Nonlinear Two-Stage Control Scheme Design for All-Aspect Guidance

This brief develops a two-stage control scheme that incorporates an all-aspect guidance law, enabling the missile to attack a maneuvering target with a predefined terminal angle, irrespective of the initial heading conditions. The fixed-time and finite-time control approaches are utilized in the first and second stages, respectively. A suitable saturation boundary is selected to resolve the smoothness problem of the two control signals at the switching point. The proposed control scheme satisfies the sufficient conditions to ensure that the missile meets the terminal angle constraint and achieves the desired miss distance. The effectiveness and superiority of the proposed methods are demonstrated by some simulation examples.