Analysis and design effort on the Advanced Maneuvering Propulsion System (AMPS) was initiated. Engine system tradeoff studies for selection of the pump drive cycle and engine mixture ratio were completed and the basic engine design parameters were defined. Engine, thrust chamber, turbopump, and controls design analyses were started. The space and thermal environments of the propulsion system were established and design analysis was begun on the main propellant tanks. Engine critical component demonstration testing was accomplished on the main engine thrust chamber segment hardware. Successful operation at full design condition of 650 psia chamber pressure, injector mixture ratio of 14:1, and fuel injector inlet temperature of 1000 F was demonstrated with the fan-type injector design. (Author)
Advanced Maneuvering Propulsion Technology Program
1968
380 pages
Report
No indication
English
Rocket Engines & Motors , Combustion & Ignition , Fuels , Liquid propellant rocket engines , Maneuvering satellites , Design , Launch vehicles , Turbopumps , Fuel pumps , Combustion chambers , Rocket nozzles , Regenerative cooling , Walls , Vibration , Propellant tanks , Space environments , Surface temperature , Acceleration , Wind , Amps(Advanced maneuvering propulsion system) , Advanced maneuvering propulsion system , Thrust , Plumes(Radiation) , Restarting , Titan 3 , Tradeoffs