Japan Aerospace Exploration Agency(JAXA)
University of Tsukuba
Japan Aerospace Exploration Agency(JAXA)
Japan Aerospace Exploration Agency(JAXA)
Japan Aerospace Exploration Agency(JAXA)
Japan Aerospace Exploration Agency(JAXA)
National Institute for Fusion Science
出版者
日本航空宇宙学会(JSASS)
出版者（英）
The Japan Society for Aeronautical and Space Sciences (JSASS)
雑誌名
Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan
巻
12
号
ists29
ページ
Po_4_7 - Po_4_11
発行年
2014-12-26
抄録（英）
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.
Research and Development of Heat Switch for Future Space Missions
