1995 NASA SBIR & STTR Abstract Archives

NASA 1995 SBIR Phase 1 SOLICITATION

PROJECT SUMMARY

Contract Id:

NAS 3 27722

Proposal Number:

01.01-0003

Project Title:

TURBINE EXHAUST PARTICULATE DETECTION BY LASER-INDUCED INCANDESCENCE

Technical Abstract:

PSI proposes to demonstrate the feasibility of laser-induced incandescence as a practical, affordable instrument package for detection of soot particles in test stand gas turbine exhausts. The basic method utilizes a pulsed laser to radiatively heat particles, and an imaging detection system to observe spatial distributions of the time-resolved incandescence from the hot particles as they cool following cessation of the laser pulse. Demonstration experiments will observe spatially resolved incandescence as a function of wavelength and time for various laser wavelengths and fluences. A key part of the proposed effort will focus on quantification of the diagnostic for particle number density and size distribution by comparison to light scattering and extinction measurements for flame-generated soot particles. The Phase I effort will also include prototype design considerations such as ruggedness, component packaging and cost, and operating characteristics.

Potential Commercial Applications:

The proposed instrument will be useful to the Federal government and the private sector for all diagnostic and process control applications requiring the non-intrusive detection of submicron particulates for environmental, tactical, or operational purposes. In particular, the device will find applications in the aviation, transportation, power generation, environmental, and semiconductor manufacturing industries.

Name and Address of Offeror:

Contract Id:

NAS 3 27731

Proposal Number:

01.01-0333A

Project Title:

PLANAR IMAGING AND LIF FOR QUANTITATIVE ASSESSMENT OF MIXING OF JETS ISSUING INTO A CROSSFLOW

Technical Abstract:

An innovative program using Laser-Induced Fluorescence (LIF) and planar imaging to examine passive scalar concentration field (indicative of thermal field) is proposed. One of the IHPTET (Integrated High Performance Turbine Engine Technology) goals is to operate turbines at 2200-2500 K inlet temperatures, maintain efficiencies in the 88-94% range and require total cooling flows of only 5% of the engine air flow rate. To attain these goals, a thorough understanding of the factors which control the attachment of film jets to the wall is mandatory. Effusion cooling offers a relatively simple technique for the efficient cooling of gas turbine combustor and turbine blade walls. Effusion cooling is strongly influenced by the number of holes, hole size, coolant flow rate, injection angle and pressure drop across the holes. The ability to evaluate the effectiveness of a design can improve design and reduce design cycle time. A fluores- cence dye will be seeded in the coolant flow. The flow configuration tested will be of direct practical relevance to state-of-the-art designs. In Phase I, passive scalar characteristics will be obtained to establish feasibility. Phase II will use the technique to evaluate the effectiveness of various designs.

Potential Commercial Applications:

Planar imaging and LIF provide a quantitative assessment of mixing of jets issuing into a crossflow, which is of primary relevance in many engineering applications. Examples include chemical processing, gas injection in combustors, film cooling for turbine and combustor, V/STOL transition flight aerodynamics, pollutant dispersion. The technique can trace several jet paths simultaneously and efficiently, and would find application in many industries. The design of a more effective film cooling system for turbines and combustors presents a second potential commercial product.

Name and Address of Offeror:

Contract Id:

NAS 3 27739

Proposal Number:

01.02-0017

Project Title:

HEAT TRANSFER ENHANCEMENT IN TURBINE BLADES WITH ASYMMETRIC RIBS

Technical Abstract:

Gas turbines are required to operate with gas flows at temperatures more than 1400oC, much higher than the melting temperatures of the blade material. The Coriolis force, induced by rotation of turbine blades, results in highly non-uniform heat transfer distribution on leading and trailing sides, leading to premature failure and unreliable thermal operation of the blade. This is mainly due to the distortion of mainstream velocity profile by cross-stream secondary flows. To combat this problem, use of Asymmetric ribs are proposed for heat transfer augmentation, namely, thicker ribs on trailing side and thinner ribs on leading side. It is anticipated that higher shear stress along the leading wall and lower shear stress on the leading wall, enforced by asymmetric ribs, will yield enhanced and more uniform heat transfer. The proposed investigation aims at obtaining uniform distributions of regional and local heat transfer coefficients through mass transfer experiments and by using the analogy between heat and mass transfer. Extensive experiments will be conducted with transverse and angled, asymmetric ribs in a two-pass, square rotating channel. The local distributions obtained will determine the extent of uniformity and enhancement of heat transfer with asymmetric ribs. A wide number of operating and geometrical parameters will be examined. The proposed Phase I project will identify the best rib configuration that can yield enhanced and more uniform heat transfer in turbine blades.

Potential Commercial Applications:

The for asymmetric ribs include gas turbine blades for aircraft engines and rotors of electrical rotating machinery. It will lead to higher power output, higher thermal efficiency, and increased life cycle of gas turbine engines and turbomachinery.

Name and Address of Offeror:

Contract Id:

NAS 3 27733

Proposal Number:

01.02-2321

Project Title:

DYNAMIC CLEARANCE CONTROL SYSTEMS FOR AXIAL COMPRESSORS

Technical Abstract:

The ability to control compressor running clearances under all gas turbine operating conditions is crucial to improving future aircraft propulsion capability, particularly as overall compressor pressure ratios increase. Existing Active Clearance Control schemes are successful in controlling steady-state cruise clearances. Current advancement in sensor, actuator, and control technologies make the idea of controlling transient compressor and engine clearances viable. This project will develop and evaluate innovative compressor dynamic clearance control (DCC) concepts and will provide hardware for demonstrating the preferred DCC configuration in a compressor development rig. Phase I will establish DCC system requirements, screen several competitive systems (including thermal, mechanical, magnetic and electromagnetic approaches) and integrate results from ongoing P&W sensor and control technology programs. Detailed technical analyses (including bench testing) of the most promising configurations will be conducted in Phase II, followed by detailed design and fabrication of preferred actuation systems. The preferred system hardware may be installed in the Advanced Concepts Evaluation (ACE) compressor rig and its effectiveness demonstrated over various operating conditions. The project is complementary (and will be coordinated) with ongoing Advanced Technology projects and goals for the IHPTET initiative.

Potential Commercial Applications:

Implementation of a compressor DCC system will provide dramatic improvements in gas turbine performance, including reduced SFC, reduced parts count (fewer stages and elimination of abradable seals), reduced engine weight, increased engine durability and decreased maintenance and operating costs. Also, the technology developed will lead to dual-use applications, due to teaming with P&W. The proposed project is complementary to several ongoing P&W advanced technology programs, is compatible with the goals of the IHPTET initiative, and will be coordinated with ongoing Advanced Technology programs.

Name and Address of Offeror:

Contract Id:

NAS 3 27682

Proposal Number:

01.02-5215B

Project Title:

FLASHBACK AND PREIGNITION PREVENTION IN LEAN, PREMIXED LOW NOX COMBUSTORS

Technical Abstract:

Lean premixed, prevaporized (LPP) high temperature combustor designs as explored for the Advanced Subsonic Initiative, High Speed Research combustor and other aerospace programs can achieve very low NOx emission levels; however, these designs may have problems with flashback and preignition at high power conditions and during surge and rapid spool down. A solution to these problems would remove a major barrier to acceptance in aircraft applications. Precision Combustion, Inc. (PCI) has developed a novel system solution to this problem. A proof of concept demonstration and evaluation is proposed in the Phase I followed by high pressure testing in Phase II.

Potential Commercial Applications:

This proposal offers a critical enabling technology for a successful premixed High Speed Research combustor and other aerospace low NOx combustor designs. Spinoff of the technology for ground based systems will improve the safety of lean premixed prevaporized gas turbine power generation units.

Name and Address of Offeror:

Contract Id:

NAS 3 27681

Proposal Number:

01.03-0092

Project Title:

NONLINEAR REAL-TIME HIGH RELIABILITY ENGINE CONTROL

Technical Abstract:

Robust nonlinear control strategies will be developed for turbine engine real-time controls This effort will accommodates an integrated nonlinear control approach for the design of a high reliability control system based on advanced sensor processing, robust and nonlinear control, and neural fuzzy control integration. Several enabling advanced control technologies ranging from robust control, analytic gain scheduling, and feedback linearization approaches will be studied to demonstrate the effectiveness of the advanced control technology to the aeropropulsion control system design. Real-time implementation of high reliability engine control system will be conducted. The ultimate goal aims to broaden the engine operating envelop, and at the same time, to ensure stability, flying quality and safety, cost reduction, graceful degradation and reoptimization in the case of failures, malfunctions and damage.

Potential Commercial Applications:

The technique of integrated control and health monitoring for turbine engines directly benefits the militarty/civilian aviation and space areas. Such a system will lead to improved performance, enhanced safety, and increased reliability, availability, and durability. The developed hardware-in-the-loop real-time simulation system can be applied to industrial manufacturing and processing plants .

Name and Address of Offeror:

Contract Id:

NAS 3 27831

Proposal Number:

01.03-1100

Project Title:

CVD OF SEMI-INSULATING SILICON CARBIDE

Technical Abstract:

Interest is rapidly increasing in wide bandgap semiconductors for superior high frequency and high power electronics. Although silicon carbide (SiC) is the most advanced wide bandgap semiconductor from a materials and device processing point of view, extension to high frequency and high circuit density applications has been hindered by the lack of insulating or semi-insulating substrates. We propose to develop a thin film technology to grow semi-insulating SiC whose structure will be analogous to that of silicon on insulator (SOI). Instead of silicon dioxide, we will use vanadium-doped SiC, grown by chemical vapor deposition, as the insulator. Semi-insulating SiC epitaxial layers will enable the development of improved high frequency SiC devices, novel sensor passivation schemes for corrosive environments, and three dimensional integration of multiple devices. In Phase I we will investigate the CVD growth of vanadium-doped SiC films to achieve semi-insulating layers. In Phase II we will optimize the growth of semi-insulating SiC thin films and promote development of a SOI device technology through fabrication of prototype devices at ATMI and in collaboration with commercial and government laboratories.

Potential Commercial Applications:

The availability of semi-insulating SiC layers will enable not only the substrate isolation but a variety of novel device structures that will exploit SiC's broad range of exceptional physical and electronic properties. Applications include integration of high power, high frequency discrete devices and circuits and sensors and electronics designed for high temperature operation.

Name and Address of Offeror:

Contract Id:

NAS 3 27685

Proposal Number:

01.03-7909A

Project Title:

ACTIVE STABILITY CONTROL OF TURBINE ENGINE COMBUSTER AND COMPRESSOR

Technical Abstract:

The firm proposes to design, develop, and test an innovative combustion control actuator, which can control pattern factor and combustion instability. The firm also proposes to investigate the coupling between active compressor stall/surge control and active combustor stability/pattern factor control. The motivation for the proposed work is three-fold: 1) a need to control the combustor pattern factor to improve efficiency and prolong life; 2) an interest to control compressor surge and rotating stall (surge/stall) to enhance operability and performance; and 3) a general lack of attention to the coupling between compressor and combustor with regard to active stabilization of either component. The innovations of the proposed program are: 1) a wide-band fuel actuator for combustion control, 2) a methodology for pattern factor and stability controls, and 3) an integrated model of compressor and combustor for analyzing their coupling and for designing active control systems.

Potential Commercial Applications:

The benefits will be to: 1) reduce development time and cost for active control systems, 2) prolong turbine stator life through pattern factor control, 3) reduce operational costs of turbine engines through increased fuel economy by active surge/stall control, and 4) enhance operability through surge and combustor control (light-off limit). The proposed technologies has great potential for future commercial turbine engines as illustrated in a market analysis.

Name and Address of Offeror:

Contract Id:

NAS 1 20635

Proposal Number:

02.01-0818A

Project Title:

HYBRID LAMINAR FLOW CONTROL TECHNIQUE FOR ENGINE NACELLES

Technical Abstract:

We propose to develop a new hybrid laminar flow control (HLFC) technique that utilizes localized heating and wall shaping to maintain large regions of laminar flow on engine nacelles. The strong stabilizing effect of localized heating in two- dimensional and axisymmetric flows has been demonstrated in computations performed at High Technology Corporation and NASA Langley Research Center as well as in Russian and U.S. wind-tunnel experiments. In phase I, a technical and economical feasibility evaluation of using localized heating and wall shaping as a HLFC technique for compressible flow past an engine nacelle will be made. The technique is very attractive because it avoids the use of suction. Furthermore, heating the leading edge region can serve as a deicing tool.

Potential Commercial Applications:

The development of a hybrid laminar flow control (HLFC) technique that utilizes localized heating and wall shaping and its application to laminarize the flow past engine nacelles avoids the problem associated with using suction on this configuration. Maintaining large regions of laminar flow past engine nacelles amounts to about 2% reduction in drag on the whole aircraft which results in fuel-cost savings.

Name and Address of Offeror:

Contract Id:

NAS 2 14326

Proposal Number:

02.01-1960

Project Title:

OPTIMAL DESIGN OF LAMINAR FLOW WINGS

Technical Abstract:

We propose to develop an innovative product that will be used to design natural laminar flow (NLF) and hybrid laminar flow control (HLFC) airfoils. The objective is to delay the transition to turbulence for the purposes of drag reduction. A unique feature of this product is the application of a systematic procedure for the design of optimal three-dimensional wing geometry and control system configurations. The explicit identification of constraining factors that inhibit design improvement is also unique. Optimizing the stability characteristics for boundary layer instabilities using inverse methods is unprecedented. This development is achieved by an innovative combination of parabolised stability equation (PSE) methodology and recent developments in adjoint methods. Non-parallel flow and wall-curvature effects are incorporated. Bonus features include rapid computation, a receptivity analysis, and a complete analysis of the most effective control strategies. There is a demand for this product in laminar wing design for commercial and military vehicles and in particular for the high speed civil transport (HSCT). It will reduce design cycle times for laminar flow wings by providing trial designs more quickly and with accurate modelling. Costly wind tunnel testing will be reduced, as will very costly flight testing.

Potential Commercial Applications:

There is a universal demand for drag reduction on aerospace vehicles. This tool will find application with aircraft designers and manufacturers aiming at efficient wing, nacelle, and control surface design. Development of a high speed civil transport (HSCT) as a commercially viable vehicle requires laminar flow wings. This product will find application with the HSCT design project.

Name and Address of Offeror:

Contract Id:

NAS 1 20639

Proposal Number:

02.01-4367

Project Title:

A TOOL FOR ANALYSIS & OPTIMIZATION OF THE DYNAMICS OF HIGH LIFT CONTROL DEVICES

Technical Abstract:

We will develop a tool which will allow NASA Langley to study the dynamical effects of control (using vortex generators) on high lift airfoils. It is crucial to further our present understanding of these control devices and their influence on the dynamics of the turbulent boundary layer if we hope to improve performance. At the present time the effects of vortex generators (VG) are examined using LDV. This provides insight into the influence of these control devices on the structure of the mean flow, but the time dependent features are lost. The proposed tool will allow the reconstruction of the dynamics of the flow and the design of control schemes based on these models. The tool will advance flow-physics modeling and control of high lift flows.

Potential Commercial Applications:

The proposed tool will provide new capabilities for design of flow control devices using experimental data. The tool will be applicable to: Flows in high lift configurations, Leading edge vortex control for maneuverabilty, Combustion instabilities, and Flows in industrial applications. The tool will be a module in a widely used instrumentation package, assuring a ready commercial market.

Name and Address of Offeror:

Contract Id:

Proposal Number:

02.01-4700

Project Title:

A SOFTWARE ARCHITECTURE FOR EFFICIENT VISUALIZATION OF LARGE, UNSTEADY CFD RESULTS

Technical Abstract:

Modern Computational Fluid Dynamics (CFD) solutions routinely generate 3D grid and solution data sets that exceed many hundreds of megabytes. This problem is further exacerbated when the flow under study is transient (time-varying), in which case they may exceed 100 gigabytes in size. Visualization of these results can be very difficult and time consuming, due to limitations in (a) processing power, memory and graphics speeds of workstations and computers and (b) current software tools used for post-processing. The offeror proposes herein to create and utilize innovative software techniques to provide significant improvements in the speed and convenience of visualizing these large CFD data sets. The approach is based on the use of Data Pre-processing, a Database Access Model and Subfield Extraction to create an access methodology that makes tradeoffs between time and space, to optimize the usage of computing and visualization hardware. Such an access methodology is applicable to both structured and unstructured grid data and can be subsequently integrated into existing and future visualization environments so that the benefits may be widely utilized. High performance, convenient visualization of such data will allow NASA to increase the pace at which transient, complex aerodynamic, aerothermodynamic and aeroacoustic phenomena are understood. _

Potential Commercial Applications:

Development of software toolkits and workbenches for the visualization of large, transient field data such as CFD and structural analysis solutions and remote sensor data. _

Name and Address of Offeror:

Contract Id:

NAS 2 14327

Proposal Number:

02.01-6346

Project Title:

ROBUST PNS CODE FOR FLOWS ABOUT COMPLEX VEHICLES WITH EMBEDDED SUBSONIC REGIONS

Technical Abstract:

The goal of this research is to produce a new,robust,parabolized Navier-Stokes (PNS) code which will significantly reduce computer time required to calculate flows about complex vehicles with embedded subsonic regions. One of the major drawbacks of "current day" PNS codes is that they cannot be used to compute inviscid subsonic/separated regions which occur near canopies, wing-body junctures, etc. The current practice is to use a full Navier-Stokes(N-S) code in these regions and use a PNS code for the remainder. Because of the difficulties associated with interfacing two different codes, many investigators have resorted to using a N-S code for the entire flowfield. This is in spite of the fact that a PNS code is at least one order of magnitude faster than a N-S code. In the proposed research, innovative techniques will be developed to detect and measure the extent of embedded subsonic regions. In these "elliptic" regions, the PNS equations will be solved "globally" in an iterative fashion to duplicate the results obtained with a N-S code. During Phase I, a 2-D version of the code will be developed using NASA's UPS code as a framework. During Phase II, a fully three- dimensional code will be produced.

Potential Commercial Applications:

The new PNS code developed in this study will significantly reduce the computer time required to calculate flows about supersonic/hypersonic vehicles such as the proposed high-speed civil transport(HSCT). The code will accurately predict surface pressures, heat transfer rates, and aerodynamic coefficients for the entire vehicle. Designers throughout the aerospace industry will be able to utilize the efficiency of the new code to incorporate viscous effects in their trade-off studies of future flight vehicles.

Name and Address of Offeror:

Contract Id:

NAS 1 20619

Proposal Number:

02.02-0818A

Project Title:

LAMINAR-TURBULENT TRANSITION PREDICTION OF REACTING FLOWS IN HYPERSONIC VEHICLES APPLICATION

Technical Abstract:

Hypersonic boundary-layer stability of chemically reacting flows is of fundamental importance in the design of future space transportation vehicles. Capability to analyze and predict disturbance evolution in reacting flows is crucial for the improvement of aerothermodynamic performance of the vehicle. We propose to apply the state-of-the-art Parabolized Stability Equations (PSE) method to tackle the problem. The PSE method includes the global history and nonlinear effects and is particularly suited for handling the supersonic-mode disturbances that are relevant in hypersonic boundary layers. Real gas effects with equilibrium or finite- rate chemistry will be studied within the framework of both linear and nonlinear PSE based upon the absolute amplitude concept. The tool developed can then be used for future aerodynamic design of hypersonic vehicles.

Potential Commercial Applications:

Aerodynamic design of hypersonic vehicles is an important element in the aerospace industry. In particular, when designing the next-generation SSTO launch system which is crucial for the competitiveness of U.S. aerospace industry, engineers are often faced with the lack of proper tools to analyze and predict the aerothermodynamic performance related to laminar-turbulent transition at hypersonic speed. The computational tool developed in this study will greatly enhance the design capability and thus provide guidelines for future development. Furthermore, the stability code for reacting flows can also be used for component designs in the inlet and combustion chamber to study the effect of mixing.

Name and Address of Offeror:

Contract Id:

NAS 1 20620

Proposal Number:

02.02-1769

Project Title:

FLUID-STRUCTURE-THERMAL INTERACTION FOR HYPERSONIC VEHICLE ANALYSIS/DESIGN

Technical Abstract:

ResearchSouth, Inc. proposes to develop computer software for analysis / design of advanced hypersonic vehicles using methods for general fluid-structure-thermal interaction. Specifically, the airframe forebody thermoelastic effects on the bow shock, and the engine cowl thermoelastic effects on the engine inlet lip shock are addressed. Using the new software,the optimum airframe-engine stiffness can be computed which provides the appropriate compromise between reduced aero / propulsion performance and added weight. In the long term, a coupled analysis will allow a smart structures capability to be developed which provides increased propulsive performance over current designs by maximizing mass capture over a range of mach numbers. The Phase I effort will treat the fluid-structure-thermal interaction problem by a loosely coupled algorithm using the Computational Fluid Dynamics code, SAM3D, and the Computational Structural Dynamics code DYNA3D. We will formulate the algorithms, code the mesh interface routines and then perform an analysis of a 3D interaction for an advanced hypersonic vehicle test problem. Phase II will extend the software to a production package with adaptive meshing in 3D, interfaces to CAD data bases, and extensive verification and validation. This software will enable NASA to perform efficient and rapid design assessment of advanced hypersonic airbreathing concepts.

Potential Commercial Applications:

Important commercial problems that require fluid-structure-thermal interaction are:Deformation or inflation of fabrics such as parachutes, airbags, parasails, and tents: Aeroelasticity of flexible structures such as thin high-aspect ratio wings, missiles and drones: Shock/Structure interaction caused by blast waves on buildings from explosions inside and outside the building: Commercial airplane design, where the deformation of the structure due to aerodynamic and aerothermal loads is large: Weather related problems such as winds from hurricanes and tornadoes impacting cars, planes, buildings, and bridges : Sea-going craft design, such as ships and boats, to withstand high speed wave impacts. This software will represent a major improvement in the power and quality of analysis / design tools available to world industries.

Name and Address of Offeror:

Contract Id:

NAS 1 20618

Proposal Number:

02.02-6100

Project Title:

WATER VAPOR SENSOR FOR HYPERSONIC WIND TUNNELS

Technical Abstract:

Knowledge of the efficiency of combustion, which can be gained through absorption spectroscopy of water vapor, is crucial to the interpretation of test results in hypersonic test facilities at Langley Research Center. Our innovation is a tunable infrared laser source, based on the nonlinear frequency conversion of diode lasers, which can be tuned onto strong absorption lines of the hot water vapor produced in the combustion process. Using this laser source, rapid measurements of water vapor temperature and concentration, from which the combustion efficiency can be derived, will be made possible for the first time. Our innovation incorporates a new material (which we are developing at Deacon Research) as the nonlinear medium in the light source. In Phase I we will prove experimentally that our light source is capable of producing useful amounts of infrared radiation at the best infrared wavelengths for water vapor detection in hypersonic wind tunnels. During Phase II we will build an optimized device, measure its performance, develop strategies for tuning the device, and deliver a working prototype to Langley Research Center for use in quantitative measurements of combustion efficiency.

Potential Commercial Applications:

Our water vapor sensor will be used for process monitoring in the semiconductor and food industries.

Name and Address of Offeror:

Contract Id:

NAS 2 14328

Proposal Number:

02.03-3473

Project Title:

ACOUSTIC PROBES FOR SOUND MEASUREMENTS IN FLOW

Technical Abstract:

This innovation consists of developing in-flow microphone enclosures (acoustic probes) that will have negligible self-noise over a wide range of free-stream and operational conditions. The goals are to provide probes that are superior to any existing ones because they are (1) less sensitive to free-stream turbulence, (2) easy to manufacture, (3) effective over a wide range of Reynolds numbers and Mach numbers, and (4) insensitive to angle of attack and yaw. The acoustic probes will be useful for measuring acoustic signals and determining noise-source locations in wind tunnels, on aircraft, in engine inlets, and in air-conditioning ducts. The probe designs will rely on a knowledge of aeroacoustic principles that relate probe self noise to probe aerodynamic characteristics. The aerodynamic design of the probes will be carried out by modifying an existing computer program for solving the full Navier-Stokes equations to serve as an iterative design-tool.

Potential Commercial Applications:

There is a wide range of opportunities for pursuing the commercial development of the probes after the completion of Phase IIwhen there will be a well validated design. There are both government and non-government markets for quiet acoustic probes that are effective in high-speed turbulent flows. Manufacturers of acoustical testing and measuring equipment have, for a number of years, marketed special microphone "nose cones" and "slit probes" that decrease turbulence-induced noise in high- speed flows. However, the quiet microphone enclosures to be developed in Phases I and II of this project should provide much better performance than the commercially available probes. In addition, the simpler designs of the new probes should make them less costly to manufacture. With those advantages there is a good opportunity to break into the special market niche. In addition to a large civilian market, there is potentially a large market for the probes for use on military weapons systems, such as the Army BAT, if the probes turn out to be significantly better than existing ones.

Name and Address of Offeror:

Contract Id:

NAS 1 20622

Proposal Number:

02.04-2416

Project Title:

DYNAMIC TESTING AND HIGH FIDELITY MODELING OF NONLINEAR UNSTEADY AERODYNAMICS

Technical Abstract:

Traditional forced oscillation and rotary wind tunnel tests produce separate sets of aerodynamic data for oscillations about the body axis and rotations about the velocity vector, respectively. However, large-amplitude maneuvers such as departure and falling leaf often subject the aircraft to complex combined motions that significantly deviate from those seen in the typical dynamic wind tunnel tests. Due to the non-linear aerodynamic phenomenon, it is often difficult to accurately predict the aerodynamic characteristics with vector addition of rotary and forced oscillation data. An innovative approach of acquiring unsteady wind tunnel data by augmenting the current rotary balance rig at NASA Langley's 20 ft wind tunnel with forced oscillation capability is proposed. Such combined- motion rig capable of superpositioning body-axis oscillations over a steady velocity-axis rotation will be used to acquiring unsteady aerodynamic data under conditions closely matching what aircraft may encounter. Further, an improved approach will be formulated to utilize such combined-motion data for accurate simulation of aircraft motions. This effort will pioneer dynamic wind tunnel testing techniques for complex, unsteady motions as well as the utilization of such data in simulations to predict aircraft characteristics under dynamic conditions. _

Potential Commercial Applications:

The successful completion of the development envisioned will provide Bihrle Applied Research with the capability to expand its current data acquisition, analysis and simulation support services to include methods for collecting and implementing all the required dynamic terms needed to simulate large angle motions in a single test environment. This singularly unique test capability will be made available to all aviation concerns, and will be particularly useful to: civil markets in their attempts to improve the fidelity of their engineering and training simulations; and military manufacturers and agencies as they attempt to improve the maneuverability of their current configurations, and all parties as they attempt to increase the safety and productivity of their flight test programs. _

Name and Address of Offeror:

Contract Id:

NAS 2 14329

Proposal Number:

02.05-0819

Project Title:

HIGH-INERTIA ROTOR & HIGH-SPEED HIGH-ATTITUDE LONG-RANGE CRUISE GYROPLANE

Technical Abstract:

A next-generation high-speed rotorcraft is achieved by combining the best qualities of the autogyro for take-off and landing with the best qualities of the airplane. The resulting high-inertia rotor gyroplane with a low disk loading of less than 4 lb/sq ft, can make vertical jump take-offs to clear 50 feet and cruise for long ranges efficiently at high altitudes to 45,000 feet and high-speeds to 300 knots. The wing allows the rotor to be unloaded and slowed in high-speed cruise flight. The objective of this SBIR is to use theory and full scale test data to demonstrate that a gyroplane can be designed to have efficient high-speed high- altitude cruise greatly exceeding that available with helicopters, and equaling or exceeding the performance of airplanes. Theoretical predictions will be made for the CarterCopters Gyroplane which is now under construction. Ground test data will be obtained using CarterCopters high-inertia rotor which is now in ground tie-down testing. Phase I will establish the feasibility of the gyroplane and the readiness and merit for using CarterCopters Gyroplane for flight research in Phase II. The commercialization plan in the final report will show an early entry into the five place pressurized or non-pressurized market and how the gyroplane will help revive general aviation.

Potential Commercial Applications:

The decreasing number of available airfields in the United States is hurting the already declining general aviation business. The gyroplane has the potential for reviving general aviation by virtue of its ability to take-off and land where there are no airfields, and its high-speed, high-altitude, long- range economical cruise. These features are also advantages in other markets including law and drug enforcement, utility use, news coverage, corporate, agriculture, emergency medical service, and military in foreign markets as well as the U.S.

Name and Address of Offeror:

Contract Id:

NAS 2 14330

Proposal Number:

02.06-4434

Project Title:

INTERACTIVE FLOW MEARSUREMENT (IFM) SYSTEM FOR HIGH REYNOLDS NUMBER WIND TUNNEL TESTING

Technical Abstract:

An Interactive Flow Measurement (IFM) system will be developed for conventional and cryogenic high-Reynolds number wind-tunnel testing. The IFM system will be the first interactive flow diagnostics tool for on-line detection and display of boundary-layer transition and flow separation. Such a system will allow the test engineer to change flow conditions and instantaneously observe the effects of these changes on the boundary layer characteristics and aerodynamic design performance of the test model without interrupting the tunnel operation. IFM will provide designers the freedom to effortlessly fine tune model configurations and try "what-if" scenarios. The innovative, hands-off instrumentation approach has become possible thanks to recent advances made by Tao Systems in multi-channel constant voltage anemometers and quantitative flow diagnostic techniques for boundary-layer measurements using multi-element, surface hot-film sensors. IFM will make design work and CFD code validation efforts faster, will increase productivity by an order of magnitude with corresponding savings in tunnel-test- hours and cost. A proof-of-concept instrumentation and flow diagnostics system will be built in Phase I to detect and display the instantaneous spatial location of boundary-layer transition.

Potential Commercial Applications:

The proposed innovation meets the critical need for real-time detection of critical boundary-layer phenomena in high Reynolds number wind-tunnel testing. The proposed system will be a useful tool for CFD code validation testing, evaluation of new design configurations, as well as for routine wind-tunnel testing of complete aircraft and their components. The proposed interactive flow diagnostics tool has the potential to revolutionize active flow control technology.

Name and Address of Offeror:

Contract Id:

NAS 1 20624

Proposal Number:

02.06-4844A

Project Title:

HIGH BANDWIDTH PRESSURE SENSOR

Technical Abstract:

_ Physitron (with support from Vanderbilt University) proposes the development of an innovative microelectronic solid state pressure sensor using a doped diamond membrane as a piezoresistive sensor. This sensor development will take advantage of and commercialize intellectual property developed at Vanderbilt University. Diamond offers extremely high values of strength, stiffness, and hardness which makes feasible its use under extreme conditions not possible with other materials. Piezoresistive sensors have precedent in pressure measurement applications, most of them being derived from silicon-based technology. The material properties of diamond, six times stiffer and 500 times stronger than silicon, will provide considerably enhanced performance (more than 10X) in high pressure environments. Diamond sensors offer the potential to meet test requirements using the same instrumentation and sensor techniques which are presently in place. Phase I of the proposed work will design, build, and test a diamond-based pressure sensor with a bandwidth greater than 250 kHz. Testing/analysis during Phase I will determine the sensitivity and temperature tolerance. The Phase II program will then develop a full-scale pressure sensor which can be applied to field testing.

Potential Commercial Applications:

_ A diamond technology sensor using a diamond membrane will allow dynamic measurements at pressures, temperatures, and environmental conditions well beyond current technology. This can be applied not only to wind tunnel tests, but also, with slight modification, it could be used for solid state testing, high explosive testing, high energy physics research, and commercially for robotics control and biosensing.

Name and Address of Offeror:

Contract Id:

NAS 1 20623

Proposal Number:

02.06-7273

Project Title:

A NEW APPROACH TO HOT-WIRE/HOT-FILM CALIBRATION IN SUPERSONIC/HYPERSONIC FLOWS

Technical Abstract:

A new approach for calibration of hot-wires is proposed, which simplifies the calibration procedure and reduces the tunnel run-time by an order of magnitude. In supersonic and hypersonic flows it is generally accepted that the velocity and density sensitivities are equal. Thus the direct measurable quantities are only mass flow, m, and total temperature, To. Very few supersonic facilities have the capability of varying To over an adequate range. However, if overheat parameter aw is used to calibrate the hot-wire, then directly measurable quantity, voltage, will be a function of mass flow, overheat parameter and wire temperature i.e., , where aw contains the needed total temperature information. In this innovation, the feasibility of calibrating 2-wire probe using CTA with functional relationship in supersonic/hypersonic flows will be shown. The advantage of using aw instead of To is that it is not necessary to know the recovery factor, , and coefficients in wire resistance to temperature relationship, and , for a given probe during calibration. This technique will provide the most accurate calibration procedure for hot wire probes and it will be possible to obtain accurate temperature fluctuation information. Other conventional methods would require additional measurements to get the required information. _

Potential Commercial Applications:

The technique simplifies the calibration process of hot-wires, significantly reducing the run- time and test matrix required to conduct calibration tests. The proposed innovation has potential application in atmospheric wind tunnels, where there is no ability to obtain any temperature sensitivity information at present. _

Name and Address of Offeror:

Contract Id:

NAS 1 20621

Proposal Number:

02.07-1000

Project Title:

NUMERICAL STRUCTURAL-ACOUSTIC ANALYSIS METHODS FOR THE MID- FREQUENCY RANGE

Technical Abstract:

In the proposed work, the first numerical analysis technique that combines both deterministic and statistical methodologies will be developed. The eventual goal is that this technique can be used for the prediction of the sound field (e.g. noise) in aircraft cabins. This technique will be initially developed and evaluated for beams (Phase I) and then extended to other types of structural components (Phase II). Furthermore, the feasibility of implementing the technique in a commercially viable finite element analysis program will be investigated. The deterministic and statistical approaches will be used for the components of beam structures that are "short" and "long," respectively, compared to a wavelength. The technique for coupling these two approaches together where short and long members join will be developed and evaluated. Evaluation will be accomplished by numerically predicting the response of a three-beam system and comparing the numerical results with known analytical solutions. The technique will be implemented in an existing finite element program and its commercial feasibility will be determined by examining such things as ease of use and execution speed. The work will be performed over a period of six months by Automated Analysis Corporation personnel with assistance from personnel at Purdue University.

Potential Commercial Applications:

The numerical analysis technique developed in Phase I will form the basis for further development of an energy finite element program currently being developed by Automated Analysis Corporation for commercial distribution. This program will be useful to noise, vibration, and harshness (NVH) engineers in the aerospace, automotive, and defense industries.

Name and Address of Offeror:

Contract Id:

Proposal Number:

02.08-0886

Project Title:

EFFICIENT PARALLEL IMPLEMENTATION OF FLOW SOLVER INS3D-UP

Technical Abstract:

We will demonstrate feasibility of an efficient parallel implementation of the incompressible 3-dimensional Navier-Stokes solver INS3D-UP on distributed-memory MIMD computers. The work will include a relatively limited solver implementation, without turbulence model, complex boundary conditions, extensive I/O, or multi- ple-zone capabilities. Initially only point-relaxation will be provided. The target architecture is an IBM SP2 computer, but use of the Message Passing Interface standard will ensure portability to other platforms. Efficiency will be demonstrated by comparison with a single-processor version of the code, to be ported to the IBM SP2 as well. Both absolute performance and scalability will be examined. The resulting parallel code will be extended in Phase II to include a 1-equation turbulence model, realistic boundary conditions, I/O for restarts and visualization, Chimera multiple-zone capabilities, and line-relaxation. More advanced solution techniques like GMRES will also be investigated. INS3D-UP is one of the three NASA Ames production flow solvers (the others are CNSFV and OVERFLOW) for overset structured grids. Availability of an efficient parallel version will greatly enhance the usefulness of the code and increases the range of flow problems that can be solved cost-effectively.

Potential Commercial Applications:

The two main target areas in the aircraft industry for use of a parallel version of INS3D-UP are that of the Advanced Subsonic Transport (AST) and of propulsion systems. Within AST, incompressible 3-dimensional flow solvers are used, among others, for the simulation of high-lift and laminar-flow-control devices. Boeing and McDonnell-Douglas would be the main beneficiaries of the parallel program. In propulsion systems Pratt\&Whitney, Rocketdyne and Aerojet constitute the most important users of high-performance incompressible-flow codes. However, paral- lelization of INS3D-UP will increase the cost-effectiveness of the program to such an extent that it will also become attractive for more traditional types of engineering computations, such as construction (wind noise around buildings) and automotive engineering (wind drag of cars).

Name and Address of Offeror:

Contract Id:

NAS 2 14332

Proposal Number:

02.08-6576

Project Title:

AN INTERFACE PROTOCOL & GENERIC REMESHING ENVIRONMENT FOR DEFORMABLE & MOVING BODY SIMULATIONS USING ANY FLOW SOLVER SYSTEM

Technical Abstract:

The difficulty in performing CFD simulations for deformable or moving bodies is primarily due to the lack of available mechanisms to link data and functionality of flow solver, grid generation and CAD systems. The development of an interface protocol and generic remeshing environment is proposed to alleviate such difficulties and allow for any flow solver system to be used for deforming and moving body flow simulations. This approach eliminates the high costs associated with developing and maintaining individual remeshing capabilities for each CFD flow solver. The proposed interface protocol and remeshing environment facilitates access to the data and functionality of each module of the multi-disciplinary analysis system by providing bi-directional data associativity between modules. All information necessary during remeshing and needed for the analysis codes will be provided for in the interface protocol. The remeshing functionality and integrated CAD and grid generation database will be provided for by a commercial geometry modeling and grid generation software system, CFD-GEOM. The remeshing environment will be user programmable through a Visual Computing Environment which will be used to control the flow of information between the remeshing environment and analysis codes using the developed interface protocol across a networked workstation system.

Potential Commercial Applications:

The remeshing environment will be commercialized by CFDRC for use in performing multi-disciplinary analysis problems involving deforming or moving bodies or for adaptive remeshing purposes. Two modes of commercialization are feasible. The first is to incorporate CFDRC Computational Fluid Dynamics products into the remeshing environment and market as a package. The second is to market just the remeshing environment and allow customers to incorporate their analysis tools of choice into the environment.

Name and Address of Offeror:

Contract Id:

NAS 3 27835

Proposal Number:

03.01-0200

Project Title:

AN ECONOMICAL HYBRID ANTI-ICING SYSTEM

Technical Abstract:

An effective and efficient hybrid ice protection system is proposed to maintain a clean leading edge (LE) surface on roughness sensitive airfoils with minimum power requirements. The innovation utilizes the best features of two systems: thermal anti-icing and mechanical de-icing. A thermal system located at the leading edge will supply the energy required only to maintain the impinging supercooled water droplets in a liquid state (running-wet operation). The LE is kept free of ice contamination with a small fraction of the power that would be required for total evaporation. Eventually, the runback water will freeze downstream of the heated zone where any thermal system would be inefficient due to the low surface wetness factor. A Low Power De-Icing (LPDI) system will be used at those locations to remove the ice accumulation periodically due to frozen runback while maintaining its thickness below 0.1". This arrangement has never been explored to the best of our knowledge. The combined system shall be capable of operating at a low power budget to meet the limitations of Regional Airliners and modern aircraft with advanced wing designs while maintaining effective lifting capabilities during icing encounters.

Potential Commercial Applications:

The commercial potential application of the proposed SBIR project covers a broad range of aircraft categories and classes. This includes turboprop, turbofan, and turbojet powered aircraft of all categories. Regional Airliners will benefit most from the innovation due to their relatively limited power budget. This innovation is particularly beneficial to new and future generation of airfoils that are sensitive to LE roughness. The hybrid system could be applied to either or both of the wing and horizontal stabilizer surfaces. Core flow is becoming more scarce in turbofan engines of large transport category airplanes which could also benefit if this trend continues. The technology could also be applied to engine inlet nacelles except where FOD is a major concern; although, the thickness of ice shed is small and could be safely ingested by the engine without damage to its rotating components. It is also possible that an electro-thermal or hot air system which is already in place but whose operation results in unacceptable runback refreeze might be retrofitted and made to perform satisfactorily. This is accomplished by reducing the heating power just enough to prevent freezing at the LE, and adding a LPDI system downstream to shatter the frozen runback.

Name and Address of Offeror:

Contract Id:

NAS 3 27683

Proposal Number:

03.01-0533

Project Title:

A LOW POWER HYBRID ICE PROTECTION SYSTEM FOR AGATE CATEGORY AIRCRAFT

Technical Abstract:

While larger turbojet and turbofan powered aircraft are typically de-iced using bleed air, electrothermal or a combination of those two technologies, lower powered aircraft are typically de-iced using pneumatic de-icers. The primary reasons for using pneumatic de-icing systems are low weight and low power requirements. However pneumatic de-icers typically impose a performance penalty wich will become even more significant on future laminar flow and AGATE category aircraft operating at over 200 kts. Pneumatic de-icers were invented prior to world war II and while they are still being incorporated into new aircraft designs they have many design limitations. Based on recent breakthroughs in low power de-icing technologies at IDI, we propose to design and build a hybrid ice protection system based on Shape Memory Alloy and electro- magnetic de-icing actuators, which are suitable for incorporation into todays high performance laminar flow wings. This approach combines the recently proven Shape Memory Alloy de-icing system which efficiently de-bonds accreted ices, and an efficient electromagnetic system which sheds the debonded ice into the free stream air. A system of the type proposed would enable the efficient de-icing of large surface areas with a very low power requirement. Such a system could be needed to meet future requirements by the FAA for large droplet ice protection. The Phase I effort will emphasize the development of a functional demonstrator. Phase II will center around designing and building a full scale wing cuff system, then testing the wing cuff both in an icing wind tunnel and in flight.

Potential Commercial Applications:

The proposed de-icing system could potentially be offered as a retrofit system to all general aviation aircraft currently equipped with pneumatic de-icing boots. Additionally, resulting improvements in thin-layer ice removal provide substantial enhancements to safety when considering the sensitivity of modern airfoils to thin layers of ice. The market for such a device in lower powered turboprop and general aviation aircraft is substantial. IDI will be teaming with Cox & Company, Inc. and Bell Helicopter Textron for commercialization of the Low Power De-Icing technology during the Phase II and III program (see enclosed letters) .

Name and Address of Offeror:

Contract Id:

Proposal Number:

03.02-4180

Project Title:

PREDICTABLE REAL-TIME MULTIPROCESSING IN AIRBORNE SYSTEMS

Technical Abstract:

The purpose of the proposed research is to incorporate predictability into the performance of embedded aircraft data systems implemented by multiprocessor artchitectures. Several characteristics required in aircraft control and associated signal processing include repeated execution of the same algorithm, highly predictable and reliable performance, and the ability to meet hard deadlines for outputs. Dataflow computational models are used to create a real-time multiprocessing design methodology which can achieve performace bounds given sufficient processors. A key approach to achieving predictable performace is to control injection rate of input data and to modify the dataflow graph precedence so that a processor is always available to execute an enabled graph node. In the proposed research effort, investigations will be carried out to achieve predictability under variable task execution times and a scheduling software tool will be developed. Computational times of tasks in aircraft data systems can vary due to cache miss in the processor, data dependent processing, or sharing of common resources such as memory. Predictability of aircraft control algorithms will be absolutely essential for safety and efficiency.

Potential Commercial Applications:

The schedulting software tool developed will be directly impacting the aircraft industry's cockpit control systems. Commercially available digital signal processing software COMDISCO can license the software from UniSoft and incorporate into their system. Aircraft data system manufacturers like Westinghouse, Loral, Harris and Allied Signal will be able to use and incorporate this tool into their systems. These systems will add value to commercial aircraft companies like Boeing, McDonnel Douglas and Lockheed and aid the pilot in making the right decision.

Name and Address of Offeror:

Contract Id:

NAS 1 20617

Proposal Number:

03.03-0818A

Project Title:

A PROGRAMMING ENVIRONMENT FOR THE DEVELOPMENT OF LARGE SCIENTIFIC SYSTEMS ON A DISTRIBUTED COMPUTING NETWORK

Technical Abstract:

Large, scientific systems composed of several application codes coupled together to execute on a distributed computer network can be complex to develop. Multi-disciplinary Design Optimization (MDO) and Systems Analysis (SA) are examples of such systems. The proposed programming environment will be designed to facilitate the building of such systems. The environment will consist of the following: a graphical and template-based programming language; an integrated debugging and code verification strategy; and a modular design with interface protocols. The high-level language is proposed to reduce the programming effort. Because of the resulting complex execution systems, the environment will provide assistance in verifying the correctness of a computation. A modular design based on appropriate standards is necessary to adapt the environment to ever improving software tools. The environment will be capable of generating execution systems with the following features: a GUI-based control and monitoring system; execution on heterogeneous networks including workstations, vector and parallel supercomputers; a distributed database management strategy; and configurable to include tools for data display and analysis.

Potential Commercial Applications:

A current trend in computing is the increased use of heterogeneous computer environments especially for large tasks. Also, parallel computing is considered to offer the best potential for performance improvements today. Both require a greater programming effort than has been historically needed. An environment which efficiently brings these programming techniques to a wider group of programmers will be very beneficial. The proposed programming environment will reduce the programming overhead and thus expand the high performance computing arena.

Name and Address of Offeror:

Contract Id:

NAS 1 20616

Proposal Number:

03.03-6471

Project Title:

MATERIAL OPTIMIZATION FOR USE WITH IN-SITU PROCESSING TECHNIQUE

Technical Abstract:

Automated Dynamics Corporation (ADC) proposes to implement a systems analysis approach to identify the relationship between key aerospace grade prepreg characterisitics and the effectiveness of composite in-situ consolidation processing. The manufacture of high perfromance composite materials systems necessitates optimization of numerous processing parameters, many of which are mutually interactive. In addition to these initial material fabrication process parameters, there are also a number of final material characteristics which affect part processing with these high perfromance materials, especially when using advanced fabrication techniques such as in-situ tape placement. Optimization of material properties has long been the focus of prepreg manufacturers. The significance of this work will concentrate on optimization of prepreg characterisitics for favorable material properties of manufactured components as well as attractive throughput rates with this in-situ processing technique. By optimizing the material for the overall manufacturing system, we hope to be able to offer the significant improvements in both final part quality and material processing rate. With these improvements will come associated cost savings over existing material / manufacturing systems.

Potential Commercial Applications:

Piping, oil field downhole applications, recreational uses, rolls and shafts, paper machine doctor blades, plastic bearings and commercial airplane structure.

Name and Address of Offeror:

Contract Id:

NAS 2 14333

Proposal Number:

03.04-7569

Project Title:

ADVANCED ALGORITMS FOR AIR-TRAFFIC CONFLICT RESOLUTION

Technical Abstract:

Projected growth in air traffic over the next decade can result in increased instances of trajectory conflicts in the nations airspace. Due to the potential for involvement of more than two aircraft in a conflict scenario, air traffic controllers will require advanced automation tools to effectively resolve the conflicts. This proposal advances the development of conflict resolution algorithms that can systematically generate advisories for multiple aircraft conflicts. Proposed methods are based on optimal control and differential game theories. The conflict resolution task is formulated as a multi-objective trajectory optimization problem, and solutions are obtained using singular perturbations theory. Phase I research will demonstrate the feasibility of the proposed method in a simulation of a multi-aircraft air traffic control environment. Phase II research will produce a software package that can be integrated with the air traffic management software system currently under development at NASA.

Potential Commercial Applications:

Conflict resolution methods are an integral part of every air traffic management system. The algorithms and software developed under the proposed research will find widespread applications in air traffic management systems in US and around the world. The conflict resolution algorithms also have applications in the intelligent vehicle/highway systems (IVHS) program.

Name and Address of Offeror:

Contract Id:

NAS 2 14334

Proposal Number:

03.04-9166

Project Title:

AIRPORT VISUALIZATION AND OPERATIONS SYSTEM TM (AVOS TM)

Technical Abstract:

The "Airport Visualization and Operations SystemTM" (AVOSTM) concept is an application of virtual reality display to aircraft operations in the vicinity and on the surface of airports under poor and zero visibility conditions. Aircraft identification, position and attitude are down-linked to the AVOSTM control center in the airport tower. A 3-D view of the airport, all aircraft and surface vehicles, exactly as would be seen by the pilot in good visibility, is computer generated in the AVOSTM control center and up-linked to the aircraft. The up-linked video signal is projected onto a pilot "Personal Display ViewerTM" (PDVTM), similar to helmet mounted displays. The pilot would use this virtual reality display to monitor the landing, guide the aircraft to the gate and back to the runway for take-off, with no other aids. The system concept supports operations of airport surface vehicles required to service aircraft. The primary innovations are the display and distributed airborne/ground system concept using data-links that could provide this capability at an affordable price. It is an important new pilot display system that can increase airport capacity in reduced and zero visibility conditions in a more natural and safer manner than map-type displays that are currently under development.

Potential Commercial Applications:

The applications are for commercial and other aircraft that require flight operations in poor and zero airport visibility conditions. Potential commercial products include: the AVOSTM airborne system, including interfaces to aircraft systems and datalinks; the Personal Display ViewerTM; the AVOSTM ground control center, including the interfaces to a D-GPS-based ground vehicle positioning system, the airport surface traffic surveillance system and data/video up-links; and, the overall system integration at each airport. It is premature to decide on commercialization strategies for the various products, until feasibility is established. Paradigm 2000 plans to apply for patents on the AVOSTM system and elements mentioned above, if feasibility is established with the SBIR effort, to obtain a competitive advantage. Strategic alliances for commercialization will be negotiated during Phase II, when Paradigm 2000 is in a stronger negotiating position.

Name and Address of Offeror:

Contract Id:

NAS 1 20634

Proposal Number:

03.05-0778

Project Title:

MATRIX ADDRESSABLE VIBRATION SENSING ARRAY

Technical Abstract:

This proposal presents a new and novel approach to fabricating a sensor array. The direct application will be vibration sensing with an array of sensors but the basic approach is compatible with virtually any physical property that can be converted to a stress, such as pressure, strain, etc. Virtually all existing transducers, whether measuring pressure, stress, acceleration, etc., are incompatible with array addressing and arrays are fabricated by individually wiring many transducers. This becomes unwieldy at high resolution and large areas. The proposed approach fabricates a vibration sensor using a magnetoelectric element for both vibration sensing and as the matrix forming element. The vibration is sensed from the acceleration on a cantilevered beam accelerometer formed from a piezoelectric magnetostrictive film. The resulting device can be matrix addressed to drastically reduce the number of leads and produce low cost sensor suitable for large area arrays. _

Potential Commercial Applications:

A new and novel method of measuring vibration using a matrix addressed array of sensors is proposed. It can be used to measure vibration, acceleration along with other physical properties _

Name and Address of Offeror:

Contract Id:

NAS 1 20633

Proposal Number:

03.05-3268

Project Title:

LOW-COST DIODE-LASER SENSOR FOR VELOCITY AND VIBRATION MEASUREMENTS

Technical Abstract:

We have experimentally demonstrated that remote optical radial velocity measurements can be made using off-the-shelf equipment costing about $300 in single quantity, far below the cost of typical LDVs, coherent lidar, and optical vibrometer systems. The sensor consists of a diode, a focusing lens, and a photo-diode. It is completely self-aligning and is easy to modify for multi-point sensing/imaging applications. With a small (6 mm) collection aperture, we have demonstrated high-accuracy measurements to ranges of several meters without the use of cooperative hard-targets, such as retro- reflectors. We propose to investigate these sensors with a several-fold aim. A good analytical model describing the sensor operation is essential in order to optimize performance. The analytical modeling will be supported by experiments to demonstrate significantly improved range and SNR performance. Successful demonstrations are expected to result in low-cost units with potential performance improvements of 10-20 dB. Such optimized sensors, when coupled with extreme compactness and array formats, makes them well suited for a number of NASA applications, including multi-point vibration/mode surveys, flow mapping, and turbulence characterization. _

Potential Commercial Applications:

Compact, rugged, reliable, and low cost velocity sensors are expected to find uses in a large number of areas, including flow measurements/visualization, traffic monitoring, collision avoidance, flow measurements, law enforcement, and vibration sensing. At low enough production cost consumer products can benefit as well. _

Name and Address of Offeror:

Contract Id:

NAS 4 50075

Proposal Number:

03.05-4434

Project Title:

AUTOMATED HOT-WIRE ANEMOMETER INSTRUMENTATION SYSTEM FOR IN- FLIGHT VELOCITY FLOW FIELD MEASUREMENTS

Technical Abstract:

An automated hot-wire anemometer instrumentation system will be developed for in-flight measurements of three-dimensional boundary-layer velocity flowfields on aircraft wing surfaces. The proposed system automatically adjusts to changes in flight environment, be relatively immune to Radio Frequency Interference, with capability to measure mean and fluctuating components and resolving mass-flow and temperature components as well. The proposed system will be particularly suitable for conducting high-speed flight tests to establish bench mark data for CFD code validation. Such an instrument will be invaluable for flow diagnostics for transition detection, investigation of boundary-layer instability, flow separation, shock, and other critical aerodynamic flow characteristics.

Potential Commercial Applications:

A routine flight test instrument will be available for validating CFD codes. Such an instrument will enhance understanding the flowfields for design of better performance aircraft which is continuously sought which in turn will produce safer and economical flight vehicles. The instrument can also be used for atmospheric turbulence measurements in addition to highly productive ground based tests like in wind tunnels as well.

Name and Address of Offeror:

Contract Id:

NAS 4 50073

Proposal Number:

03.05-7273

Project Title:

PIEZOELECTRIC FILM SENSOR ARRAYS FOR WIND-TUNNEL & FLIGHT MEASUREMENTS

Technical Abstract:

The proposed innovation is to develop piezoelectric film sensor arrays to simultaneously measure fluctuating pressure, separation, presence of shock wave, buffeting, boundary layer disturbance, and vibration of wing and/or fuselage surface. A thin piezoelectric film can be directly mounted on wing/fuselage surface on which any type and size sensor array configuration can be formed. A miniature charge amplifier, which will be located close to the sensing area to obtain maximum signal-to-noise ratio, will be developed. The piezoelectric foil sensors register, both vibration and pressure fluctuation, which will be separated in real time using a new signal processing technique. The piezoelectric film sensors are non-intrusive and many sensors can be spaced very closely for multi-point measurements. They offer distinct size and weight advantage over conventional sensors/transducers, are very inexpensive and require no power. Control of structure-borne noise is an important problem in aerospace and marine applications. The piezoelectric foil sensors will make an active vibration control systems in future airplane possible. The proposed innovation will develop piezoelectric film sensor arrays and associated instrumentation in wind tunnel tests to measure fluctuating pressure, transition, flow separation, boundary layer disturbances and vibrations on wing surfaces. _

Potential Commercial Applications:

The proposed innovation will be first to provide simultaneous measurements of flow, structural and noise characteristics in real time. Diagnostic tools could be developed based on this innovation to determine, potentially hazardous influence of environmental factors like gusts, wind shear, shock, which result in a decrease in the lift to drag ratio due to flow separation. It will also be useful as a diagnostic tool during the design and testing phase of an aircraft, and will cut down the development costs. _

Name and Address of Offeror:

Contract Id:

NAS 1 20638

Proposal Number:

03.05-7772

Project Title:

SINGLE POINT 3-AXIS STRAIN AND TEMPERATURE FIBER OPTIC GRATING SENSOR

Technical Abstract:

Dual overlaid fiber optic gratings are written onto polarization preserving optical fiber to form four effective fiber gratings. A broadband light source is used to illuminate the resulting 3 axis strain plus temperature fiber grating sensor resulting in four wavelength outputs. The result of demodulation using a tunable spectral filter such as the tunable etalon proposed in this project is four equations involving the four output wavelengths and the unknowns corresponding to each axis of strain and temperature. The equations can be solved to determine all three axes of strain and temperature at a single point.

Potential Commercial Applications:

Health monitoring systems for aircraft and spacecraft to perform maintenance and flight readiness checks, civil structures including buildings, bridges and highways, manufacturing process control and measurements of residual stress induced during manufacture, and new markets where a cost effective, environmentally rugged, EMI immune 3 axis strain plus temperature sensor does not exist.

Name and Address of Offeror:

Contract Id:

NAS 2 14335

Proposal Number:

03.06-9447

Project Title:

AN ACTIVE CONTROL STICK WITH PILOT FORCE CUEING FOR AGILE HELICOPTERS

Technical Abstract:

The proposed SBIR program is to develop an active control stick with specific applications relevant to NASA flight simulator studies and research helicopter programs. The system proposed is an innovative new helicopter control stick system which can actively cue the pilot with information concerning the onset of flight envelope limitations by changing the feel characteristics on command from the flight control computer. The new stick will be moved by electric motors controlled by a computer system which will calculate the stick movement based upon the force applied by the pilot, a programmable force-feel characteristic and commands from the flight control computer. The system will be designed as a side-stick and will be suitable for fitting in flight simulator systems and test aircraft. The stick will be designed from the outset to be usable left or right handed. Phase I will be completed within six months, with six man months of effort. Anticipated results are a demonstrator unit and specification for NASA applications and subsequent test and evaluation. It is relevant to subtopic 03.06 because it introduces the function of a status monitoring system that informs and advises the crew within an existing device. Innovative active landing gear concepts are to be evaluated, with objectives of ride improvement and structural load reduction for very large subsonic and supersonic transport aircraft. Multi-disciplinary design integration procedures will be developed and applied to the high-order complex assembly of structural, aerodynamic, flight control system and landing gear system models for design optimization of the active landing gear control systems. The modeling and design integration analysis will be carried out using a software package developed by Stirling Dynamics for the evaluation of landing gear systems. The software package will be extended to provide a unique capability for integrated analysis of active landing gear systems including the interaction with the aircraft structural dynamics. The project addresses the subtopic requirements by the analysis of complex physical models and provision of an efficient software tool for facilitating the building of complex multi- disciplinary system models. Phase I will be completed within six months, with eight man-months of effort. Anticipated results are improved understanding of active landing gear systems and enhanced analysis procedures, with benefits to NASA in future aircraft programs, particularly HSCT, where the long slender fuselage can produce large amplitude ground response at the pilot's position.

Potential Commercial Applications:

Commercial applications include not only the NASA helicopter and simulator applications to be addressed by the proposed SBIR project but also civil aircraft, ASTOVL thrust vector control, fixed wing carefree handling systems and non-aerospace specialized control systems. Initial applications will be non-safety-critical with flightworthy systems being developed as interest is simulated by the research and evaluation systems.

Name and Address of Offeror:

Contract Id:

NAS 4 50071

Proposal Number:

03.07-3800

Project Title:

ON-BOARD REAL-TIME DATA ACQUISITION AND ANALYSIS SYSTEM

Technical Abstract:

We propose an advanced portable data acquisition and analysis Flyscan system for on-board flight testing and other demanding telemetry-based field applications. The Flyscan system integrates on-board real-time data acquisition with real-time analysis of analog and digital telemetry data. It will greatly enhance the productivity and safety of researchers by providing processed test information directly to the personnel closest to the systems under test. Existing computing and instrumentation systems typically address the acquisition and analysis of data separately; test data is first collected then later analyzed as a separate data reduction task. But many flight test and other applications demand combined real-time data acquisition and analysis, such as those involving great risk and expense, or human-in-the-loop data evaluation and verification. Creare currently has a foundation technology in its Scanalyzer system which integrates real-time data acquisition and analysis tasks in a benchtop workstation configuration. By adapting this state-of-the-art software to new-generation portable computing hardware, and developing a full set of acquisition and analysis features within the constraints imposed by this hardware, we will provide an innovative solution to this pressing need for on-board test data assimilation.

Potential Commercial Applications:

In addition to flight testing, the Flyscan system will have commercial applications in vehicle testing, factory floor equipment diagnostics, as a shared portable laboratory tool, at-home medical health monitoring, and field test and equipment diagnostics. The Flyscan system will also be competitive with existing fixed non-portable data acquisition systems.

Name and Address of Offeror:

Contract Id:

NAS 4 50074

Proposal Number:

03.07-7212

Project Title:

A FLIGHT TEST PLANNER FOR THE VFRC SYSTEM

Technical Abstract:

The innovative concept proposed herein involves the development of a flight test planning software package for the NASA Virtual Flight Research Center (VFRC) program. The VFRC flight test planning package we propose to develop will be a separate package from TEST_PLAN, our commercial flight test planning software program for computer workstations. As the only flight test planning package commercially available, TEST_PLAN meets most production and experimental flight test planning requirements: it does not meet VFRC and NASA unique requirements concerning data access, remote operations, platform independence, sub-orbital vehicle testing and research oriented testing. The proposed VFRC-Planner will support these VFRC and NASA unique requirements. Our concept is innovative because coupled with the VFRC system, it allows off-site as well as on-site (but remotely located), flight test planning and data access, across a wide area network using a variety of workstations and personal computers. Thus, a wide variety of customers including engineers from government agencies, US industry participants and academic institutions can plan and participate in the execution of flight tests almost as if they were in mission control.

Potential Commercial Applications:

As the near-real-time flight test planning and documentation tool in the VFRC, the VFRC- Planner will be commercially marketable to all users of the VFRC. Users who have a VFRC_Planner license will be able to plan flight tests in detail at their own location, monitor flight tests in progress and replan as necesssary using all of the tools available within the program. Users will be able to access flight and/or simulation data through the VFRC-Planner's flight card facility and generate flight trajectories for planning purposes using the VFRC-Planner's performance simulation facility.

Name and Address of Offeror:

Contract Id:

NAS 4 50072

Proposal Number:

03.08-3800

Project Title:

ULTRA-LIGHTWEIGHT, LOW-DRAG HEAT EXCHANGER FOR HIGH-ALTITUDE AIRCRAFT

Technical Abstract:

We propose to develop an extremely compact and lightweight, low drag heat exchanger for engine cooling on high altitude aircraft. The heat exchanger uses an innovative flow configuration to make highly efficient use of heat transfer area and reduce air flow requirements. Frontal area is reduced by a factor of three compared to conventional heat exchangers. Because of the flow arrangement, low-density nonmetallic materials can be used to fabricate the heat exchanger, resulting in a factor of five reduction in weight compared to aluminum tube-fin radiators. In Phase I we show the feasibility of the innovative heat exchanger by (1) demonstrating the key fabrication processes required to construct the heat exchanger, and (2) designing a liquid-to-air heat exchanger to meet the specifications of a particular high-altitude aircraft. In Phase II, we will build and test full-scale prototype heat exchangers on the ground and in aircraft.

Potential Commercial Applications:

The heat exchanger is lightweight, compact, and extremely resistant to corrosion. The heat exchanger is ideal for small unmanned aircraft, including drones for military and civilian surveillance applications. The heat exchanger is also ideal for heat rejection from oil and engine coolant in general aviation aircraft. The compact, lightweight radiator will also be applied to vehicular applications, such as radiators for engines in automobiles, trucks, and marine vessels. The heat exchanger can also be used for electronics enclosures and heat rejection for air conditioning systems.

Name and Address of Offeror:

Contract Id:

NAS 4 50068

Proposal Number:

03.08-8457

Project Title:

EXHAUST GAS PARTICULATE INSTRUMENT FOR FACULTATIVE INTERNAL COMBUSTION ENGINE CONTROL

Technical Abstract:

An exploratory investigation is proposed which seeks to establish the technical feasibility of a novel instrumentation approach for the continuous measurement of particle density in the exhaust of a compression ignition engine. The proposed instrument is required to satisfy the critical sensing function of a certain full-authority fuel injection and engine control system now under development for very-high-altitude, subsonic, unmanned aircraft propulsion. The proposed instrument is comprised of a single, self-contained, rugged unit that can be mounted remotely from the engine to provide a robust indication of the concentration of exhaust particulate matter. Such a system facilitates a facultative compression ignition engine that is capable of effectively utilizing highly variable amounts of air with a combination of two cylinder-injected fuels under computer control, one fuel of high energy content, the other highly oxygenated. By such means, fuel consumption can be minimized during the protracted climb phase anticipated for very high altitude vehicles thereby allowing greater cruise / loiter fuel reserves. The proposed investigation combines analytical studies with breadboard instrument testing to establish feasibility for the intended application. Correlations with established photopic and particulate methods will also be undertaken.

Potential Commercial Applications:

A highly portable and easily operated "smokemeter" has wide-spread commercial potential. All diesel engines are prone to emit excessive particulate matter under prominent operating conditions. Virtually all such engines now manufactured are sold and operated subject to compliance with stringent state and federal particulate emission criteria. However, the emission regulations are not yet fully effective because there are no completely satisfactorily and valid particulate instruments available for field use. The proposed instrumentation technology offers such prospects.

Name and Address of Offeror:

Contract Id:

NAS 4 50069

Proposal Number:

03.09-1992A

Project Title:

ROTATING SHAFT STABILITY ANALYSIS MODEL (SHASAM)

Technical Abstract:

ORBITEC proposes to develop a new tool for condition monitoring and design of rotating machinery. The ultimate objective of this research is to develop a PC and microprocessor based expert system for determining and evaluating the dynamic and stability characteristics of elastic shaft/disc/bearing systems. The approach is based on previous research using Liapunov's direct method for calculating critical speeds and employing the variation of parameters technique for vibrational analysis. This research has shown repeatedly that continuum models of elastic shafts and discs can be accurately modeled by very assumed mode terms, greatly reducing the computational burden for obtaining key information. The proposed Phase I project will develop, test, and evaluate a PC based program for a two bearing elastic shaft/disc system supported on anisotropic elastic bearings with cross-coupled stiffness and sampling included as a preliminary model.

Potential Commercial Applications:

The Rotating Shaft Stability Analysis Model (SHASAM) provides a powerful new tool to quickly analyze shaft stability for monitoring and/or design purposes. Potential applications include aircraft and helicopter engines, rocket engines, and power generation machinery. ORBITEC plans to market SHASAM as a software package and analysis service, and to produce and sell a microprocessor based rotating machinery device.

Name and Address of Offeror:

Contract Id:

NAS 4 50079

Proposal Number:

03.10-6821

Project Title:

NEW HIGH-ORDER ELEMENTS FOR EFFICIENT MULTIDISCIPLINARY ANALYSIS

Technical Abstract:

A new family of plate/shell finite elements has been conceived. Versions with 3, 4, 6, 8, 9 and 10 nodes are possible. More efficient and more accurate calculation is expected for deflection, stress, thermal stress, buckling, and for vibration which is influenced by all of these. Interlaminar shear stress calculation should be especially improved. Shear deformation is included, which is essential for analysis of composite and sandwich structures. All constant strain states are represented exactly in the new elements. In contrast, the shear-deformable plate/shell elements in current commercial use have spurious shear energy in (what should be) pure bending, and frequently require arbitrary reduction of shear moduli or under-integration to avoid "locking," which can in turn cause zero-energy deformation modes or "mechanisms." The LU71 element in the STARS program used at DFRF is equivalent to the 3-node version of the new family. Safety-critical calculations such as predicting flutter in flight tests requires a higher standard of reliability than most applications. The new family of elements can provide an independent verification based on a different theoretical formulation as well as improve efficiency and accuracy.

Potential Commercial Applications:

Incorporation in the STARS code used at DFRF may be the first application. It is expected that these superior-quality finite elements will be incorporated in a package of isoparametric elements and licensed for use in one or several of the major American commercial finite element programs. Finite element analysis is a multi-billion- dollar-per-year worldwide industry.

Name and Address of Offeror:

Contract Id:

NAS 5 33242

Proposal Number:

03.11-3330

Project Title:

RAPTOR-RAPID APPLICATION PRODUCTION TOOL USING OBJECT RELATIONSHIPS

Technical Abstract:

The RAPTOR tool will provide an effective mechanism for building correct software by: a) simplifying the process of defining relationships between application objects, b) providing automated mechanisms for test scenario generation and regression testing, and c) reducing the risks of system modifications that inadvertently violate earlier design decisions. RAPTOR is built on top of an underlying spreadsheet engine that associates object attributes with cells in a spreadsheet. RAPTORs attribute-based assertions and Test Generator facilitate the automation of program verification and regression testing, and its living memory feature provides a mechanism for recording object-specific design decisions and rationale for automatic notification should a future developer attempt to override the design decision. Its Relationship Builder provides an intuitive, interactive approach for defining complex object-to-object relationships. The proposed Phase I effort focuses on developing effective approaches for RAPTOR assertions, living memory, automatic test script generation, triggering of the spreadsheet engine, the addition of new RAPTOR objects, and relationship definitions at the object class-level as well as the object instance level. A related Phase II effort would complete the features for a full commercial product, focusing particularly on RAPTOR as an integrated adjunct to other commercial GUI builders.

Potential Commercial Applications:

The RAPTOR tool will provide software development organizations with a powerful adjunct to existing need software development tools, allowing much more of the development of applications to be done without the for direct programming, and by providing efficient, effective, and integrated tools for automatic verification and regression testing, thus contributing significantly to the ability to develop correct safety-critical and mission- critical applications. RAPTOR will be easily integrated with commercial GUI builders, adding substantial new capability for a large number of installed users of these tools.

Name and Address of Offeror:

Contract Id:

NAS 1 20625

Proposal Number:

03.11-8018

Project Title:

SAFETY-CRITICAL SOFTWARE REQUIREMENTS ENGINEERING ENVIRONMENT

Technical Abstract:

Our company proposes to research and develop the first engineering environment specifically supporting software safety analysis at the requirements stage. For Phase I we plan to (1) improve and extend RSML, a successful graphical requirements language, (2) research and prototype a graphical simulator for RSML, (3) research and prototype an extended completeness and consistency analysis based on the improved RSML, (4) research and prototype a commercially-viable version of a new hazard analysis method called deviation analysis, and (5) evaluate the research results and prototype for feasibility. These innovations will provide the software and systems engineers with ``formal mathematical methods for specification, design, and analysis of digital systems.'' Many of the largest NASA programs contain safety-critical software, so the Administration should especially benefit from our proposed innovations.

Potential Commercial Applications:

The ideas presented in this proposal are part of our long-term goal to develop a flexible, extensible, and customizable systems development environment in the form of commercial software. We intend to develop and market our software and services for a wide range of companies that write safety-critical software.

Name and Address of Offeror:

Contract Id:

NAS 8 40675

Proposal Number:

04.01-1354

Project Title:

RAPID DENSIFICATION OF CERAMIC MATRIX COMPOSITES

Technical Abstract:

Low-cost, reliable densification of ceramic matrix composites is of critical importance to NASA and many commercial applications. Present densification technologies are slow, need very high temperatures and use densification aids which leave reliability-crippling impurities after densification. The proposed innovation can enable densification at rates that are orders of magnitude faster and at temperatures that are more than 500 C lower the best available technology today; furthermore, the innovation can lead to a densification technology that works without expensive and impurity inducing densification aids. In cursory investigations, NRC has obtained encouraging results supporting the proposed innovation. The Phase I seeks to systematically establish the proof-of-concept; Phase II will optimize, scale-up and produce prototype components for NASA and lead commercial customers; Phase III will commercialize the technology.

Potential Commercial Applications:

Potential applications of low temperature, rapid densification technology extends to many industries. The enormous savings in energy consumed to form useful ceramic components with associated reduction in pollutant (NOx) formation in kilns is of interest not only to ceramic- matrix composite manufacturers but also for cleaner environment.

Name and Address of Offeror:

Contract Id:

NAS 8 40686

Proposal Number:

04.01-6100

Project Title:

PROPOSAL FOR AN INK-JET RAPID PROTOTYPING MACHINE

Technical Abstract:

Sander's Design International is proposing an ink-jet rapid prototyping machine (IRPM) that can shorten the development time for many of NASA's new projects and programs. The proposed IRPM provides NASA with the capability to make models and tool patterns accurately, with a wider variety of materials than is currently available with any other rapid prototyping machine. The proposed IRPM will be accurate enough to make master tool patterns by transforming 3-D CAD files into models with an accuracy of 0.001" per inch or better. The major tasks to be accomplished under Phase I of the proposed program will be to design a fine and bulk jetting system for a thermal ink-jet printing mechanism to provide both accuracy and speed when building prototype models. The fine jetting system provides for an extremely good surface finish, while the bulk jetting system speeds up the building of models by an order of magnitude. The bulk jetting system allows the jetting of a wider range of materials than is currently available from other rapid prototyping machines. To provide high accuracy patterns, a servomechanism with continuous position feedback from the jet-heads will be designed.

Potential Commercial Applications:

The potential applications for the proposed Ink-jet Rapid Prototyping Machine include the following industries: automotive manufacturers, rapid prototyping service bureaus, electronics/electrical manufacturers, appliances/toys/consumer products manufacturers, industrial machine manufacturers, aerospace companies, and medical equipment manufacturers. All of these industries can achieve faster speed to market at a competitively lower cost with the proposed IRPM.

Name and Address of Offeror:

Contract Id:

NAS 8 40658

Proposal Number:

04.01-9351

Project Title:

RAPID, E-BEAM CURABLE, FILAMENT WOUND, OXYGEN RESISTANT POLYMERIC COMPOSITES FOR STRESS FREE ROCKET MOTOR CASES, CRYOGENIC STORAGE & SPACECRAFT PRESSURE VESSELS

Technical Abstract:

The objective of the proposed program is to demonstrate the superiority of an innovative, cost- effective, rapid E-Beam Cured, filament wound rocket motor, cryogenic tank or spacecraft structure processing technique that minimizes molded in stresses (typical in thermally cured composites) therefore providing more optimal specific strength and stiffness characteristics as well as oxygen resistance, for polymeric composite structures. Aeroplas Corporation International (ACI) proposes to demonstrate and further expand their line of atomic oxygen resistant(AOR), E-Beam curable composites developed for NASA LaRC for use by spacecraft manufacturers that use the new highly penetrating, 10 MeV E-Beam rapid curing technique which can cure up to one inch laminated in seconds as the Winding passes the wide scanning beam. This series of AOR and newly developed low cost resins are expected to exhibit outstanding processability and a low stable filament winding processing viscosity. After a major discovery and recent formulation optimization work, they are now suitable for high specific strength and stiffness applications using other composite manufacturing methods such as vacuum assisted-resin transfer molding, wet-layup, pultrusion and thick (solid) versions that are appropriate for constant-tack automated prepreg tape/tow lay- up.

Potential Commercial Applications:

The proposed process is cost effective (does away with the costs associated with oven curing or autoclaving); rapid (minutes versus hours); environmentally friendly; is a low, ambient temperature process (for less molded in thermal stresses); is less expensive and less complicated; is amenable to scale up. The impact of the proposed concept is tremendous. The rapid E-Beam cure technologies will find immediate application in Infrastructural, Automotive, Aerospace and other industries where rapidly produced filament wound vessels are required.

Name and Address of Offeror:

Contract Id:

NAS 2 14378

Proposal Number:

04.02-0236

Project Title:

REUSABLE LIGHTWEIGHT THERMAL PROTECTION SYSTEM

Technical Abstract:

In this Phase I project, Ultramet proposes to develop a reusable lightweight, environmentally robust thermal protection system that is able to survive single- and multiple-use reentry conditions at a weight of 1.0-1.5 lb/ft2 and at low operational costs. This system will utilize the low-cost alumina-enhanced thermal barrier (AETB-12) felt, currently being developed by Rockwell under contract to NASA, as the insulator, combined with Ultramet's highly oxidation- and erosion-resistant facesheet materials to withstand the high temperature and gas erosion. These facesheet materials are composed of either carbon or silicon carbide fiber-reinforced SiC overcoated with a refractory ceramic composite consisting of alternating hafnium carbide and silicon carbide layers. These materials have been tested successfully in the 60-MW arcjet facility at NASA Ames Research Center, demonstrating excellent results (no erosion) at heat flux levels up to 300 Btu/ft2sec and temperatures exceeding 4500F. In addition, this material has been shown to have structural capabilities to temperatures exceeding 5000F. By utilizing the low-density, extremely low thermal conductivity, and low-cost rigid AETB ceramic felt as a core structure and insulator to support the oxidation/erosion-resistant facesheet, an extremely efficient lightweight structure with optimal performance in terms of mechanical, thermal, and ablative properties, can be achieved. Issues to be addressed during the course of the project include facesheet/insulator attachment, interfacial adhesion bonding, and the effect of cyclic oxidation or torch testing on facesheet/insulator bonding. Thermostructural performance across the panel will be evaluated as well, through techniques such as bend testing and thermal conductivity measurement.

Potential Commercial Applications:

In addition to thermal protection systems for reentry and hypersonic vehicles, the technology to be developed in this project can be applied to the space shuttle orbiter, single stage-to-orbit (SSTO) vehicles, leading edges, rocket nozzle throats, aerobraking structures, missile radomes, turbine and ramjet engine components, jet vanes, low mass heat engine components, filtration media, exhaust aftertreatment materials, and high temperature furnace materials.

Name and Address of Offeror:

Contract Id:

Proposal Number:

04.02-2056

Project Title:

A LOW-DENSITY HIGH-TEMPERATURE FLEXIBLE INSULATION FOR SPACECRAFT THERMAL PROTECTION SYSTEMS

Technical Abstract:

This project will ivestigate a unique flexible insulation blanket suitable for the thermal protection system (TPS) of future spacecraft during atmospheric entry. Its temperature range is expected to be up to at least 1000OC (1800OF) and its density will be about 60% that of AFRSI (Advanced Flexible Reusable Surface Insulation) which is currently used in the Shuttle. This low density can be achieved by using a special, light weight barrier in a high temperature MultiLayer Insulation to inhibit convective and radiative heat transfer. Several configurations are described in the proposal. Prototypes of these designs will be made and tested according to ASTM methods. Data from the tests will be used to develop correlation curves that predict performance under a variety of conditions. TPS performance will be calculated for a particular NASA mission.

Potential Commercial Applications:

The next generation of commercial aircraft require improvements in the thermal insulation systems. The X33, and other transatmospheric vehicles, require special high temperature insulations on the fuselage. Current aircraft designs can be made more efficient by reducing the weight of the insulation system such as that used on the engine nacelle. Commercial aircraft will benefit greatly through improvements in insulation efficiency and reductions in insulation weight.

Name and Address of Offeror:

Contract Id:

NAS 2 14357

Proposal Number:

04.02-2525

Project Title:

HIGH-TEMPERATURE GRADATED FIBROUS AEROGEL THERMAL PROTECTION SYSTEM

Technical Abstract:

This proposal describes an innovative material design concept for a high-temperature, high-strength thermal protection material by engineering the microstructures of the composite. This advance material is a fiber-reinforced aerogel composite which contains a gradation of fiber type and volume fraction. The type and concentration of fibers in each region of the composite are tailored to optimize the heat transfer and mechanical properties. The resulting advanced thermal insulation is expected to accommodate very high temperatures and heat fluxes for meeting NASA's future mission requirements. Phase I consists of modeling, analysis, and prototype fabrication. The feasibility of the proposed concept will be demonstrated in Phase I. Advanced modeling, performance optimization, and fabrication of optimized material configurations will be the focus of Phase II.

Potential Commercial Applications:

The design methodology and material fabrication technology from this research can be applied to develop various types of advance thermal insulations for many commercial and industrial applications over a wide temperature range. These include high- performance insulations for refrigerators, ovens, aircraft cabins,load-bearing and non-load bearing combustion engine components, etc.

Name and Address of Offeror:

Contract Id:

NAS 3 27816

Proposal Number:

04.03-0110

Project Title:

FUZZY AND PROBABILISTIC DESIGN TOOL FOR ACTIVELY CONTROLLED SMART COMPOSITE STRUCTURE

Technical Abstract:

The present proposal suggests a novel research and development study to provide a fuzzy and probabilistic-based computational tool that can be readily applied for integrated design, optimization and tailoring of actively controlled, smart composite structures. The innovative aspects of the methodology are: (i) integrated material/structural/control systems approach to design and optimization (ii) unified set of material/structural/control/sensor/ actuator design parameters for optimization and tailoring (iii) systematic accounting for all categories of uncertainties present in the problem using both fuzzy theory and probabilistic approaches New active "smart" or "intelligent" composite structural systems with integrated sensors, actuators and control capabilities appear to be promising candidates for the next generation high-performance structural and mechanical systems used in aeropropulsion, aircraft and space structures. One of the major attractions for the use of composite materials in structural applications is the ability to optimize and tailor their performance to desired response characteristics. Strategies and methodologies that have been employed to achieve this objective are not directly applicable to actively controlled smart structures because the structural, control, and materials aspects of this class of structures have unique characteristics that must be simultaneously considered in order to achieve the best overall performance.

Potential Commercial Applications:

The computational design tool product envisaged has a tremendous commercial potential. The technology of "smart" or "intelligent" structures is growing rapidly, and their applications are spreading. We believe that the application of smart materials in engineering structure will become a routine practice for effective monitoring of the "state-of-health" and for the control of response. It is expected that the design tool to be produced in Phases I and II will be a most valuable software package that would be of interest to designs/owners of aircraft, vibrating structures and machinery (whose noise and vibration control are of vital importance), ground transportation vehicles, and even home appliances.

Name and Address of Offeror:

Contract Id:

NAS 3 27741

Proposal Number:

04.03-0540

Project Title:

IN-SERVICE DIAGNOSTIC AND DAMAGE-LIMITING STRATEGIES FOR COMPOSITE FLYWHEELS

Technical Abstract:

This proposal describes the development of an in-service diagnostic system for high speed composite flywheels which combines cost-effective non-contact sensors with appropriate software algorithms to: 1. determine the current state of integrity of the composite flywheel 2. estimate the remaining life at current or modified operating conditions 3. modify operating conditions at selected thresholds to guarantee either continued safe operation or benign shutdown. The key innovation here is the use of non-contact sensors to measure attributes of the composite flywheel related to its fatigue integrity, and to modify flywheel operating conditions as required to avoid catastrophic failures. The measurement and flywheel control functions occur in real time during operational service, and are based upon a model of fatigue damage growth. The proposed system will redress the most significant barrier to composite flywheel acceptance. This barrier is the lack of compelling evidence to substantiate predictions of service life and integrity, and the exorbitant cost of using test data alone to provide such evidence. _

Potential Commercial Applications:

The use of this system in spin pit testing will allow test personnel to stop tests prior to rotor burst, thus saving the test article for comprehensive post mortem. As a key component of safety-critical commercial flywheel systems, the diagnostic system will monitor rotor performance in service and modify operating conditions to avoid failure and/or extend service life. It is anticipated that in the industrial UPS market alone, a market considerably in excess of 10,000 units exists. _

Name and Address of Offeror:

Contract Id:

NAS 3 27837

Proposal Number:

04.03-5005C

Project Title:

LIFE PREDICTION SOFTWARE & METHODOLOGY FOR TITANIUM MATRIX COMPOSITES

Technical Abstract:

The primary objective of the proposed program is to develop a product in the form of a software and methodology to predict response and life of titanium matrix composites (TMCs) under isothermal creep-fatigue loading, using a combination of critical experiments and modeling. The approach proposed to achieve these objectives involves detailed mechanics modeling, characterization testing, and mechanism studies. Our research team consists of outstanding researchers from Research Applications, Inc. (a minority owned small business) and UES ( a small business). The proposed staff has been directly involved in engine component design and life prediction issues by working with engine manufacturers. Thus, we offer not only a fundamentally sound, but also a pragmatic approach which addresses the most critical design issues related to MMC components.

Potential Commercial Applications:

The US commercial aircraft industry will increasingly be in need of advanced modeling and design tools which can exploit the use MMCs. Also, in the automotive industry metal matrix composites are being considered for several engine components. Therefore the proposed product has an immediate and growing market in the commercial aerospace as well as automotive industries.

Name and Address of Offeror:

Contract Id:

NAS 3 27737

Proposal Number:

04.03-7780

Project Title:

NONDESTRUCTIVE TOMOGRAPHIC ACQUISITION OF STIFFNESS & DENSITY INFORMATION

Technical Abstract:

Finite element analyses of aeropropulsion components typically need input on material stiffness and density. The proposed program will address the feasibility of combining X-ray computed tomography (CT) and acoustic tomography to produce three-dimensional images of density and stiffness. The density and stiffness information can then be incorporated into finite element analyses of structures allowing actual components to be modeled. The Phase I technical objectives are to determine the feasibility of using a priori information from X-ray CT to reconstruct acoustic tomography data and the feasibility of combining the X-ray CT data and the acoustic tomography data to produce a 2-D stiffness map of an object. The effort will consist of acquiring X-ray CT and acoustic data of a test object and applying iterative reconstruction methods to the data. A conceptual design will also be developed of an acoustic tomography system which can acquire acoustic data that will be compatible with existing X-ray CT equipment. This technique will provide a nondestructive approach to predicting failure modes and life of aerospace propulsion and power components including those made from composite materials.

Potential Commercial Applications:

The commercial products resulting from this work will be X-ray CT and acoustic tomography data acquisition systems and software. Once feasibility of the technique is established, demand for this equipment should increase. The equipment and associated software will allow actual components to be fully characterized nondestructively which will reduce the need for extensive destructive characterization of new material systems and structural configurations to obtain statistically significant databases of performance.

Name and Address of Offeror:

Contract Id:

NAS 3 27734

Proposal Number:

04.03-8547A

Project Title:

PROGESSIVE FRACTURE OF BRAIDED COMPOSITE TURBOMACHINERY STRUCTURES

Technical Abstract:

Alpha STAR proposes to develop a computational tool to assess progressive fracture and durability of 3D braided fiber reinforced polymer matrix composite (PMC) rotor and rotor blade structures. Effects of aging., manufacturing defects, residual stresses, thermal and hygral environments, cyclic and monotonically increasing mechanical loading, thermomechanical loading and fiber patterns will be taken into account. The progressive fracture simulation computational tool will be developed by extension of an existing software code, CODSTRAN, which integrates the ICAN composites mechanics code module with a finite element analyzer. The ICAN module will be extended to assess 3D braided fiber composite properties and stress limits according to the local braiding configuration at each finite element node. Simulation of progressive fracture will be accomplished by iterative re-assembly and re-evaluation of generalized service load stresses and an assessment made of damage progression caused by additional load cycles. This proposed extension of CODSTRAN will allow detailed damage tracking of braided composite rotors and blades by computer simulation. The military and commercial aerospace industries stand to gain substantial benefits from use of the developed software in the form of design and manufacturing cost reductions, accurate life cycle predictions, and improved durability and reliability of braided fiber PMC structure.

Potential Commercial Applications:

(1) -significant reduction of design time for the turbomachinary developer, and air vehicle (2)-reduction of full scale prototype testing by use of computational simulation to extend subscale experimental results to full scale prototype structures. (3)-improved braided composite durability and performance in end user applications (4)-accurate establishment of performance and useful life limits of braided PMC turbomachinary, aircraft components