中文摘要：

针对反作用飞轮安装存在偏差的过驱动航天器姿态跟踪问题，提出一种有限时间姿态补偿控制策略．通过设计自适应滑模控制器保证实现对不确定性转动惯量与外部干扰的鲁棒控制，同时实现对飞轮安装偏差的补偿控制，并应用Lyapunov稳定性理论证明了该控制器能够在有限时间内实现姿态跟踪控制．最后，将该控制器应用于某型航天器的姿态跟踪控制，仿真结果验证了所提出方法的有效性．

英文摘要：

A finite-time control scheme is presented to address the attitude tracking problem of over-actuated spacecraft, in which reaction wheel misalignment, external disturbance and uncertain mass of moment inertia are considered. A finite time controller using adaptive sliding mode control technique is developed. It can guarantee finite-time reachability of the given attitude motion even in the presence of external disturbance＇s, and uncertainties in the configuration matrix due to reaction wheel misaiignment and mass of moment inertia. Numerical simulation results of an application to spacecraft show the effectiveness of the proposed attitude tracking control law.