航天器的自适应鲁棒姿态控制器设计  

Adaptive robust attitude maneuvering control for rigid spacecraft

作　　者：袁国平[1] 史小平[1] 李隆[1] 

机构地区：[1]哈尔滨工业大学控制与仿真中心,黑龙江哈尔滨150001

出　　处：《系统工程与电子技术》2012年第12期2524-2528,共5页Systems Engineering and Electronics

基　　金：某预研基金资助课题

摘　　要：针对带有转动惯量不确定性和干扰的航天器姿态控制问题,提出了一种基于鲁棒自适应方法的解耦控制算法。首先,将航天器模型变换成3个子回路分别进行控制器综合,并利用自适应方法对模型中的不确定参数进行补偿。然后,将外干扰力矩和自适应补偿误差视为复合扰动,通过鲁棒控制算法对其进行抑制,保证了姿态跟踪误差在期望的范围内。最后,数字仿真结果表明了所设计的控制器在处理航天器姿态控制问题的正确性和有效性。A decoupling attitude control algorithm based on adaptive robust control method is proposed for spacecraft in the presence of external disturbances and uncertainties of moment of inertia. Firstly, the spacecraft model is divided into three independent loops for respective controller synthesis and the adaptive method is adopted as a compensation for the parameters uncertainties. Secondly, regarding the external disturbances and the adaptive compensation errors as composite disturbances, the robust control law is used to attenuate the effect to ensure that the attitude tracking errors is kept within a desired range. Finally, the validity and effectiveness of the proposed method for the spacecraft attitude control are well testified via numerical simulation results.

关 键 词：自适应鲁棒控制 姿态机动 非线性系统 不确定性 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]