| Item type |
紀要論文 / Departmental Bulletin Paper(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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|
タイトル |
Assessment of Forebody and Backbody Radiative Heating Rate of Hypervelocity Reentry Capsule |
|
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 |
departmental bulletin paper |
| 著者 |
大津, 広敬
鈴木, 宏二郎
藤田, 和央
安部, 隆士
Otsu, Hirotaka
Suzuki, Kojiro
Fujita, Kazuhisa
Abe, Takashi
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| 著者所属 |
|
|
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静岡大学 |
| 著者所属 |
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東京大学地震研究所 |
| 著者所属 |
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|
宇宙科学研究所 |
| 著者所属 |
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宇宙科学研究所 |
| 著者所属（英） |
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|
en |
|
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Shizuoka University |
| 著者所属（英） |
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|
en |
|
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University of Tokyo |
| 著者所属（英） |
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en |
|
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Institute of Space and Astronautical Science (ISAS) |
| 著者所属（英） |
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|
en |
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Institute of Space and Astronautical Science (ISAS) |
| 出版者 |
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|
出版者 |
宇宙科学研究所 |
| 出版者（英） |
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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. 93-105,
発行日 2003-03
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| 抄録（英） |
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内容記述タイプ |
Other |
|
内容記述 |
The thermally and chemically nonequilibrium hypersonic flow around the MUSES-C reentry capsule was analyzed to evaluate the radiative heating environment. The typical reentry speed is 11.6 km/s at the altitude of 64 km. Since the radiative heating strongly depends on the vibrational-electronic temperature distribution, the energy relaxation mechanism for vibrational-electronic energy was clarified by investigating the contribution of each term for energy exchange between translational and vibrational-electronic energy. From this investigation it was found that the energy relaxation terms related to ions are dominant under such a severe reentry heating environment such as the MUSES-C reentry flight condition. The predicted value for the radiative heat flux at the stagnation point amounts to 1.4 MW/m(sup 2). In the afterbody region, the radiative heat flux is relatively small, and at the base, it is less than 1 percent of the stagnation point. All around the vehicle surface, the radiative heat flux is much smaller than the convective heat flux. The effect of ablation gas on the radiation was also assessed. It was also found that in the forebody region the effect of the ablative gas on the radiative heating environment for MUSES-C is not so significant but in the afterbody region the effect is relatively large. |
| 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 |
0288-433X |
| 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 |
AA10455137 |
| 資料番号 |
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内容記述タイプ |
Other |
|
内容記述 |
資料番号: SA0200017000 |
SA0200017.pdf (3.5 MB)
