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アイテム
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Research and Development of Heat Switch for Future Space Missions
https://jaxa.repo.nii.ac.jp/records/22447
https://jaxa.repo.nii.ac.jp/records/22447d6603dd4-1c8d-4991-b33c-21f7a98824cf
Item type | 学術雑誌論文 / Journal Article(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Research and Development of Heat Switch for Future Space Missions | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Heat Switch; Rover; Mechanical; Paraffin | |||||
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 | |||||
著者 |
篠崎, 慶亮
× 篠崎, 慶亮× Nohara, Takehiro× 安藤, 麻紀子× 岡本, 篤× 前田, 真克× 杉田, 寛之× Takada, Suguru× Shinozaki, Keisuke× Nohara, Takehiro× Ando, Makiko× Okamoto, Atsushi× Maeda, Masakatsu× Sugita, Hiroyuki× Takada, Suguru |
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著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
筑波大学 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
核融合科学研究所 | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
University of Tsukuba | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
National Institute for Fusion Science | ||||||
出版者 | ||||||
出版者 | 日本航空宇宙学会(JSASS) | |||||
出版者(英) | ||||||
出版者 | The Japan Society for Aeronautical and Space Sciences (JSASS) | |||||
書誌情報 |
en : Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan 巻 12, 号 ists29, p. Po_4_7-Po_4_11, 発行日 2014-12-26 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | A heat switch provides a thermal switching (high or low thermal conductance) as appropriate according to the thermal environment of a spacecraft. It has an advantage for a thermal control for lunar rover and planetary exploration spacecraft for which it is difficult to secure sufficient electrical power. A mechanical heat switch is being developed in our group forJapanese spacecraft including the lunar rover. Required on / off thermal conductances are 1 W/K and 10 mW/K respectively with lower than 5 cm of height as a goa1. The volume expansion of paraffin was introduced for the on / off mechanismaccording to the result of a trade-off study including feasibility, power and expected mass. The heat switch test model we fabricated has a mass of 660 g, height of 53 mm, and outer diameter of 62 mm. In our thermal performance test, the thermal conductance was 0.86 W/K when the switch was turned on and an on / off ratio exceeding 110 was measured. In this paper, a description of the heat switch, mission targets, conceptional design study and the thermal performance result of the test model are presented. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 1884-0485 | |||||
DOI | ||||||
識別子タイプ | DOI | |||||
関連識別子 | http://dx.doi.org/10.2322/tastj.12.Po_4_7 | |||||
関連名称 | info:doi/10.2322/tastj.12.Po_4_7 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: PA1410088000 |