Design and analysis of a moment control unit for agile satellite with high attitude stability requirement
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- 作者：Yao Zhanga ; 1 ; zhangyao@bit.edu.cn" class="auth_mail" title="E-mail the corresponding author ; Mou Lia ; 2 ; 15201622364@163.com" class="auth_mail" title="E-mail the corresponding author ; Zhuoyue Songa ; 3 ; szhuoyue@bit.edu.cn" class="auth_mail" title="E-mail the corresponding author ; Jinjun Shanb ; 4 ; jjshan@yorku.ca" class="auth_mail" title="E-mail the corresponding author ; Xin Guanc ; 5 ; guanxin2007@tsinghua.org.cn" class="auth_mail" title="E-mail the corresponding author ; Liang Tangc ; 6 ; tl614@sina.com.cn" class="auth_mail" title="E-mail the corresponding author
- 关键词：Control moment unit ; Vibration isolation ; Control moment gyro ; Attitude control
- 刊名：Acta Astronautica
- 出版年：2016
- 出版时间：May-June 2016
- 年：2016
- 卷：122
- 期：Complete
- 页码：90-105
- 全文大小：1733 K
文摘
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A presented moment control unit is employed as an actuator for attitude control.
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This unit reduces the required electronics for each CMG and the weight.
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This unit can improve the stability of the satellite attitude.
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Dynamic model of this unit is built and analyzed.
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The application of this unit on a satellite is discussed by numerical simulation.