Optimization of Propulsion Cycles for Advanced Shuttles.

Abstract

Two years ago NASA and DLR computer codes were combined in order to analyse and optimize advanced rocket launcher systems. During the past year further effort has been made on this combined code concerniconcerning influences induced by the propulsive parameter such as chamber pressure, kind of cycle for the rocket motor and therefore by the required preburner pressure, mixed cycle, tripropellant cycle, nozzle extension, two-position nozzle effects etc. The emphasis of this work is to describe the performance part of the propulsion model and to apply the revised code on the optimization of single stage advanced shuttles.