Suboptimal guidance law design based on discrete dynamic programming

A suboptimal guidance law is designed for commanding satellite-guided projectiles to move with a large landing angle. Based on the characteristics of the projectile trajectory, motion state equations are established. A method for suboptimal guidance law design is presented based on discrete dynamic programming. Using the method, the suboptimal guidance law is obtained by inverse recursion at all the discrete time point. Comparing with the existing analytical design method of guidance laws, its benefit is that the hypothesis of constant or changing slowly for speed is not required, so it can be used in a wide variety of situations. Whole ballistic simulation of six degree-of-freedom is made using the suboptimal guidance law and general proportional navigation law respectively. The proposed method is effective for landing angle increased 100 percent.