Systems Analysis of a Future Semi-Reusable Launcher, Based on a High Thrust Bleed Cycle Rocket Engine

Abstract

In this paper a high thrust, cryogenic bleed cycle engine, to be used for propulsion of future reusable booster stages (liquid fly back boosters), of an expendable heavy lift launcher, is analyzed. The system configuration remains unchanged, in terms of total available fuel and the number of engines, whereas the variation of the engine parameters results in a change of total system mass and payload capacity. Different arrangements of bleed cycles are being analyzed, and compard with each other. The paper describes a simplified heat transfer model, used in the analysis of the suggested cycles. The thrust chamber design is discussed and a preliminary design of the booster vehicle, including a trajectory analysis, is presented.