Adaptive, integrated guidance and control law design using sliding-mode approach

The problem of integrated guidance and control for homing missiles was investigated. The integrated guidance and control model of the pitch plane was established, and further changed into the normal form by nonlinear coordinate transformation; in order to deal with the unmatched and unknown bounded uncertainty, an adaptive, nonlinear integrated guidance and control law was designed by adopting sliding-mode approach, to ensure the accuracy of target interception and the stability of the missile dynamics. The 6DOF nonlinear missile simulation results demonstrate the correctness and feasibility of the proposed integrated guidance and control design strategy.