Simple Analysis of Prolate-Spin Attitude Stability

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抄録

How can a prolate satellite spinning about its axis of minimum moment of inertia be attitude-stabilized using dual spin? To this question, we find a simple, clear answer. We replace the satellite with an equivalent frame model and describe its attitude motion as small deviations from its nominal attitude. We show that a friction-like torque applied to the spin axis reduces its nutation motion, and that a similar torque is generated by a nutation damper on a de-spun platform. Thus, we derive a simple attitude-stability theory using minimal mathematical analysis. This theory is applicable to the spin stabilization of geosynchronous communication satellite.

収録刊行物

  • Transactions of the Japan Society for Aeronautical and Space Sciences

    Transactions of the Japan Society for Aeronautical and Space Sciences 50(170), 246-250, 2008-02-04

    THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

参考文献:  5件中 1-5件 を表示

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    Satellite Communications, 2000

    被引用文献1件

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    被引用文献1件

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    HUGHES P. C.

    Satellite Attitude Dynamics, 1986

    被引用文献1件

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    AGRAWAL B. N.

    Design of Geosynchronous Satellite, 1986

    被引用文献1件

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    Satellite Dynamics and Control, 1997

    被引用文献1件

各種コード

  • NII論文ID(NAID)
    10021152465
  • NII書誌ID(NCID)
    AA0086707X
  • 本文言語コード
    ENG
  • 資料種別
    ART
  • ISSN
    05493811
  • NDL 記事登録ID
    9383000
  • 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
    Z53-M236
  • データ提供元
    CJP書誌  NDL  J-STAGE 
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