Terminal Angle Constraint Guidance Law Based on SDRE Method

In this paper, a new guidance law based on SDRE method is designed to solve the problem of terminal angle constraint of a missile by using nonlinear kinematics model and dynamic model of a missile. The constraint of collision angle can be realized by the guidance law under the condition of satisfying the requirement of miss distance of terminal guidance. In addition, the guidance instructions in the form of feedback and the analytic solution of the guidance law are obtained in the two-dimensional plane. Compared with previous terminal guidance methods, the advantage of the method is that it does not depend on the estimation of the time to go. The effectiveness of the proposed guidance law can be verified by digital simulation.