Model Following Control Approach for Missile Autopilot Design

Abstract

This paper presents a model following control strategy to design missile roll, pitch and yaw autopilots. The proposed approach is characterized by the facts that the autopilot is of constrained complexity, thus lowering the computing costs, and is relatively easy to implement. The proposed autopilot structure changes minimally over the full ight envelope, providing good missile performance with lower computational cost than classical scheduling techniques. The study of a nonlinear missile autopilot showed satisfactory target tracking performance as well as appropriate roll angle stabilization.