Abstract:

A sliding mode control method based on finitetime control technology is designed for the spacecraft attitude tracking control system in the presence of uncertain term. The tracking error system can not only be controlled to the sliding manifold from any initial state in finitetime but also converge to zero along the sliding manifold in finitetime. Rigorous mathematical proof is also given. In order to avoid the chattering problem, the sign function in control law is substituted by a new saturation function.

Key words: attitude , control,  , finitetime , convergence,  , sliding , mode , control,  , spacecraft