Abstract
The lithium-ion secondary batteries have been widely used for the space programs, today. Among them, REIMEI was one of the first satellites using lithium-ion secondary battery. In 2005, the satellite was launched, and injected into the low earth polar orbit. Eleven years has passed since the launch and over 60,000 cycles of charge and discharge was experienced in space.The lithium-ion secondary cell of the REIMEI battery was designed using spinel manganese oxide type material for the positive electrode, and the graphitized type carbon for the negative electrode. The cell case was made of aluminium laminated film and the structure was reinforced by the epoxy resin and aluminium housing. After the operation of eleven years, the cells still maintain the appropriate uniform balance and operative. In order to identify the internal condition of the battery/cell, we calculated the ac impedance by the pulse duration to the on-board battery.
Highlights
Today, lithium-ion secondary battery is widely used for the spacecraft and satellites
The constant increase in impedance is obtained, which reflects the performance of the battery taking place after the long term operation of REIMEI satellite
It is well known that the increase in ac impedance proceeds due to the degradation of capacity and formation of Solid Electrolyte Interface (SEI)
Summary
Lithium-ion secondary battery is widely used for the spacecraft and satellites. We discuss the ac and dc impedance conditions of the batteries/cells after the long term operation of REIMEI satellite in space. 2. OUTLINE OF REIMEI AND CELL/BATTERY ‘REIMEI’ satellite before launch is shown Fig. 1. The satellite was launched in August, 2015 [2, 3] It was an engineering demonstrator for the cutting-edge satellite technology. It carried onboard instruments for scientific aurora observations which were suitable for a small satellite. The specifications of the cell are listed in Tab. 2 It was a lithium-ion secondary cell, whose positive material was spinel manganese oxide and the negative was graphitized carbon. We decided that the nominal charge voltage should be up to 4.1 V/cell to realize the longer operational period of the satellite. The current was acquired by 8 bit-data-recorder, and had the accuracy of ±23 mA [5]
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