When hypersonic vehicle changes the flight state, the calculation process will be very complicated if the attitude control system is designed by using the traditional state feedback method, since the linearization calculation is repeated at different balance points to maintain the stability of the system.Besides, the actuator saturation should be taken into consideration due to the input constraint in high-speed flight.Aiming at the above problems, a two-step method was developed.Firstly, a model reference controller based on Linear Parameter Varying (LPV) system was designed.The system matrix and feedback gain of the controller were calculated by using singular value decomposition and linear matrix inequation, respectively.So the tracking response of the command signals could be realized after the flight state changes.Then, considering the case of actuator saturation, an anti-windup compensator was introduced, and LQR optimal control theory was used to calculate the compensator gain so as to limit the control input.Simulation result shows that:The designed controller has smaller overshoot and shorter adjustment time, and the calculation amount of the controller design is reduced effectively.