Optimal Guidance Solution for Impact Angle Control Based on Linearization about Collision Triangle

Abstract

AbstractIn this paper, an optimal guidance problem is investigated where specific missile-target geometry at the time of the intercept of, or a terminal impact angle with respect to, a maneuvering target is prescribed. The kinematics is linearised to obtain a closed-form optimal solution and the proposed approach addresses the question of how to accomplish the linearization in a right manner. We use, as the basis of linearization, the perfect (or zero effort) collision triangle for the impact angle control problem which varies depending on the value of the prescribed impact angle, and solve a linear optimal guidance problem. The performance of the resultant guidance law is illustrated by performing some numerical simulations and the selection of a guidance variable that effectively capture the distance between the missile and the zero effort collision triangle is discussed.