太阳阵暴露高压导体面积对低轨道航天器绝对带电影响研究
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- 英文论文题名：Study of effects of exposed conductor area of high voltage solar array on absolute charging of spacecraft in low earth orbit
- 论文作者：汤道坦 ; 杨生胜 ; 李得天 ; 史亮 ; 秦晓刚 ; 陈益峰 ; 蒋锴
- 英文论文作者：Tang Daotan ; Yang Shengsheng ; Li Detian ; Shi Liang ; Qin Xiaogang ; Chen Yifeng ; Jiang Kai ; Science and Technology on Vacuum & Cryogenics Technology and Physics Laboratory ; Science and Technology on Material Performance Evaluating in Space Environment 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;兰州空间技术物理研究所空间环境材料行为及评价技术重点实验室;
- 论文关键词：电流平衡 ; 电流收集面积 ; 航天器悬浮电位 ; 仿真分析 ; 等离子体空间电势
- 英文论文关键词：Current balance ; Current collection area ; Floating potential ; Numerical simulation ; plasma potential
- 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
- 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：570k
- 原文格式：D
- 会议级别：全国
摘要
绝对带电是低轨道航天器带电效应研究的主要方向之一。本文首先基于电流平衡理论,分析了无限大平板的绝对带电模型。在此基础上,利用SPIS(Spacecraft Plasma Interaction Software)等离子体与航天器相互作用仿真分析软件开展了暴露高压导体面积对电流收集、悬浮电位的影响分析。仿真计算结果表明:当电子电流收集面积足够大时,悬浮电位结果满足无限大平板模型。而当暴露的高压导体尺寸小于等离子体的德拜尺寸时,由于等离子体空间电势的影响,导致航天器的收集电流并不满足无限大平板的收集模型,航天器的悬浮电位仅充至负的数伏左右。
Absolute charging is one of the most important research fields of spacecraft charging in low earth orbit.In this article,the model of absolute charging of infinity plane was analyzed based on the theory of current balance.Then the SPIS have been applied to study the effects of exposed conductor area of high voltage solar array on current collection and floating potential.The simulation results indicate that when the dimensions of an electron collecting conductor is larger than the debye length in plasma,the simulation results are consistent with the in the model of infinity plane.However if the dimensions of an electron collecting conductor is less than the debye length in plasma,the result is different due to the space potential of the plasma environment.
Absolute charging is one of the most important research fields of spacecraft charging in low earth orbit.In this article,the model of absolute charging of infinity plane was analyzed based on the theory of current balance.Then the SPIS have been applied to study the effects of exposed conductor area of high voltage solar array on current collection and floating potential.The simulation results indicate that when the dimensions of an electron collecting conductor is larger than the debye length in plasma,the simulation results are consistent with the in the model of infinity plane.However if the dimensions of an electron collecting conductor is less than the debye length in plasma,the result is different due to the space potential of the plasma environment.
引文
[1]Ferguson D C,Snyder D B,Carruth R.Findings of the joint workshop on evaluation of impacts of space station freedom ground configuration[R].NASA Lewis Research Center.No.NASA TM-103717 689-694
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[4]Ferguson D C,Hillard G B.2003,Low Earth Orbit Spacecraft Charging Design Guidelines(Virginia:The NASA Scientific and Technical Information Program Office,212287)
[5]Ferguson D C.1991,LEO space plasma interactions[C].Proc.10th space photovoltaic research and technology Conf.(Cleveland)
[6]Carruth M R,Vaughn J A,Bechtel R T.Experimental Studies on Spacecraft Arcing[J].JOURNAL OFSPACECRAFT AND ROCKETS,1993,Vol.30,No.3:323~327
[7]Carruth M R,Schneider J T,Mc Collum M,et al.2001,ISS and Space Environment Interactions Without Operating Plasma Contactor[C].Proc.39th Aerospace Sciences Meeting and Exhibit(Nevada)
[8]Ferguson D C,Gardner Barbara.2002,Modeling International Space Station(ISS)Floating Potentials[C].Proc.39th Aerospace Sciences Meeting and Exhibit(Nevada)
[9]Tang D T,Yang S S,Zheng K H,et al.Particle-in-cell simulation study on the floating potential of spacecraft in the low earth orbit[J].Plasma science and technology,2015,Vol.17,No.14:288~293
[10]Dale C.Ferguson.Space solar cell edge,interconnect,and coverglass designs and their effect on spacecraft charging and plasma interactions[C].2010,35th IEEE Photovoltaics Specialists Conference,Honolulu
[11]Dale C.Ferguson.The Role of Electrical Potential Barriers in LEO Spacecraft Charging[C].2012,50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition,Tennessee
[12]冯宇波,王世金,关焱炳.空间等离子体对飞船对接过程的充放电影响[J].上海航天,2013,第30卷:53~58
[13]Forest J,Eliasson L,Hilgers A,et al.A New Spacecraft Plasma Interactions Simulation Software,Pic Up3D/SPIS[C].2001,7th Proc.of the Spacecraft Charging Technology Conf.(The Netherlands)
[14]杨集,陈贤祥,周杰,夏善红.尾迹对卫星周围等离子体扰动特性分析[J].宇航学报,2010,第3l卷第2期:521~535
[15]杨昉,师立勤,刘四清,龚建村.低轨道航天器的表面充电模拟[J].空间科学学报,2011,31(4):509-513
[16]杨集,陈贤祥,周杰,任仁,夏善红.伸杆对星载电场探测仪的影响研究[J].电子与信息学报,2009,第31卷第4期:1010~1012
[17]Birdsall C K,Landon A B.Plasma Physics Via Computer Simulation[M].Bristol:Institute of Physics Publishing,1991
[2]Ferguson D C.1993.Interactions between spacecraft and their environment[C].31st Aerospace sciences meeting and exhibit(Nevada)
[3]Fennell J F,Anderson P C.2008,LEO orbit surface charging and its relationship to environment,Vehicle Geometry,and ionospheric conditions[R].Space and Missile systems center.No.TR-2008(8570)-2
[4]Ferguson D C,Hillard G B.2003,Low Earth Orbit Spacecraft Charging Design Guidelines(Virginia:The NASA Scientific and Technical Information Program Office,212287)
[5]Ferguson D C.1991,LEO space plasma interactions[C].Proc.10th space photovoltaic research and technology Conf.(Cleveland)
[6]Carruth M R,Vaughn J A,Bechtel R T.Experimental Studies on Spacecraft Arcing[J].JOURNAL OFSPACECRAFT AND ROCKETS,1993,Vol.30,No.3:323~327
[7]Carruth M R,Schneider J T,Mc Collum M,et al.2001,ISS and Space Environment Interactions Without Operating Plasma Contactor[C].Proc.39th Aerospace Sciences Meeting and Exhibit(Nevada)
[8]Ferguson D C,Gardner Barbara.2002,Modeling International Space Station(ISS)Floating Potentials[C].Proc.39th Aerospace Sciences Meeting and Exhibit(Nevada)
[9]Tang D T,Yang S S,Zheng K H,et al.Particle-in-cell simulation study on the floating potential of spacecraft in the low earth orbit[J].Plasma science and technology,2015,Vol.17,No.14:288~293
[10]Dale C.Ferguson.Space solar cell edge,interconnect,and coverglass designs and their effect on spacecraft charging and plasma interactions[C].2010,35th IEEE Photovoltaics Specialists Conference,Honolulu
[11]Dale C.Ferguson.The Role of Electrical Potential Barriers in LEO Spacecraft Charging[C].2012,50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition,Tennessee
[12]冯宇波,王世金,关焱炳.空间等离子体对飞船对接过程的充放电影响[J].上海航天,2013,第30卷:53~58
[13]Forest J,Eliasson L,Hilgers A,et al.A New Spacecraft Plasma Interactions Simulation Software,Pic Up3D/SPIS[C].2001,7th Proc.of the Spacecraft Charging Technology Conf.(The Netherlands)
[14]杨集,陈贤祥,周杰,夏善红.尾迹对卫星周围等离子体扰动特性分析[J].宇航学报,2010,第3l卷第2期:521~535
[15]杨昉,师立勤,刘四清,龚建村.低轨道航天器的表面充电模拟[J].空间科学学报,2011,31(4):509-513
[16]杨集,陈贤祥,周杰,任仁,夏善红.伸杆对星载电场探测仪的影响研究[J].电子与信息学报,2009,第31卷第4期:1010~1012
[17]Birdsall C K,Landon A B.Plasma Physics Via Computer Simulation[M].Bristol:Institute of Physics Publishing,1991