Concurrent subspace design optimization and analysis of hypersonic vehicles based on response surface models

The airframe/scramjet engine integration in hypersonic vehicles causes strong couplings among relevant disciplines. Due to the importance of these couplings, research on algorithms and frames of hypersonic vehicle design optimization has become an active area. Targeting on vehicles similar to X-43A, this paper establishes a multidisciplinary performance analysis model, which involves disciplines such as parameterized configuration geometry, aerodynamics, propulsion, aerodynamic heat, mass properties, radar cross section (RCS) and trajectory. Based on the polynomial response surface approximation technique, a design optimization is performed by using the concurrent subspace optimization method, which yields a set of design variables (configuration parameters of the airframe/propulsion integration and cruise trajectory parameters) that maximize the cruise range of the vehicle. Performances of the vehicle before and after optimization are also compared. The result shows that the optimization leads to an increase of vehicle range as much as 18.9%.