Integrated design of ballistic missile guidance and autopilot using adaptive sliding control with 5 DOF inputs

In this research, we propose an integrated controller of missile guidance and autopilot systems based on adaptive sliding-mode control with actuators, mainly consisting of thrust vector control and divert control system, for the task of intercepting of a theater ballistic missile. The aim of the present work is to achieve bounded target interception under the mentioned 5 degree-of-freedom (DOF) control such that the distance between the intercepting missile and the target missile will enter the range of triggering the missile's explosion. First, the adaptive sliding-mode guidance law of the intercepting missile considering external disturbances is designed to minimize the distance between the center of the intercepting missile and that of the target missile while coping with variation of missile's mass. Next, a quaternion-based adaptive sliding-mode autopilot controller is developed to track the attitude command while grasping the variation of missile's inertia and uncertain aerodynamic force/wind gusts. Finally, the stability of the overall system is analyzed thoroughly via Lyapunov stability theory to achieve the integrated controller design of missile guidance and autopilot systems based on adaptive sliding-mode control. Furthermore, Extensive simulation results are conducted to validate the effectiveness of the proposed integrated guidance and autopilot systems by use of the 5 DOF inputs.