S191014 音響擾乱が半球殻前方に発生する衝撃波振動へおよぼす影響について([S19101]大気突入・減速技術)

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概要

• 論文の詳細を見る

• The purpose of this study is to analyze shockwave vibrations that occur in front of a hemisphere model. Supersonic parachutes are used for decreasing speed of re-entry and planetary vehicles. Solid hemisphere models are used for the purpose of obtaining general characteristics of parachute shape. From past studies, detached shockwave vibrations were observed at Mach number from 3.0 to 4.0 by photographs. The purpose of analyzing shockwave vibrations, experiments was conducted by using high-speed video camera. A solid hemisphere model was attached in supersonic wind tunnel. A schlieren system with high-speed video camera was used for flow visualization. Flow Mach number was 4.0. The moment of initiation of shockwave vibrations were clearly visualized with high-speed video camera. Unsteady internal flow was supposed to cause the vibrations of shockwaves ahead of the model used here. The cause of shockwave vibrations is unsteady internal flow in the solid hemisphere model.

• 一般社団法人日本機械学会の論文
• 2011-09-11

著者

• 水書 稔治

  東海大学工学部

• 川村 尚史

  東海大学大学院工学研究科

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• レーザ誘起熱音響波による非定常温度場計測法(流体計測・実験(2),一般講演)
• Background-Oriented Schlieren 法による定量的可視化計測
• S191014 音響擾乱が半球殻前方に発生する衝撃波振動へおよぼす影響について([S19101]大気突入・減速技術)
• MABS 22参加報告

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