低地球轨道航天器表面充电及其环境影响因素  

Surface Charging and Its Environment Influencing Factors for Low Earth Orbit Spacecraft

作　　者：赵呈选[1] 李得天[1] 杨生胜[1] 秦晓刚[1] 王俊[1] 

机构地区：[1]兰州空间技术物理研究所真空技术与物理重点实验室,兰州730000

出　　处：《高电压技术》2017年第5期1438-1444,共7页High Voltage Engineering

基　　金：国家自然科学基金(11605080;11305084)~~

摘　　要：低地球轨道(LEO)航天器(简称低轨航天器)表面充电电位及附近等离子体分布受空间环境条件的影响,空间环境变化引起的表面电位及附近等离子体分布变化会影响星上探测载荷的功能发挥。为此,通过建立低轨航天器表面电位3维仿真模型,计算了光照区、阴影区、极区极光椭圆区内,航天器表面不同材料及航天器结构地的充电电位和充电时间。研究结果表明:无光照时,航天器表面不等量带电很小,结构地电位为-0.7 V,当航天器经过存在极光电子沉降的极区时,表面不等量带电电位差>500 V;有光照时,航天器表面不等量带电电位差约为几十V,并且随着太阳电池阵偏置电位的增大而增大,同时航天器形成的尾迹形状随光照条件的变化而改变。计算数据为科学探测载荷的安装位置及主动电位控制提供了参考。Low earth orbit （LEO） spacecraft surface charging and ambient plasma distribution are affected by the space environment, and potential changes on the surface of the materials and the changes of the plasma distribution will affect the function of payloads on spacecraft. Consequently, we established a three-dimensional simulation model of surface charging of the low earth orbit spacecraft. The charging potentials of different materials and spacecraft frame and charg- ing balance time were comprehensively analyzed in sunlight, eclipse, and the polar auroral oval. The research results reveal that, in the absence of sunlight, the surface differential charging is small and the frame potential is -0.7 V, while the surface differential charging can be up to 500 V as spacecraft passing through polar region. For comparison, the dif- ferential charging are tens of volts, and increases with the increases of the solar array bias potential when spacecraft is in sunlight. Moreover, the spacecraft wake shape changes with light conditions. The calculations can provide an important reference for scientific exploration load installation and active potential control.

关 键 词：LEO航天器 PIC方法 材料充电 光照区充电 阴影区充电 极区充电 

分 类 号：V419[航空宇航科学与技术—航空宇航推进理论与工程]