The design and analysis of non-singular Terminal adaptive fuzzy sliding-mode controller

Abstract

The control system with fast response speed, high precision of tracking error, and high robust performance is still a kernel technology of Attitude Control System (ACS) of spacecraft, which directly affects the whole performance of spacecraft. Hence, a non-singular Terminal adaptive fuzzy sliding-mode controller is designed to come true the high precision and high performance control. The theory of this controller is to introduce the limited time mechanics - Terminal mode to the sliding-mode controller that improves the system convergent performance and enhances the dynamic response speed. Then to realize the tracking error of spacecraft attitude convergent to zero in “limited time”. Meanwhile, an adaptive fuzzy algorithm has been proposed to suppress the chattering of sliding-mode controller, which improves the control precision better. Furthermore, an adaptive approach has been designed to estimate the different kinds of uncertain space environment disturbance and model errors during the process of spacecraft control, which further improves the control performance. In addition, the convergent time and performance of the controller have been analyzed in this paper. Finally, the simulation results demonstrate the high reliability and advantages of the controller.