Phase-A design of a reusable re-entry vehicle

In this paper, a design procedure developed to obtain a Phase-A compliant optimal aeroshape is presented. The proposed vehicle performs a low Earth orbit re-entry and a landing on a horizontal runway. A conceptual aeroshape design obtained by a multi-disciplinary, multi-objective optimization is modified by the addition of two functionally independent body flaps to the concept windside to envisage the aeroshape control along both the longitudinal and later-directional axes. Body flaps are also added on the rearward sections of the spacecraft leeside. Aerodynamic analyses are carried out throughout the speed regimes expected during re-entry, to address the feasibility of the vehicle design. Furthermore, CFD computation are specifically performed at very low Mach numbers to address body flaps effects on spacecraft aerodynamics at landing conditions. Flowfield results are also provided, with a particular focus on the vortex lift phenomenon generated by the delta planform shape of the vehicle configuration. Specifically, the flow pattern at landing angle of attack is highlighted to account for safety landing conditions. Finally, a single objective optimization is performed to find the best guidance law allowing a safer re-entry compatible with the assigned operational constraints. In doing this, two kinds of re-entry strategies are compared, namely Shuttle-like and heat-flux tracking profiles.