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首页> 外文会议>55th International Astronautical Congress 2004 vol.10 >BATTERY BASED ON LI-ION AND COTS TECHNOLOGIES: A TEST CASE TO IMPLEMENT HIGH PERFORMANCE, AUTONOMY, AND MODULARITY FOR FUTURE MICROSATELLITES
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BATTERY BASED ON LI-ION AND COTS TECHNOLOGIES: A TEST CASE TO IMPLEMENT HIGH PERFORMANCE, AUTONOMY, AND MODULARITY FOR FUTURE MICROSATELLITES

机译：基于锂离子和柯茨技术的电池：未来微卫星实现高性能，自律性和模块化的测试案例

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The paper describes the design, prototype realization, and preliminary tests on an experimental battery module designed taking into account typical microsatellites power requirement, but integrating small capacity terrestrial Li-Ion battery cells, charge/discharge electronics based on COTS integrated circuits and logical electronics able to provide an internal battery management capability. A string of six Li-ion cells (SAFT® prismatic MP17650 - 5.5Ah) able to meet typical microsatellites power requirements has been used (mass of 0.9 Kg, volume of 4.6* 10~(-4) m~3, and experimentally verified charge/discharge efficiency of 90%). The battery charge consists in constant current/constant voltage realized by means of the Linear Technology LTC4008 and the battery discharge is performed at constant power, by means of DC-DC step-up conversion based on the Maxim MAX668. Both electronics have experimentally demonstrated efficiencies well above 90%, with associated a mass of 14 g and a volume of 4*10~(-6) m~3. The internal control level is performed using a Microchip PIC18F248, that meet all defined requirements and can be integrated in a control area network to simplify the interfacing with the other satellite system. In order to verify space environment compliance, an analysis on EMI required tests and the possible radiation related failure have been performed.
机译：本文介绍了针对实验性电池模块的设计，原型实现和初步测试，该模块的设计考虑了典型的微卫星功率需求，但集成了小容量地面锂离子电池，基于COTS集成电路的充电/放电电子设备和具有逻辑功能的电子设备。提供内部电池管理功能。已使用一串可满足典型微卫星功率要求的六节锂离子电池（SAFT®棱柱形MP17650-5.5Ah）（质量为0.9 Kg，体积为4.6 * 10〜（-4）m〜3，并经过实验验证）充放电效率达90％）。电池充电包含通过Linear Technology LTC4008实现的恒定电流/恒定电压，而电池放电是通过基于Maxim MAX668的DC-DC升压转换以恒定功率进行的。两种电子设备均已通过实验证明其效率远高于90％，并具有14 g的质量和4 * 10〜（-6）m〜3的体积。内部控制级别使用Microchip PIC18F248来执行，该芯片可以满足所有定义的要求，并且可以集成到控制区域网络中以简化与其他卫星系统的接口。为了验证空间环境合规性，已对EMI所需的测试以及可能的辐射相关故障进行了分析。

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