High Thrust Bleed Rocket Engines for a Fly-Back Booster Application

Kurzfassung

In this paper a high trust, cryogenic bleed cycle engine is analyzed, to be used for propulsion of future reusable booster stages of a heavy lift launcher. Based on results of an earlier cycle analysis, an improved engine variant is investigated. Its performance is calculated, and a preliminary engine sizing and mass analysis is carried out. Improvement options as well as growth potential of the cycle is regarded. Different turbo-pump lay-outs are looked upon to indicate the most promising one. An ascent trajectory optimization and a discussion of the complete vehicle are performed to evaluate the engine as part of a future semi reusable launch system.