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傾斜前面円柱先頭形状によるTSTO極超音速空力干渉の低減
http://hdl.handle.net/2237/13874
http://hdl.handle.net/2237/1387419e48de5-f064-4dbc-beef-dc08129c674e
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
jjsass_v56_n648_p8.pdf (1.5 MB)
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| アイテムタイプ | 学術雑誌論文 / Journal Article(1) | |||||
|---|---|---|---|---|---|---|
| 公開日 | 2010-07-27 | |||||
| タイトル | ||||||
| タイトル | 傾斜前面円柱先頭形状によるTSTO極超音速空力干渉の低減 | |||||
| 言語 | ja | |||||
| その他のタイトル | ||||||
| その他のタイトル | Reduction of TSTO Hypersonic Aerodynamic Interactions Due to Diagonally-Cut Circular Cylinder Orbiter Nose | |||||
| 著者 |
小澤, 啓伺
× 小澤, 啓伺× OZAWA, Hiroshi× 花井, 勝祥× HANAI, Katsuhisa× 中村, 佳朗× NAKAMURA, Yoshiaki |
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| アクセス権 | ||||||
| アクセス権 | open access | |||||
| アクセス権URI | http://purl.org/coar/access_right/c_abf2 | |||||
| キーワード | ||||||
| 主題Scheme | Other | |||||
| 主題 | TSTO (Two-Stage-To-Orbit) | |||||
| キーワード | ||||||
| 主題Scheme | Other | |||||
| 主題 | Hypersonic Flow | |||||
| キーワード | ||||||
| 主題Scheme | Other | |||||
| 主題 | Aerodynamic Interaction | |||||
| キーワード | ||||||
| 主題Scheme | Other | |||||
| 主題 | Temperature Sensitive Paint (TSP) | |||||
| キーワード | ||||||
| 主題Scheme | Other | |||||
| 主題 | Heat Flux | |||||
| キーワード | ||||||
| 主題Scheme | Other | |||||
| 主題 | Orbiter Nose Shape | |||||
| 抄録 | ||||||
| 内容記述タイプ | Abstract | |||||
| 内容記述 | To make space activities more brisk, TSTO (Two Stage To Orbit) has been investigated worldwide as an advanced space transportation system. TSTO vehicles, which have a booster and an orbiter, have to make flight in a wide range of flight speed from subsonic to hypersonic, where they undergo aerodynamic interactions due to their combined bodies. In hypersonic flow regime, aerodynamic heating is critical, which depends on aerodynamic interaction pattern. In the present study, a delta-wing is employed as a booster and a diagonally-cut circular cylinder as an orbiter to reduce the aerodynamic interaction between these two bodies. It was found as a result of experiment that the heat flux on the head part of the diagonally-cut circular cylinder becomes about 2.4 times as large as the stagnation heat flux, while that on the delta-wing becomes about 0.5 times as large. These two values are roughly half of those in the case of a baseline combination: hemisphere-cylinder and delta-wing, which suggests that the diagonally-cut circular cylinder is promising as an orbiter head shape. | |||||
| 言語 | en | |||||
| 出版者 | ||||||
| 出版者 | 日本航空宇宙学会 | |||||
| 言語 | ja | |||||
| 言語 | ||||||
| 言語 | jpn | |||||
| 資源タイプ | ||||||
| 資源タイプresource | http://purl.org/coar/resource_type/c_6501 | |||||
| タイプ | journal article | |||||
| 出版タイプ | ||||||
| 出版タイプ | VoR | |||||
| 出版タイプResource | http://purl.org/coar/version/c_970fb48d4fbd8a85 | |||||
| ISSN | ||||||
| 収録物識別子タイプ | PISSN | |||||
| 収録物識別子 | 1344-6460 | |||||
| 書誌情報 |
ja : 日本航空宇宙学会論文集 巻 56, 号 648, p. 8-14, 発行日 2008-01-05 |
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| フォーマット | ||||||
| 値 | application/pdf | |||||
| 著者版フラグ | ||||||
| 値 | publisher | |||||
| URI | ||||||
| 識別子 | http://hdl.handle.net/2237/13874 | |||||
| 識別子タイプ | HDL | |||||
