该文介绍一种卫星太阳翼在轨功率输出预测方法,由单体太阳电池根据固体物理理论推导出来直流理论分析模型获得其等效电路,通过对单体太阳电池串、并联后组成的太阳翼电气电路,获得太阳翼等效电路,并根据该等效电路推导出太阳翼的直流分析模型。将太阳翼的直流分析模型转化为由单片太阳电池片开路电压Voc、短路电流Isc、最大功率点电压Vmp、最大功率点电流Imp这4个参数决定的太阳翼工程应用方程。同时,通过地面试验获得单体太阳电池的电压和电流衰降系数,获取太阳翼实际在轨不同时刻的开路电压VAoc、短路电流IAsc、最大功率点电压VAmp、最大功率点电流IAmp,并通过计算获取太阳翼工作点电压、电流,得到太阳翼的在轨预测工作输出功率。通过将该文模型预测值与太阳翼实际在轨输出电流、电压遥测值进行比较,验证该预测模型的有效性。该预测模型可通过单体太阳电池的4个工程参数,获得整个太阳翼的直流分析模型,便于太阳翼设计阶段建模分析的工程化应用。
Abstract
A solar array DC analysis model is introduced in this paper, by exploiting equivalent circuit of solar array which is composed of solar cell series and parallel connected and DC analysis model of cell derived from solid-state physics theory, the output power of solar array on orbit is predicted. The solar array DC analysis model is converted to an equation determined by four parameters： open circuit voltage of solar cell Voc; short circuit current of solar cell Isc; maximum power point voltage of solar cell Vmp; maximum power point current of solar cell Imp. By getting the real parameters of solar array VAoc, IAsc, VAmp, IAmp on orbit through obtaining the degradation coefficient for solar cell current and voltage through ground testing. The working point voltage and current of solar array is calculated, and the output power of solar array on orbit is predicted. The prediction model is proved to be effective by comparing the solar array on orbit remote telemetry value of working point voltage and current with the prediction result. The prediction model can get the DC analysis model of solar array with four parameters of solar cell and help to analysis of solar array modeling for engineering application during system design stage.
关键词
卫星 /
太阳翼 /
功率预测 /
建模 /
直流分析模型
Key words
satellite /
solar array /
power prediction /
modeling /
DC analysis model
{{custom_sec.title}}
{{custom_sec.title}}
{{custom_sec.content}}
参考文献
[1] 马世俊. 卫星电源技术[M]. 北京: 中国宇航出版社, 2001: 142-144.
MA S J.Satellite power technology [M]. Beijing: China Astronautics Press, 2001: 142-144.
[2] 李国欣. 航天器电源系统技术概论[M]. 北京: 中国宇航出版社, 2008: 363-365.
LI G X.Spacecraft power system technique summary[M]. Beijing: China Astronautics Press, 2008: 363-365.
[3] 穆肯德∙R∙帕特尔. 航天器电源系统[M]. 韩波, 陈琦,崔晓婷,译. 北京: 中国宇航出版社, 2010: 139-142.
[4] 苏建徽, 余世杰, 赵为, 等. 硅太阳电池工程用数学模型[J]. 太阳能学报, 2001,22(1): 409-412.
SU J H,YU S J,ZHAO W,et al.Investigation on engineering analytical model of silicon solar cells[J]. Acta energiae solaris sinica , 2001, 22(1): 409-412.
[4] MOHSEN T, GHAFOOIFARD H, REZAIE A H, et al.Evaluation end-of-life power generation of a satellite solar array[J]. Energy conversion and management, 2011, 52: 2518-2525.
[5] CHO B H, LEE C Y.Modeling and analysis of spacecraft power systems[J]. Transactions on power electronics, 1988, 3(1): 44-52.
[6] 彭乐乐, 孙以泽, 林学龙, 等. 工程用太阳电池模型及参数确定法[J]. 太阳能学报, 2012, 33(2): 283-286.
PENG L L, SUN Y Z, LIN X L, et al.Engineering model and parameters determination method of photovoltaic cell and array[J]. Acta energiae solaris sinica , 2012, 33(2): 283-286.
[7] JANG S S, KIM S H, LEE S R, et al.The failure analysis of paralleled solar array regulator for satellite power system in low earth orbit[J]. Journal of astronomy and space sciences, 2011, 28(2): 133-141.
[9] 鄢婉娟. 太阳同步轨道卫星电源系统设计计算方法研究[J]. 中国空间科学技术, 2011, 21(2): 19-25.
YAN W J.Research of sun synchronization orbit satellite power system design computation method[J]. Chinese space science and technology, 2011, 21(2): 19-25.
[10] 张翼, 姜东升, 刘震. 卫星电源系统太阳电池建模与仿真研究[C]//电力电子与航天技术高峰论坛, 中国深圳, 2014: 343-348.
ZHANG Y, JIANG D S, LIU Z.Research on Modeling and simulation of satellite electrical power system[C]// Electrical, Electronic and Aerospace Forum, Shenzhen, China, 2014: 343-348.
[11] 姜东升, 刘书豪, 马宁, 等. 一种适用于卫星太阳翼在轨输出功率预测的工具方法[C]// 第四届高分辨率对地观测学术年会, 中国武汉, 2017: 24-35
JIANG D S, LIU S H, MA N, et al.The Tools and method for satellite solar array power prediction on orbit[C]//The 4th China High Resolution Earth Observation Conference, Wuhan, China, 2017: 24-35.
PDF(1635 KB)
