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Trajectory-based Coupled Analysis of Viscous Shock Layer and Charring Material Ablation at Stagnation Point
https://jaxa.repo.nii.ac.jp/records/33253
https://jaxa.repo.nii.ac.jp/records/33253af1a2a50-7999-4c99-b3ab-d55d08776c09
名前 / ファイル | ライセンス | アクション |
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SA0200026.pdf (4.1 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 | Trajectory-based Coupled Analysis of Viscous Shock Layer and Charring Material Ablation at Stagnation Point | |||||
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× Suzuki, Kojiro |
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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(英) | ||||||
en | ||||||
Department of Advanced Energy, Graduate School of Frontier Sciences, The University of Tokyo | ||||||
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. 217-232, 発行日 2003-03 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | To predict the characteristics of the ablation thermal protection for the MUSEE-C superorbital re-entry capsule, the trajectory-based analysis of the hypersonic shock layer flow and the ablator interior has been made on the stagnation line in a coupled manner. For the flow analysis, the Viscous Shock-Layer (VSL) equations with the nonequilibrium chemistry of C-O-H-N 26 species are solved. For the ablator, the in-depth thermal response is solved by the Charring Material Ablation (CMA) model. The boundary condition at the surface, which is necessary for both solutions, is determined by the mass and energy balance. Various surface reactions and the surface injection of the pyrolysis gas are considered. The results are compared with the experimental data obtained at the arc-heated wind tunnel. Analysis by using the empirical relations all along the re-entry trajectory is also made and the results are compared with those by the VSL/CMA coupled method. It is shown that such engineering prediction method provides reasonable prediction for the surface temperature and the mass loss of the ablator with sufficient safety margin. The effects of the initial ablator thickness on the ablator temperature are 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: SA0200026000 |