A novel scheme for ATBM guidance design

This paper presents a Anti-Tactical Ballistic Missile (ATBM) guidance law for controlling the lateral acceleration of a missile. Three strategic phases are proposed in the engagement process. A recursive form of solution is derived for the discrete Linear-Exponential-Quadratic-Gaussian (LEQG) performance criterion. The proposed LEQG control gain can explicitly take both the system and measurement noise covariances into consideration. It is shown that the critical items of guidance performance such as the mean and standard deviation of miss distances for the proposed method are lower. Some guidelines for applying the method are also given.