Accession Number : AD0511036

Title :   Advanced Maneuvering Propulsion System (Lockheed Propellant Feed System Design). Volume I--Summary.

Descriptive Note : Final rept. 1 Dec 67-31 Dec 69.

Corporate Author : ROCKETDYNE CANOGA PARK CALIF

Report Date : SEP 1970

Pagination or Media Count : 76

Abstract : The propulsion stage has a mass fraction of 0.854, a dry weight of 2,028 lb, a reliability value of 0.9872 (minus the engine) and a delta v capability of 20,197 to 21,765 ft/sec (with a 2,000 lb payload), which varied over this range depending on the duty cycle and thrust level used. With prior knowledge of the duty cycle to be performed, i.e., if the mission is known after achieving orbit, the delta v capability rises to 22,800 ft/sec with the same payload weight. Extended mission durations up to 30 days reduces the vehicle delta v capability by only 85 ft/sec. For missions to 180 days, the resulting delta v capability of this vehicle with optimized insulation is 90 percent of the 14-day value. Using subcooled propellants and optimized insulation, the 180-day delta v is approximately 98 percent of the 14-day mission capability. The primary missions for the vehicle are orbital intercept, rendezvous, and evasive maneuvers with reconnaissance maneuvering capability over 14 days.

Descriptors :   (*LIQUID PROPELLANT ROCKET ENGINES, PROPELLANT CONTROL), WEIGHT, RELIABILITY, THERMAL INSULATION, PROPELLANT TANKS, PRESSURIZATION, PROPELLANT TRANSFER, BAFFLES, SLOSHING, MISSION PROFILES (U) *CONTROLLABLE-THRUST ROCKET MOTORS, *CRYOGENIC PROPELLANTS, LIQUEFIED GASES, POLAR ORBIT TRAJECTORIES, FLUORINE, HYDROGEN, ADVANCED WEAPONS, LAUNCH VEHICLES, SHROUD RINGS, PAYLOAD, ACCELERATION, LIFE EXPECTANCY, INTERCEPTOR SPACECRAFT, RENDEZVOUS SPACECRAFT, RECONNAISSANCE SATELLITES, STARTING, MANEUVERABILITY, MANEUVERING SATELLITES, SYNCHRONOUS SATELLITES, MARS PROBES

Subject Categories : Liquid Propellant Rocket Engines
      Liquid Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE