Development of Li Ion Cells for Satellite Applications Masahiro Yamamoto Akira Takamuku Hiroki Ooto Shigeru Sakai Abstract Based on affluent R&D and production experiences of both Ni-Cd and Ni-MH cells for space and satellite applications, lithium ion secondary cells were developed. Prismatic cells encapsulated with plastics cases have been cycle-tested in continuation by test modes simulated for Geostationary Orbit Satellite (GEO) and Low Earth Orbit Satellite (LEO) since 1996. Hermetic cells with 14.5 Ah capacity were developed in thin-walled SUS casing with specially designed ceramic-sealed terminals. Lithium ion cells were demonstrated having energy density more than two times above the conventional cells along with long-life and reliability performance through varied electric and mechanical testing. Cycle life over 3800 in GEO mode doubled GEO target and one passing 15000 in continuation of test suggests to meet with LEO's ultimate target. 1. LIB LIB 1998Y. Sone LIB 1 Chad O.Kelly LIB 50 DOD 104025DOD 2780 2 1999 H. Yoshida LIB 100 * 25 DOD30000 3 H.Saito LIB 40 DOD 3500 4 1971 Ni-Cd 1998Ni-MH R&D 1996 LIB 7 LIB 13Ah LIB1999 2. GEO22 500 64
FBNo.56 2000. 11. 1 2000km LEO1 4 1 2 3. 3.1 LIB3.6V Ni-Cd Ni-MH 1.2V 20 45Wh/kg 1/3 3.2 LIB 120Wh kggeo 2000 LEO 30000 Ni-MH2 Items Rated Voltage (V) Rated Capacity (Ah) Specific Energy (Wh/kg) Volumetric Energy Density (Wh/L) Cycle Life in GEO () in LEO Available Temperature () Operation Life (yrs) 3.6 25 >120 >240 >2 k >30 k -2045 3.3 GIC LiMO2 PC 10Wh14Wh LIB 10Wh LIB 100 DOD 1 Fig.1 1 Table 1 Developmental Targets of Li Ion Cells for Satellite Applications. LIB Target 10 Ni-Cd 1.2 30 >27 >90 >1 k >20 k 035 5 Ni-MH 1.2 15 45 120 >1 k >15 k 035 5 100%DOD 2.6Ah Capacity and Energy Efficiency of 2.6 Ah Li Ion Cells during Cycle Test at of 100 %DOD 65
3.55400 62 GEO 10Wh LIB 65 DODLEO 14Wh LIB 33 DOD EVoD GEO3.5 4000 GEO EVoD 3.45V 72 LEO3 15000 500100%DOD 30000 LEO 33 DOD LEO 25 DOD 25 DOD40000 3 Fig.3 Relationship between Depth of Discharge and Cycle Life of Li Ion Cells 2 Fig.2 GEO65%DODLEO33%DOD 33%DOD Discharge Performance of Li Ion Cells during Cycle Test in GEO and LEO. DOD90 DOD100 DOD 90% 90 DOD DOD 3.4 3.3 LIB 13Ah 85Wh/kg 220Wh/l 3.4.1 2 Table 2 Specification of Li Ion Cells for Satellite. Rated Capacity Size WTH Mass Specific Energy Volumetric Energy Density 13.2 Ah 69.324.4132 mm 570 g-max >85 Wh/kg >220 Wh/ l 66
FBNo.56 2000. 11. 1 1 Phot 1 13Ah External View of a 13 Ah Class Li Ion Cell for Satellite. PC LiCoO2 PC PC 0.4mm 4 Fig.4 Cross Sectional View of a Li Ion Cell for Satellite. 3.4.2 1 100.2CA2CA 1CA 4.1V 2.5 100.2CA 14.5Ah 1CA3.6V 5 Fig.5 Discharge Characteristics of Li Ion Cells for Satellite at Various Discharge Rates. 2-20 10 67
10 0.5CA4.1V3.0 10 10 10 10 6 Fig.6 Discharge Characteristics of Li Ion Cells for Satellite at Various Discharge Temperature. 3 65 DOD 870 EVoD 10Wh 7 Fig.7 65%DOD Change in Discharge Performance of Li Ion Cells for Satellite during Cycle Test at 65% DOD. CHG : 1CA and 4.1V CCCV (Charge cut off after 2.5hr) DIS : 0.2CA CC (Discharge cut off at 8.85Ah) 4 1CA 3 Table 3 Conditions of Random Vibration Test Frequency/Hz 2045 4561 61150 150800 8002000 0 A Level +6dB/oct 3 G 2 /Hz -6dB/oct 0.5 G 2 /Hz -6dB/oct 27.6 Grms Test Duration : 45 seconds / each axis 4 Table 4 Conditions of Drop Shock Test Axis X, Y, Z Level 25G 0-P /10msec with half sin wave A drop shock test is conducted by applying the shock twice along each of mutually perpendicular three axes. 5 68
FBNo.56 2000. 11. 1 8 Fig.8 Discharge Curves of Li Ion Cells for Satellite during Random Vibration TEST. 10 Fig.10 Overcharge Test Results of Li Ion Cells for Satellite. Cell Condition: 100%SOC CHG: 13.2ACC (Charge cut off after 1hr) 9 Fig.9 Discharge Curves of Li Ion Cells for Satellite during Drop Shock TEST 11 Fig.11 Cell Condition: 100%SOC External Short Test Results of Li Ion Cells forsatellite. 104.1V 1CA2.5 1CA 1 200 20 4. 14.5Ah Ni-CdNi-MH 2 LEO GEO 12 3 69
5. 1) Y. Sone, H. Kusawake, K. Kanno, and S. Kuwajima, "The Applicability of Lithium-Ion Battery Cells to Space Programs," The 1998 NASA Aerospace Battery Workshopp.161-191, February 1999. 2) Chad O.Kelly, Shellie Wilson, "Satellite Cell Development : Lithium-Ion Profile", 12th AIAA/USU Conference on Small Satellites, p.1-111998. 3) H. Yoshida, S. Kitano, M. Terasaki, M. Mizutani, T. Inoue, and K. Komada,"Development of Large-scale Lithium Ion Batteries for Space Applications," GS News Technical ReportVol.58, No.1 p.21-261999. 4) H. Saito, T. Mizuno, K. Tanaka, Y. Masumoto, M. Shirakata, H. Kawai, T. Muramatsu, A. Saito, "Development of Li-ion Rechargeable Battery for INDEX", Proceedings of the 19TH ISAS SPACE ENERGY SYMPOSIUM, p.6-9, Februay 2000. 5) K. Matsumoto, K.Takahashi, M.Kikuta, T. Iwabuchi and M.Tajima, "A Variety of Development Test Results of NiMH Cells for Space Applications," Proceedings of the Fifth European Space Power Conference, Tarragona, Spain, ESA SP-416, pp.703-708, September 1998. 6) PLANET-BNiMH44 200010 7) M. Yamamoto, H. Ooto, A. Takamuku, S. Sakai, M. Tajima, K. Takahashi, "Lithium Secondary Cell for Space Satellite ; Development of Long Life Cell and Basic Properties", Proceedings of the 18TH ISAS SPACE ENERGY SYMPOSIUM, p.47-50, February 1999. 70