Design of missile autopilot based on fuzzy control

Abstract

The aerodynamic parameters of missile control system will be changed with the variations of the missile flight speed and altitude, etc. In order to reduce the influence of the changing aerodynamic parameters on control performance of missile autopilot, use variable universe fuzzy control to deal with this problem and improve the dynamic and steady-state performance of the missile autopilot. Considering the random disturbance, white noise, wind disturbance, electromagnetic disturbance during the flight, simulation results show that when the variable universe fuzzy PID control and fuzzy PID control missile autopilot are compared, they can both achieve effectively to track the missile guidance command, the former design system has smaller overshoot, shorter response time, higher control precision, more strong anti-disturbance ability, so it is more suitable to design the missile autopilot.