电推进等离子体对航天器表面带电影响的理论研究
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- 英文论文题名：Theory study of ion thruster plume to spacecraft charging
- 论文作者：冯娜 ; 杨生胜 ; 李得天 ; 陈益峰 ; 秦晓刚 ; 赵呈选 ; 汤道坦 ; 郭睿
- 英文论文作者：FENG Na ; YANG Sheng-sheng ; LI De-tian ; CHEN Yi-feng ; QIN Xiao-gang ; ZHAO cheng-xuan ; TANG Dao-tang ; GUO Rui ; Science and Technology on Vacuum Technology and Physics Laboratory ; Lanzhou Institute of Physics
- 年：2015
- 作者机构：兰州空间技术物理研究所真空技术与物理重点实验室;
- 论文关键词：离子推力器 ; 表面充放电效应 ; 空间等离子体 ; 交换电荷离子 ; 理论研究
- 英文论文关键词：Ion thruster ; spacecraft charging ; space charging ; charge-exchange ions ; theory study
- 会议召开时间：2015-08-12
- 会议录名称：静电放电：从地面新技术应用到空间卫星安全防护—中国物理学会第二十届全国静电学术会议论文集
- 语种：中文
- 分类号：V419;V439.4
- 学会代码：WLJD
- 会议名称：静电放电 ; 从地面新技术应用到空间卫星安全防护—中国物理学会第二十届全国静电学术会议
- 会议地点：中国河北石家庄
- 主办单位：中国物理学会静电专业委员会
- 学会名称：中国物理学会静电专业委员会
- 页数：4
- 文件大小：665k
- 原文格式：D
- 会议级别：全国
摘要
电推进在轨工作时将产生低温稠密等离子体,与GEO轨道的空间离子体特性存在较大差异,且羽流中交换电荷等离子体易受到卫星表面电位的作用,形成返流并作用于大型太阳电池阵,对航天器表面带电效应的产生重要影响。为此,本文开展电推进等离子体对航天器表面带电效应的理论研究。本文利用麦克斯韦分布描述空间等离子体分布特性,计算获得空间等离子体中电子和离子充电电流,综合考虑材料二次电子和背散射电子发射电流,分析电推进产生等离子体充电特性,并基于充放电平衡方程建立表面充电电位的计算方法,进行电推进产生等离子体和空间等离子体综合作用下的表面带电机理分析。空间等离子体电子电流密度约为10-6A/m2,交换电荷返流及中和电子电流密度约为10-3A/m2,因此当电推进工作时,其羽流离子体成为卫星充电的主导因素。在综合考虑空间等离子体充电电流以及材料特性时,太阳电池玻璃盖片表面充电平衡电位为-30000V,而仅考虑电推进充电电流时,卫星表面电位钳制在-10V左右。通过与国外在轨实验数据进行对比,研究表明,电推进工作时,其羽流等离子体为卫星表面带电的主要影响因素,且交换电荷返流及中和电子可以缓解由空间等离子体造成的危害性表面充放电效应。
Dense plume induced by electric propulsion thruster has high density and low energy which is quite different from space plasma on geosynchronous orbit.The difference between thruster and space plasma may result in spacecraft surface charging becoming more complicated.Moreover,in ion plume the charge-exchange ions(CEX)influenced by spacecraft surface potential may form backflow,then also induce surface charge and discharge.Therefore,this paper focuses on theory study of ion thruster plume to spacecraft charging.By describing the distribution feature of the space plasma by Maxwell function,the paper calculated the electron and ion charging current,secondary electron and backscattered electron emission current,analyze physics characteristics of the thruster plume,and built the computation method of the surface charge potential by charge and discharge balance equation.The space plasma electron current density is about 10-6A/m2,and the CEX ions and neutralization electron current density can be reached 10-3A/m2 which is far greater than the space charging current.Therefore,the thruster plasma current becomes main reason for spacecraft surface charging when thruster is working.Synthetically considering the electron and ion charging current,secondary electron and backscattered electron emission current,the spacecraft surface charge potential is about-30000V.However,the spacecraft surface charge potential is about-10V just with thruster plasma.Comparisons with experiment data on orbit,the results suggested that the thruster plasma current becomes main reason for spacecraft surface charging when thruster is working.Moreover,the backflow and neutralization electron current can release damage effect caused by spacecraft charging.
Dense plume induced by electric propulsion thruster has high density and low energy which is quite different from space plasma on geosynchronous orbit.The difference between thruster and space plasma may result in spacecraft surface charging becoming more complicated.Moreover,in ion plume the charge-exchange ions(CEX)influenced by spacecraft surface potential may form backflow,then also induce surface charge and discharge.Therefore,this paper focuses on theory study of ion thruster plume to spacecraft charging.By describing the distribution feature of the space plasma by Maxwell function,the paper calculated the electron and ion charging current,secondary electron and backscattered electron emission current,analyze physics characteristics of the thruster plume,and built the computation method of the surface charge potential by charge and discharge balance equation.The space plasma electron current density is about 10-6A/m2,and the CEX ions and neutralization electron current density can be reached 10-3A/m2 which is far greater than the space charging current.Therefore,the thruster plasma current becomes main reason for spacecraft surface charging when thruster is working.Synthetically considering the electron and ion charging current,secondary electron and backscattered electron emission current,the spacecraft surface charge potential is about-30000V.However,the spacecraft surface charge potential is about-10V just with thruster plasma.Comparisons with experiment data on orbit,the results suggested that the thruster plasma current becomes main reason for spacecraft surface charging when thruster is working.Moreover,the backflow and neutralization electron current can release damage effect caused by spacecraft charging.
引文
[1]张天平.国外离子和霍尔电推进技术最新进展[J].真空与低温.2006,12(4):187~193
[2]Dudzinski L A,Pen Pencil E J.Electric propulsion requirements and mission analysis under NASA’s in-space propulsion technology project[C].30th International Electric Propulsion Conference,Italy,2007
[3]Martin Tajmar,RenéSedmik,and Carsten Scharlemann.Numerical Simulation of SMART-1 Hall-Thruster Plasma Interactions[J].Journal of Propulsion and Power.2009,25(6):1178-1188.
[4]Likar J J.Interaction of charged spacecraft with electric propulsion plume:on orbit date and ground test result[J].IEEE Transactions on Nuclear Science,2006,53(6):345~356
[5]刘磊,张庆祥,王立,薛玉雄,杨生胜,安恒.电推进羽流与航天器相互作用的研究现状和建议[J].航天器环境工程.2011,28[5]:440-445.
[6]Katz et al.The importance of accurate secondary electr on yields in modeling spacecraft charging[J].Journal of Geophysical Research.1986,vol.91:589~512.
[7]D.Hastings,M.Cho,and P.Chang.Interactions between a plasma flow and a highly biased solar array[C].In 25th Joint Propulsion Conference,1989.
[8]H.B.GARRETT.The Charging of Spacecraft Surfaces.Reviews of Geophysics and Space Physics,1981,19(4):577-616.
[9]KATE,M.MANDELL,G.JONGEWARD,et al.The Importance of Accurate Secondary Electron Yields in Modeling Spacecraft Charging.Journal of Geophysical Research.1986,91(12):13739-13744.
[10]S.Brosse,S.Clerc.Modeling of the plasma thruster impact on spacecraft charging[C].The 29th International Electric Propulsion Conference,.2005.10.
[11]Mandell,M.J.,Davis,V.A.,Gardner,B.,Jongeward,G.,Electron collection by international space station solar arrays.8th spacecraft charging technology conference,Huntsville,Alabama,October20-24,2003.
[12]Joel L.Herr,TROPIX Plasma Interactions Group Report,NASA Contractor Report 191149,Sverdrup Technology Inc.,NASA Lewis Research Center Group.
[2]Dudzinski L A,Pen Pencil E J.Electric propulsion requirements and mission analysis under NASA’s in-space propulsion technology project[C].30th International Electric Propulsion Conference,Italy,2007
[3]Martin Tajmar,RenéSedmik,and Carsten Scharlemann.Numerical Simulation of SMART-1 Hall-Thruster Plasma Interactions[J].Journal of Propulsion and Power.2009,25(6):1178-1188.
[4]Likar J J.Interaction of charged spacecraft with electric propulsion plume:on orbit date and ground test result[J].IEEE Transactions on Nuclear Science,2006,53(6):345~356
[5]刘磊,张庆祥,王立,薛玉雄,杨生胜,安恒.电推进羽流与航天器相互作用的研究现状和建议[J].航天器环境工程.2011,28[5]:440-445.
[6]Katz et al.The importance of accurate secondary electr on yields in modeling spacecraft charging[J].Journal of Geophysical Research.1986,vol.91:589~512.
[7]D.Hastings,M.Cho,and P.Chang.Interactions between a plasma flow and a highly biased solar array[C].In 25th Joint Propulsion Conference,1989.
[8]H.B.GARRETT.The Charging of Spacecraft Surfaces.Reviews of Geophysics and Space Physics,1981,19(4):577-616.
[9]KATE,M.MANDELL,G.JONGEWARD,et al.The Importance of Accurate Secondary Electron Yields in Modeling Spacecraft Charging.Journal of Geophysical Research.1986,91(12):13739-13744.
[10]S.Brosse,S.Clerc.Modeling of the plasma thruster impact on spacecraft charging[C].The 29th International Electric Propulsion Conference,.2005.10.
[11]Mandell,M.J.,Davis,V.A.,Gardner,B.,Jongeward,G.,Electron collection by international space station solar arrays.8th spacecraft charging technology conference,Huntsville,Alabama,October20-24,2003.
[12]Joel L.Herr,TROPIX Plasma Interactions Group Report,NASA Contractor Report 191149,Sverdrup Technology Inc.,NASA Lewis Research Center Group.