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Aerodynamic Heating Around Flare-Type Membrane Inflatable Vehicle in Suborbital Reentry Demonstration Flight

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タイトル: Aerodynamic Heating Around Flare-Type Membrane Inflatable Vehicle in Suborbital Reentry Demonstration Flight
著者: Takahashi, Yusuke 著作を一覧する
Yamada, Kazuhiko 著作を一覧する
Abe, Takashi 著作を一覧する
Suzuki, Kojiro 著作を一覧する
発行日: 2015年11月
出版者: American Institute of Aeronautics and Astronautics
誌名: Journal of spacecraft and rockets
巻: 52
号: 6
開始ページ: 1530
終了ページ: 1541
出版社 DOI: 10.2514/1.A33170
抄録: A demonstration flight of an advanced reentry vehicle was carried out using a sounding rocket. The vehicle was equipped with a flexible (membrane) aeroshell deployed by an inflatable torus structure. Its most remarkable feature was the low ballistic coefficient that enables reduction in aerodynamic heating and deceleration at a high altitude. During the suborbital reentry, temperatures at several locations on a backside of the flexible aeroshell and inside the capsule were measured by means of embedded thermocouples. The aerodynamic heating behavior of the vehicle was investigated using the measured temperature history, in combination with a numerical prediction in which a flow-field simulation of the heating was conducted. In this flow-field simulation, both laminar flow and turbulent flow were assumed, and the deformation of the flexible aeroshell was considered. A thermal model of the capsule and membrane aeroshell was developed, and the heat flux profiles of the vehicle surface during aerodynamic heating were constructed based on the measured temperatures. The measured temperature data were found to be in reasonable agreement with the predicted data if the flow field near the capsule of the vehicle was assumed to be laminar, with a transition to turbulent flow near the membrane aeroshell.
Rights: © 2015 American Institute of Aeronautics and Astronautics
資料タイプ: article (author version)
URI: http://hdl.handle.net/2115/60702
出現コレクション:雑誌発表論文等 (Peer-reviewed Journal Articles, etc)

提供者: 高橋 裕介

 

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