High-Performance, Partially Reusable Launchers for Europe

RLV configurations with partial reusability of 1 or booster stages are in focus of ongoing system studies. Parallel stage arrangement is preferred with a winged stage connected to an expendable upper segment with potentially various internal architectures. The non-symmetrical architecture consists of a winged RLV-stage and attached ELVpart comprising either one or two stages. The selected rocket propulsion is mostly cryogenic LOX-LH2 (gas generator or staged-combustion cycle) but also the two fuel combinations methane and hydrogen are looked at. An engine similar to the European PROMETHEUS is also considered for main stage propulsion and architecture implications are discussed.