Multidisciplinary Design of Reusable Re-Entry Vehicles by Optimization and Computational Fluid Dynamics

This paper deals with the development of a multi-fidelity design framework for reusable re-entry vehicles. A multidisciplinary shape optimization procedure, for Low Earth Orbit re-entry missions, is performed using a parametric model able to promote the search for unconventional concept aeroshapes. Low order fidelity methods are adopted in the optimization procedure to obtain several design candidates reasonably consistent with a set of mission requirements and constraints at an affordable computational time. Optimal design candidates are validated performing more reliable Computational Fluid Dynamics simulations in a set of specified waypoints along with the re-entry trajectory.