how the materials grow or are etched, in many instances the exact mechanism or reaction pathways by which the resulting film is achieved is not fully understood.

In the Phase I study, a Monte Carlo (MC) model will be developed to better understand the mechanisms, reaction pathways and the resultant surface morphology during SiC growth. The MC model will be developed to include n- nearest neighbor scope, surface energy, and improvements in the adatom movement algorithm. The new adatom movement algorithm will take into account the temperature effect on residence time, the surface energy, awareness of empty space in the lattice, and identity of adsorbed adatom and lattice atoms.

The modified model will elucidate how the operating temperature, atom face (Si or C), and wafer polytypes affect film morphology. Step bunching during step flow growth will also be explored. In Phase II the MC model will be extended to allow for variation of bond direction and have a more general treatment of polytype in the lattice data structure. These improvements will allow for the study of 3C-inclusions and impediments to step-flow growth such as growth pits, dislocations, micropipes, and dislocation loops.

This project will produce a model that will help identify microscopic and acroscopic conditions necessary for obtaining desired SiC morphologies and composition. This computational tool will be valuable in designing processing conditions for the production of high quality SiC films for applications in areas such as high temperature devices.

Dr. P. J. Stout
CFD Research Corporation
3325 Triana Blvd.
Huntsville, AL 35805

Dr. P. J. Stout
CFD Research Corporation
3325 Triana Blvd.
Huntsville, AL 35805

PROJECT TITLE : Novel Pulse-Burst Laser System for Imaging Diagnostics in High Speed Combustion Flows

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

NASA has identified a need for new non-intrusive measurement systems capable of obtaining global scalar and vector data in high-speed combustion flow fields. This proposal, prepared in collaboration with Dr. Walter Lempert and Professor Richard Miles of Princeton University, offers an innovative, 1 MHz repetition rate, high-power, pulse-burst laser system designed to be a flexible optical source for a wide variety of quantitative optical diagnostic techniques. The key innovation is a novel pulse-burst master oscillator for the amplifier chain. This source will be capable of generating a burst of 1 to ~100 near transform-limited `seed' pulses, with the ability to decrease the inter-pulse period to as short as 1æs and to vary pulse widths continuously from a few hundred picoseconds to ~10ns. Individual amplified pulse energies will be ~10-100mJ, depending on the number of pulses per burst. This flexibility will allow access to a wide range of flow sampling rates and pulse intensities.

Phase I will prove the feasibility of the proposed concept by demonstrating MHz repetition rate Spectrally Filtered Rayleigh/Mie planar imaging in supersonic flow. Phase II will then develop a self-contained, `turn-key' flow diagnostics system and explore developing the master oscillator as a compact, relatively inexpensive short pulse 1æm source for seeding regenerative amplifiers (including those manufactured by Positive Light).

The MHz repetition rate and wide pulse width range offered by the proposed system will provide the flexibility to perform a wide variety of modern optical diagnostic techniques (such as Rayleigh and Raman imaging and laser-induced fluorescence) with previously unattainable temporal resolution. Commercial applications include structural evaluation of machinery and jet engine acoustic noise reduction. During Phase II we will also explore developing the gain switched diode master oscillator as a compact source of low power, subnanosecond 1064nm pulses. Such a device will find a ready route to market as a seed source for Positive Light's existing series of Nd:YAG regenerative amplifiers, and would prove attractive as a cheaper alternative to currently available diode-pumped CW mode locked Nd:YAG lasers.

Dr Leigh Bromley
Research Scientist
POSITIVE LIGHT, INC.
103 Cooper Ct
Los Gatos, CA 95030

POSITIVE LIGHT, INC.
103 Cooper Ct
Los Gatos, CA 95030

PROJECT TITLE : Computation of Generation and Convection of Aircraft Vortices

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

A new numerical algorithm, ``Vorticity Confinement,'' is proposed to accurately and economically compute vortices produced by aircraft. Completely Eulerian, the method involves the addition of a self-interaction term to the discretized equations which depends only on the local computed velocity. This term eliminates numerical diffusion and prevents concentrated vortices from spreading due to numerical discretization error. Only 2-3 grid cells are required to resolve the vortices. Vorticity Confinement thus combines the generality and ease of use of Eulerian fixed-grid methods with the efficiency of Langrangian methods for treating concentrated, convecting, and possibly merging vortices. The specific application to be addressed in Phase I is the computation of the flow around aircraft including generated vortex wakes as well as their long term convection in a variety of configurations including cruise and high lift. Currently, full-featured 3-D codes designed to compute the evolution of trailing vorticity in realistic atmospheric conditions, including ground effect, have no satisfactory method of obtaining good starting conditions. Computations using Vorticity Confinement will solve this problem by accurately and efficiently computing the generation and convection of trailing vorticity up to $\sim40$ spans downstream of the aircraft.

The innovative usage of the method will benefit, not only to the present developing comprehensive code, but also to existed computer codes and tools to make them more versatile and efficient. The robust and routine use of the Vorticity Confinement method will enable rotorcraft companies to design more efficient, less costly rotorcraft. It also allows the propeller-driven aircraft, wind mill, sail boat, and automobile industries to be more competitive.

Yonghu Wenren
Flow Analysis, Inc.
1601, Damron Rd., Estill Springs, TN 37330

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

PROJECT TITLE : Seven-Sensor Probes for Dusty and/or Compressible Flows

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Five-hole or seven-hole probes are impact probes which have been employed in the past to measure flow velocity and direction in aerodynamic applications. These probes are inexpensive, reliable, easy to use and return three components of the velocity as well as static and dynamic pressure. A variety of tip shapes has been employed, like conical or spherical but so far, no serious effort has been made to carry out a comprehensive comparison of their performance. Moreover, very little is known about the Reynolds-number and Mach-number effects on the calibration of these probes. Some modifications of the design are also needed, namely incorporating temperature sensors at the tip to allow simultaneous temperature measurements and also mounting miniature pressure transducers at the tip to increase the frequency response. An artificial neural network developed with NASA LaRC support will be modified and a subsonic/supersonic continuous flow tunnel will be equipped with calibration hardware to extend the calibration range to high Reynolds numbers and Mach numbers.

Aeroprobe Corporation manufactures a variety of probe sizes and configurations and markets such multi-hole probes as well as the peripherals necessary for stand-alone systems. The peripherals include, but are not limited to, traversing scales, automatic calibration units, data acquisition boards and software. Such systems have been employed in wind tunnel testing, mostly related to problems in aeronautics. The proposed work will document carefully the performance of different designs. It will also help in the design and calibration of probes that could be used in a variety of applications, thus expanding the markets of the company.

Matthew D. Zeiger,
Aeroprobe Corp.,
3138 Indian Meadow Dr.,
Blacksburg, VA 24060

PROJECT TITLE : A Graphical Interface Toolkit for Network Based CFD

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The value of graphical user interfaces has been recognized by the Computational Fluid Dynamics (CFD) community, and most commercial CFD programs are supplied with a GUI. The complexity of CFD programs, however, makes GUI development impractical in academic and research and development environments. The value of GUIs in such environments motivates the development of a simple programmer's user interface toolkit, with which researchers and beginning CFD students can add GUIs to example or research codes in order to interactively control the execution of these codes, and observe solutions as they are calculated, even if the CFD codes are running on remote machines.

Amtec proposes to develop a FORTRAN-callable user interface toolkit, initially consisting of only five subroutines, which, in combination with Tecplot and existing Unix libraries, will enable network-based interactive control of a CFD program, "on-the-fly" changing of program parameters (such as time step), and the full feature set of Tecplot to examine solutions as they are calculated.

The proposed toolkit will substantially aid both instructors and researchers by allowing much greater interaction with and control over their CFD codes. It will be marketable to academic markets, as well as to government and private research labs as an addition to Tecplot, Amtec's graphical post-processing program.

David E. Taflin
Amtec Engineering, Inc.
PO Box 3633
Bellevue, WA 98009-3633

Amtec Engineering, Inc.
PO Box 3633
Bellevue, WA 98009-3633

PROJECT TITLE : On-Line Identification of Unsteady Viscous Effects for Flow Modeling and Control.

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Micro-thin smart-sensor arrays and multi-channel Constant Voltage Anemometer (CVA) instrumentation system will be integrated with hybrid digital signal processing (DSP) techniques to obtain quantitative characterization of viscous flow phenomena. The proposed innovation will be the first quantitative unsteady aerodynamic diagnostics system (QUADS) for simultaneous on-line identification of attachment line, flow reversal, separation and boundary-layer transition. Wind-tunnel tests will be conducted in Phase I to quantitatively characterize unsteady viscous flow phenomena on a flat plate with unsteady separation, and on pitching and oscillating cylinder and airfoil models using measured signal RMS, intermittency, mean output voltage and correlation coefficients. Hybrid DSP techniques incorporating higher-order statistical moments, wavelets transforms, and neural networks will be developed in Phase II. QUADS will be a highly productive and accurate tool for creating bench-mark experimental data for transition and turbulence modeling, CFD code validation testing, development of accurate mathematical modeling of unsteady aerodynamics, evaluation of new design configurations, as well as for routine wind-tunnel testing of complete aircraft and their components in steady and unsteady motion. QUADS has the potential to revolutionize active flow control technology and the applications include separation control, buffet control, high-lift augmentation, and viscous drag reduction.

QUADS has the potential to revolutionize active flow control technology including separation control, buffet control, high-lift augmentation, and drag reduction. QUADS will be a useful tool for CFD code validation, transition and turbulence modeling, evaluation of new design configurations, and routine wind tunnel testing of complete aircraft and their components, encompassing the entire spectrum of viscous flows encountered by subsonic-to-supersonic aircraft

Siva M. Mangalam
Tao of Systems Integration, Inc.
22 Enterprise Parkway, Suite 150
Hampton, VA 23666

Tao of Systems Integration, Inc.
22 Enterprise Parkway, Suite 150
Hampton, VA 23666

PROJECT TITLE : A New Approach to Turbulence Modeling

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Turbulence is a crucial component of viscous flow computations. In this work a novel approach to turbulence modeling is proposed which has a complexity and computational cost comparable to two-equation models, while at the same time having a much greater predictive capability and accuracy associated with Reynolds stress transport equation models. The model is constructed by using a mathematical transformation to reduce the tensor Reynolds stress transport equations to a vector system of equations. Besides computational efficiency, the proposed model is significantly easier to implement in numerical schemes which employ unstructured or curvilinear meshes. It is superior to standard two-equation models because it captures more of the turbulent physics, and also because additional physical effects (heat transfer, chemical reactions, sprays, etc.,) can be included in a straightforward manner. A numerical algorithm will be developed to demonstrate the efficiency and accuracy of this model. The model will be tested and tuned using a variety of standard benchmark turbulent flows, and it is anticipated that preliminary results from this model will demonstrate the superior predictive capabilities of the model. The accuracy and reduced cost of this turbulence model will significantly enhance NASA's ability to predict complex turbulent flows.

This turbulence model will be sold as an add-on (black-box) enhancement to existing commercial CFD codes, and is expected to significantly enhance the sales of the company's internal CFD code, currently under development.

J. Blair Perot,
Aquasions Inc.,
190 South Road,
Canaan NH 03741

J. Blair Perot,
Aquasions Inc.,
190 South Road,
Canaan NH 03741

PROJECT TITLE : Implicit Pressure and Density Based Solution Methodologies for All Speed Flows on Distributed Memory Machines

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

This SBIR Phase I project proposes to develop two all speed flow solution methodologies for adaptive Cartesian/prism grids, with parallel implementation on distributed memory machines. The first methodology will be pressure-based and will employ a fully implicit SIMPLE-like approach based on cell-wise least squares linear reconstruction and a Conjugate Gradient Squared (CGS) linear equation solver preconditioned with Incomplete LU factorization (ILU). The governing equations will be solved in a segregated (sequential) manner. The second methodology will be a density-based solution approach with a new flux-splitting scheme (FUSS), applicable to all speed flows. The same linear reconstruction scheme and preconditioned CGS solver will be employed. However the governing equations will be solved in a coupled manner. Both methodologies will be implemented on distributed memory machines based on domain decomposition. The Message Passing Interface (MPI) will be employed to provide data communication.

Several representative test cases will be simulated to evaluate efficiency, robustness and convergence properties of both methods. The parallel performances of both methods will be evaluated on an IBM SP2 and a cluster of SGI workstations.

In Phase II the selected method(s) will be implemented and evaluated for 3D problems on distributed memory machines.

The developed all speed flow solvers along with their parallel implementation will provide an efficient tool for CFD simulations for design purposes. An all speed flow solver capable of tackling flow from incompressible to hypersonic speeds will have wide applications in many distinct industries such as material processing, electronic packaging, automobile, as well as aerospace.

Z.J. Wang
CFD Research Corporation
3325 Triana Blvd.
Huntsville, AL 35805

Z.J. Wang
CFD Research Corporation
3325 Triana Blvd.
Huntsville, AL 35805

PROJECT TITLE : A Novel Computational Tool for Hypersonic Transition Prediction

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Laminar to turbulent transition phenomenon in hypersonic flows remains poorly understood although it has a profound impact on the thermal protection system weight, vehicle drag and air-breathing engine performance. Transition location uncertainty forces designers to be conservative by adding weight and reducing thrust. Accurate prediction techniques are in dyer need. Here, we propose to develop a transition prediction tool based on an innovative Navier-Stokes solver. The resulting code is computationally efficient and can be used to study the receptivity and disturbance growth without the restriction of slowly varying mean flows. The low streamwise resolution requirement in the proposed approach is made possible by a transformation which not only improves the accuracy but also helps in imposition of the outflow boundary conditions. The proposed tool can be used for studying various instability problems of relevance in supersonic and hypersonic flows such as blunt body flow and flow past a corner. This project will result in a reliable tool for prediction of transition for hypersonic vehicles.

Transition location affects thermal protection system weight, vehicle drag and air-breathing engine performance. The proposed project will be a major step towards developing reliable techniques for hypersonic transition prediction. Therefore, the code will be of interest to aerospace companies. Since NASA is also involved in designing hypersonic vehicles, the developed code will also be of interest to NASA.

Dr. Mujeeb R. Malik
High Technology Corporation
28 Research Drive
Hampton, VA 23666

High Technology Corporation
28 Research Drive
Hampton, VA 23666

PROJECT TITLE : Pulse Detonation Engines for High Mach Number Applications

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

APRI has previously been involved in the development of Pulse Detonation Engines for subsonic propulsion applications and is interested in applications of these engines to combined-cycle systems for hypersonic airbreathing propulsion.

In these systems, the critical characteristic of PDE operation is the upper speed limit that is determined by thermal and/or chemical kinetic considerations.

Pulse Detonation Engines operate in a cyclic manner that requires filling the engine with detonable mixture, initiating a detonation, and allowing blowdown of the high pressure engine. The filling must occur without bulk chemical reaction.

However, at some inlet Mach number, the temperature of the air coming into the PDE will be high enough that reaction will occur before the desired time in the PDE cycle. With appropriate valve timing and engine cooling, the upper limit of the inlet Mach number may be increased. Thus, the focus of the proposed work is to develop cooling and valve technology required to maximize this upper Mach limit. This represents a unique opportunity to develop the critical technology required to transform the PDE into a device that can serve as an element of hypersonic air-breathing propulsion systems.

APRI intends to apply this technology to the development of supersonic target drones. With success on these systems, application to the replacement of other ramjet-based systems such as turboramjet, air-turbo-ramjet, and ram/scramjet engines is anticipated.

Dr. James D. Sterling
Advanced Projects Research, Incorporated
1925 McKinley Avenue, Suite B
LaVerne, CA 91750

Advanced Projects Research, Incorporated
1925 McKinley Avenue, Suite B
LaVerne, CA 91750

PROJECT TITLE : A Stand-Alone Sensitivity Solver for Hypersonic Design Applications

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Recent advancements in both computational efficiency and physical-modeling capabilities have increased the utility of computational fluid dynamics in the hypersonic, vehicle-design process. However, beyond knowing the aerodynamic characteristics of a fixed configuration, the vehicle designer is interested in how to change the design to improve the system's performance. Recent research into the sensitivity-equation (SE) approach has demonstrated the ability to efficiently determine sensitivity derivatives in the framework of a high-order aerodynamic analysis. AeroSoft, Inc. as a small-business concern, proposes to provide a stand-alone software package which solves the valuable and insightful sensitivity equations and couples with any CFD flow solver. Building on past research, the objectives are to improve the sensitivity field at boundaries, incorporate viscous effects, derive the sensitivity equations for the Reynolds-Averaged Navier-Stokes equations and develop models applicable to turbulent flows. The main goal of the sensitivity package is to support NASA's interests in hypersonic flight and air-breathing propulsion systems by providing engineers with a useful tool for aerodynamic optimization, parametric guidance of complex flows, and approximation to near-by flows.

Military, commercial and general-aviation aircraft companies may acquire a missing tool for design of aerodynamic systems at all operational speeds - from high-lift approach to hypersonic re-entry. The software will lead to technological progress, economic growth and new jobs.

Andrew G. Godfrey, Senior Research Scientist
AeroSoft, Inc.
1872 Pratt Drive, Suite 1275
Blacksburg, VA 24060-6363

AeroSoft, Inc.,
1872 Pratt Drive,
Suite 1275,
Blacksburg, VA 24060-6363

PROJECT TITLE : Boundary and Finite Element Methods for the Application of Nearfield Acoustical Holography

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

It is proposed to develop the first commercial code for the application of Nearfield Acoustical Holography (NAH) to arbitrarily shaped interior and exterior spaces. NAH is a powerful noise control tool that allows sound fields to be visualized in three dimensions based on sound pressure or surface velocity measurements over two-dimensional surfaces. To-date, however, NAH has been applied commercially only in planar geometries and based solely on sound pressure measurements. If NAH is to be used to visualize sound radiation into aircraft interiors, or from the casings of aero engines, for example, holographic procedures must accommodate arbitrary geometries. Here, it is proposed to use boundary and finite element techniques to perform the NAH sound field projections in arbitrarily shaped spaces. A feature of the proposed work that will enhance its practicality is the allowance for mixed inputs to the holographic process: i.e., either sound pressures, surface velocities or a combination of the two. Another important feature of the present approach is that it makes use of the same codes that are now used for acoustical prediction and optimization. Thus, the result of this project will be an integrated tool for acoustical design, optimization and experimental analysis.

The Boundary Element Method implementation of Nearfield Acoustical Holography will extend the capabilities of our current Boundary and Finite Element program, COMET/Acoustics. This research will lead to a product that will enhance coupling between numerical and experimental methods and will bring the first commercial implementation of Nearfield Acoustic Holography to the aerospace, defense and automotive industries.

Bryce Gardner
Automated Analysis Corporation
2805 S. Industrial Hwt., Suite 100
Ann Arbor, MI 48104-6791

Automated Analysis Corporation
2805 S. Industrial Hwt., Suite 100
Ann Arbor, MI 48104-6791

PROJECT TITLE : Turbulence Modeling Framework for Analysis of Subsonic/Supersonic Jet Noise Reduction Concepts

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

A primary limitation in our ability to analyze jet noise reduction concepts stems from deficiencies in the turbulence models utilized. >From a practical viewpoint, a simple two-equation model framework (e.g. ke) is desirable, yet it requires corrections (compressibility, vortex-stretching, etc.) whose unification is complex. More advanced models (non-linear ke, algebraic or full Reynolds-stress) have not yet demonstrated invariance for building-block unit problems forming the basis for the analysis of jet noise reduction flowfields. This proposed research program establishes an overall framework for practical turbulence model utilization based on detailed and systematic data comparisons. It provides the means to evaluate new/advanced turbulence models in an efficient and organized manner so that deficiencies can quickly be identified. This effort involves organization of jet data into building-block format, construction of a hierarchy of jet turbulence research computer codes (asymptotic, parabolic, PNS, RNS, LES), inclusion of varied turbulence models into these codes, and, establishment of procedures for selection of "best available" turbulence modeling frameworks for analysis of specific jet noise reduction concepts. The overall approach is a dynamic one and as more data and/or advanced models become available, improved frameworks will become available.

The proposed research supports commercial applications to noise reduction concepts now being investigated under the HSR and AST programs. It also supports other commercial activities of airframes and engine companies related to the design of next-generation aircraft and propulsive systems, which require utilization of improved turbulence models emphasizing aeropropulsive flowfields which influence jet noise emission.

Combustion Research and Flow Technology, Inc.
174 North Main Street, Building 3
P.O. Box 1150
Dublin, PA 18917

PROJECT TITLE : Closed Loop Flow Control System for Improved High Angle-of-Attack Maneuverability (7117-070)

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

A program for the development of a closed-loop system for controlling transient separation and unsteady lift during high angle-of-attack maneuvers is proposed. The system utilizes an array of pulsed jet actuators near the airfoil leading edge. The control system will be developed and tested on a swept-wing model mounted in a low-speed subsonic wind tunnel at Physical Sciences Inc. The ability to control dynamic lift characteristics of a pitching wing will be evaluated in open-loop experiments. Surface pressure profile histories will be measured using conditional sampling and evaluated to identify appropriate control sensor positions. A closed-loop controller will be implemented on a high-speed digital signal processor and evaluated on-line for its ability to maximize unsteady lift during pitch-up. The experimental results will be used as guidelines for the design of a Phase II prototype control system for large-scale testing at flight conditions.

The development of a closed-loop system for controlling unsteady lift at high angle-of-attack will lead to improved performance and maneuverability for advanced aircraft. In addition, the control system could be used for controlling dynamic stall on helicopter rotors. It is anticipated that both commercial and military aircraft would benefit from an active control system for lift control due to its potential impact on improving lift/drag ratios and avoiding stall.

Dr. Keith R. McManus
Physical Sciences Inc.
20 New England Business Center
Andover, MA 01810-1077

PROJECT TITLE : Stereo-Imaging of Flow-Field Phenomena

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The development of future generations of high speed rotorcraft will require improvements in the understanding of basic flow-field phenomena and in the understanding and modeling of rotorcraft aerodynamics, dynamics, and acoustics. Optical images, such as shadowgraphs and schlieren, of three-dimensional (3-D) flow-field phenomena will be used to enhance this understanding and to validate design tools, such as Computational Fluid Dynamics (CFD) codes. The proposed innovation is a turn-key system that combines image acquisition, image processing, and stereo-optic transformations. This system will identify and locate flow-field phenomena in 2-D images and transform image measurements to 3-D positions and orientations. It will have an interactive environment that guides the user through the selection and implementation of various system tools.

This interactive environment will make extensive use of Graphical User Interfaces (GUI's) designed to facilitate training and ensure user friendliness.

A turn-key system for acquiring flow-field images, identifying flow-field phenomena in the images, and determining their location in 3-D space can be used for any flow-visualization study in air and/or water. Furthermore, the algorithms for tracing lines and transforming line measurements to 3-D coordinateshave other commercial applications in, for example, the medical and security industries.

Dr. Leslie A. Yates, Vice President
AerospaceComputing, Inc.
4906 El Camino Real, Suite 107
Los Altos, CA 94022

AerospaceComputing, Inc.
4906 El Camino Real, Suite 107
Los Altos, CA 94022

PROJECT TITLE : Design and Assessment Tool for Smart Rotor Active Control

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The final Phase II product of the proposed effort will be an experimentally validated methodology and associated tools for active control design for smart rotor helicopters. The focus will be on the trailing-edge flap as the candidate additional control surface, and the Phase I study will assess its potential for noise and vibration reduction and handling qualities improvement. The key innovation is the use of robust control design methods which allow control design to proceed even when there is uncertainty about the mechanism used to actuate the flap. The flap position and size will be optimized simultaneously with the control design.

The analysis will consist of a preliminary helicopter model and an implicit inclusion of noise considerations in Phase I, but will be replaced with a more sophisticated model including improved noise modeling in Phase II. Finally, control strategies and laws developed will be validated with a rotor test in Phase II. The results of this test will be used to refine the analysis and a final product consisting of a complete set of robust smart rotor design and analysis tools will be delivered.

The final Phase II product of this effort will be a validated tool for the evaluation and design of smart rotor control concepts in a comprehensive flight dynamics setting. This tool will aid current efforts to use smart structures technology in the U.S. rotorcraft industry in order to gain a competitive advantage in the global helicopter market. The unique combination of software backed by actual rotor tests will lead to a high degree of confidence in the results of such a tool.

Vineet Sahasrabudhe
Systems Technology, Inc.
13766 S. Hawthorne Blvd.
Hawthorne, CA 90250-7083

Systems Technology, Inc.
13766 S. Hawthorne Blvd.
Hawthorne, CA 90250-7083

PROJECT TITLE : Multipurpose Advance Tilt Rotor Control System Design using Model Predictive Control

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The design of control systems for advanced tilt rotor aircraft can be divided into two major areas: the first, and by far the most important, is the stability and control of the aircraft including the rigid blade behavior of the two rotor systems; and the second concerns the fuselage vibrations over the flight envelop. The primary focus of Phase I investigation is to demonstrate the feasibility of designing a robust flight control system for the rigid body modes using Model Predictive Control (MPC) design approach. Phase II effort will extend this approach to fuselage vibration control using transfer functions at rotor blade harmonics. Over the last two decades starting with the pioneering work of Richalet et. al (1976) in France and Culter et. al (1980) in USA, great progress has been made in the development of Model Predictive Control (MPC) methods for optimal control of nonlinear uncertain dynamic systems under hard constraints on inputs and outputs.

Applications of MPC to aerospace and defense problems were pioneered by Scientific Systems and are receiving increasing attention with the availability of low cost high speed chips and processors (Mehra et. al (1977, 1980)). Phase I will involve the following specific tasks: Task 1: Acquisition of math models, real time simulation and control requirements from BHTI. Task 2: Design and development of a Model Predictive controller (MPC). Task 3: MPC Controller tuning and testing. Task 4: Hardware/Software Implementation Requirements. Task 5: Reports, meetings and Phase II Recommendations.

MPC methodology is very general and is finding increasing applications in all areas of control. Commercial applications of MPC exist in chemical, automotive, power generation, pulp and paper, manufacturing and metal processing industries.

Dr. Raman K. Mehra
Scientific Systems Company, Inc.
500 West Cummings Park Suite 3000
Woburn, MA 01801

Scientific Systems Company, Inc.
500 West Cummings Park Suite 3000
Woburn, MA 01801

PROJECT TITLE : Optical Monitor for Combustion Efficiencies in SCRAMJET Pulse Facilities (7117-160)

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Continued development of SCRAMJET engines requires in-situ measurements of combustion efficiency. Physical Sciences Inc. (PSI) proposes to develop a compact, non-intrusive optical instrument to detect spatially distributed H2O concentrations and temperatures at the combustor exit, thereby providing determinations of the combustion efficiency as limited by mixing and chemistry. The instrument detects the infrared thermal emission from H2O and measures the concentration and exhaust temperature at the combustor exit plane. The instrument would use thermoelectrically cooled detectors which are suitable for field deployment or integration into a flight instrument. In addition, the measurement would be designed to be compatible with particulate laden flows such as are common in high enthalpy pulsed facilities. Phase I will demonstrate the concept and Phase II would develop and produce a deliverable instrument.

The proposed R&D will produce a combustion effluent diagnostic instrument with a variety of commercial applications and demonstrate and validate technology for future commercial diagnostic and testing services.

Dr. W. Terry Rawlins
Physical Sciences Inc.
20 New England Business Center
Andover, MA 01810-1077

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

PROJECT TITLE : : Sol-Gel-Derived Pressure-Sensitive Coatings for Cryogenic-Wind- Tunnel Applications

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The proposed SBIR research targets the development and application of advanced optical-based pressure instrumentation for cryogenic aerodynamic flows. Sol-gel-derived pressure-sensitive coatings suitable for low-temperature wind-tunnel applications will be designed for the measurement of both static and transient unsteady aerodynamic flows. This noninvasive, optical measurement is based on the quenching of luminescent molecules dispersed within a sol-gel-derived glass matrix. A deposition technique that allows the formation of thin, uniform films has recently been developed and has been shown to produce robust composite coatings characterized by: 1) tunable pressure sensitivity, 2) molecular-scale (< 100 nm) surface roughness, and 3) fast (sub-ms) temporal response. In addition, these composites exhibit both high- and low-temperature stability and, thus, find application in extreme-temperature environments. Existing and innovative technologies will be used in concert to provide two powerful tools for the NASA wind-tunnel mission: 1) an optical-based instrument capable of accurate surface-pressure and -temperature measurements and 2) protocols for the production of coatings optimized for performance within predetermined test conditions.

The ultimate goal of this SBIR effort is the development of a commercially available, non-intrusive, optical-based pressure instrument which can be used to investigate the flow conditions of interest in ground testing of aircraft and their components. This program will greatly benefit both the commercial and the military aircraft industries in the United States as well as the automotive and architectural industries.

Larry P. Goss, Ph.D.
Innovative Scientific Solutions, Inc.
3845 Woodhurst Ct.
Beavercreek, OH 45430

Innovative Scientific Solutions, Inc.
3845 Woodhurst Ct.
Beavercreek, OH 45430

PROJECT TITLE : : Surface Pressure Measurements Without Wind-Off Correction

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Dakota Technologies, Inc. (DTI) proposes an innovative technique to measure luminescence lifetime images on test bodies in wind tunnels. The determination of surface pressures via pressure sensitive paint (PSP) technology will be improved and simplified. Incorporation of electro-optic shutters into the apparatus will provide the essential time-domain information at a fraction of the cost associated with pulsed excitation sources and intensified charge-coupled device (CCD) cameras. There will no longer be a need for the "wind-off" measurement and accompanying extensive calculations to account for model movement and distortion between the "wind-on" and "wind-off" conditions. The effects that non-uniform illumination of the body under test, response variation across the detector array, photodegradation of the paint, and surface contamination by oil and dirt, have on the results will be minimized. The new instrumentation maintains compatability with the NASA-Langley approach to an internal reference luminophore. The most important Phase I technical objective is to demonstrate that luminescence lifetimes in the appropriate range for pressure sensitive paints can be measured precisely and accurately with the new instrumentation. Data processing algorithms will be written and tested to meet this objective.

Success in eliminating wind-off correction will clear the way for standard instrumentation in all wind tunnels. The defense-related applications fall into three categories: 1) aircraft models; 2) turbines and rotors; 3) missiles and ballistic objects. Aside from obvious civilian aviation applications, there is an extremely wide range of potential commercial uses, the automotive industry being one of the most important.

Gregory D. Gillispie
Dakota Technologies, Inc.
2201A 12th Street North
Fargo, ND 58102

Dakota Technologies, Inc.
2201A 12th Street North
Fargo, ND 58102

PROJECT TITLE : Non-intrusive skin-friction interferometer

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

A new fiber-optic device with non-moving parts capable of time-dependent single-point skin-friction measurements in subsonic/supersonic flow ranges and in separated/unseparated, steady/unsteady flow regimes is proposed. The device is low cost, very high resolution, interferometric (non-intrusive) and miniature (2.5"x2.25"x0.5"). The device needs calibration only once in its lifetime, and it can be used in cramped, highly vibrational environments due to its compact size and non-moving-parts design. The unique design of the device ensures that only a small portion of the device is in contact with high/low temperature environments which makes the device easily accommodating to different flow environments. The device generates linearly varying interference fringes perpendicular to the measurement surface within the sublayer of a boundary layer and uses the Doppler effect to measure one of the horizontal-to-surface velocity components within the sublayer. The linear variation of the velocity component within the sublayer and the linear variation of the fringes form a relation between the velocity component and the skin friction component on the surface due to Newtonþs principle.

The device will be used in applications where skin-friction drag on a surface is crucial in the design of a new product/device such as in the automotive, aircraft and maritime industries. The race car, speed boat, cycling industries and smaller industries such as surfing and skiing are also prime potential targets.

The device can be used in designing more efficient pumps, turbo machinery, jet engine, and internal combustion engine components where flow qualities including separation of the flow must be well known.

Dr. Semih Mehmet (tm)l?men
Sensor Technology
1402 Ascot Lane
Blacksburg, VA 24060

Sensor Technology
1402 Ascot Lane
Blacksburg, VA 24060

PROJECT TITLE : Anti Icing System Using Engine Waste Heat

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Ice formation on aircraft flight surfaces such as wing leading edges and engine cowls during flight is extremely hazardous. There is a method for deicing in development that involves breaking the ice from these surfaces. Mechanical de-icing is energy efficient, but dislodged chunks of ice can damage engine components. A safer approach is to anti ice which involves heating of critical surfaces to prevent ice from forming, but this exacts a penalty in engine power and thrust. Loop Heat Pipes can provide passive anti-icing using engine waste heat. The only impact on engine performance is due to the heating of inlet air. Since waste heat is extracted from the air oil cooler (AOC), this component can be made smaller with a net savings on specific fuel consumption.

Already accomplished work has established the technical suitability of the Loop Heat Pipe for the application and quantified the performance advantage versus bleed air. Depending on the engine the use of waste heat can effect a 5-6% increase in available shaft horsepower and a 1-5% reduction in specific fuel consumption. In a NASA debriefing, a recent anti icing proposal was criticized because, AIt does not address the real technology issues...for inflight aircraft ice protection. ...requires early integration work.... It neglects issues of system weight and cost.@ The proposed program will resolve these issues for use of a Loop Heat Pipe (LHP)Anti Icing system aboard the Teledyne Ryan Tier II Plus high altitude endurance UAV (the Global Hawk). Two prototype aircraft are presently under construction. Phase I will examine the integration of LHP anti icing for the engine cowl on the prototype aircraft and produce a preliminary design at a level that will permit the evaluation of the system=s mass and cost efficiency versus other options. Phase II will produce an LHP anti icing system integrated into the engine cowl and test it in the NASA LeRC Icing Chamber.

The ability to perform anti icing using waste heat instead of bleed air or electrical power, would be a tremendous benefit for both military and commercial aircraft. The economic and safety incentives resulting from a 5% increase in available engine thrust and a 1-5% improvement in specific fuel consumption will lead to a very large world market.

Thermacore, Inc.,
780 Eden Road,
Lancaster, PA, 17601

Thermacore, Inc.,
780 Eden Road,
Lancaster, PA, 17601

PROJECT TITLE : A Pilot-Centered Turbulence Assessment and Monitoring System

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Airborne encounters with various types of atmospheric turbulence continue to significantly affect the safety and efficiency of aviation. The proposed innovation will improve the detection, assessment, categorization and reporting of inflight turbulence, so as to give flight crews, air traffic controllers, flight planning/dispatch organizations and weather forecasters more timely and accurate information on the extent and severity of turbulence that may impact their operations. The Phase I effort will yield a design for an nexpensive, aircraft-based system that will inform both aircraft operators and airspace managers in a timely and appropriate manner of the location and severity of various forms of turbulence. TAMS (Turbulence Assessment and Monitoring System) uses an innovative approach to the problem, and this proposal will study the merits of developing a standardized scale, similar to the Richter scale used in earthquake assessment, to accurately quantify the energy state of the atmosphere. By integrating data already available from the flight deck avionics with potentially new software designs, the goal of TAMS is to develop a standardized rating system of turbulence that would provide meaningful information to all airspace users, allowing better short-term operational decisions and improved longer-term forecasting models.

Airline companies and their insurers are particularly interested in reducing the costs associated with turbulence encounters. For example, one major airline recorded about 80 turbulence encounter incidents in which flight attendant injuries cost over $500,000 in the first six months of 1996! The costs included medical bills and lost work days only, and were limited to flight attendants; passenger costs, airplane damage and other costs were specifically excluded. A turbulence assessment and monitoring system that could substantially reduce these costs clearly has strong commercialization potential.

Ronald L. Small
Search Technology, Inc.
Aviation Systems Division
4898 South Old Peachtree Rd., Suite 200
Norcross, GA 30071-4707

Search Technology, Inc.
4898 South Old Peachtree Rd., Suite 200
Norcross, GA 30071-4707

PROJECT TITLE : : Cost Minimization and Schedule Optimization via GN&C Avionics Interface Standardization

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The lack of interface standards for information exchange among spacecraft subsystems/avionics together with non-standardized architecture have resulted in high cost spacecraft systems with long integration and test times and increased flight operational complexity. Industry constantly driven to increase performance is in need of a practical means to minimize cost, shorten development schedule and simplify design. To support these goals, the Welch Engineering and Hughes Space and Communications team is pleased to propose to develop a novel architecture coupled with interface standards to allow optimal cooperation and information sharing among spacecraft subsystems such as power, propulsion, communications, and control disciplines. The proposed approach employs STEP-EXPRESS as the baseline to define interface standards for spacecraft Guidance, Navigation, and Control (GN&C) avionics. STEP based interface standards will allow GN&C avionics to effectively exchange information among themselves as well as to other spacecraft avionics while the EXPRESS Language Based Modeling Approach (ELBMA) provides checks to insure that information is complete, unambiguous, and non-redundant. ELBMA will model interface standards of all GN&C avionics and define the object oriented Interface Control Database (ICD) to provide optimal information sharing and effective cross-communication among spacecraft subsystems. Cross-platform avionics communication is achieved via CORBAnet-like mechanism.

The success of this project will lay important groundwork for future development of GN&C interface standards for the entire aerospace industry. As a result, cost effective products and parts for spacecraft, missiles, and many other systems such as aircraft, submarines, automobiles, etc. will be practically produced and available to users at a much more affordable price. Interface standardization facilitates the growth of the entire aerospace industry.

WELCH ENGINEERING, Ltd,
1700 Research Blvd, STE 105,
Rockville, MD 20850

PROJECT TITLE : Integration of Process Based Cost (PBC) Models into Robust Design Simulation (RDS) for Aircraft Life Cycle Cost Analysis (ALCCA) in MDO/SA

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Robust design is defined as a systematic approach to finding optimum values of design factors which result in economical designs with low variability. Many Japanese and U.S. companies strive to achieve robust design through the use of Statistical Process Control (SPC) and Six Sigma approaches. However, these methods are usually applied to address manufacturing variability in the later stages of the design process, when as much as 70-80% of the LCC has already been committed through earlier design decisions. These early design decisions have been predominantly product performance based and passed on to subcontractors, suppliers, and vendors for implementation. It is during the early stages, i.e. conceptual/preliminary or system design, where technology uncertainty and design freedom are the greatest, and it is when life cycle affordability must be addressed. All of theses processes involve a relationship between time and cost.

Theoretical Cost/Time Analysis (CTA) curves will be developed from Process Based Cost (PBC) models for the critical aeronautical system process of certification. CTA will also be included in a system level Aircraft Life Cycle Cost Analysis (ALCCA) for cost-performance trades using Robust Design Simulation (RDS) in a Mutidisciplinary Design Optimization/Systems Analysis (MDO/SA).

Activity Based Costing (ABC) methods are being developed for re-engineering business processes in many industries. For selection of new technologies in the aircraft design process, PBC methods can be used to address downstream processes, such as certification cost/time considerations. An ALCCA using Robust Design Simulation (RDS) and PBC models can provide a set of PC-based software tools for rapid evaluation of new processes, including development, manufacturing, certification and support.

NAME Jerry W. Phillips
ORGANIZATION NAME Executive AeroSystems Inc. (EAI)
MAIL ADDRESS P.O. Box 788 Roswell, GA 30077

ORGANIZATION NAME Executive AeroSystems Inc. (EAI)
MAIL ADDRESS P.O. Box 788 Roswell, GA 30077

PROJECT TITLE : : Air Traffic Control Automation in Heavy Weather

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Our innovation, the Weather Route Generator (WRG), is an all-weather Air Traffic Control (ATC) software tool that bridges the gap between today's weather information systems and ATC automation algorithms. Current sensor technology, meteorological methods, and displays are capable of producing accurate and timely mesoscale nowcasts (pictures of the current weather) and forecasts in the terminal area. But controllers still find it exceedingly difficult to vector aircraft around storm cells, maintain safety, and achieve efficient throughput. In short, the weather and airspace management information is available, but the lack of time to mentally solve this complex problem causes inefficient solutions and high workloads for air traffic controllers. However, this type and magnitude of data is well-suited for today's ATC automation algorithms. Our innovation provides the computational geometry for weather analysis, algorithmic route planning, and scheduling software that designs arrival aircraft trajectories that are properly spaced and avoid penetrating heavy weather. A preliminary concept version has been tested with real weather data; results indicate that it is feasible to maintain high throughput even in relatively heavy weather. Thus, our innovation will help NASA provide the technology for enhanced terminal area productivity, safety, and airspace management.

The WRG commercial potential is very high because the trend in air traffic control is towards giving airlines more and more autonomy. The recent and on-going Free Flight initiative is an example of this trend. Researchers at NASA and the FAA envision reduced control of air traffic. The FAA's and CAA's roles will be more of managing air traffic. As this occurs, airlines and other operators will require the WRG to vector their aircraft in heavy weather. In the future, this could be applied to en route airspace as well as terminal areas.

George Hunter
Seagull Technology, Inc.
21771 Stevens Creek Boulevard
Cupertino, CA 95014-1175

Seagull Technology, Inc.
21771 Stevens Creek Boulevard
Cupertino, CA 95014-1175

PROJECT TITLE : Agent-Based Performance Assessment Tool for General Aviation Operations Under Free Flight

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Although considerable effort is being devoted to understanding the effect of free flight air traffic management (ATM) concepts on commercial aviation, the consequences for general aviation (GA) have received relatively less attention. We thus propose to develop a computational tool to assess free flightÕs potential GA impact, combining an agent-based representation of the overall pilot/vehicle/ATM system with model-based metrics of pilot situation awareness (SA) and performance. We will focus on the single GA pilot, and demonstrate overall feasibility of generating objective SA and error metrics for evaluating procedures design options, across a range of free flight scenarios. The approach relies on a multi-stage agent-based representation of the pilot's SA and decision-making behavior, and a multidimensional metric that reflects SA, performance, and error propensity. Bayesian networks support SA computations, and an object-oriented implementation facilitates integration with other software packages; a graphical user interface supports scenario specification and on-line performance analysis. We propose to develop a prototype tool, apply it to the free flight environment, integrate it with a realistic ATM model, and demonstrate its use in design option evaluation.

The proposed technology will directly support closing the human factors loop on the development of free flight ATM concepts. The underlying modeling approach will support human factors assessments in other domains (e.g., nuclear power plants, chemical processing centers, power dispatch stations, intelligent vehicle highway system control centers, etc.) where it is desirable to determine how system design affects operator awareness and performance before committing to a specific configuration. We plan to extract the belief network algorithm that emulates pilot situation assessment in the presence of uncertainty, and develop a commercial-quality software tool for computer-based reasoning under uncertainty.

GregL. Zacharias
55 Wheeler St.
Cambridge, MA 02138

PROJECT TITLE : : Dynamic Resectorization and Route Coordination for Air Traffic Management

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Significant discussion has occurred in the Air Transportation Management (ATM) community over the last year about the concept of "Free Flight." The motivation behind this call to action is the clear need to improve the efficiency of the current ATM system. However, to effectively and safely implement a new system, it is critical that the limitations of the current system be understood. This proposed effort will address the direct relationship that exists between the human Air Traffic Specialist (ATS), the division of airspace into `sectors,' and the route and altitude restrictions that are used in the ATM system today. To date, the Free Flight concept has not recognized this relationship.

Wyndemere Incorporated proposes a new set of procedures for dynamic resectorization and coordination of aircraft routings that will allow the desired flexibility of the Free Flight concept while still providing the necessary cues, information and organization of the traffic situation such that the ATS can maintain situational awareness and provide the separation assurance function necessary for Free Flight.

As this effort is focused on the development of innovative techniques for Air Traffic Management, the primary sources for non-SBIR funding are the organizations and agencies that maintain and improve the ATM systems of the United States, and of the world. Wyndemere Incorporated has previous involvement in many areas of development of the National Airspace System (NAS) of the United States.

The high level of interest displayed by the FAA and the Airline Industries to expedite the implementation of a free flight system requires that we begin examining, as soon as possible, the types of procedures and tools to support those procedures that controllers will need to maintain a proper level of awareness of system state for effective control. This research will provide Wyndemere with system requirements that can be used in the development of future ATC systems (such as CTAS, DSR, STARS, and other international systems). We plan to use the results from this study, combined with our existing capabilities in ATC software development, to obtain subcontracts for the development of future ATC systems. Initial discussions with FAA representatives about the Dynamic Resectorization concept have already been conducted.

Name: Christopher R. Brinton
Title: Vice President
Address: Wyndemere Incorporated
4875 Pearl East Circle, Suite 301
Boulder, CO 80301
USA

Wyndemere Incorporated
4875 Pearl East Circle, Suite 301
Boulder, CO 80301

PROJECT TITLE : Optical Air Mass Flux Sensor for Flight Applications (7117-060)

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Flight qualified sensors for inlet air mass flux are desired for improved control of conventional aeropropulsion gas turbine power plants and variable-geometry, mixed-compression inlets of advanced flight vehicles. This proposal describes an effort to develop and flight test an optical air mass flux sensor that provides continuous, rapid-response mass-flux data within the inlet duct over the entire flight envelope. It builds on the previous, successful demonstration of the sensor on a full-scale F-100 engine in ground tests. In the proposed program, PSI will develop a small, flight compatible package suitable for installation and testing on a NASA Dryden flight research vehicle. The Phase I portion will be devoted to completing the design task and will include a detailed reduction of the hardware to a flight compatible package, as well as automated and streamlined software for continuous mass flux reporting with a target bandwidth of 10 Hz. The successful flight demonstration in the Phase II portion of the proposed program will represent a significant milestone in the evolution of diode laser sensor technology for aeropropulsion applications and is expected to enable a suite of related diode laser sensors, including emissions and combustor exit temperature sensors.

The optical air mass flux sensor has identified commercial applications to military and civilian aircraft for improved engine control. Commercial stall and surge sensing are already being pursued with industry in ground tests. PSI will continue commercialization of this technology through similar licensing arrangements throughout the proposed program. Variants of the proposed sensor using different wavelength laser have commercial application as mass flow meters for natural gas and process chemical flows. Pre-commercial applications for NASA missions such as the hyper-X program are also envisioned.

Dr. Mark G. Allen
Physical Sciences Inc.
20 New England Business Center
Andover, MA 01810-1077

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

PROJECT TITLE : Universal Fiber Optic Test/Instrumentation System (UFO-TIS)

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The universal fiber optic test/instrumentation system (UFO-TIS) will provide an embedded test/instrumentation system to assist aircraft designers to assess health/status of fiber optic subsystems during dynamic flight environment. SPEC's proposal is to study and design (in Phase I) and build (in Phase 2) a prototype test/instrumentation system. This universal system will be adapted to a wide range of multimode optical fibers used in various aircraft by simply switching between optical adapters. The system will be capable of operating in a photon-counting mode, resulting in minimal "dead zones" for short fiber runs used in typical aircraft applications. In parallel or as an extension to phase II, the UFO-TIS can be packaged as a flyable instrumentation device for test in the NASA F-18 Systems Research Aircraft (SRA). The SPEC UFO-TIS coupled with the NASA SRA will also provide an instrumentation/platform to assist the Fiber Optics Working Group (FOWG) to use in their upcoming fiber evaluations, and for NASA to investigate (and mitigate) communications issues with upcoming fly-by-light control systems. In addition, the proposed program will provide synergy with other programs, such as the fiber-optic sensor suite being developed for the X-33 by NASA-Langley (LaRC) and Lockheed Martin.

The proposed universal fiber optic test/instrumentation system (UFO-TIS) will be capable of supporting commercial aviation in the design, installation and tests of fiber optic interconnect systems for commercial and military aircraft. Potential customers are The Boeing Company for the 757, 767 and 777 airframes; Lockheed Martin for the F-22, McDonnell Douglas for the F-18 family and the Boeing/Sikorsky Aircraft RAH-66 helicopter. In addition, SPEC has a long term working relationship with 3M's Telecom Systems Division for the design and development of Optical Time Domain Reflectometers. NAME AND ADDRESS OF PRINCIPAL Name: Dr. Newton B. Penrose Organization and address is the same as Offeror.

Systems & Processes Engineering Corporation (SPEC) Phone: (512) 306-1100
401 Camp Craft Road
Austin, TX 78746-6558

PROJECT TITLE : Airborne Doppler Lidar Measurement of Vertical Velocity as Input to a Gust Load Alleviation System

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

A short to moderate range, forward looking scanning Doppler lidar is proposed to be used onboard commercial transport aircraft to sense the vertical velocity ahead, in the vicinity of the flight path, particularly that associated with intense turbulent wind structures, The goal is to provide a closed-loop flight control system with an accurate measurement of the upcoming vertical velocity at sufficient look-ahead distance that the structural loads on the aircraft can be significantly reduced through manipulation of the aircraft control surfaces. The proposed effort leverages two ongoing CTI development efforts of airborne Doppler lidar sensors. The Phase I program will develop and evaluate scanning and processing concepts appropriate for the measurement objectives. A preliminary scanner and algorithm design will be developed in Phase I. The Phase II effort will construct the scanner, implement the appropriate hardware and software changes to the available instrumentation, and perform proof-of-concept flight tests.

Primary end-use applications for the subject sensor are directly related to commercial airlines and aircraft manufacturers. Airborne measurement of wind environments for commercial as well as military aircraft, including gusts, and turbulence, wind shear, wind profiling and wake vortices are the primary application areas. Data acquired and recorded by such instrumentation could be used to validate, and extend, descriptions of the wind shear environment used in flight simulation environments for pilot training.

Coherent Technologies, Inc.
P.O. Box 7488
Boulder, CO 80306

PROJECT TITLE : Impulse Feedback-Based Health Management System for Aircraft Engine Systems

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Both historical and recent experience shows that aircraft require improved monitoring and maintenance of engine system condition. Vibration-based health management systems generally depend upon the dynamic response of a machine or structure to operational forces. They cannot reliably determine causes of anomalies. CETI proposes to use Micro Electrical Mechanical Systems (MEMS) technology to deploy a proven troubleshooting technique in a real-time health management system for turbine engines and critical airframe components. This technology will directly support the objective of Subtopic 01.15 for real-time measurement techniques to acquire aerodynamic, structural, and propulsion system performance characteristics in flight and to safely expand the flight envelope of aerospace vehicles. The proposed system would be capable of fault identification, diagnosis, and prediction of remaining component life. The technique is based on combining natural and impulse excited response data to extract system component characteristics. The proposed effort would demonstrate the feasibility of transitioning the technique to a health management system in a bread-board MEMS. System components (on-board exciter, sensors, adaptively modifiable component and tribological models, and evaluation software) can then be incorporated in a MEMS device. Successful deployment of this technology would provide substantial new health management capabilities for aircraft engines and critical stationary components.

Achievement of the project goals will provide NASA with a health management system that reliably protects advanced engine systems from unexpected failures. The proposed system provides assessment of operability and remaining time- to-failure for both critical stationary components and all types of turbomachinery, particularly aircraft gas turbines, rocket engine fuel and oxidizer pumps, and other turbomachinery subsystems. Industrial applications, which also might have some application to aircraft auxiliary systems, include pumps, compressors, steam turbines, fans, and large electric motors.

William D. Marscher
Concepts ETI, Inc.
4 Billings Farm Road
White River Jct., VT 05001

Concepts ETI, Inc.
4 Billings Farm Road
White River Jct., VT 05001

PROJECT TITLE : Micromachined Fiber Optic Accelerometers

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The materials and technology now exist to construct miniaturized, light weight, robust, highly multiplexed, fiber optic-based, micromachined accelerometers for wind tunnel and in-flight instrumentation. This instrumentation is crucial to the development and operation of affordable, safe and efficient 21st century aircraft and other high-speed vehicles. The development of smart structures and adaptive control systems will require the accurate and reliable measurement of vibration important for understanding the basic flight dynamics leading to improvements in the design and operation of future high-speed transportation systems.

An excellent development team has been assembled including 1) the Fiber & Electro-Optics Research Center at Virginia Tech, a world leader in fiber optic sensor development, 2) Bell Laboratories/Lucent Technologies, which has invested over $50 million developing grating-based devices for communications applications, 3) Litton, with a micromachined product line and current agreements with F&S for joint product development, and 4) F&S, a leader in fiber optic sensor development and commercialization. This F&S team is both qualified and motivated to build upon its combined demonstrated capabilities to accomplish this development and commercialization project.

The development of light weight, small size, highly multiplexed accelerometers for wind tunnel instrumentation will find applications for in-flight aircraft health monitoring and active control of vibration in flaps and ailerons. These transducers will find tremendous markets in 1) transportation system design, development and operation, specifically automotive, aircraft, ships and submarines, 2) the power generation and monitoring systems for coal-fired, nuclear and fuel-cell technologies, 3) medical applications, and 4) specialty products including golf clubs, skis and other sports equipment.

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

PROJECT TITLE : : Monolithic Fully Integated Optic Inertial Navigation System

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The GPS is an affordable and accurate means of guiding military and civilian aircraft. However, at times the GPS signal becomes blocked or degraded due to loss of satellite lock or poor viewing angle. It is necessary to back it up with inertial navigation. However, there is no inertial navigation system which is accurate enough and inexpensive enough to interface with GPS. A completely monolithic fully integrated micromachined INS is proposed which has potentially navigational grade performance to provide all the inertial measurements, by virtue of the materials used, the fabrication processes adopted, and the transduction technique. This INS will be interfaced with GPS. The two systems will be uncoupled initially. The Kalman filter will include 17 states. In Phase II the coupling will be tightened to include feedback states to the GPS first and then to the INS to model its error states. It will have the capability of aligning the INS in flight and of compensating for its drift in real time.

An integrated optic monolithic inertial measurement unit that has navigational grade performance and low cost and provides all the axes can interface with GPS to guide aircraft. It has also applications in in car and truck navigation. It has also geophysical and seismological applications for inertial navigation during well drilling and for well imaging. It can also be used for automotive safety research.

Dr. John Farah
Optisensors, Inc.
M.I.T. P.O.Box 397301
Cambridge, MA 02139

M.I.T. P.O.Box 397301
Cambridge, MA 02139

PROJECT TITLE : Advanced High Performance Intelligent Aircraft Control Techniques

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

This project proposes intelligent control for advanced flight control system design. Specifically, an integrated design framework utilizing neural networks, fuzzy logic, and nonlinear control will be developed to address specific issues, such as complexity, nonlinearity and uncertainty, arising in advanced aircraft control. The goal is to improve stability robustness and performance robustness for all flight conditions. In this project, the complexity and uncertainty issues are addressed via the distributed parallel processing, learning, and online reoptimization properties of neural networks. The nonlinear dynamics due to severe kinematic and inertial coupling as well as aerodynamics is naturally incorporated into the design framework. The knowledge base and decision making logic furnished by a fuzzy system leads to a human intelligence enhanced adaptive control scheme. At the end of Phase I, the effectiveness of the integrated intelligent control approach will be demonstrated on a fully integrated prototype module. It is anticipated that this project together with our on-going research on intelligent guidance laws will greatly enhance the status of current aircraft guidance and control system design.

The resulting design software toolkit in this project can find applications to a whole spectrum of flight control systems, including missile autopilot, aircraft flight control, spacecraft flight control, and unmanned aerial vehicle control.

Dr. Ching-Fang Lin
American GNC Corporation
9131 Mason Avenue
Chatsworth, CA 91311

American GNC Corporation
9131 Mason Avenue
Chatsworth, CA 91311

PROJECT TITLE : UAV Droplet Heat Exchanger

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Unmanned aerial vehicles (UAVs) are now being used for atmospheric sampling, but significant advances in performance must be achieved for sustained flight at altitudes up to 30 km. It is proposed to replace the standard metal finned circulating glycol/water heat exchanger with a droplet heat exchanger developed in this program. A circulating liquid sprayed into a ducted airstream creates a dense droplet field that directly transfers heat from the liquid to the gas and is then captured at the end of the duct by inertial separation from a sharply turning flow. A droplet heat exchanger efficiently rejects engine heat under widely varying conditions while greatly reducing heat exchanger weight and lowering aircraft drag. Heat transfer can be increased for high altitude flight, lower weight increases altitude capability and together with decreased drag increases range. Heat transfer and droplet collection can be maintained during speed and attitude changes, and the system tolerates rain, snow, and dust. DHXs have already been demonstrated experimentally; a Phase 1 modeling and analysis program is proposed to demonstrate the feasibility of a droplet heat exchanger for a UAV.

A droplet heat exchanger successfully applied to a UAV will permit a significant reduction in both aerodynamic drag and vehicle weight. The resulting increase in aircraft efficiency will greatly enhance the capabilities of a redesigned UAV. Droplet heat exchangers can be used for rejecting heat from any commercial engine. Once developed, weight savings and simplicity may lead to aircraft and other applications.

Stephen C. Bates
Thoughtventions Unlimited
P. O. Box 1310
Glastonbury, CT 06033

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

PROJECT TITLE : Real-Time Health Monitoring of Flight-Critical Systems Using Fuzzy CMAC

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Many existing approaches to fault detection and diagnostic systems are after-the-fact methods, i.e. failure has occurred and the machine is down. As a result, the mean-time-between-failure (MTBF) is short and many man-hours are needed to repair the machine. The key to preventing failure to occur is the ability to identify degraded states of the machine so that machine can be repaired during regular maintenance hours.

In this proposal, we propose a new method to machine degradation monitoring, fault detection and diagnostics, which is robust to sensor noise and is also efficient in training and learning. We are also able to detect new fault conditions that have not occurred before, which may include sensor failures and hence the capability of validity self-checks. Our idea is to use a new type of biologically-realistic neural net, called Fuzzy CMAC. The Fuzzy CMAC (Cerebellar Model Arithmetic Computer) inherits preferred features of arbitrary function approximation and parallel processing from the original CMAC neural network, and the capability of acquiring and incorporating human knowledge into a system and the capability of processing information based on fuzzy inference rules from the fuzzy logic. Our learning rates are at least an order of magnitude faster than conventional neural nets. The Fuzzy CMAC can be designed in such a way that each output corresponds to one type of failure condition. Hence the neural network is able to monitor the degradation and to identify the type of failure simultaneously.

The range of applications of the Fuzzy CMAC is very large. Other applications include medical monitoring, image classification, self-repairing control systems, system health monitoring, in-process control of manufacturing processes, and real-time error compensation for machine tools using calibration data to train the network.

Dr. C. M. Kwan
Intelligent Automation, Inc.
2 Research Place, Suite 202
Rockville, MD 20850

Intelligent Automation, Inc.
2 Research Place, Suite 202
Rockville, MD 20850

PROJECT TITLE : Software Metrics Decision Support System

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The objective of this work is to develop a software metrics decision support system to assist managers in making programmatic and technical decisions concerning management metrics program implementation on software projects. Our goal is to provide managers with an innovative decision support system that combines methods from software measurement and decision analysis. The system will: alert a manager to possible problems in a software development, evaluate alternative corrective actions, and evaluate risks. The system will also provide a means for extensive "what if" analyses. The proposed research will combine the power of decision analysis with software metrics to support software development managers. This will be pursued by conducting three tasks in Phase I: (1) identification of important factors in a software metrics decision support system, (2) development of a methodology, and (3) development of a plan of approach for a computer prototype to be developed in Phase II.

We expect applications for the product of the Phase II R&D in both commercial and Federal Government markets. These include markets for the decision support process (service), the software decision support system (product), and a technology transfer course (service). The product should meet a significant need both in the specific application of a system for software program management support and in the more general application as a general-purpose evaluation system. Clients for the specific service and supporting software are in the federal government, its contractors, and commercial organizations. Customers for the general purpose software are practitioners in the operations research and management science professions as well as program/project managers in corporations. Technology transfer activities, especially in the form of executive education courses and consulting on pilot applications, are also expected to have a commercial market from the organizations that purchase the software metrics decision support system. Targeted companies are those that engage in substantial software product development.

Jacob W. Ulvila
Decision Science Associates, Inc.
10980 Poplar Ford Trail
Manassas, VA 20109

Decision Science Associates, Inc.
10980 Poplar Ford Trail
Manassas, VA 20109

PROJECT TITLE : Verified VHDL Synthesizable Cores

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The development of verified reusable hardware specification components, manifest as synthesizable VHDL cores, represents a key technology that will enable engineering discipline to manage design complexity. The specific innovation we propose is the development of verified, synthesizable VHDL cores that include all the features, documentation, and support necessary to insure integration with customer designs with the high degree of reliability provided by the application of formal methods. The innovation is relevant to NASA as (i) an innovative approach to software and systems reuse, (ii) formal mathematical methods for specification, design, and analysis of digital systems, and (iii) techniques and tools for integrating formal methods with existing methods, tools, and languages. The technology will provide a means by which there are no tradeoffs between COTS (commercial off the shelf) components and those required to satisfy the stringent reliability and safety requirements of safety-critical systems.

The POTENTIAL COMMERCIAL APPLICATION is in the electronics design industry for both safety-critical and commercial systems. These products will be used by engineers within the computer, networking and semiconductor markets to develop reusable designs, reduce design cycle times and reduce time to market for electronic products and systems.

Dr. Bhaskar Bose
Derivation Systems, Inc.
5963 La Place Court, Suite 208
Carlsbad, CA 92008

Derivation Systems, Inc.
5963 La Place Court, Suite 208
Carlsbad, CA 92008

PROJECT TITLE : Design and Manufacture of a Deployable Highly Loaded Airfoil Structure

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The ability to rapidly and economically deploy airfoil structures represents one of the greatest technical challenges in the development of roadable aircraft. Our telescopic wing principles offer the roadable aircraft the safe and fast automatic conversion from aircraft to automobile mode. These principles will improve utility of the aircraft and provide rapid point to point single vehicle transportation. The R&D objective is to develop deployable wing and to demonstrate the motion characteristics and drive system principles. Met objectives will provide the background for development and demonstration of a full size half wing for a four passenger advanced flying automobile. The commercialization of these technologies once matured will improve economics of the U.S. industry. Additionally, automotive standards, will reduce noise levels of private air transportation providing better community acceptance.

The successful development and demonstration of deployable airfoil structures based on telescopic wing principles will allow application of this technology in the following areas: AIRCRAFT STRUCTURES: general aviation, subsonic transports, supersonic(future), helicopter blades. MARINE CRAFT: sail boats, hydrofoils, ships. MACHINE STRUCTURES: telescopic arms, robotics.

Mike Czajkowski,
AFA Inc.,
P.O. Box 193,
La Jolla, Ca 92038.

Dr. Branko Sarh,
AFA Inc.,
19542 Pompano Ln #107,
Huntington Beach, Ca 92648

PROJECT TITLE : Intelligent wireless Airborne Gateway to Aviation Information Services

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The innovation is an infrastructure operating system designed specifically for General Aviation that will serve as an automated wireless airborne gateway to Aviation Information Services. The system will be supported by a national infrastructure and will run on currently developing hardware and products. The Aviation Information Service will be enabled through an automated interconnect to the Public Switch Telephone Network (PSTN) and will provide services that include weather information, flight planning, in-flight flight-plan revision, GPS based navigation, traffic information, and Automated Dependent Surveillance (ADS) capabilities. Also, the ability to make airborne phone calls, send fax / e-mail, and utilize services on the internet will be provided with the Aviation Information Service. Further, the system includes tracking flight paths and recording pertinent data at base stations with a system for an emergency locator in event of an accident . The system is truly an innovation as it brings to General Aviation a complete package of capabilities under one system that can run on any PC compatible unit / lap top. The attributes of the system summarized above brings an overall utility of increased safety and convenience through the access to information to the General Aviation cockpit in a low cost structure

An Aviation Information Service will be created which will serve as a wireless gateway to information to the GA cockpit. Through access to the internet a multiple of service providers will be enabled to make their service available to the airborne GA pilots. GA pilots will have the capability to make phone calls, send fax / e-mail, access real time weather, conduct in-flight flight revisions, and utilize a number of other services from the air that are not presently available to the airborne GA pilot. This form of service which can be delivered to market in a low cost structure, provides for a strong need in the GA industry and will bolster industry as a whole.

Ross Norsworthy
ROSS Engineering Company
12505 Starkey Rd. Ste. E
Largo FL 34643

ROSS Engineering Company
12505 Starkey Rd. Ste. E
Largo FL 34643

PROJECT TITLE : Affordable Computer Based Trainer

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The innovation being proposed by Advanced Creations, incorporated (ACi) is an affordable Computer-Based-Training (CBT) system configured around a complex system of software modules developed by the ACi under internal funds. The software modules comprise a subset of a comprehensive software system called OASIS (Onboard Avionics Synergistic Information System) which is configured to be the core software package for a fully integrated avionics suite. Specific modules from this package that provide an engine gauge cluster, an attitude direction indicator (ADI), a horizontal moving map (HMAP), and a three dimensional out-of-cockpit view of actual flight plans (with an actual terrain and obstacle database) can be ported to a personal computer domain in concert with one of the latest generation graphics generator to yield a very low cost trainer capability. The OASIS software is easily modified to provide simulations for any cockpit configuration or specific aircraft dynamics.

The CBT, as proposed, is one that will meet or exceed the primary vision and goals of the AGATE training work package. The simulator concept will be driven to emulate the AGATE cockpit, permitting a realistic preflight planning, inflight readjustments, and post flight review and critique.

This innovation will result in a highly versatile computer based trainer with broad potential for use in General Aviation, high school drivers training and many others. Dr. John A. Little, Advanced Creations, inc., 4401 Dayton-Xenia Rd., Dayton OH, 45432

Advanced Creations, inc.,
4401 Dayton-Xenia Rd,
Dayton OH, 45432

PROJECT TITLE : An Affordable Human Factors Engineered Aircraft Energy Performance Management System

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Pilot induced fuel exhaustion, stall/spin and flight path control accidents, and near-accidents, continue to plague the general aviation safety record. The current instrumentation force the pilot to maintain a very high proficiency level to safely utilize the inadequately 'Human Factors Engineered' (HFE) cockpit of GA aircraft. Studies of aircraft accidents have shown that during stress and high workload situations, pilots experience 'Cognitive Tunneling' ( See Technical Background ), which results in dramatic impairment of the ability to interpret instrument data and make correct decisions. To address this critical problem, VMD proposes utilizing HFE technology to direct the design of an innovative and affordable General Aviation Energy Performance Management System (EPAMS). This system will provide precise energy management control from takeoff to touchdown via a real-time 'cued' display and sensor system. HFE techniques can be used in designing specific flight path control display formats that can virtually eliminate pilot misinterpretation errors, especially during high workload or stressful periods. The goal of this effort is to create a key technology necessary for takeoff to touchdown flight management, thereby reducing pilot training, improving GA safety and efficiency, and therefore increase its utility and market base.

All general aviation and corporate aircraft in service or newly constructed.

Lance G. Turk
Vision Micro Design Inc.
5501 East Road
Bellingham, WA 98226

Vision Micro Design, Inc.
5501 East Road
Bellingham WA 98226

PROJECT TITLE : A Novel Muffler/Auxiliary Power Source for General Aviation Aircraft

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The proposed project will develop a unique exhaust powered auxiliary power system which could be used on any general aviation aircraft. This project will produce a complete FAA-certified auxiliary system which will supply enough energy to power the alternator, air conditioning system, cabin pressurization system, deice system, and other (to be identified) system requirements. The source of this power will be the energy which is currently wasted in the engine's exhaust and produces environmental noise. This wasted energy will be captured by the use of a turbocharger which will then in turn power the various subsystems. The total available power in the exhaust of a GA air-cooled Av-gas fueled engine is approximately 50% greater than the useful power from the engine. It is expected that approximately one third of this wasted energy can be harnessed to do useful work (70 BHP) by supplying auxiliary power for engine accessories, alternator, cabin pressurization, and either system requirement.

The proposed innovation will furnish a complete FAA-certified unique auxiliary power system which can efficiently furnish energy for various auxiliary system on any general aviation aircraft. This unit will improve the aircraft's efficiency, increase the amount of auxiliary power available, and reduce cabin noise for any general aviation aircraft. Global Aircraft is very interested in this concept for incorporation in its GT-3 Trainer and future GA airplanes. Global is especially interested in developing an FAA certificated retrofit kit for existing airplanes. If the general aviation aircraft market is revitalized to the levels of annual sales achieved in the 1970's and this concept captured 20% of the market, there would be a market for about 3,600 units per year by 2000. If in addition, retrofits were made to a small portion (<5%) of the current general aviation fleet, then another 10,000 units could be marketed over the next ten years. At the target price for the unit ($3,000) the total market for this product would be approximately $13,800,000 per year. It should be noted that a simpler, cheaper version of this product might have application in the automobile market and that if this market were shown to be feasible, then the demand for this product would be enormous.

W. G. Wells
Global Aircraft Corporation
P.O. Box 850
Starkville, MS 39760-0850

Global Aircraft Corporation
P.O. Box 850
Starkville, MS 39760-0850

PROJECT TITLE : Advanced High-Lift Systems to Enhance Performance and Utility of Existing and New GA Aircraft.

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The innovation proposed in this SBIR effort is the development of an advanced new technology high-lift flap system for General Aviation aircraft. Until now, no high-lift flap system has been theoretically designed and tested, using state-of-the-art computational tools to optimally design a high-lift flap system for GA applications. Not only will the latest technology be brought to the GA market for optimal high-lift design, but this technology will be developed for optimization of two market segments: (1) retrofitting a high-lift system to existing aircraft wings and (2) optimally designing a high-lift system to get the best performance from the latest technology low drag NLF wings. The design and implementation of this concept poses a direct need to GA, first to provide safety with lower stall speeds and second the ability to add needed utility and growth potential to existing aircraft. This innovation is relevant to the Aircraft Configuration part of the GA subtopic that calls for vehicles that enhance performance and safety.

For commercialization IAT will have three perspective markets, all large ones in the aircraft industry. The following three markets appear highly p