Abstract
Flight control system plays an important role in the process of missile designing. The quality of flight control system will affect the missile's performance significantly. In this article, we design a flight control system using variable structure control theory. Firstly, we establish a mathematical model of the missile and the basic content of variable structure control theory is introduced. Next chapter are mainly aiming at designing the control system of the missile's normal overload. Consequently, the linearized missile's normal overload is designed by using the mathematical model in chapter two. Then the variable structure controller is designed. In addition, we use the variable structure controller to optimize the linear normal load control system. The numerical simulation of two different control methods are given. And the result illustrate that the robustness of the control system based on variable structure theory are better.
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