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

An aerothermodynamic design optimization framework for hypersonic vehicles

In the aviation field great interest is growing in passengers transportation at hypersonic speed. This requires, however, careful study of the enabling technologies necessary for the optimal design of hypersonic vehicles. In this framework, the present work reports on a highly integrated design environment that has been developed in order to provide an optimization loop for vehicle aerothermodynamic design. It includes modules for geometrical parametrization, automated data transfer between tools, automated execution of computational analysis codes, and design optimization methods. This optimization environment is exploited for the aerodynamic design of an unmanned hypersonic cruiser flying at M∞=8 and 30 km altitude. The original contribution of this work is mainly found in the capability of the developed optimization environment of working simultaneously on shape and topology of the aircraft. The results reported and discussed highlight interesting design capabilities, and promise extension to more challenging and realistic integrated aerothermodynamic design problems

Launcher Aerodynamics: A Suitable Investigation Approach at Phase-A Design Level

This chapter deals with launcher aerodynamic design activities at phase-A level. The goal is to address the preliminary aerodynamic database of a typical launch vehicle configuration as input for launcher performances evaluations, control, sizing, and staging design activities. In this framework, different design approaches relying on both engineering and numerical methods are considered. Indeed, engineering-based aerodynamic analyses by means of a three-dimensional panel methods code, based on local surface inclination theory, were performed. Then, accuracy of design analysis increased using steady-state computational fluid dynamics with both Euler and Navier-Stokes approximations