Robust control system design for missiles based on theory of time-delay and uncertainty

A state feedback controller is designed for a closed-loop control system with parameter and input uncertainty and time-delay which can meet the requirements of closed-loop asymptotic stability and satisfy H_∞ performance at the same time. A linear discrete model for a missile control system is built and the method proposed is applied to the missile pitch-yaw channel autopilot design. The simulation results show that the proposed control system design method can ensure that the missile autopilot track the reference inputs quickly and demonstrate good performance of anti-jamming under the condition that the aerodynamic parameter perturbation is ±30% and the delay time is a sampling period. In addition, the problem of instability caused by uncertainty and time-delay is solved.