SBIR-STTR Award

Development of a low-cost, near term approach to flight testing a hypersonic, storable fuel, scramjet engine using ballistic range technology is proposed. Flight-testing is easily the most expensive component of the triad of computational fluid dynamics (CFD), ground-testing and flight-testing needed to develop and demonstrate sustained and accelerating airbreathing flight at hypersonic speeds. Cost reduction by a factor of 100 to 200 relative to rocket launching a full-scale engine is sought. The proposed approach will leverage off GASL's low-cost, rapid prototyping capabilities for scramjet engines for wind tunnels and for NASA's Hyper-X flight test program, Boeing's prior experience in launching a scramjet from the SHARP gun at LLNL, and prior Army Research Lab personnel in data telemetry from gun-launched munitions. Essential aspects of the proposed approach are use of closely coordinated CFD and ground-testing to maximize the flight data yield and minimize the risk and cost, and use of a controlled flight environment to permit proper simulation of flight dynamic pressure. Flight speeds from Mach 6 to 12 are considered within existing ballistic range capabilities. Mach 8 is the proposed test point since it supports the goals of the HyTech and ARRMD programs.

Demonstration of a low cost, near term approach to flight-testing a hypersonic, storable fuel, scramjet engine using ballistic range technology is proposed. Flight-testing is easily the most expensive component of the triad of computational fluid dynamics (CFD), ground-testing, and flight-testing needed to develop and demonstrate sustained and accelerating air-breathing flight at hypersonic speeds. Cost reduction by a factor of 100 to 200 relative to rocket boosting a full-scale engine is sought. The proposed approach leverages off GASL's low cost, rapid prototyping capabilities for scramjet engines for wind tunnels and for NASA's Hyper-X flight test program, previous scramjet launch results in the SHARP gun at LLNL, and Army Research Lab free-flight acceleration measurements on gun-launched munitions. Essential aspects of the proposed approach are coordinated CFD and ground-testing prior to flight-test to maximize data yield and value while minimizing risk and cost, and use of a controlled flight environment to achieve a properly scaled flight dynamic pressure. An integrated engine design and vehicle mold line, provided by a commercial engine manufacturer and potential customer for the service, will be used as the baseline for the initial launch vehicle to demonstrate from the outset traceability to developmental hardware. Mach-8 flight speed has been chosen as the demonstration launch speed since it supports the ARRMD and HYTECH programs.

Keywords:
SCRAMJET FLIGHT TESTING; BALLISTIC RANGE; STORABLE FUEL SCRA