Experiences with Pressurized Discharge of Liquid Oxygen from Large Flight Vehicle Propellant Tanks

Abstract

Liquid propellant missiles and space vehicles require pressurization of the propellant containers during flight to provide sufficient net positive suction head for the pumps and structural rigidity for the tanks. It is important in this application that the pressurization system be of light weight and that it use a pressurant compatible with the propellant. The problem of determining the pressurant requirements for cryogenic propellants is being studied extensively by various groups in the cryogenics and rocket vehicle field. Mathematical models describing the internal thermodynamics of pressurization systems are being devised for this purpose. Unfortunately, most of the experimental studies are confined to small-model tests, the results of which have to be applied to tank systems several orders larger in capacity.