最適化手法を用いたスペースプレーンの上昇フェーズにおける成立性 Feasibility Study for Spaceplane's Concepts in Ascent Phase Using the Optimization Method

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This paper investigates and compares the effect that the airframe configuration and installed engine have on the feasibility of a space plane. For this purpose, multi-disciplinary optimization of the aerodynamic shape and ascent flight path of the airframe was carried out assuming two types of airframe configurations, single stage to orbit (SSTO) and two stage to orbit (TSTO), and two types of propulsion systems, turbine-based combined-cycle (TBCC) and rocket-based combined-cycle (RBCC). The optimization calculation was performed using the stochastic process optimization technique (SPOT) that we have proposed. In this study, to reduce the computational load, the airframe weight and aerodynamic performance are estimated based on historical statistics. According to the results of the optimization, the TSTO configuration equipped with a RBCC engine had the highest feasibility. Sensitivity analysis was carried out for the time history of the angle of attack, and the structure of the characteristic solution space that reflects the airframe configuration and the installed engine was clarified. As a result, the importance of steering controls for each flight condition could be assessed.

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 59(694), 291-297, 2011-11-05

    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)
    10030274978
  • 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
    023334202
  • NDL 請求記号
    Z74-B503
  • データ提供元
    CJP書誌  NDL  J-STAGE 
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