@inproceedings{oai:jaxa.repo.nii.ac.jp:00008015,
 author = {中村, 慶太 and 増田, 英樹 and 井上, 剛文 and 吉田, 浩明 and 鵜野, 将年 and 豊田, 裕之 and 曽根, 理嗣 and 齋藤, 宏文 and 田島, 道夫 and Nakamura, Keita and Masuda, Hideki and Inoue, Takefumi and Yoshida, Hiroaki and Uno, Masatoshi and Toyota, Hiroyuki and Sone, Yoshitsugu and Saito, Hirobumi and Tajima, Michio},
 book = {第27回宇宙エネルギーシンポジウム　平成19年度, The Twenty-seventh Space Energy Symposium},
 month = {May},
 note = {Application of Large scale lithium-ion battery to various satellites and space vehicles has progressed well because of high capacity and high specific energy demands. GS Yuasa Technology (GYT) had developed 100 Ah lithium ion cells in 1999. And we consecutively had developed 50 Ah and 175 Ah cell with the same basic electrode design as the 100 Ah cell. In this study, we investigated the internal cell temperature during charge and discharge operation that is important information to assess the cell life. The temperature measurements were performed on three sizes cells which are the 50 Ah, 100 Ah, and 175 Ah cell. Each cell were opened at the bottom of the cell case and four thermo couple temperature sensors were installed into the cell inside. The detail locations are top (in height)-center (of wound element), middle-center, bottom-center, and bottom-outer (of wound element, but inside of case). The opened cell bottom was sealed by epoxy resin for the charge and discharge test. And additional four thermo couple temperature sensors were attached at cell surface. The charge and discharge conditions are simulated LEO (Low Earth Orbit) and GEO (Geostationary Earth Orbit) satellite operation, as shown below. LEO: Charge: 0.5 CA for 60 minutes, Discharge: 0.8 CA for 30 minutes. GEO: Charge: 0.1 CA for 22 hours 48 minutes, Discharge: 0.58 CA for 72 minutes. These charge and discharge test were repeated six cycles at 0 C, 15 C, and 25 C, respectively. In these test, following results were obtained. Larger cell shows larger temperature difference within the cell. However, even at 175 Ah cell, the largest temperature difference was 3.3 C that is measured between inside and outside of wound element. As for top and bottom direction, the maximum temperature difference was 0.9 C. We think that the reason of this small temperature difference at vertical direction depends on high thermal conductivity of Cupper and Aluminum foil that consist the cell wound element., 資料番号: AA0063965002},
 pages = {6--10},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)},
 title = {宇宙用大型リチウムイオン電池の充放電中における電池内部温度検証},
 year = {2008}
}