Re-entry Simulation for Reusable Launch Vehicle

In this paper the RLV flight control system is designed by combining MPC with Feedback Linearization (FBL). The feedback linearization is based on the full rotational equations of motion rather than on a conventional model derived from time-scale separation. Input state constraints and are applied to MPC algorithms to avoid input saturations, to guarantee a smooth tracking performance with non-linear rotational dynamics and a strong roll-yaw coupling of RLV model. The results of simulation show the control system can follow the parameters of guidance significantly.