Design of Attitude Control Law for Over-Shoulder Launch of Helicopter-borne Air-to-ground Missile

In order to realize the agile turn for over-shoulder launch of helicopter air-to-ground missile, a design method of attitude controller based on sliding mode approach law is proposed. The motion equation of missile is established by the quaternion method. Then the small disturbance linear state space model is adopted to design control system. Through the linear distribution strategy of the air / gas-rudder composite actuator, a simplified control system design model is obtained. The attitude controller is designed based on the sliding mode approach law theory, and the disturbance compensation is adopted to ensure the stability of the system. The simulation results show that the motion equation based on quaternion is effective, and the attitude control system can effectively track the pitch attitude command and meet the performance requirements.