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ADVANCED THRUST CHAMBER FOR SPACE MANEUVERING PROPULSION, TASK I SYSTEM STUDIES
ROCKETDYNE CANOGA PARK CA
The previous study results of Contract AF04611-10745 are extended to investigate the capabilities of increased gross weight Maneuvering Space Propulsion Systems MSPS using LF2LH2, LO2LH2, and N2O4N2H4-UDMH50-50 propellants. The range of stage gross weights considered was based on the payload capabilities of Titan III-C and Saturn I-B and several growth versions of these launch vehicles. Maneuvering space propulsion system gross weights ranging from 20,000 to 50,000 pounds were shown to result in velocity increment capabilities up to 29,000 ftsec for the 2000-pound payload LF2LH2 system. The concentric aerodynamic spikebell engine configuration was selected for the LF2LH2 and LO2LH2 system design thrust levels investigated. The configuration selected for the N2O4N2H4-UDMH50-50 consisted of one larger primary bell nozzle engine and two small secondary bell nozzle engines. The orbit storage life capabilities of the three propellant combinations were determined and compared for a 20,000-pound-gross weight stage. The LF2LH2 system provided higher delta V capabilities than the other propellants for orbital storage times up to 2 years with full propellant tanks. The delta V advantage for the LF2LH2 systems is also maintained when mission duty cycles result in partial propellant loads for the major portion of the storage duration.
Final rept. 16 May-15 Aug 1966
Approved for public release; distribution is unlimited.