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平成19年度宇宙輸送シンポジウム（2008年1月28日-29日. 宇宙航空研究開発機構宇宙科学研究本部）, 相模原市, 神奈川県, Space Transportation Symposium FY2007 (January 28-29, 2008. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000004016

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

GS Yuasa Technology (GYT) had developed large capacity lithium ion cells for space applications in 1999. The chemical design of the cell was fixed at that time and it has not changed up to now. Since satellite applications require very long life and the replacement during missions is impossible, it is very important to evaluate life characteristics of the cell. GYT established a capacity estimation formula under consideration of two major capacity loss mechanisms from matrix life tests. The estimation method makes it possible to estimate cell life in any missions. On the other hand, GYT has performed many life tests which simulate actual satellites missions since the cell development. These tests have reached the end of the required mission shown as follows. (1) 40 seasons (20 years): Semi-accelerated GEO (Geostationary Earth Orbit) (max. 80 percent DOD (Depth Of Discharge) (2) 30 seasons (15 years): Semi-accelerated GEO (max. 70 percent DOD) (3) 40,000 cycles (7 years): LEO (Low Earth Orbit) 25 percent DOD. From these results, GYT confirmed that the cells can meet general requirements of life performance for GEO and LEO., 資料番号: AA0063965001

第26回宇宙エネルギーシンポジウム 平成18年度（2007年3月12日. 宇宙航空研究開発機構宇宙科学研究本部 (JAXA)(ISAS)）, 相模原市, 神奈川県, The Twenty-sixth Space Energy Synmposium (March 12, 2007. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000025003

High energy density Li-ion battery is expected for next generation satellites and the other space usage. GS Yuasa Technology Ltd. (GYT) has developed two types of large capacity Li-ion cells through cooperation with Mitsubishi Electric Corporation (MELCO). One is satellite type (50,100 and 175 Ah) for long life applications and the other is rocket type (55,110 and 190 Ah) for high energy applications. The energy density of the cells are 136 Wh/kg-164 Wh/kg. They correspond to the 1.5-2.0 times of Ni-H2 cell. The cells have completely sealed structure achieved with ceramic hermetic seal in order to endure the space environment. GYT has confirmed that the cells performance satisfies space application requirements. SERVIS-1 that equipped with Li-ion battery system (cells: by GYT, battery: by MELCO) was launched on October 2003. The Li-ion battery consists of eleven Li-ion cells (50 Ah) in series. SERVIS-1 has been operated smoothly on orbit. The results more than two years in total will be obtained on orbit in SERVIS-1. 100 Ah cells have been operated in a GEO satellite since 2005. It is scheduled that the Li-ion cells of 50-175 Ah by GYT are installed in some satellites. GYT cells have been tested in accelerated GEO cycle tests. GYT confirmed that the cells will satisfy general life requirement of GEO mission (15 years)., 資料番号: AA0049121004

High energy density Li-ion battery is expected for next generation satellites and the other space usage. Japan Storage Battery Co., Ltd. (JSB) has developed two types of large capacity Li-ion cells through cooperation with Mitsubishi Electric Corporation (MELCO). One is satellite type (50, 100 and 175 Ah) for long life applications and the other is rocket type (55, 110 and 190 Ah) for high energy applications. The energy density of the cells are 136 Wh/kg to 164 Wh/kg. They correspond to the 1.5 to 2.0 times of Ni-H2 cell. The cells have completely sealed structure achieved with ceramic hermetic seal in order to endure the space environment. JSB has confirmed that the cells performance satisfies space application requirements. Furthermore, JSB has started developing small size Li-ion cell (10 Ah) for small satellites. SERVIS-1 that equipped with Li-ion battery system (cells: by JSB, battery: by MELCO) was launched in October 2003. The Li-ion battery consists of eleven Li-ion cells (50 Ah) in series. SERVIS-1 has been operated smoothly on orbit. The results more than two years in total will be obtained on orbit in SERVIS-1. It is scheduled that the Li-ion cells of 50 to 175 Ah by JSB are installed in some satellites that will be launched by 2007., 資料番号: AA0047275003

High energy density Li-ion battery is expected for the next generation satellite and the other space usage. Japan Storage Battery Co., Ltd. (JSB) has developed two types of large capacity Li-ion cells through cooperation with Mitsubishi Electric Corporation (MELCO). One is satellite type (50, 100 and 175 Ah) for long life applications and the other is rocket type (55, 110 and 190 Ah) for high energy applications. The energy density of the cells are 136 Wh/kg to 164 Wh/kg. They correspond to the 1.5 to 2.0 times of Ni-H2 cell. The cells have completely sealed structure achieved with ceramic hermetic seal in order to endure the space environment. It has been confirmed that the cells performance satisfies space application requirements by many tests and analysis as follows: For environmental characteristics evaluation, various environmental tests such as vibration tests, thermal vacuum tests, irradiation tests and so on have been performed for the cells. It is found that the cells satisfy general environmental requirements of space applications. 100 Ah Li-ion cells have been qualified for space applications by MELCO. For cell life evaluation, the calendar life test and the cycle life test have been performed in matrix of temperature, state of charge (SOC), and depth of discharge (DOD). As the results, experimental equations for capacity fading has been found out. The equations have been verified by comparing capacity estimation curve and test data. By using the experimental equations, it was tried to calculate capacity fading for general geostationary orbit (GEO) and low earth orbit (LEO) satellites applications. It was confirmed that the estimation suggested the 100 Ah Li-ion cells satisfied requirements for their use in general satellites., 資料番号: AA0045915004

It has been attempted to develop a multidisciplinary design optimization tool for a large-scale system using Genetic Algorithm (GA), and to apply this results of the latest calculation for the problem above obtained by the developed tool showed that airframes (solutions) converged on four areas in the solution space and sensitivity of design variables of the airframe shape was remarkably different in each convergence area. Although high-ranking solutions having good value of the performance index have various airframe configurations, those flight trajectories hardly changed. The best solution showed that it is necessary to reduce the weight of airframe components and to improve the performance of air-breathing engine for realizing a feasible airframe size. It is suggested that this tool is absolutely useful for searching a solution at the conceptual designing phase of a spaceplane., 資料番号: AA0045426034

第56回宇宙科学技術連合講演会（2012年11月20日-22日. 別府国際コンベンションセンター（ビーコンプラザ）), 別府市, 大分県, 資料番号: ARDS12095000

第30回宇宙エネルギーシンポジウム(2011年2月25日, 宇宙航空研究開発機構宇宙科学研究所相模原キャンパス), 相模原市, 神奈川県, The thirtieth Space Energy Symposium (February 25, 2011. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)), Sagamihara, Kanagawa Japan, GS Yuasa Technology has developed the prototype 110 Ah class next generation lithium-ion cells in cooperation with JAXA in order to meet the requirements of higher energy density and longer life performances for future satellite applications. The cells were then subjected to cycle life and safety tests.The cells show extremely small discharge capacity loss ratio of 15% after long term 100% DOD cycling of 2,000 cycles.This ratio is only about half of that of the standard cells. The cells also show only a small decrease in discharge voltage after the cycle test. From this result, the cells are considered to deliver larger capacity and higher power at the end of satellite life.Furthermore, the cells show the superior safety against external short circuit, overcharge, and over-discharge tests though the energy density is increased by 10% compared with that of the standard cells., 形態: カラー図版あり, 形態: CD-ROM1枚, Physical characteristics: Original contains color illustrations, Note: One CD-ROM, 資料番号: AA0065107001

第18回高温エレクトロニクス研究会. 日時: 2008年3月5日. 会場: 宇宙航空研究開発機構宇宙科学研究本部相模原キャンパス, 宇宙環境に適応した容量50-175Ahのリチウムイオンセルを開発し、これらセルの種々の条件下での寿命性能評価(カレンダー寿命および充放電サイクル性能)を1999年から開始している。約7年間におよぶ試験データとリチウムイオン電池の劣化メカニズムに基づき、これらリチウムイオン電池の寿命予測方法を確立した。本講演では、リチウムイオン電池の劣化メカニズム、寿命予測方法、そして高温下での充放電挙動について説明する。, Large capacity Li-ion cells with 50-175 Ah had been developed to meet the requirements of space environment. Calendar and cycle life characteristics of the Space Li-ion cells have been evaluated under various test conditions with wide range of temperature (0 deg. C - 60 deg. C), depth of discharge (3 % - 80 % DOD), and state of charge (0 % - 100 % SOC). The test was started in June 1999, and the data have been accumulated for around seven years. From these results, based on capacity loss mechanism, we have established calendar and cycle capacity loss estimation method for the Li-ion cells. In this presentation, we will explain capacity loss mechanism, life estimation method and charge-discharge performance at high temperature for the Lithium-Ion Cells., 資料番号: AA0063966007

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制度:新 ; 文部省報告番号:乙860号 ; 学位の種類:博士(文学) ; 授与年月日:1991/11/19 ; 早大学位記番号:新1753

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