LPV model reference control method for hypersonic vehicle control system

The traditional state feedback control method needs longer adjustment time and needs longer time to stably track the changes of the flight state commands. Aiming at the above situation, a LPV model reference control method is developed in this paper. Firstly, considering the changes of the flight states of the hypersonic vehicle, the control law of the hypersonic vehicle based on LPV model reference control method is designed according to the characteristics of the longitudinal model of the aircraft. Then, the singular value decomposition is used to solve the controller's coefficient matrix and the controller's state feedback gain is solved by the linear matrix inequality. Under the action of the controller, the actual output of the model converges to the output of the reference model. Finally, effectiveness of the controller is verified by the simulation results. The comparison between the designed controller and the traditional state feedback controller shows that the designed controller has shorter adjustment time and smaller overshoot.