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再突入飛行体のCFD解析における熱化学モデルの影響について:電磁力を利用した空力加熱低減法への影響
https://jaxa.repo.nii.ac.jp/records/6448
https://jaxa.repo.nii.ac.jp/records/64484624025e-569b-4660-95cd-ea0357be973f
名前 / ファイル | ライセンス | アクション |
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48469008.pdf (844.5 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 | 再突入飛行体のCFD解析における熱化学モデルの影響について:電磁力を利用した空力加熱低減法への影響 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 再突入機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | CFD | |||||
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 | 熱化学モデル | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 電磁力 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 熱力学的平衡 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | Lorentz力 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 宇宙輸送システム | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 再利用型宇宙機 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | reentry vehicle | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | CFD | |||||
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 | thermochemical model | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | electromagnetic force | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | thermodynamic equilibrium | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Lorentz force | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | space transportation system | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | reusable spacecraft | |||||
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 | Effect of thermochemical model on reentry heating reduction using electromagnetic force | |||||
著者 |
大津, 広敬
× 大津, 広敬× 安部, 隆士× Otsu, Hirotaka× Abe, Takashi |
|||||
著者所属 | ||||||
静岡大学 工学部 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 宇宙科学研究本部 | ||||||
著者所属(英) | ||||||
en | ||||||
Shizuoka University Faculty of Engineering | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space and Astronautical Science | ||||||
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. 51-56, 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 | An applicability of the electrodynamic heat shield system to a super-orbital reentry vehicle was investigated. In the case of the super-orbital reentry flight, due to the strong ionization reactions inside the shock layer, the electrodynamic heat shield system is expected to work well. In order to evaluate the ambiguity of the thermochemical model on the efficiency of this heat shield system, a CFD analysis including thermochemical non-equilibrium effect was performed. The flight condition used for the present study is that the velocity is 11.6 km/sec at the altitude of 64 km. From the CFD result, it was found that the ambiguity of the thermochemical model on the electrodynamic heat shield system is negligible. Additionally, it was found that the stagnation point heat flux could be reduced by about 1.0 MW/sq m when the magnetic field strength of 0.5 T is applied. | |||||
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: AA0048469008 | |||||
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 |