Design of impact angle control guidance laws via high-performance sliding mode control

Abstract

In this article, a new impact angle control guidance law for a stationary or slowly moving target is developed using the high-performance sliding mode control methodology. The law can produce various missile trajectories by changing the damping ratio of the guidance loop motion during interception in order to achieve not only the satisfaction of the terminal impact angle constraint but also the additional guidance objectives. Since the proposed guidance law is given using the general function term, different forms of guidance laws can be designed by choosing specific functions. It can also lead to zero magnitude of the guidance command at the terminal time. The first-order lag system and acceleration disturbances such as measurement noise are considered in the guidance law design. These properties can provide the advantages for the guidance operation, whereas other impact angle control guidance laws may not easily allow this. Numerical simulations are performed to investigate the characteristics and performance of the proposed guidance law. Some application results of the proposed guidance law are also shown.