Steering law of control moment gyros using optimization of initial gimbal angles for satellite attitude control

Yasuyuki Nanamori, Masaki Takahashi

Research output: Contribution to journalArticle

3 Citations (Scopus)

Abstract

Control Moment Gyros (CMGs) has been expected to be applied to an earth observing satellite in recent years. However it is not easy to control it because CMGs has a singularity condition and a major source of disturbance. Although there are many singularity avoidance logics, these optimal methods from the viewpoint of singularity avoidance may cause inner disturbance by fast and furious motion of gimbals in avoiding singularity. From the previous background, this paper presents a new but simple CMGs 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 CMGs.

Original languageEnglish
Pages (from-to)2698-2704
Number of pages7
JournalNihon Kikai Gakkai Ronbunshu, C Hen/Transactions of the Japan Society of Mechanical Engineers, Part C
Volume74
Issue number11
Publication statusPublished - 2008 Nov
Externally publishedYes

Fingerprint

Attitude control
Satellites
Earth (planet)
Control systems

Keywords

  • Attitude control
  • CMG
  • Disturbance
  • Gimbals
  • Manipulability
  • Satellite
  • Singularity

ASJC Scopus subject areas

  • Mechanical Engineering
  • Mechanics of Materials
  • Industrial and Manufacturing Engineering

Cite this

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AB - Control Moment Gyros (CMGs) has been expected to be applied to an earth observing satellite in recent years. However it is not easy to control it because CMGs has a singularity condition and a major source of disturbance. Although there are many singularity avoidance logics, these optimal methods from the viewpoint of singularity avoidance may cause inner disturbance by fast and furious motion of gimbals in avoiding singularity. From the previous background, this paper presents a new but simple CMGs 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 CMGs.

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