Control of electromagnetic current at final docking phase of small satellites

Ayako Torisaka, Satoru Ozawa, Hiroshi Yamakawa, Nobuyuki Kobayashi

研究成果: Article査読

7 被引用数 (Scopus)

抄録

This paper proposes a relative position and attitude control method by using only magnetic force with multi-dipole for formation-flying spacecrafts. The control method can be widely applied to re-configurable space structures that architect large structure or reconstruct themselves by assembling basic structural units. One remarkable benefit of the method is that it does not require reaction wheels for relative attitude controls and then fuels for unloading. This paper focuses on current control of dipoles which produce strong nonlinear magnetic forces and suggests a way of linearization by using a corresponding linear reference system. A feasibility of this method and controllability of the strong nonlinear system is discussed, and then the series of position and attitude control simulation are shown, and the future works are suggested in the paper.

本文言語English
ページ(範囲)1540-1549
ページ数10
ジャーナルNihon Kikai Gakkai Ronbunshu, C Hen/Transactions of the Japan Society of Mechanical Engineers, Part C
79
801
DOI
出版ステータスPublished - 2013
外部発表はい

ASJC Scopus subject areas

  • 機械工学
  • 材料力学
  • 産業および生産工学

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