挠性航天器大角度机动的振动抑制控制  

Vibration Suppression Control of Flexible Spacecraft During Large Angle Attitude Maneuver

作　　者：刘军[1] 韩潮[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《系统仿真学报》2008年第7期1880-1883,共4页Journal of System Simulation

摘　　要：建立了带变速控制力矩陀螺群的挠性航天器的动力学模型,应用误差四元数来描述姿态运动,将星体大角度姿态机动问题转化为误差四元数的调节问题。针对挠性航天器三轴同时姿态机动时挠性附件的振动抑制问题,提出了基于动态输出反馈控制的振动抑制方法,设计了仅利用姿态四元数而无需以角速度测量、挠性变形位移及速率测量作为反馈的动态控制规律。基于Lyapunov方法证明了所设计的动态控制器保证了姿态的渐近稳定和模态振动的衰减。基于Matlab/Simulink进行了仿真验证,结果表明了所提出的控制方法的可行性和有效性。The dynamical equations of a flexible spacecraft with VSCMGs （variable speed control moment gyros） were established, and the attitude kinematics was described by the error-quaternion so that the large angle maneuver of the satellite could be converted into the problem of regulation of the error-quaternion. A dynamic controller was proposed for rest-to-rest flexible spacecraft attitude maneuver with the vibration suppression. The controller did not need the knowledge of modal variables and spacecraft angular velocity. The dynamic controller capable of performing maneuvers for the flexible spacecraft by only using attitude measures, was used to dampen the vibration of flexible booms induced during the maneuvers. The Lyapunov technique was applied to design this dynamic controller, which ensured the stability of the system. Based on Matlab/Simulink, the simulation results reveal the interest and the practical feasibility of such a control scheme.

关 键 词：变速控制力矩陀螺 挠性航天器 姿态机动 振动抑制 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]