研究了基于时间尺度分离和滑动模态的航天器姿态控制问题.利用时间尺度分离的方法将航天器状态分成对应于姿态角的慢子系统和对应于姿态角速度的快子系统,从而构成内外两个控制回路,外回路跟踪给定的姿态角,内回路跟踪设计的姿态角速度.针对每个子系统分别设计PI型的滑动平面,在Lyapunov稳定性分析的基础上,推导出两个回路的变结构控制律.仿真结果证明了所提控制方法能够克服大幅值、高频率的外部干扰,比传统控制方法具有更高的精度和鲁棒性. The spacecraft attitude control problem based on time-scale separation and sliding modes is studied. The spacecraft state is divided into subsystems corresponding to attitude angles and fast sub-systems corresponding to attitude angular velocities by time-scale separation method, The control loop and the outer loop are used to track the given attitude angles and the attitude angular velocities of the inner loop tracking design.For each subsystem, a PI-type sliding plane is designed respectively. Based on the Lyapunov stability analysis, the variable structure of the two loops Control law.The simulation results show that the proposed control method can overcome large amplitude and high frequency external disturbances and has higher accuracy and robustness than the traditional control methods.