推力方向制約付き月軟着陸の最適化 Optimization of Lunar Soft Landing with Constraints of Thrust Direction

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The purpose of this paper is to obtain the optimum trajectory for the fuel minimum guidance phase of lunar soft landing experiments NASDA is planning. In this phase the lander descends to a few km altitude from 15km altitude realized by the Hohmann transfer from the circular orbit of 100km altitude. Characteristics of the phase are thrust direction constraints near the terminal point, which are (A) thrust direction at the terminal point must be vertical and (B) change rate of the thrust direction must be smaller than the specified value. It was obtained the minimum thrust should be used for the latter half of the interval just before the terminal point where the thrust direction is changing largely. The optimum thrust direction except the region where the thrust direction is changing largely coincided with the one for no constraints. This fact will ease the derivation of guidance law.

収録刊行物

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

    日本航空宇宙学会誌 = Journal of the Japan Society for Aeronautical and Space Sciences 45(527), 744-751, 1997-12-05 

    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)
    10002862309
  • NII書誌ID(NCID)
    AN00189072
  • 本文言語コード
    JPN
  • 資料種別
    ART
  • ISSN
    00214663
  • NDL 記事登録ID
    4353053
  • 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
    Z16-436
  • データ提供元
    CJP書誌  NDL  J-STAGE 
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