Advanced inversion control for a Hypersonic Vehicle based on PSO and Arranged Transient Process

A high-order curve-fitted model which is suitable for a large flight envelope is adopted for the aerodynamic coefficients of the Generic Hypersonic Vehicle (GHV). As a supplement, the expressions of the thrust coefficients for the whole hypersonic flight range are presented in this paper. Based on this model, a general Nonlinear Dynamic Inversion (NDI) controller is designed with the feedback linearization theory for the velocity and altitude tracking purpose. However, the robustness of this general NDI controller needs to be improved, particularly when a large step command is given. For these reasons, an advanced inversion controller is designed, where both the Particle Swarm Optimization (PSO) algorithm and Arranged Transient Process (ATP) technique are applied. The PSO is used to optimize the feedback coefficients of the inversion controller, while the ATP technique is employed to guarantee that the system has better dynamic performance and control quality. Simulation results demonstrate that the advanced inversion controller has better tracking performance and robustness in a large envelope of flight condition.