Missile Guidance System Design Using Optimal Control

Abstract

method has been presented and used to get the most favorable intercept guidance law in order to ensure an accurate and effective missile-target tracking and hitting. Finally, simulation results have been presented and discussed to study the dynamics of an open loop 6DOF missile model and show the aptitude of the performed optimal control law of a 3DOF missile guidance system to track and hit a fast moving and maneuvering target.