Design Of VSC for overload control in high angle-of-attack missile

Abstract

The purpose of this paper is to design a overload control system of the high angle-of-attack missile. First, the problems of the high angle-of-attack missile in flight process and the advantages of the variable structure control theory are analyzed. Then, the longitudinal motion model is built. Based on the accelerometer flight control system, the sliding mode controller and the control law are designed. The performance of the controller is tested under parameter perturbation in simulink. The result shows that the variable structure autopilot of overload is superior to the traditional design under the condition of the high angle-of-attack flight.