The design problem for autopilot systems of homing missiles is investigated considering the guidance loop dynamics. The closed-loop guidance system is regarded as a reference model and the model reference tracking theory is employed to design the autopilot system. A parametric approach for the design of the feedforward tracking compensator and the global stabilizing feedback controller is given. According to the proposed method, the states of the guidance system are incorporated directly into the controller of the autopilot system and consequently the guidance loop dynamics can be well considered during the autopilot design procedure. Simulation results show the effect of the proposed method.
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