FIXED-TIME CONTROL DESIGN FOR SPACECRAFT ATTITUDE STABILIZATION

Fixed-time controller features an upper bound of settling time, which does not depend on initial states of control system. In view of that nearly all the existing fixed-time control methods are based on the terminal sliding mode, a new fixed time control law is developed by using a special Lyapunov function with a power integrator form for the spacecraft attitude stabilization in the presence of external disturbance. The bounded convergence time is given through a strictly theoretical deduction. Numerical simulations are performed to illustrate the effectiveness of the proposed fixed-time control scheme in the spacecraft attitude control system.