Missile guidance with constrained terminal body angle

Abstract

A novel missile guidance law that simultaneously minimizes the miss distance and imposes a predetermined terminal body angle is presented. The guidance law is derived by analyzing an interception scenario within the framework of a linear quadratic (LQ) terminal control problem. The derivation is for first order linear missile dynamics and a non-maneuvering target. The performance of the proposed guidance law is demonstrated in a planar interception scenario.