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)
Altitude Ignition Studies
1971
29 pages
Report
No indication
English
Combustion & Ignition , Rocket Propellants , Hypergolic ignition , Hypergolic rocket propellants , Thrust vector control systems , High altitude , Vernier rocket engines , Combustion chambers , Attitude control systems , Nitrogen oxides , Hydrazine , Altitude chambers , Ignition lag , Mathematical models , Cold flow , Aerozine 50 propellant , Hydrazine/monomethyl , Nitrogen oxide(N2o4) , Nitrogen compounds , Tetroxides , Nto(Nitrogen tetroxide)
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