Family of Launchers Approach vs. “Big-Size-Fits-All”

Abstract

One option for future space transportation concepts could be a family of launchers supporting a wide range of payload performance. The idea bases upon using “building blocks” of common stages or main propulsion rocket engines and applying them in a modular way. A somehow contrarious option is a single TSTO launch vehicle serving all kinds of missions, even those which have payload mass requirements much below the design capacity. The technical investigations described in this paper evaluate the two antipodal design approaches of either establishing a launcher family consisting of modular building blocks or choosing a full-size launcher which serves all missions with minimal adaptations of the upper- and kick-stage selection. The paper summarizes major results of the preliminary technical design process. The overall shape and aerodynamic configuration, the propulsion and feed system, the architecture of the stages are described and different technical solutions are compared. Payload performance is optimized for the different concepts in the GTO-mission, manned flight to ISS and to SSO. The winged configurations’ controllability in hypersonic reentry and subsequent subsonic flight is assessed. The study is completed by a relative comparison of to be expected RC/NRC of the different launcher concepts.