航天器表面充电快速估算与主动控制技术研究  

Research on fast estimation and active control technology of spacecraft surface charging

作　　者：张兰勇 王嘉豪 ZHANG Lanyong;WANG Jiahao(Harbin Engineering University,Harbin 150001,China)

机构地区：[1]哈尔滨工程大学,哈尔滨150001

出　　处：《兵器装备工程学报》2022年第11期130-135,共6页Journal of Ordnance Equipment Engineering

基　　金：黑龙江省自然科学基金项目(LH2021E045)。

摘　　要：空间等离子体的注入导致航天器表面不等量充电是引发航天器静电放电的一个重要原因。针对地球同步轨道中等地磁亚暴空间环境的AST-6卫星,基于等效电路理论和电流平衡方程建立了航天器表面充电电位随时间变化的微分方程组,通过求解该微分方程组实现对航天器表面各等效元充电电位快速估算,发现了各等效元之间存在不等量充电的问题,进一步分析了通过模拟在航天器表面发射电子束来实现主动控制各等效元充电电位的有效性,结果表明:当电子束流密度J_(ee)由0 A/m^(2)增大到1.8×10^(-6) A/m^(2)时,航天器表面各等效元之间的最大充电电位差由4899 V降至785 V。此外,通过改变电阻、电容值来模拟航天器表面材料特性对航天器表面充电电位的影响,结果表明:航天器表面材料的电阻、电容值越小,其充电电位值越接近航天器金属结构的电位值。可见在航天器表面发射合适的电子束和选取合适的表面材料可以有效的降低充电过程中各等效元之间的充电电位差,减小航天器静电放电的可能性,以保障航天器的安全运行。The unequal charging of spacecraft surface caused by space plasma injection is an important reason for spacecraft electrostatic discharge.Aiming at the AST-6 satellite with medium geomagnetic substorm space environment in geosynchronous orbit,based on the equivalent circuit theory and current balance equation,the differential equations of spacecraft surface charging potential varying with time were established.By solving the differential equations,the rapid estimation of the charging potential of each equivalent element on the spacecraft surface was realized,and the problem of unequal charging between each equivalent element was found.The effectiveness of actively controlling the charging potential of each equivalent element by simulating the emission of electron beam on the spacecraft surface was further analyzed.The results show that when the electron beam J_(ee) increases from 0 A/m^(2) to 18 A/m^(2),the maximum charging potential difference between equivalent elements on the spacecraft surface decreases from 4899 V to 785 V.In addition,the influence of the characteristics of spacecraft surface materials on spacecraft charging was simulated by changing the resistance and capacitance values.The results show that the smaller the resistance and capacitance values of spacecraft surface materials are,the closer the charging potential value is to the potential value of spacecraft metal structure.It can be seen that launching an appropriate electron beam on the spacecraft surface and selecting appropriate surface materials can effectively reduce the maximum charging potential difference between equivalent elements in the charging process,reduce the possibility of spacecraft electrostatic discharge,and ensure the safe operation of spacecraft.

关 键 词：航天器表面充电 中等地磁亚暴 等效电路 电位主动控制 数值模拟 

分 类 号：V416.5[航空宇航科学与技术—航空宇航推进理论与工程] TP391.9[自动化与计算机技术—计算机应用技术]