Application of Anti-Windup Based on Adaptive Variable Parameter in Guided Rocket Autopilot

During the flight of guided rocket, the deflection angle of rudder is affected by the mechanical limit, and its output deflection angle cannot be increased indefinitely. In order to eliminate steady-state error, autopilot often adopts PI integral structure. However, in some flight stages, the rocket is prone to the situation that the rudder cannot fully meet the acceleration command when it reaches the mechanical limit position. At this time, the accumulated error value in the integrator will continue to increase, making the integral saturation and affecting the response speed of the acceleration instruction. In this paper, an anti-windup control method with adaptive variable control parameters is proposed. It is proved that the method can satisfy the rapid response to the acceleration command in extreme cases, and the structure is simple and easy to implement in engineering.