Abstract:

Based on the eigenstructure assignment and model following theories for linear systems, and the optimization tool, a multi model switching control policy with the capability of chattering attenuation is proposed, and applied to the pitch/yaw channel autopilot design of BTT missile. Several characteristic operating points are selected along the missile's whole flight trajectory, and the time invariant systems, which describe the pitch/yaw motion of BTT missile, are then set up. For each time invariant system, based on the eigenstructure assignment method, a feedback controller is designed to stabilize it, and a feedforward controller is designed by using the model following method, so that the closed system is able to track the guidance command. While the missile's flight state comes from the neighborhood of an operating point into that of the next one, the controller switches from one into another. Because of the abrupt variation of the controller, chattering is inevitable in the switching process. The authors treat the difference of the two system's outputs on a switching point as the evaluation index, and expect to attenuate the chattering by selecting the degree of freedoms of the controller. Simulation results demonstrate the validity of the proposed method in command tracking and switching chattering attenuation.

Key words: BTT missile, autopilot, mult i-model switching, eigenst ructure assignment, chattering