@article{oai:jaxa.repo.nii.ac.jp:00022447,
 author = {篠崎, 慶亮 and Nohara, Takehiro and 安藤, 麻紀子 and 岡本, 篤 and 前田, 真克 and 杉田, 寛之 and Takada, Suguru and Shinozaki, Keisuke and Nohara, Takehiro and Ando, Makiko and Okamoto, Atsushi and Maeda, Masakatsu and Sugita, Hiroyuki and Takada, Suguru},
 issue = {ists29},
 journal = {Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan},
 month = {Dec},
 note = {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., 資料番号: PA1410088000},
 pages = {Po_4_7--Po_4_11},
 title = {Research and Development of Heat Switch for Future Space Missions},
 volume = {12},
 year = {2014}
}