GUIDANCE OF A HOMING MISSILE VIA NONLINEAR GEOMETRIC CONTROL METHODS

This paper examines the guidance problem of an acceleration constraine d homing missile when the initial missile heading is far from intercep t course. A guidance strategy based on the theory of feedback lineariz ation is presented, and simulation results are given comparing miss di stance performance of the feedback linearized guidance law to proporti onal navigation. It is demonstrated that the feedback linearized guida nce law is a viable option under these conditions.