中文摘要：

为了提高航天器姿态控制系统的鲁棒性和动态特性,应用非光滑控制方法设计了连续的姿态控制律,使闭环姿态控制系统具有齐次性,且齐次度为负,实现了姿态控制系统的有限时间稳定,以保证系统状态的动态特性。分别针对标称系统、参数不确定性和外部扰动等情形进行了仿真验证,仿真结果表明所设计的控制律在保证标称系统有限时间稳定性的同时,针对系统的不确定性和扰动具有鲁棒性。

英文摘要：

For the attitude control system of a spacecraft, non-smooth control technique is utilized to improve the robustness and dynamic performance. A continuous attitude control law is given to ensure the homogeneity of the closedloop attitude control system with a negative degree of homogeneity. The resulting attitude control system is finite-time stable, thus guaranteeing the dynamic performance of state variables. Simulation is carried out under the cases of the nominal system and the systems with parameter uncertainties and external disturbances, respectively. The simulation results show that, under the designed control law, the nominal system is finite-time stable, and uncertain systems are robust against uncertainties and disturbances.