Application of Optimal Control in Guidance Law

Abstract:
Based on the optimal control theory, the optimal control theory is used to study guidance accuracy with terminal landing angle constraints. The optimization problem is to propose a terminal guidance law that meets both the miss distance requirement and the expected terminal landing angle. The guidance system can measure all kinds of signals, such as the relative position of the missile and the target, the angle and complete the calculation, calculate the best attack angle and path, and then generate guidance instructions to strike the target. On the basis of linearization, the optimal control theory is introduced, the terminal guidance law of the missile is studied, the optimal performance index is first designed, and then the guidance law with terminal landing angle constraint is derived, which consumes less energy. The simulation results show that the optimal guidance law with landing angle constraint is derived. Its superiority and feasibility are proved by numerical simulation.