Comparative Analysis of Fully Reusable Launch Vehicles: Fuel Choices and Landing Architectures

Kurzfassung

Fully reusable two-stage-to-orbit (TSTO) launch vehicles, such as SpaceX's Starship, are poised to reshape the future of space access. Yet, systematic design studies of this architecture remain scarce, particularly in the European context. This paper addresses that gap through a parametric assessment of key design variables: propellant type, engine cycle, and stage propellant ratio. A unified modelling framework combines mass estimation, ascent trajectory optimization, and booster recovery analysis to explore performance across multiple configurations. The goal is to build an understanding of Starship class systems and assess their applicability to future European heavy-lift development.