SBIR-STTR Award

Utilizing plasma interactions on hypersonic vehicles for aerodynamic control, drag reduction, thermal management and propulsion are proposed by-US agencies, industry and foreign interests (Russian AJAX). These schemes address the Air Force's need for future hypersonic vehicles. This SBIR will develop a plasma MGD/MHD system designed to enable ' hypersonic propulsion by electromagnetic flow interactions with the inlet capture stream. This system is coined the "MGD Inlet' is a non-intrusive means for enhancement of scramjet operation. The MGD inlet is defined from experimental and analytical studies of plasma assisted propulsion concepts. It is conceived for the first generation plasma augmented scramjet to use those interactions considered realizable in the near term. The interactions exploited with this inlet are pre-compression of the capture stream, internal flow compression, and scramjet entrance flowfield conditioning. Phase I will perform R&D for the MHD inlet to refine its design and identify test requirements. Phase I combines analysis of hypersonics and plasma/MGD/MHD phenomena with system engineering and integration to include trade-off and vehicle integration studies. Phase I will evaluate sub-systems for an MHD inlet design for test and evaluation in Phase II. Phase II will produce design criteria for a flight hardware inlet for Phase III

Utilizing electromagnetic interactions with plasma air stream over hypersonic vehicles for aerodynamics, drag reduction, thermal management and propulsion enhancement are of interest to US agencies, industry, and foreign organizations (AJAX). This concept addresses the Air Force's mission for future high performance hypersonic aircraft. This SBIR will develop an MHD system to control flow into and within the hypersonic vehicles's air induction system. The "MHD Inlet" or "Virtual Inlet" provides a non-mechanical means for inlet flow compression and capture. It is an integrated, self-driven system that modulates the incoming hypersonic stream to cushion shocks, provide compression over the forebody, reduce thermal loads, and control boundary layers. It markedly improves inlet performance by lending a smaller capture area requirement, eliminating inlet ramps, and holding design point operation. Phase II will perform experimental the R/R&D to define operation and system design and demonstrate the MDH inlet. It combines hypersonic analysis with plasma/MGD/MHD phenomena and system engineering and integration to realize an advanced MHD assisted inlet hypersonic vehicle design. Phase II will evaluate sub-systems of the MHD inlet for extended applications to other areas of hypersonic aircraft. It will produce designs for production of flight and flight test hardware for Phase III