| Item type |
学術雑誌論文 / Journal Article(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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タイトル |
Post-Flight TPS Analysis of Hayabusa Reentry Capsule |
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言語 |
en |
| 言語 |
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言語 |
eng |
| 資源タイプ |
|
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資源タイプ識別子 |
http://purl.org/coar/resource_type/c_6501 |
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資源タイプ |
journal article |
| アクセス権 |
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|
アクセス権 |
metadata only access |
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アクセス権URI |
http://purl.org/coar/access_right/c_14cb |
| 著者 |
鈴木, 俊之
藤田, 和央
山田, 哲哉
稲谷, 芳文
石井, 信明
Suzuki, Toshiyuki
Fujita, Kazuhisa
Yamada, Tetsuya
Inatani, Yoshifumi
Ishii, Nobuaki
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| 著者所属 |
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宇宙航空研究開発機構研究開発本部(JAXA) |
| 著者所属 |
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宇宙航空研究開発機構研究開発本部(JAXA) |
| 著者所属 |
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宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS) |
| 著者所属 |
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宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS) |
| 著者所属 |
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宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS) |
| 著者所属（英） |
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en |
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Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA) |
| 著者所属（英） |
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en |
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Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA) |
| 著者所属（英） |
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en |
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Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS) |
| 著者所属（英） |
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en |
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Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS) |
| 著者所属（英） |
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|
en |
|
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Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS) |
| 出版者（英） |
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出版者 |
American Institute of Aeronautics and Astronautics (AIAA) |
| 書誌情報 |
en : Journal of Spacecraft and Rockets
巻 51,
号 1,
p. 96-105,
発行日 2014-01-01
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| 抄録（英） |
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内容記述タイプ |
Other |
|
内容記述 |
The thermal response of the ablative thermal protection system of the Hayabusa capsule is calculated along the most probable reentry trajectory by using the integrated analysis method. The analysis method consists of an axisymmetric nonequilibrium Navier-Stokes flow solver and a radiative heat transfer analysis code loosely coupled to an ablation thermal response code. The calculated results are compared with the flight data obtained at the present time. It is found that a reasonable agreement is obtained between the calculated surface temperature and the temperature values estimated from the DC-8 airborne observation and the ground observation. In contrast, the calculated surface recession overestimates the measurement along the wall surface by a factor of three. It is also found that the density distributions inside the ablator can be reproduced reasonably both at the stagnation point and at the downstream region by taking account of the conventional surface reaction set and nitridation reaction with a laminar boundary condition. Especially for the thickness of the char layer at the downstream region, calculation overestimates the flight data when the effect of turbulence due to the pyrolysis gas is considered, whereas it underestimates the flight data when the effect of surface roughness of the ablative thermal protection system is taken into account. |
| ISSN |
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収録物識別子タイプ |
ISSN |
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収録物識別子 |
0022-4650 |
| ISSNONLINE |
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収録物識別子タイプ |
ISSN |
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収録物識別子 |
1533-6794 |
| 書誌レコードID |
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収録物識別子タイプ |
NCID |
|
収録物識別子 |
AA00707776 |
| 資料番号 |
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内容記述タイプ |
Other |
|
内容記述 |
資料番号: PA1420003000 |
