Computational Study of Supersonic Parachute on Opening Dynamics

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  • TOKUNAGA Kentarou
    連絡先著者（Corresponding author）：kentarot2017@gmail.com 東京大学大学院新領域創成科学研究科先端エネルギー工学専攻
  • TAKAYANAGI Hiroki
    国立研究開発法人宇宙航空研究開発機構
  • SUZUKI Toshiyuki
    国立研究開発法人宇宙航空研究開発機構
  • MORI Koichi
    名古屋大学大学院工学研究科航空宇宙工学専攻
  • FUJITA Kazuhisa
    国立研究開発法人宇宙航空研究開発機構

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Other Title
  • 超音速パラシュートの開傘ダイナミクスに関する数値解析
  • チョウオンソク パラシュート ノ カイサン ダイナミクス ニ カンスル スウチ カイセキ

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This paper presents the recent efforts to characterize the maximum load experienced by a Disk-Gap-Band type parachute to support Mars landing mission currently considered at JAXA. We simulated the structure-flow interaction with CFD solver coupled with a mass-spring-damper structural model. The interaction was modeled using a 3D elastic canopy model and the immersed boundary method. Flow parameters were computed for a Mach 1.6 free stream condition. The flow field solution was post processed to yield the drag coefficient. In addition, experimental campaigns were conducted at JAXA supersonic wind tunnel facilities. The time histories of the drag coefficient were recorded; the shock shapes and the canopy opening process were visualized by Schlieren diagnostics to provide data and validate the numerical models. The computed averaged drag coefficient was found to be within 5% with the measurement. The breathing frequency computed from Fast Fourier Transform analysis was found to be a similar tendency with the experimental data.

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