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在一种简化的太阳电池阵结构模型基础上,利用太阳电池阵电流收集经验模式,基于电流平衡,建立了一种计算低轨道航天器高电压太阳电池阵在等离子体环境中电流泄漏的方法.利用该方法,对高电压太阳电池阵电流泄漏效应与低轨道等离子体环境、电池阵电压、电池阵裸露金属面积的关系进行了分析计算.结果表明,随着轨道高度增加,电流泄漏引起的电池阵功率损失迅速下降,影响最严重的区域为电离层等离子体密度最高的300～400 km高度的轨道区域;电流泄漏引起的功率损失与太阳电池阵电压呈指数关系,电压越高功率损失越大;200 V以下的电池阵功率损耗较小,远低于电源系统总功率的1%;电流泄漏与太阳电池阵裸露金属导体的表面积呈正比关系,因此,通过减少太阳电池阵裸露面积,可以降低电流泄漏的影响.
Based on a simplified model of solar array structure, a model for calculating the current leakage in high-voltage solar arrays of low-orbit spacecraft based on the current balance is established based on the experience model of solar array current collection. The relationship between the current leakage effect of high voltage solar array and the environment of low orbit plasma, the cell array voltage and the bare metal area of the array is analyzed and calculated by this method.The results show that with the increase of orbital height, the current leakage caused by the battery The power loss rapidly decreases. The most serious area is the orbit area of 300-400 km with the highest ionospheric plasma density. The power loss caused by current leakage is exponential with the solar array voltage. The higher the voltage, the greater the power loss ; Less than 200 V power loss of the battery array smaller, far less than 1% of the total power system; current leakage and solar cell array bare metal conductor surface area is proportional to, therefore, by reducing solar cell array exposed area, can reduce Effect of current leakage.