Control of Electromagnetic Current at Final Docking Phase of Small Satellites

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概要

• 論文の詳細を見る

• 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 doesn't require any fuel 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.

• 一般社団法人 日本機械学会の論文

著者

• KOBAYASHI Nobuyuki

  Aoyama Gakuin University

• OZAWA Satoru

  Japan Aerospace Exploration Agency

• YAMAKAWA Hiroshi

  Waseda Univ. Dept. of Mechanical Engineering

• TORISAKA Ayako

  Aoyama Ggakuin Univ. Dept. of Mechanical Engineering

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• Preface
• Control of Electromagnetic Current at Final Docking Phase of Small Satellites

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