Singularity problem of control moment gyro cluster with vibration isolators

作     者：Cui Yinghui Zheng Gangtie 

作者机构：School of Aerospace Tsinghua University 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2016年第29卷第1期

页      面：238-247页

核心收录：

学科分类：12[管理学] 083002[工学-环境工程] 1204[管理学-公共管理] 120402[管理学-社会医学与卫生事业管理(可授管理学、医学学位)] 0830[工学-环境科学与工程（可授工学、理学、农学学位）] 08[工学] 081105[工学-导航、制导与控制] 0837[工学-安全科学与工程] 0811[工学-控制科学与工程] 

基　　金：sponsored by the National Natural Science Foundation of China(No.11272172) 

主　　题：Satellite Singularity Steering logic Torque error Vibration isolation 

摘      要：As powerful torque amplification actuators, control moment gyros （CMGs） are often used in the attitude control of many state-of-the-art high resolution satellites. However, the distur- bance generated by the CMGs can not only reduce the attitude stability of a satellite but also dete- riorate the performance of optic payloads. Currently, CMG vibration isolators are widely used to target this problem. The isolators can affect the singularity of the CMG system as they are placed between the CMGs and the satellite bus and provide additional freedoms to the CMG system due to their flexibility. The formulation of the output torque of a CMG is studied first considering the dynamic imbalance of its spin rotor and then the deformation angle as a result of the isolator＇s flex- ibility is calculated. With the additional freedoms, the influence of isolator on the singularity problem is studied and a new steering logic to escape from the singular states is proposed.