LEO航天器太阳电池阵激光诱导电弧放电试验与分析  

Laser-induced Arc Discharge Experiment and Analysis of LEO Spacecraft Solar Array

作　　者：尉德杰 朱立颖[2] 武建文[1] 刘业楠[3] 王志浩[3] 王思展 聂翔宇[3] 杜嘉余 WEI Dejie;ZHU Liying;WU Jianwen;LIU Yenan;WANG Zhihao;WANG Sizhan;NIE Xiangyu;DU Jiayu(School of Automation Science and Electrical Engineering,Beihang University,Beijing 100191,China;Beijing Institute of Spacecraft System Engineering,Beijing 100094,China;Beijing Institute of Spacecraft Environment Engineering,Beijing 100094,China)

机构地区：[1]北京航空航天大学自动化科学与电气工程学院,北京100191 [2]北京空间飞行器总体设计部,北京100094 [3]北京卫星环境工程研究所,北京100094

出　　处：《航天器工程》2024年第1期131-137,共7页Spacecraft Engineering

摘　　要：基于太阳电池阵空间电弧放电理论,对纳秒脉冲激光诱导太阳电池阵电弧放电机理进行分析,采用空间放电模拟试验系统,试验研究了低地球轨道(LEO)等离子体环境下纳秒脉冲激光诱导太阳电池阵电弧放电的功率密度阈值及其放电特性。试验结果表明:LEO等离子体环境下激光诱导太阳电池阵电弧放电的功率密度阈值约为1.08×10^(8)W/cm^(2),与无激光诱导相比,放电持续时间增加了20%,且每施加1次纳秒脉冲激光诱导电弧放电概率约为60%。对比分析不同工况下的太阳电池阵损伤效应可得:纳秒脉冲激光诱导电弧放电破坏绝缘层最严重,容易造成太阳电池阵中部分PN结短路失效,其损坏程度远远大于空间环境太阳电池串间电弧放电烧蚀损坏效应和盖玻片表面热应力损伤造成的PN结断路失效。此结论可为航天器太阳电池阵放电试验的措施及试验参数选取提供参考。Based on the space arc discharge theory of solar array,the mechanism of nanosecond pulse laser-induced arc discharge of solar array is analyzed.The power density threshold and discharge characteristics of nanosecond pulse laser-induced arc discharge of solar array in LEO(low earth orbit)plasma environment are experimentally studied by using space discharge simulation experiment system.The results indicate that the power density threshold of laser-induced solar array arc discharge in the LEO plasma environment is about 1.08×108 W/cm 2.Compard with no laser-induced discharge,the discharge duration has increased by 20%,and the probability of discharge induced by each nanosecond pulse laser application is about 60%.By comparing and analyzing the damage effects of solar array under different working conditions,it can be concluded that nanosecond pulse laser-induced arc discharge destroys the insulation layer most seriously,which is easy to cause partial PN junction short circuit failure in solar cells.The damage degree is far greater than that of discharge ablation damage effect between strings in the space environment and the PN junction open circuit failure caused by thermal stress damage on cover glass surface.This conclusion can provide a reference for measures and parameters for discharging tests of spacecraft solar array.

关 键 词：低地球轨道航天器 太阳电池阵 纳秒脉冲激光 电弧放电特性 

分 类 号：V442[航空宇航科学与技术—飞行器设计]