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titleれいめいにおけるリチウムイオン2次電池の運用シミュレーション
Other TitleSimulation tests of the lithium-ion secondary battery for piggy-back satellite Reimei
Author(jpn)武田 康男; 鵜野 将年; 曽根 理嗣; 齋藤 宏文; 廣瀬 和之; 田島 道夫
Author(eng)Takeda, Yasuo; Uno, Masatoshi; Sone, Yoshitsugu; Saito, Hirobumi; Hirose, Kazuyuki; Tajima, Michio
Author Affiliation(jpn)エイ・イー・エス; 宇宙航空研究開発機構 宇宙科学研究本部; 宇宙航空研究開発機構 宇宙科学研究本部; 宇宙航空研究開発機構 宇宙科学研究本部; 宇宙航空研究開発機構 宇宙科学研究本部; 宇宙航空研究開発機構 宇宙科学研究本部
Author Affiliation(eng)Advanced Engineering Services Co. Ltd.; Japan Aerospace Exploration Agency Institute of Space and Astronautical Science; Japan Aerospace Exploration Agency Institute of Space and Astronautical Science; Japan Aerospace Exploration Agency Institute of Space and Astronautical Science; Japan Aerospace Exploration Agency Institute of Space and Astronautical Science; Japan Aerospace Exploration Agency Institute of Space and Astronautical Science
Issue Date2006-06
PublisherInstitute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)
宇宙航空研究開発機構宇宙科学研究本部
Publication title第25回宇宙エネルギーシンポジウム 平成17年度
The Twenty-fifth Space Energy Symposium March 10, 2006
Start page11
End page15
Publication date2006-06
Languagejpn
AbstractReimei is a piggy-back satellite launched by Dnepr rocket from Baykonur Cosmodrome in August 24, 2005. The major mission of the satellite is the in-orbit demonstration of the advanced technologies using piggyback satellite system. The electric power sub-system is using multi junction solar cells with solar reflector for energy generation and the off-the-shelf lithium-ion secondary battery for energy storage. In the case of the battery, we applied the 'pouch cell' whose case is the laminated film with aluminum thin film to prevent the leakage of the electric solution. Seven months have passed since the launch of the satellite, and we still observe the stable charge/discharge performance of the battery in the low-Earth-orbit. We also started the simulation test of the battery operation ahead of the launch. In order to compare the ground test data with the orbital performance precisely, we calibrated the discharge curves in the orbit based on the DC performance of the lithium-ion cells. We also measured the AC impedance which increases with cycles. Based on these data, REIMEI is now appropriately operable in the orbit.
Keywordslithium-ion battery; small demonstration satellite; small satellite technology; small scientific satellite; piggyback system; multi-junction solar cell; aerospace environment; charge/discharge cycle test; low Earth orbit; リチウムイオン電池; 小型実証衛星; 小型衛星技術; 小型科学衛星; ピギーバックシステム; 多接合太陽電池; 航空宇宙環境; 充放電サイクル試験; 低高度地球周回軌道
Document TypeConference Paper
JAXA Categoryシンポジウム・研究会
SHI-NOAA0049121003
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/55414


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