A facility for analyzing the effects of engine hardware parameters on the pulse characteristics of bipropellant attitude control thrusters in a space environments was constructed at the Air Force Rocket Propulsion Laboratory (AFRPL). In a series of tests involving 32 engine configurations, 17 engine parameters were varied. The propellants considered were N2H4-UDMH (50/50) and MMH fuels and NTO as the oxidizer. The experimental phase of the program was based on a statistical test matrix designed to minimize the number of firings and the hardware requirements. This report includes a detailed description of the altitude ignition facility and presents an analysis of the system and the data obtained. (Author)


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    High Altitude Laboratory Studies of Compression Ignition Engines

    Woomert, Dale E. | SAE Technical Papers | 1966


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    Engineering Index Backfile | 1945


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    TAYLOR, J. / WIDENER, S. | AIAA | 1986


    Compression-Ignition Engine Performance at Altitude

    Moore, Charles S. / Collins, John H. | SAE Technical Papers | 1937