A Non-singular Terminal Adaptive Fuzzy Sliding-Mode Controller

Abstract

Attitude Control System(ACS) with high performance, high precision, and high reLiabiLity is the kernel technology of the research of spacecraft, which directly affects the whole performance of spacecraft. Hence, a non-singular Terminal adaptive fuzzy sLiding-mode controller is proposed to come true the high performance control. The theory of this controller is to introduce the time mechanics-Terminal mode to the sLiding-mode control, which can reaLize the convergence of spacecraft attitude in Limited time, in order to enchance the performance of fast response. Meanwhile, the chattering of sLiding-mode controller has been effectively suppressed by the estimation of adaptive fuzzy algorithm, which improves the control precision. Furthermore, a adaptive approach has been designed to estimate the different kinds of space environment disturbance and model error during the pocess of spacecraft control, which further improves the control performance. At last, the simulation results demonstrate the high reLiabiLity and advantages of the controller.