Integrated guidance and control based on high-order sliding mode method

Under the coupling effect between guidance system and control system, the performance of traditional guidance and control method is limited. Therefore, integrated guidance and control (IGC) method is proposed to solve the problem. This method is characterized by the guidance loop and control loop which are considered as a whole part in accordance with the information of the relative motion between the aircraft and the target or trajectory, directly generating a command of actuator angle deflection. In this paper, simplifying kinematics and dynamics equations of the aircraft are primarily based on assumptions. Then, sliding mode controller is designed to make the whole system asymptotically stable. When designing the system controller, it uses a high-order sliding mode controller instead of the commonly backstepping design method. The advantages of IGC over ordinary method is that it not only simplifies the design process and shortens the time cost, but also increases the potential and reduces the manufacturing cost of the aircraft. On the basis of the experimental results, the high-order sliding mode controller can guarantee the stability of the aircraft system, which also has fast responding time and can intercept the target accurately.