Joint optimal design of missile guidance and control law for minimizing miss distance

Missile guidance law and control law are separately designed in the real application. This design leads to unsatisfactory performance of the whole guidance and control system. The method of integrating guidance and control has not yet been achieved in engineering practice. This paper proposes a method of joint optimization, aimed to minimize the miss distance, for both guidance and control parameters. That method is based on guidance and control designed separately. A robust sliding mode control law is designed to reduce the chattering through treating the discontinuous part of conventional sliding mode control law into continuous. However, such robust design lowers the guidance accuracy. With regard to the dynamics of missile body, a liner quadratic optimal controller is designed simultaneously. It is hard to design the parameters of the guidance and control for their interactions. A genetic algorithm with global optimization ability was highly used to optimize the parameters of guidance and control system. Simulation result shows that the design meets the expected demand and lowers the miss distance effectively.