Design of robust H∞ controller for BTT missile based on parameter uncertainty theory

In order to solve the instable problem of system caused by aerodynamic parameters uncertainty with BTT missile at high speed, a robust H_∞ controller is designed based on the parameter uncertainty theory. The main idea of the method is to consider the maximum value of uncertain parameter and to build a maximum uncertain matrix, by constructing and solving the Riccati equation; the parameters of a robust state feedback controller are obtained based on LMI method. In the paper, a certain type of BTT missile is taken as an example, and the roll and the pitch-yaw channels are designed independently. The simulation results show that the autopilot designed can inhibit the effects of parameters uncertainty effectively and possess strong robust performance.