Finite-time attitude synchronization for spacecraft formation flying via output feedback

In this paper, finite-time attitude synchronization problem for spacecraft formation flying is investigated without angular velocity measurement. An output feedback control law combined with a filter is developed by using the homogenous system theory, which can ensure the attitude of spacecraft in the formation synchronized in a finite time with zero finial angular velocity. Rigorous proof is carried out to demonstrate finite-time stability of the closed-loop system theoretically. Finally, numerical simulation results show the effectiveness of proposed control law.