Abstract: Control surface design and optimization is a main challenge of horizontal take off and horizontal landing (HTHL) aerospace vehicles with relaxed static stability. An integrated control surface/parameter design method based on surrogate model is proposed in this paper. Firstly, an automatic aerodynamic surrogate model is established based on improved pigeon swarm algorithm for aerospace vehicles with different control surface size, which effectively reflects the relationship of aerodynamic coefficients with flight conditions, control surface size, and center of gravity position, providing necessary input for integrated design. Then, the longitudinal reference model tracking control structure is built based on C * control law, and the integrated design is transformed into multi objective optimization under multi constraints. The non smooth optimization algorithm is adopted to solve this non convex problem, resulting in minimum control surface size and corresponding control parameters, which simultaneously satisfies handling quality, control surface deflection, and deflection rate saturation constraints. Finally, simulation results indicate that the proposed integrated design method can effectively reduce the control surface size while satisfying the performance constraints, making it suitable for industrial applications.

Key words: Horizontal take off and horizontal landing (HTHL), Aerospace vehicles；Relaxed static stability (RSS)； Handling quality constraint； Control surface optimization