航天器姿态跟踪系统自适应滑模控制  

Adaptive sliding mode control for spacecraft attitude tracking system

作　　者：李隆[1] 侯建文[2] 史小平[1] 杨婧[1] 

机构地区：[1]哈尔滨工业大学航天学院,黑龙江哈尔滨150080 [2]上海航天技术研究院,上海201109

出　　处：《电机与控制学报》2015年第2期96-100,108,共6页Electric Machines and Control

基　　金：航天科技创新基金

摘　　要：针对刚体航天器存在外部有界干扰问题,结合自适应控制方法和滑模控制方法的优点,提出并设计了自适应滑模控制器。由于引入自适应律可以实现对外部干扰的在线估计,提高了控制律对外部干扰适应能力,体现了用自适应滑模方法设计的控制器对外部干扰的鲁棒性。将经典滑模控制器中的符号函数用双曲正切函数替换,消除了系统产生的抖振。最后将设计的控制器应用于航天器姿态跟踪控制中,并用Lyapunov稳定性理论分析了闭环系统的渐进稳定性,仿真结果表明该方法对系统外部干扰的影响具有良好的鲁棒性,设计的该控制策略可以实现高精度航天器姿态跟踪控制。An adaptive sliding mode controller combined with the advantage of adaptive control method and sliding mode control method was designed for rigid spacecraft with external bounded disturbances.By using adaptive law,the external disturbances were estimated and the robustness of the control system was improved.System buffeting was eliminated by substituting the signal function with hyperbolic tangent function.Designed controller was applied in spacecraft attitude tracking system,and the asymptotic stability of the close loop system was analyzed by employing Lyapunov stability theory.The simulation results show that this method has a good robustness to external disturbances.High precision attitude tracking control is achieved.

关 键 词：航天器 姿态跟踪 抖振 自适应 滑模 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]