2ホイールによる人工衛星の最小エネルギマヌーバ軌道 Minimum Energy Maneuver of Satellites by Two Wheels

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This paper discusses on the minimum energy maneuver of a satellite using two reaction wheels. The problem is a rest-to-rest maneuver around the axis, which is perpendicular to each wheel axes. The attitude of satellite is described using the parameters that are presented by Tsiotras et al. The parameters are useful for the description of maneuvers by two wheels. The relation between the optimal maneuver and the moment of inertia is shown analytically and numerically. The results show that the symmetry satellite whose all moments of inertia are same does not have a unique optimal solution. A group of minimum energy trajectories exists. On the other hand, the asymmetry satellite has a unique optimal solution. The numerical solutions show that the wheel on the axis of smaller moment of inertia consumes more energy than the other wheel.

収録刊行物

  • 日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences

    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 51(598), 613-620, 2003-11-05

    一般社団法人 日本航空宇宙学会

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各種コード

  • NII論文ID(NAID)
    10012565808
  • NII書誌ID(NCID)
    AA11307372
  • 本文言語コード
    JPN
  • 資料種別
    ART
  • ISSN
    13446460
  • NDL 記事登録ID
    6767542
  • NDL 雑誌分類
    ZN25(科学技術--運輸工学--航空機・ロケット)
  • NDL 請求記号
    Z74-B503
  • データ提供元
    CJP書誌  NDL  J-STAGE 
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