Singularity avoidance of control moment gyros using optimization of initial gimbal angles and application to multi target pointing for satellite attitude control

Yasuyuki Nanamori, Masaki Takahashi, Shigemune Taniwaki, Kazuo Yoshida, Yoshiaki Ohkami

研究成果: Conference contribution

1 被引用数 (Scopus)

抄録

Control Moment Gyros (CMG) has been expected to be applied to an earth observing satellite in recent years. However it is not easy to control it because CMG has a singularity condition and a major source of disturbance. Although there are many singularity avoidance logics, these use much resource of computer mounted on satellite. From the previous background, this paper presents a new but simple CMG steering law using preferred initial gimbal angles and null motion for high accurate attitude control system on an agile satellite. Preferred initial gimbal angles are decided by evaluating function considering inner state of CMG.

本文言語English
ホスト出版物のタイトルAstrodynamics 2007 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Astrodynamics Specialist Conference
ページ2337-2352
ページ数16
出版ステータスPublished - 2008 12 1
外部発表はい

出版物シリーズ

名前Advances in the Astronautical Sciences
129 PART 3
ISSN(印刷版)0065-3438

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science

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