Terminal sliding mode attitude control for satellite

A finite time control method based on terminal sliding mode (TSM) is presented for satellite attitude control system in this paper. Using the concepts of finite time stability and TSM, a finite time stable sliding mode is designed, and then a continuous TSM finite time controller using the inverse dynamic method is designed for the second-order dynamic system of the satellite. In order to eliminate the oscillation, a new type of saturation function is also designed to replace the conventional symbolic function. The validity for the proposed algorithm is testified through simulations.