A computational method for optimal midcourse guidance law with impact gust wind

A computational method is described as a method used for constructing an optimal midcourse guidance law, which is based on the optimal control theory and initial boundary conditions. This proposed guidance law is derived from an optimal control theory with the boundary conditions which allow relative distance between missile and target at the final time, and at a small line-of-sight rate. A numerical simulation verifies the performance of this guidance law with the impact of harmonic wind. The simulation results demonstrate that the quality of effectiveness as well as the applicability of this proposed guidance law.