Analysis and design effort on the Advanced Maneuvering Propulsion System (AMPS) progressed satisfactorily. Engine system mixture ratio, operating range, and operational requirements were conducted. Thrust chamber turbopump, and control subsystem design analysis were performed. Propellant feed system analysis and design effort was accomplished on the propellant tanks, outer shroud and tank supports, insulation, and pressurization subsystems. Engine critical component demonstration testing was accomplished on the main engine thrust chamber segment hardware. Forty firing tests were accomplished with the 5-inch solid-wall segment configuration over a chamber pressure range of 650 psia to 72 psia, which meets the design requirement.
Advanced Maneuvering Propulsion Technology Program
1968
680 pages
Report
Keine Angabe
Englisch
Manned Spacecraft , Rocket Engines & Motors , Combustion & Ignition , Spacecraft , Liquid propellant rocket engines , Design , Ignition , Thrust , Model tests , Mathematical models , Combustion chambers , Turbopumps , Propellant control , Propellant tanks , Pressurization , Thermal insulation , Captive tests , Instrumentation , Flow fields , Fuel injectors , Gas flow , Valves , Structural members , Heat transfer , Cooling , Control systems , Amps(Advanced maneuvering propulsion system) , Concentric thrust chambers , Titan 3