Accession Number : AD0468416

Title :   PRESSURIZATION SYSTEM ANALYSIS FOR CRYOGENIC PROPULSION SYSTEMS,

Corporate Author : BOEING CO SEATTLE WASH

Personal Author(s) : Chopp ,Frederick

Report Date : 10 AUG 1965

Pagination or Media Count : 33

Abstract : Stored gas pressurization and boost pump liquid rocket engine propellant transfer systems were investigated to compare their suitability for use on hydrogen-oxygen upper stage vehicles. The purpose of this document is to present the results of this study and to describe the method of analysis used. System comparisons were based on the overall system weight. The mission duty cycle, NPSH, propellant weight, and propellant type were held constant. Results indicated that liquid transfer with boost pumps will provide a minimum system weight for the selected baseline configuration and ground rules. For stored gas pressurization, it was determined that storage of the gas bottle should be in the hydrogen tank with the pressurant heated prior to entering the tanks. Optimum pressurant temperature for the hydrogen tank was found to be 350 R. No calculations were made to optimize the oxygen tank pressurant temperature. (Author)

Descriptors :   (*GAS PUMPS, CRYOGENICS), (*CRYOPUMPING, LIQUID ROCKET PROPELLANTS), PROPELLANT TANKS, MATHEMATICAL MODELS, HELIUM, PRESSURE, FUEL PUMPS, OXYGEN, VAPORIZATION, LIQUID PROPELLANT ROCKET ENGINES, SUSTAINER ENGINES, LIQUEFIED GASES, HANDLING, SPACE ENVIRONMENTS

Distribution Statement : APPROVED FOR PUBLIC RELEASE