Jascha Wilken, Martin Sippel, Michael Berger
DOI Number XXX-YYY-ZZZ
Conference Number HiSST-2022-210
For the first time in the history of spaceflight a fully reusable launch system appears possible within the
near future. Since its presentation in 2016 SpaceX’s next generation space transport system has gone
through multiple names and design iterations but some key design features remained constant: Full
reusability, Full-Flow Staged Combustion engines and deeply subcooled LOX/LCH4 as propellants.
The current design iteration is of special interest because hardware is being integrated and the first
test flights, including landings, of the upper stage have been completed. A key feature of this iteration
is the novel approach to use a “skydiving” maneuver to dissipate as much energy as possible through
aerodynamic forces before initiating a landing burn and landing vertically.
The implications of a fully reusable system of this size on the orbital launch market are significant even
if the ambitious plans for quick turnaround of stages are not fulfilled right from the beginning.
Within this paper, the two-staged system is analyzed from a technical perspective based on publicly
available information. The principal goal is to form an understanding of the high-level system properties.
Of special interest are the return methods, which exhibit some novel properties. Overall a reasonable
agreement between the generated models and the publicly available information is found. The design
and its driving factors are discussed and a fundamental understanding of the high-level properties of
the system is attained.