Experimental investigation on the draining behavior in scaled models of the new A5ME upper stage propellant compartments with respect to different flight conditions

Abstract

The maximum possible mass, launched to orbit by a rocket, depends on the launcher performance and the desired target orbit. To provide as much capacity to the payload as possible, the total mass of the launchers upper stage has to be minimized. Intelligent propellant management can contribute significantly to increase the performance of the launcher. To optimize the flight missions the tank outlet design is required, to achieve that a maximum of the propellant is available for the mission and a minimum of propellant loading remains as unused residual.