NASA's Hyper-X research program was developed primarily to flight demonstrate a supersonic combustion ramjet engine, fully integrated with a forebody designed to tailor inlet flow conditions and a free expansion nozzle/afterbody to produce positive thrust at design flight conditions. With a point-designed propulsion system the vehicle must depend on some other means for boost to its design flight condition. Clean separation from this initial propulsion system stage within less than a second is critical to the success of the flight. This paper discusses the early planning activity, background, and chronology that developed the series of wind-tunnel tests to support multi-degree-of-freedom simulation of the separation process. Representative results from each series of tests are presented, and issues and concerns during the process and current status are highlighted.
Hyper-X Stage Separation Wind-Tunnel Test Program
AIAA 18th Applied Aerodynamics Conference ; 2000 ; Denver, CO, United States
Journal of Spacecraft and Rockets ; 38 , 6
2001-11-01
Miscellaneous
No indication
English
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