Spacecraft Attitude Control Using Nonsingular Finite-Time Convergence Terminal Sliding Mode

Finite-time convergence control strategies based on adaptive Nonsingular Terminal Sliding Mode are proposed for spacecraft attitude tracking control subject to external disturbances and actuator faults. The designed attitude tracking controller meets the multi-constraints, and has singularities avoidance attributes. It is further shown that the controller with parameter adaptations is independent from bound of external disturbances. The Lyapunov stability analysis shows that the controller designed in this paper can guarantee the fast convergence of the closed-loop system, and has a good fault tolerant performance on actuator faults under the multi-constraints on external disturbances and actuator faults. Numerical simulation verified the good performance of the controller in the attitude tracking control.