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ガリレオ探査衛星突入飛行時のアブレータ損耗量再現の試み
https://jaxa.repo.nii.ac.jp/records/6450
https://jaxa.repo.nii.ac.jp/records/64509f4aacac-6bbd-4078-9332-134f6ecec856
名前 / ファイル | ライセンス | アクション |
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48469010.pdf (782.1 kB)
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Item type | 会議発表論文 / Conference Paper(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | ガリレオ探査衛星突入飛行時のアブレータ損耗量再現の試み | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ガリレオプローブ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 空力加熱 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | アブレーション材料 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 放射熱伝達 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 炭素・フェノール樹脂複合材料 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 大気圏突入 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 熱化学モデル | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 熱力学的平衡 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Galileo probe | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic heating | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | ablative material | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | radiative heat transfer | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | carbon-phenolic composite | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | atmospheric entry | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | thermochemical model | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | thermodynamic equilibrium | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_5794 | |||||
資源タイプ | conference paper | |||||
その他のタイトル(英) | ||||||
その他のタイトル | An attempt to reproduce the ablator recession data of Galileo probe entry flight | |||||
著者 |
松山, 新吾
× 松山, 新吾× 澤田, 恵介× Matsuyama, Shingo× Sawada, Keisuke |
|||||
著者所属 | ||||||
宇宙航空研究開発機構 総合技術研究本部 | ||||||
著者所属 | ||||||
東北大学 大学院工学研究科 | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics | ||||||
著者所属(英) | ||||||
en | ||||||
Tohoku University Graduate School of Engineering | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構 | |||||
出版者(英) | ||||||
出版者 | Japan Aerospace Exploration Agency (JAXA) | |||||
書誌情報 |
宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2004論文集 en : JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2004 巻 JAXA-SP-04-012, p. 63-68, 発行日 2005-03-25 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | A trajectory-based heating analysis of the Galileo probe entry flowfield is attempted to reproduce the heatshield recession data obtained during the entry flight. In the present calculation, the mass conservation equations for the freestream gas (hydrogen-helium gas mixture) and the ablation product gas are solved with an assumption of thermochemical equilibrium. The ablation process is assumed to be quasi-steady and is coupled with the flowfield calculation. The radiative energy transfer calculation is tightly coupled with the flowfield calculation, where the absorption coefficients of the gas mixture are given by the multiband radiation model having 4,781 wavelength points for wavelength range from 750 to 15,000 A. The injection-induced turbulence model proposed by Park is employed to account for the enhanced turbulence effect due to the ablation product gas. It is shown that the final recession profile of the flight data at the frustum region can be closely reproduced if the injection-induced turbulence model is employed, although that at the stagnation region is overestimated. The cause of the enhanced radiative heating that occurs at the frustum region is given in connection with the enhanced turbulence effect in the shock layer. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 1349-113X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA11984031 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0048469010 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: JAXA-SP-04-012 |