不同轨道航天器表面带电的模拟  

Surface Charging Simulation of Spacecraft in Different Orbit

作　　者：原青云[1] 孙永卫[1] 

机构地区：[1]军械工程学院静电与电磁防护研究所,河北石家庄050003

出　　处：《河北师范大学学报（自然科学版）》2015年第1期38-45,共8页Journal of Hebei Normal University：Natural Science

基　　金：国家自然科学基金(51177173);电磁环境效应国家重点实验室基金(9140C87010313JB34004)

摘　　要：针对航天器表面充放电效应带来的影响,基于粒子分室法(PIC),利用SPIS(spacecraft plasma interaction system)模拟了低地球轨道(LEO)和地球同步轨道(GEO)上航天器表面的带电情况,分析了航天器表面充电电位、充电时间、航天器周围等离子体电荷分布等规律.结果显示,由于GEO上等离子体温度高、浓度低,而LEO上等离子体温度低、浓度高,因此,GEO上航天器表面电位远大于LEO上航天器表面电位;航天器的尾迹效应对周围等离子体分布影响显著;由于传统估算公式没有考虑航天器表面电子聚集速度降低的问题,因此,SPIS模拟计算航天器表面电位达到稳定状态的充电时间要比估算值大.Considering the effects of surface charging on spacecraft,based on the particle-in-cell（PIC）method,the surface charging of spacecraft in low earth（LEO）and geosynchronous earth orbit（GEO）were simulated by spacecraft plasma interaction system（SPIS）,and the surface charging potential,charging time and charge distribution of plasma around spacecraft were also analyzed.The results show that the surface potential of spacecraft in GEO is larger than that in LEO,because of the high temperature and low concentration plasma in GEO,and the low temperature and high concentration plasma in LEO.The plasma distribution around spacecraft is influenced evidently by the wake effect of spacecraft.The decreasing of the electron collected speed on the spacecraft surface is not considered in the traditional estimated formula,therefore,the charging time of the spacecraft surface charging potential increasing to a stability condition simulated by SPIS is longer than that calculated by the estimated formula.

关 键 词：表面充电 低地球轨道 地球同步轨道 等离子体 

分 类 号：O441[理学—电磁学] TK519[理学—物理]