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The pressurization system of cryogenic propellant rockets requires on-board pressurant\udgas. The objective of this study was to analyze the influence of the pressurant gas temperature\udon the required pressurant gas mass in terms of lowering the launcher mass. First,\udground experiments were performed in order to investigate the pressurization process with\udregard to the influence of the pressurant gas inlet temperature. Second, a system study\udfor the cryogenic upper stage of a small Two Stage to Orbit (TSTO) launch vehicle was\udperformed with focus on the influence of the pressurant gas temperature on the propellant\udmanagement system mass. One important experimental result is that for evaporated propellant\udas pressurant gas, the maximum applicable gas temperature is best for reducing\udthe needed pressurant gas, but on condition that all pressurization lines are chilled down.\udMoreover, the use of helium is very advantageous with regard to lowering the pressurant gas\udmass. Also significant is that an immediate pressure drop occurred after the pressurization\udend. The conclusion drawn from the system analysis is that an increased evaporated propellant\udand helium pressurant gas temperature resulted in a decrease of the total propellant\udmanagement system mass, despite the application of external helium vessels

Analyses of Cryogenic Propellant Tank Pressurization based upon Ground Experiments