極超音速気流中における形状記憶合金製フレームを有する柔構造体エアロシェルの展開実験 Deployment Tests of Membrane Aeroshell with Shape Memory Alloy Frame in a Hypersonic Flow

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抄録

For re-entry missions, deployable-flexible aeroshell is expected to have an advantage because it can significantly reduce the aerodynamic heating due to deceleration at relatively high altitudes thanks to its small mass and large area (i.e. low ballistic coefficient), while it can be stowed compactly during the launch phase. In this study, we propose deployable aeroshell supported by the shape memory alloy frame, which can deploy itself automatically by receiving the aerodynamic heating. The present system neither requires additional sensors nor acuators. It seems suitable for small re-entry capsule because of its simple, fault-tolerant and low-cost nature. It is experimentally demonstrated by the wind tunnel tests that a model having a membrane aeroshell with a shape memory alloy frame is smoothly deployed and kept stable in hypersonic flow.

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 55(646), 561-562, 2007-11-05 

    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)
    10021152638
  • NII書誌ID(NCID)
    AA11307372
  • 本文言語コード
    JPN
  • 資料種別
    NOT
  • ISSN
    13446460
  • データ提供元
    CJP書誌  CJP引用  J-STAGE 
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