The research focuses on the interception guidance method during the boost phase

Abstract To effectively intercept enemy ballistic missiles during the boost phase, the interceptor must possess high velocity and acceleration capabilities, necessitating a guidance mechanism capable of maneuvering precisely with the target. This paper analyzes the characteristics of booster phase interceptor missiles based on relevant research and establishes a trajectory simulation model. Considering the required guidance performance throughout the missile’s flight process, we design guidance laws for the initial, mid-course, and final stages to conduct trajectory simulations. The results demonstrate that the guidance law proposed in this paper outperforms the conventional guidance mechanism regarding miss distance, ballistic angle, and required overload. Moreover, it satisfies the interception accuracy requirements during the boost phase interception.