@inproceedings{oai:jaxa.repo.nii.ac.jp:00008090,
 author = {森田, 泰弘 and 曽根, 理嗣 and 安田, 誠一 and 佐藤, 豊 and 長谷川, 和雄 and 加藤, 弘一郎 and 中野, 隆行 and Morita, Yasuhiro and Sone, Yoshitsugu and Yasuda, Seiichi and Sato, Yutaka and Hasegawa, Kazuo and Kato, Koichiro and Nakano, Takayuki},
 book = {第24回宇宙エネルギーシンポジウム　平成16年度, The Twenty-fourth Space Energy Symposium March 7, 2005},
 month = {Jun},
 note = {The TVC (Thrust Vector Control) system for the 3rd stage of the M-V launch vehicle performs thrust direction control by driving a movable nozzle with two electric actuators, and uses a Silver-Zinc battery to supply 28 V electric power to them. A high-power density battery for launch vehicle did not exist except the Silver-Zinc battery when the M-V TVC system was developed. Therefore, Silver-Zinc battery was adopted, although it has drawbacks of its short storage life and charge/discharge cycle life. After four launches of M-V, this battery system needs to be reconsidered, because of above demerits. The new battery requirements are as follows, (1) Long storage and cycle life, (2) Low cost, (3) Small size and light weight. We selected the lithium ion battery for HEV (Hybrid Electric Vehicle), that can satisfy our requirements. This battery has the following key advantages, (a) High discharge rate, (b) Long life, (c) Low cost, (d) Stabilized Quality, and (e) High safety design. To apply the lithium ion battery for HEV to M-V launch vehicle the following items have been verified. (1) Electrical compatibility with the TVC system of the M-V launch vehicle, (2) Environmental resistance, (3) Space level quality assurance., 資料番号: AA0049120004},
 pages = {17--21},
 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 = {M-Vロケット第3段TVCアクチュエータ駆動用高率放電リチウムイオンバッテリ},
 year = {2005}
}