Fixed-time spacecraft attitude stabilization using homogeneous method

Fixed-time controller features an upper bound of settling time, which does not depend on the initial states of control system. In view of that nearly all the existing fixed-time control methods are based on the terminal sliding mode technique, the problem of fixed-time attitude stabilization of a rigid spacecraft is investigated based on a homogeneous method in this paper. Numerical simulations are performed to illustrate the effectiveness of the proposed fixed-time control scheme in the spacecraft attitude control system.