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
