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

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Citation (Scopus)

Abstract

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.

Original languageEnglish
Title of host publicationAstrodynamics 2007 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Astrodynamics Specialist Conference
Pages2337-2352
Number of pages16
Publication statusPublished - 2008 Dec 1
Externally publishedYes

Publication series

NameAdvances in the Astronautical Sciences
Volume129 PART 3
ISSN (Print)0065-3438

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science

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