航天器内部孤立导体电子照射表面起电时域特性  

Time Domain Characteristics of Isolated Conductor Surface Electrification by Electronic Irradiation Inside Spacecraft

作　　者：曹鹤飞[1,2] 孙永卫[1] 原青云[1] 许滨[1] 

机构地区：[1]军械工程学院静电与电磁防护研究所,石家庄050003 [2]石家庄学院物理系,石家庄050035

出　　处：《高电压技术》2015年第3期991-997,共7页High Voltage Engineering

基　　金：中国博士后科学基金(2012M521886;2014T71006);国家自然科学基金(51177173);石家庄学院科研平台(XJPT002)~~

摘　　要：为解决高能电子给航天器内部孤立导体带来的静电充电问题,综合考虑空间环境中电子流密度、照射电子能量、金属材料二次电子特性及材料大小等因素,理论推导出电子照射金属表面起电时域一般微分表达式。利用有限差分法对微分方程进行数值求解,通过具体例子讨论了不同金属在电子照射下表面电位随时间变化的情况。得到了入射电子流密度、电子能量、金属二次电子系数及照射时间等因素与航天器内部孤立导体表面电位变化规律。结果表明,通过对材料及航天器内部空间环境参数的控制,可以使充电至放电电位所需时间大于放电时间,避免持续不间断放电的发生,从而减小放电造成的危害。In order to solve electrostatic charging problems of internal isolated conductor in spacecraft caused by high energy electron, taking the factors such as the electron current density in the space environment, irradiating electronic energy, secondary electron characteristics of metal materials, material size and other factors, into consideration, we deduced a general differential expression of metal surface electrification under electron irradiation in time domain. Then, the differential equations are numerically calculated using the finite difference method for several specific examples. Moreover, the dependence of surface potential on time for different metals under electron irradiation is discussed. Spacecraft isolated conductor surface electrification is affected by many factors including the electron density, electron energy, the coefficient of secondary electron, irradiation time and so on. The results show that the charging time can be prolonged over the discharge time by controlling the material parameters and spacecraft internal environment parameters,avoiding the occurrence of continuous discharge and reducing the damages.

关 键 词：孤立导体 电子照射 二次电子 表面电位 起电时间 电子能量 

分 类 号：V443[航空宇航科学与技术—飞行器设计]