Award Data

WE PROPOSE THE DEVELOPMENT OF AN INNOVATIVE NEUROCONTROLLER THAT GENERATES TRAJECTORIES WHICH REDUCE PLASMA EFFECTS ON THE COMMUNICATION SYSTEM OF THE NASP. WE WILL MODEL PLASMA SHEATH GENERATION AND INCORPORATE THIS MODEL INTO A GHAME FLIGHT SIMULATOR ON A SILICON GRAPHICS WORKSTATION. THIS MODEL WILL THEN BE USED IN THE DEVELOPMENT OF THE CONTROLLER AND SUITABLE ADAPTATION LAWS. COST FUNCTIONS W ...

THIS PROPOSAL INVOLVES RESEARCH INTO A SUPERCOMPUTER-BASED ENVIRONMENT FOR RESEARCH INTO MASSIVELY PARALLEL NEURAL-NETWORK ALGORITHMS FOR LARGE SCALE, COMPUTATIONALLY INTENSE PROBLEMS. THIS ENVIRONMENT WILL HAVE APPLICATION TO AREAS SUCH AS IMAGE PROCESSING, PATTERN RECOGNITION, CONTROL SIGNAL PROCESSING, DATA COMPRESSION, AND FAULT DIAGNOSIS. ALL OF THESE ARE AREAS WHICH INVOLVE MASSIVE AMOUNTS O ...

The study of neural networks which possess the capability to learn and grow with little or no supervision will be explored during this research effort. These networks exhibit ontogenic behavior and are termed ontogenic neural networks. This reasearch effort explores the use of hybrid neural network structures which are capable of self-organization, feature discovery and self generation in a compos ...

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This proposal describes a novel, high thrust density Detonation Wave Engine (DWE) applicable to the Mach range of 0 to 3. The geometry of this novel engine concept naturally provides for integration into a new Combined Cycle Engine with Ramjets. The concept is an intermittent combustion jet engine that harnesses travelling detonation waves to accomplish compression and chemical reaction. The goal ...

An innovative actively cooled structure concept is proposed which integrates proven cooling techniques and state-of-the-art fabrication methods to extend the maximum combustor wall temperature, thereby reducing cooling requirements and aircraft weight while improving engine performance. Specifically, CONvective and TRANspiration cooling (CONTRAN) are uniquely combined, relying on hydrogen coolant ...

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There is a need for non-intrusive instrumentation to characterize the drop size distribution and volume flux in support of on-line engine/inlet icing tests. The ducts may vary from three to twelve feet in diameter with flow field speeds from Mach 0.2 to 0.5. The Phase Doppler technique offers the best potential for making these measurements non-intrusively and with sufficient accuracy to meet the ...