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An Integrated Numerical Method for Predicting Aerodynamic Heating Environment for MUSES-C Entry Capsule with Ablation
https://jaxa.repo.nii.ac.jp/records/33254
https://jaxa.repo.nii.ac.jp/records/33254cd7d5d9a-792f-4f09-b2ca-4318a20b6162
名前 / ファイル | ライセンス | アクション |
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SA0200027.pdf (3.5 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 | An Integrated Numerical Method for Predicting Aerodynamic Heating Environment for MUSES-C Entry Capsule with Ablation | |||||
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 |
澤田, 恵介
× 澤田, 恵介× Sawada, Keisuke |
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著者所属 | ||||||
東北大学大学院 工学研究科 航空宇宙工学専攻 | ||||||
著者所属(英) | ||||||
en | ||||||
Department of Aeronautics and Space Engineering, Tohoku University | ||||||
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. 233-244, 発行日 2003-03 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | An integrated numerical method to obtain trajectory-based aerodynamic heating environment for entry probe vehicles with ablation is briefly described. In this method, a thermochemical nonequilibrium CFD code is loosely coupled with an ablation module along the entry trajectory. Radiative heating is estimated by the use of multi-band radiation module. The effect of earlier turbulent transition of the boundary layer due to ablation product gas is included. Calculated results for MUSES-C sample return capsule are shown and are compared with the results of existing analysis. | |||||
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: SA0200027000 |