Accession Number : AD0511031

Title :   Advanced Maneuvering Propulsion System (Convair 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 : 145

Abstract : A high performance LF2/LH2 maneuvering propulsion system has been defined, which provides an in orbit delta V capability in excess of 21,000 ft/sec with a 2000 pound payload. The system, which is designed for launch into a 100 nautical mile polar orbit with the Titan IIID, weighs 18,000 pounds fully loaded, has instant response and multi-start capability, while providing a nominal space residence duration of 14 days. Longer orbital stay times (up to 180 days) can be accommodated with some design modification without significantly degrading performance. This design can be used as the basis of a ground test article to demonstrate the feasibility of technical concepts applicable to a wide range of high performance stage sizes. (Author)

Descriptors :   (*LIQUID PROPELLANT ROCKET ENGINES, PROPELLANT CONTROL), PROPELLANT TANKS, SLOSHING, VENTS, BAFFLES, THERMAL INSULATION, STRUCTURAL MEMBERS, SHELLS(STRUCTURAL FORMS), PROPELLANT TRANSFER, PRESSURIZATION, PIPES, STARTING, WEIGHT (U) *CONTROLLABLE-THRUST ROCKET MOTORS, *CRYOGENIC PROPELLANTS, LIQUEFIED GASES, POLAR ORBIT TRAJECTORIES, ADVANCED WEAPONS, FLUORINE, HYDROGEN, MANEUVERING SATELLITES, MANEUVERABILITY, THRUST VECTOR CONTROL SYSTEMS, ATTITUDE CONTROL SYSTEMS, PAYLOAD, SPACE ENVIRONMENTS, LIFE EXPECTANCY, LAUNCH VEHICLES, ALUMINUM ALLOYS

Subject Categories : Liquid Propellant Rocket Engines
      Liquid Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE