| アイテムタイプ |
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 |
Thermal Protection System of the Reentry Capsule with Superorbital Velocity |
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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 |
departmental bulletin paper |
| 著者 |
山田, 哲哉
石井, 信明
稲谷, 芳文
本田, 雅久
Yamada, Tetsuya
Ishii, Nobuaki
Inatani, Yoshifumi
Honda, Masahisa
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| 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 |
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宇宙科学研究所 |
| 著者所属 |
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アイ・エイチ・アイ・エアロスペース |
| 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) |
| 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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IHI Aerospace Company |
| 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. 245-261,
発行日 2003-03
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| 抄録（英） |
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内容記述タイプ |
Other |
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内容記述 |
In the final phase of the MUSES-C mission, a small capsule with asteroid sample conducts reentry flight directly from the interplanetary transfer orbit at the velocity over 12 km/s. The severe heat flux, the complicated functional requirements, and small weight budget impose several engineering challenges on the designing of the thermal protection system of the capsule. The heat shield is required to function not only as ablator but also as a structural component. The cloth-layered carbon-phenolic ablator, which has higher allowable stress, is developed in newly devised fabric method for avoiding delamination due to the high aerodynamic heating. The ablation analysis code, which takes into account of the effect of pyrolysis gas on the surface recession rate, has been developed and verified in the arc-heating tests in the facility environment of broad range of enthalpy level. The capsule was designed to be ventilated during the reentry flight up to about atmospheric pressure by the time of parachute deployment by being sealed with porous flow-restrict material. The designing of the thermal protection system, the hardware specifications, and the ground-based test programs of MUSES-C capsule are summarized and discussed here in this paper. |
| 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 |
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収録物識別子 |
AA10455137 |
| 資料番号 |
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内容記述タイプ |
Other |
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内容記述 |
資料番号: SA0200028000 |
SA0200028.pdf (4.8 MB)
