带可收缩挠性附件受控航天器稳定性分析  

The Stability Analysis of a Controlled Spacecraft with a Retractable Flexible Appendage

作　　者：沈少萍[1] 李智斌[1] 

机构地区：[1]北京控制工程研究所,北京100190

出　　处：《航天控制》2008年第3期49-53,共5页Aerospace Control

基　　金：973计划资助(项目号2002CB312205);刚-柔-控耦合系统几何非线性动力学;控制及实验(批准号:10372015);国家自然基金重点项目(60034010)

摘　　要：带可伸缩挠性附件受控航天器在附件收缩过程中可能因为收缩率设计不当导致系统不稳定,本文利用李亚普诺夫稳定性定理,推导出利用姿态角和姿态角速度反馈设计的PD控制律来实现可伸缩挠性附件在收缩过程稳定性控制的充分条件,对设计满足系统稳定性要求的收缩率和控制律具有指导意义。The controlled spacecraft with a retractable flexible appendage may be unstable during retraction of appendage because of the improper rate of retraction designed. According to the Lyapunov second method, the sufficient conditions which guarantee the stability of the system controlled by the PD law in retracting phase are deduced. These conditions are instructive for designing the proper rate of retraction and control law to satisfy the stabilization requirement of this system.

关 键 词：可收缩挠性附件 航天器 李亚普诺夫稳定性定理 

分 类 号：V414.3[航空宇航科学与技术—航空宇航推进理论与工程]