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  1. コンテンツタイプ
  2. 紀要論文 (Departmental Bulletin Paper)
  1. 機関資料(JAXA, former ISAS, NAL, NASDA)
  2. 旧機関資料 (JAXA, former-ISAS, NAL, NASDA)
  3. 宇宙科学研究所: ISAS Report等を含む (former ISAS (The Institute of Space and Astronautical Science): Including ISAS Report etc.)
  4. The Institute of Space and Astronautical Science report

Thermal Behavior of Axially Grooved Heat Pipes aboard a Rocket

https://jaxa.repo.nii.ac.jp/records/31359
https://jaxa.repo.nii.ac.jp/records/31359
642b9e58-e457-4f70-a45f-01e814b6812b
名前 / ファイル ライセンス アクション
SA0034916.pdf SA0034916.pdf (1.1 MB)
Item type 紀要論文 / Departmental Bulletin Paper(1)
公開日 2015-03-26
タイトル
タイトル Thermal Behavior of Axially Grooved Heat Pipes aboard a Rocket
言語 en
言語
言語 eng
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 departmental bulletin paper
著者 MURAKAMI, Masahide

× MURAKAMI, Masahide

en MURAKAMI, Masahide

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TADEUCHI, Ryo

× TADEUCHI, Ryo

en TADEUCHI, Ryo

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HAYASHI, Tomonao

× HAYASHI, Tomonao

en HAYASHI, Tomonao

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MACHIDA, Tsuneo

× MACHIDA, Tsuneo

en MACHIDA, Tsuneo

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KATO, Seiichi

× KATO, Seiichi

en KATO, Seiichi

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MATSUFUJI, Yukio

× MATSUFUJI, Yukio

en MATSUFUJI, Yukio

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著者所属(英)
en
Institute of Structural Engineering, University of Tsukuba.
著者所属(英)
en
Institute of Structural Engineering, University of Tsukuba.
著者所属(英)
en
NEC Nippon Electric Co., Ltd.
著者所属(英)
en
NEC Nippon Electric Co., Ltd.
著者所属(英)
en
NEC Nippon Electric Co., Ltd.
出版者
出版者 宇宙科学研究所
出版者(英)
出版者 Institute of Space and Astronautical Science
書誌情報 en : The Institute of Space and Astronautical Science report

巻 601, p. 1-19, 発行日 1982-10
抄録(英)
内容記述タイプ Other
内容記述 Two axially grooved heat pipes, one using ammonia as the working fluid and another using freon 11,were launched aboard S-520 sounding rockets in January 1980 and in September 1981,respectively. The former was made of aluminum and the latter of aluminum alloy. N-eicosane was employed as a phase change heat sink material for both cases. They were fixed on the rocket axis with the condenser top. The heat pipes experienced several levels of varying acceleration such as large positive during the boosting period, small negative immediately after the burnout caused by the aerodynamic drag on the rocket, zero-gravity, and again positive while the re-entry. They responded to these situations. Such responses as dryout, recovery from the dryout with partial liquid blockage in the condenser section, and resumption of normal heat pipe operation were resulted from the dynamic behavior of the working fluid. The flight data were analyzed to understand the heat pipe performance and to investigate the dependence of the liquid motion on the body force and on the surface tension. The critical Bond number which gave a boundary between surface tension dominating and body force dominating regions was found to be the order of 10^-3
ISSN
収録物識別子タイプ ISSN
収録物識別子 0285-6808
書誌レコードID
収録物識別子タイプ NCID
収録物識別子 AA10632072
資料番号
内容記述タイプ Other
内容記述 資料番号: SA0034916000
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