火星着陸探査に向けた大気突入モジュールのエアロシェル開発

機関リポジトリ

書誌事項

タイトル別名
  • Development of Aeroshell Module for Mars Exploration Mission

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抄録

第47回流体力学講演会/第33回航空宇宙数値シミュレーション技術シンポジウム (2015年7月2日-3日. 東京大学生産技術研究所), 目黒区, 東京

47th Fluid Dynamics Conference /the 33rd Aerospace Numerical Simulation Symposium (July 2-3, 2015. Institute of Industrial Science , the University of Tokyo), Meguro-ku, Tokyo, Japan

Lightweight ablative material has been developed in Japan Aerospace Exploration Agency for Mars rover mission in Japan. Basic thermal characteristics of ablating material are obtained by conducting heating tests in high enthalpy facilities. Thermal conductivity measurements and thermogravimetry analysis are made to develop a numerical analysis code to predict the thermal performance of ablator in flight environments. Tensile strength tests are carried out to examine the mechanical performance of ablator. Effects of Martin dust storm on the surface erosion of ablator are also investigated experimentally. Finally, a breadboard model of the lightweight ablator aeroshell with the diameter of 500mm is developed to examine a manufacturability of proto flight model of aeroshell. The developed BBM is qualified through vibration tests, pyro shock tests, and thermal-vacuum tests at the qualification test level of the mission requirements.

形態: カラー図版あり

Physical characteristics: Original contains color illustrations

資料番号: AA1630005029

レポート番号: JAXA-SP-15-013

収録刊行物

詳細情報 詳細情報について

  • CRID
    1050855511216172928
  • NII論文ID
    120006827622
  • NII書誌ID
    AA11984031
  • ISSN
    1349113X
  • Web Site
    http://id.nii.ac.jp/1696/00003648/
  • 本文言語コード
    ja
  • 資料種別
    conference paper
  • データソース種別
    • IRDB
    • CiNii Articles

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