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ロケット慣性飛行中の二相流挙動および熱伝達特性の観測実験: 実験装置部の開発
https://jaxa.repo.nii.ac.jp/records/21655
https://jaxa.repo.nii.ac.jp/records/2165505c33cb6-7f8e-42d7-b68a-9bfdd525615c
Item type | 学術雑誌論文 / Journal Article(1) | |||||
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公開日 | 2016-02-01 | |||||
タイトル | ||||||
タイトル | ロケット慣性飛行中の二相流挙動および熱伝達特性の観測実験: 実験装置部の開発 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Cryogenic Two-Phase Flow | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Microgravity | |||||
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 | journal article | |||||
アクセス権 | ||||||
アクセス権 | metadata only access | |||||
アクセス権URI | http://purl.org/coar/access_right/c_14cb | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Measuring Two-phase Flow Behavior and Heat Transfer Characteristics during Coasting Flight, Development of Experimental Equipment for S-310-43 Sounding Rocket | |||||
著者 |
小林, 弘明
× 小林, 弘明× 杵淵, 紀世志× 更江, 渉× 梅村, 悠× 藤本, 圭一郎× 薮崎, 大輔× 杉森, 大造× 姫野, 武洋× 佐藤, 哲也× 北古賀, 智史× 角, 悠輝× 坂本, 勇樹× 野中, 聡× 藤田, 猛× Kobayashi, Hiroaki× Kinefuchi, Kiyoshi× Sarae, Wataru× Umemura, Yutaka× Fujimoto, Keiichiro× Yabusaki, Daisuke× Sugimori, Daizo× Himeno, Takehiro× Sato, Tetsuya× Kitakoga, Satoshi× Sumi, Yuki× Sakamoto, Yuki× Nonaka, Satoshi× Fujita, Takeshi |
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出版者 | ||||||
出版者 | Japan Society for Aeronautical and Space Sciences | |||||
出版者(英) | ||||||
出版者 | 日本航空宇宙学会 | |||||
書誌情報 |
日本航空宇宙学会論文集 en : Journal of the Japan Society for Aeronautical and Space Sciences 巻 63, 号 5, p. 188(14)-196(22), 発行日 2015-10-05 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The Japan Aerospace Exploration Agency launched the S-310-43 sounding rocket from the Uchinoura Space Center on Aug. 04, 2014 for the purpose of investigating such behavior as boiling and flow of cryogenic liquid rocket propellant in an environment simulating coasting flight on orbit by using the sounding rocket's sub-orbital ballistic flight. In the low-gravity state, the cryogenic fluid (liquid nitrogen) was introduced into the test sections of similar shapes to the flow channels in the cryogenic propulsion systems. The boiling of liquid nitrogen inside the test-sections and the transition of flow regimes from gas/liquid two-phase flow to liquid mono-phase flow were visualized. The temperatures, pressures and void fractions of each channels were measured as well. Development of the experimental equipment for S-310-43 sounding rocket is described in this paper. | |||||
内容記述 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 形態: カラー図版あり | |||||
内容記述(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Physical characteristics: Original contains color illustrations | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 1344-6460 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA11307372 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: DS1540301003 |