Robust control applied to missile guidance

Abstract

This paper introduces an application of the modern robust control theory to the missile guidance problem where the successful intercept criterion has been defined in terms of minimizing the terminal miss distance. This output feedback controller steers the initial state of the missile system into an ellipsoidal bounding set in a specified flight time. The underlying system in this problem is a time-varying uncertain linear system in which the uncertainty satisfies a certain integral quadratic constraint. The performance of the robust controller was compared with output LQR feedback controller and proportional navigation (PN) controllers.