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摘要:
太阳电池阵为航天器提供能源，在型号研制和在轨运营过程中需对其供电能力进行计算，为此提出了一种航天器太阳电池阵供电能力的计算方法。首先，利用太阳电池片的地面测试数据得到标准测试条件（STC）下的电池片伏安模型，并利用电池片在轨等效光强和温度修正电池片伏安模型的光生电流、串联电阻和并联电阻等参数，得到电池片在轨伏安模型，然后，根据基尔霍夫定律推导出电池阵中电池片工作电压、电流以及旁路二极管和隔离二极管的输出情况，从而得到太阳电池阵的伏安模型。仿真结果表明，本文方法可以精确计算航天器在任意光强、温度和遮挡下的太阳电池阵伏安模型，可以精确分析旁路二极管和隔离二极管对太阳电池阵供电能力的影响，较已有方法计算精度提高20%。
Abstract:The solar array supplies power to spacecraft. Thus, it is important to predict power supply capability for spacecraft design and certification of on-orbit flight operation, and a calculation method for power supply capability of spacecraft solar array is proposed. The current versus voltage model of photovoltaic cell under standard test condition (STC) was developed using a group of ground test data, and then the parameters of the model such as photon current, cell series resistance, and cell shunt resistance were adapted to on-orbit irradiation intensity, temperature and shadow. According to Kirchhoff law, the outputs of photovoltaic cell working voltage, current, bypass diodes and block diodes in solar array were obtained, and the model of photovoltaic array was built. Simulation was performed for a typical spacecraft. Results show that this method is applicable to photovoltaic array power capability analysis under arbitrary irradiation intensity, temperature and shadow pattern, the influence of bypass diode and block diode in the solar array is analyzed accurately, and calculation accuracy is improved by 20% compared to traditional method.
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Key words:
- solar array /
- power supply capability /
- shadow /
- irradiation intensity /
- temperature
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图 1 太阳电池阵供电能力计算流程
Figure 1. Calculating process of solar array's power supply capability
图 3 标准测试条件下太阳电池片伏安测试数据
Figure 3. I-V test data of solar cell under standard test condition
图 5 不同光强下的太阳电池片I-V曲线
Figure 5. Solar cell I-V curves under different irradiation intensity
图 11 航天器几何模型与太阳电池片电路模型
Figure 11. Spacecraft geometric model and solar cell circuit model
图 14 太阳帆板1电流与太阳入射角余弦关系
Figure 14. Relationship between current of solar array 1 and cosine of sun incident angle
图 18 不同阴影形状下的太阳电池阵输出电流
Figure 18. Output currents of solar array with different shadow patterns
参数 数值 短路点电流Isc/A 0.17123 短路点导数dsc -0.87479 开路点电压Voc/V 2.71 开路点导数doc -5000.5 最大功率点电流Im/A 0.16725 最大功率点电压Vm/V 2.41 电池片尺寸/(mm×mm) 50×38 电流温度系数a/(A·℃-1) 0.011×10-3 
下载: 导出CSV
表 2 旁路二极管和隔离二极管参数
Table 2. Parameters of bypass diode and block diode
参数 数值 理想因子n 1.95 二极管饱和电流Io/A 0.9×10-8
下载: 导出CSV
表 3 航天器轨道参数
Table 3. Orbit parameters of spacecraft
参数 数值 轨道高度/km 393 轨道倾角/(°) 42 太阳入射角(太阳矢量与轨道面夹角)/(°) 0~60 轨道环境光强/(W·m-2) 1353 太阳电池阵温度/℃ 75
下载: 导出CSV
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