Abstract: The purpose of this paper is to study the 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 nonlinear variation of aerodynamic parameters are treated as bound-limited movement of linear parameters. Based on the accelerometer flight control system, the sliding mode controller and the control law are designed. The performance of the controller is test 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.

Key words:  high angle-of-attack, sliding mode, parameter perturbation, air defence missile