@inproceedings{oai:jaxa.repo.nii.ac.jp:00038694,
 author = {畠中, 龍太 and 野々村, 拓 and 藤田, 和央 and 石上, 玄也 and 豊田, 裕之 and 高井, 元 and 佐藤, 毅彦 and 杉田, 寛之 and Hatakenaka, Ryuta and Nonomura, Taku and Fujita, Kazuhisa and Ishigami, Genya and Toyota, Hiroyuki and Takai, Moto and Sato, Takehiko and Sugita, Hiroyuki},
 book = {第58回宇宙科学技術連合講演会講演集, Proceedings of 58th Space Sciences and Technology Conference},
 month = {Nov},
 note = {第58回宇宙科学技術連合講演会（2014年11月12日-14日. 長崎ブリックホール), 長崎市, 長崎県, "Preliminary thermal design and analysis of a Mars surface exploration spacecraft has been conducted. The sensitivities of thermal mass, envelope size and allowable temperature range of the component for heater power are presented based on preliminary EXCEL thermal calculation, and it is shown that allowable temperature range of external component is a critical parameter, and that heat leaks though electrical wire and coaxial cable for telecommunication is not negligible. These results suggest significant importance of expanding allowable temperature range of component,instead of accepting the current specification as-is.", 資料番号: AC1500054000, レポート番号: JSASS-2014-4162},
 publisher = {日本航空宇宙学会(JSASS), The Japan Society for Aeronautical and Space Sciences (JSASS)},
 title = {火星着陸探査機の熱設計},
 year = {2014}
}