著者

能美 亜衣 高橋 正樹

出版者

一般社団法人 日本機械学会

雑誌

日本機械学会論文集 (ISSN:21879761)

巻号頁・発行日

vol.81, no.826, pp.14-00297-14-00297, 2015 (Released:2015-06-25)

参考文献数

12

被引用文献数

1

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This paper proposes a design method of the fault-tolerant attitude control system for spacecraft. In recent years, there has been requirement for accurate and agile attitude control of spacecraft. To meet this demand there has been an increasing use of Control Moment Gyros (CMGs), which can generate much higher torque than reaction wheels that are used as conventional spacecraft actuators. Furthermore, it is important for attitude control systems to be fault-tolerant. In a conventional 4 CMGs system, the CMGs are placed in a pyramid mounting arrangement with a skew angle set to 54.74 degree. The maximum angular momentum of the CMG system is changed according to the skew angle. A suitable skew angle should be designed to consider normal and failure situations. Moreover, the suitable parameters of spacecraft attitude and CMG control systems are changed according to the skew angle. In the proposed method, the skew angle and the parameters of the control system are tuned simultaneously using a genetic algorithm. To verify the fault-tolerance of the proposed method, numerical simulations for the case when one CMG has failed are carried out.