Adaptive control at launching using three loop autopilot

In order to guarantee the precise initial flight trajectory, control the missile disturbance of large disturbance torque, three loop adaptive autopilot was researched. The characteristics of the projectile and three loop autopilot instruction formation characteristics were analysed. From equivalent pitching angle of lateral acceleration feedback loop, combined with the instruction of generalized error, autopilot structure was simplified, and three loop autopilot adaptive control law and stability were designed. The test data show that when disturbance torque was 600Nm, the attitude angle generalized error was -4.4°. In the time lasted about 15s, late trajectory accuracy was within 1.0°. Three loop autopilot adaptive control law was able to control the disturbance of initial trajectory and adapt to dynamic characteristics changes, control system stability. It was the initial trajectory accurate solution method of flight.