Integrated Guidance and Control Design for Guided Projectile Using Sliding Mode Method

Abstract

According to the characteristics of special launch and flight environment such as high dynamic and large disturbance of guided projectile, the separate design method of traditional guidance system and control system will bring large errors, even affect the stability of the system, and the accuracy of projectile hitting the target is poor. In this paper, the guidance and control integrated control law of guided projectile is designed based on the sliding mode variable structure theory. The correctness, accuracy and stability of the designed control law are verified by numerical simulation. Numerical simulation shows that the guidance control integrated control law designed by sliding mode control theory can still have high control accuracy in the case of large perturbation. At the same time, Monte Carlo simulation shows that this method can meet the needs of engineering.