Three flightweight Aerojet AJ10-179 engine assemblies were tested under vacuum conditions. The testing had two objectives. First was demonstration that the engine could meet the requirements of a Ballistic Missile Post Boost Propulsion System with N2O4-N2H4 as the propellants. The second was measurement and evaluation of the engine's capability to perform pulsing missions, such as a space maneuvering mission, using N2O4-MMH as the propellants. Injector erosion was encountered in 3 of 5 tests using MMH. Higher gas temperatures, less cooling capability and possible combustion roughness caused higher heat loads which produced the erosion. (Modified author abstract)
Altitude Testing of the Aerojet AJ10-179 Liquid Rocket Engine
1973
105 pages
Report
Keine Angabe
Englisch
Surface Launched Missiles , Rocket motors(Liquid propellant) , Guided missiles(Surface-to-surface) , Captive tests , Nitrogen oxides , Hydrazine , Combustion chambers , Injectors , Valves , Propellant control , Specific impulse , Bipropellants , PBPS(Post Boost Propulsion Systems) , Post boost propulsion systems , AJ10-179 engines , AJ-10 engines
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