航天器固定时间姿态饱和控制

For the spacecraft attitude control system subject to unknown external disturbances and actuator saturation，a robust adaptive anti-saturation fixed-time control strategy is proposed to address the attitude tracking control problem. Initially，a non-singular full-order terminal sliding mode surface，which converges to zero within a fixed time，is designed utilizing homogeneity theory. Subsequently，by integrating this sliding mode surface with adaptive control，a robust adaptive anti-saturation controller is developed. This controller ensures that the spacecraft system's state tracks the desired command within a fixed time frame. The effectiveness of the proposed control strategy is substantiated through both theoretical analysis and numerical simulation，providing a high-precision control method for spacecraft attitude tracking under the aforementioned constraints.