Finite-time attitude tracking control for spacecraft with input saturation

In view of the spacecraft attitude tracking system, two finite-time controllers with input saturation are designed by using the hyperbolic tangent function and the auxiliary system under the disturbed and undisturbed condition. The hyperbolic tangent function can strictly guarantee that the control torque of the sapcecraft is bounded. The system which can quickly converge to the equilibrium point is asymptotically stable and finite-time stable by using Lyapunov theory. Numerical simulations also demonstrate the effectiveness of the proposed control scheme. ©, 2015, Northeast University. All right reserved.