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Chemical Nonequilibrium Viscous Shock-Layer Analysis over Ablating Surface of Superorbital Re-Entry Capsule
https://jaxa.repo.nii.ac.jp/records/33239
https://jaxa.repo.nii.ac.jp/records/3323977447a29-042d-45a1-bf51-7dece3e2202a
名前 / ファイル | ライセンス | アクション |
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SA0200012.pdf (5.1 MB)
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Item type | 紀要論文 / Departmental Bulletin Paper(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Chemical Nonequilibrium Viscous Shock-Layer Analysis over Ablating Surface of Superorbital Re-Entry Capsule | |||||
言語 | ||||||
言語 | eng | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_6501 | |||||
資源タイプ | departmental bulletin paper | |||||
著者 |
鈴木, 宏二郎
× 鈴木, 宏二郎× 藤田, 和央× 安部, 隆士× Suzuki, Kojiro× Fujita, Kazuhisa× Abe, Takashi |
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著者所属 | ||||||
東京大学 大学院新領域創成科学研究科 | ||||||
著者所属 | ||||||
宇宙科学研究所 | ||||||
著者所属 | ||||||
宇宙科学研究所 | ||||||
著者所属(英) | ||||||
en | ||||||
Department of Advanced Energy, Graduate School of Frontier Sciences, The University of Tokyo | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Space and Astronautical Science (ISAS) | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Space and Astronautical Science (ISAS) | ||||||
出版者 | ||||||
出版者 | 宇宙科学研究所 | |||||
出版者(英) | ||||||
出版者 | Institute of Space and Astronautical Science | |||||
書誌情報 |
en : The Institute of Space and Astronautical Science report. S.P. : Aerodynamics, Thermophysics, Thermal Protection, Flight System Analysis and Design of Asteroid Sample Return Capsule 巻 17, p. 23-42, 発行日 2003-03 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The aerodynamic heating environment with ablation injection and the mass loss rate of the ablator under the superorbital re-entry condition of the MUSES-C sample return capsule are numerically studied by solving the Viscous shock-layer (VSL) equations with the nonequilibrium chemistry of both the air and the ablation gas. The boundary conditions at the ablator surface are formulated by considering the surface oxidation and surface sublimation. Computational results on the variation of the surface mass loss rate with the wall temperature demonstrate that the diffusion-controlled regime and the sublimation regime are successfully described by the present model. The time history of the wall temperature at the stagnation point is estimated along the re-entry trajectory by assuming the energy balance at the surface. The streamwise distributions of the convective heating rate and the surface mass loss rate over the forebody of the capsule are calculated at the peak heating flight condition and their characteristics are clarified. The effects of the pyrolysis gas of hydrocarbon species on the convective heating rate are investigated. The possibility of wall heating augmentation due to the turbulence induced by the ablation injection is also discussed. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0288-433X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA10455137 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: SA0200012000 |