Finite-time attitude tracking control for spacecraft with uncertainn actuator configuration

摘要

The issue of attitude tracking control with finite-time convergence is investigated for spacecraft in the presence of external disturbance and uncertain actuator configuration as well. More specifically, in view of backstepping technique, the attitude quaternion can firstly track the demanded command in finite time under the virtual control law by introducing a novel terminal sliding manifold. Then, the finite-time convergence to the sliding mode of the angular velocity error will be achieved un