Auxiliary system based integrated missile guidance and control

Abstract

The problem of integrated guidance and control for homing missiles is considered. A time-varying integrated guidance and control model of the pitch plane is formulated, and further changed into the normal form by nonlinear coordinate transformation. In order to deal with the unmatched and unknown bounded uncertainties, an adaptive auxiliary system is first constructed to approximate the normal plant, and then a sliding mode based controller is designed with the help of the auxiliary system. It is proved that the proposed feedback controller can ensure not only the accuracy of target interception, but also the stability of the missile dynamics. The 6DOF nonlinear missile simulation results indicate the effect and feasibility of the proposed integrated guidance and control design scheme.