电推进羽流空间离子能量分布研究
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- 英文论文题名：Researching on Ion Thruster's plume Ion Energy Space Distribution
- 论文作者：颜则东 ; 马亚莉 ; 田恺 ; 庄建宏 ; 姚日剑 ; 孔风连 ; 蒋锴
- 英文论文作者：YAN Ze-dong ; MA Ya-li ; TIAN Kai ; ZHUANG Jian-hong ; YAO Ri-jian ; KONG Fen-lian ; JIANG Kai ; Science and Technology on Vacuum Technology and Phy sics Laboratory Lanzhou Institute of Physics
- 年：2015
- 作者机构：真空技术与物理重点实验室兰州空间技术物理研究所;
- 论文关键词：电推进 ; 阻滞势分析仪 ; 离子能量 ; 离子速度 ; 离子温度 ; 分布
- 英文论文关键词：Electric Prop ulsion ; Retarding Potential Analy zer ; Ion Energy ; Ion Velocity ; Distribution
- 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：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：5
- 文件大小：730k
- 原文格式：D
- 会议级别：全国
摘要
电推进带电离子羽流严重改变航天器周围的等离子体环境,造成诸如卫星表面带电、沉积污染、干扰力矩、电磁干扰等一系列效应。本文针对电推进系统返流区域的离子,开展了离子能量、离子速度和离子温度的分布测试,试验分析电推力器返流区域的离子能量分布及参数状况,为我国电推进卫星平台提供方法与数据支持。电推进系统正常工作时,利用阻滞势分析仪对不同位置的离子参数进行测试,试验获取电推进羽流的离子能量、离子速度和离子温度等参数随空间位置的变化关系。结果表明:阻滞势分析仪测试曲线与理论曲线趋势一致,测试后认为推力器返流区离子主要为电荷交换碰撞产生的低能量离子,离子能量小于10eV。经阻滞势分析仪测试,与束流中心相比推力器返流区离子密度非常低,在10~5个/cm~3量级,离子温度在10~4K量级。在不同位置,对电推进羽流的离子能量、离子速度和离子温度的分布进行测试,得到离子参数的空间分布关系。
Spacecraft plasma environment is charged by particles plume of electric propulsion,such as charging satellite surface,depositing contamination,disturbing moment,interfering electromagnetic.Ion energy,ion velocity and ion temperature of electric propulsion system were measured in this paper.Ion energy distribution and parameter status is by Experimental testing,providing methods and data support for electric propulsion satellite platform.Retarding Potential Analyzer probing is used to measure the ion parameters in different locations during the electric propulsion to work properly.Test to obtain the relationship between the spatial position and ion parameters.Retarding Potential Analyzer test curve is consistent with the theoretical curve.After the test regard that region of the ion thrusters mainly for charge-exchange collisions of low-energy ions,ion energy less than 10 eV.Compared with the central beam ions,thruster ion density in regur gitation is very low,at 10~5/cm~3,ion temperature at 10~4K.In different locations,measured the ion energy,ion velocity and ion temperature at electric propulsion plasma plume.Obtain the spatial distribution of plasma ion parameters relationship.
Spacecraft plasma environment is charged by particles plume of electric propulsion,such as charging satellite surface,depositing contamination,disturbing moment,interfering electromagnetic.Ion energy,ion velocity and ion temperature of electric propulsion system were measured in this paper.Ion energy distribution and parameter status is by Experimental testing,providing methods and data support for electric propulsion satellite platform.Retarding Potential Analyzer probing is used to measure the ion parameters in different locations during the electric propulsion to work properly.Test to obtain the relationship between the spatial position and ion parameters.Retarding Potential Analyzer test curve is consistent with the theoretical curve.After the test regard that region of the ion thrusters mainly for charge-exchange collisions of low-energy ions,ion energy less than 10 eV.Compared with the central beam ions,thruster ion density in regur gitation is very low,at 10~5/cm~3,ion temperature at 10~4K.In different locations,measured the ion energy,ion velocity and ion temperature at electric propulsion plasma plume.Obtain the spatial distribution of plasma ion parameters relationship.
引文
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[5]Rich F J.Users guide for the topside ionosp heric p lasma monitor(SSIES,SSIES-2 and SSIES-3)on sp acecraft of the Defense M eteorological Satellite Program.Air Force Phillip s Laboratory,Hanscom AFB,M A,1994,1125.
[6]Knudsen W C.Evaluation and demonstration of the use of retarding p otential analy zers for measuring several ionosp heric quantities[J].J.Geop hys.Res.,71:4669-4678.
[7]颜则东,杨生胜,孔风连.深空电推进阻滞势分析仪探测方法研究[J].真空与低温,2014,20(1):29-33.
[8]马亚莉,薛玉雄,陈益锋等.电推力器羽流离子能谱测试仪设计及在轨数据分析[J].真空与低温,2014,20(2):90-93.
[9]孙明明,顾佐,郭宁等.电推进系统空心阴极热特性研究进展[J].真空与低温,2010,16(2):113-117.
[10]郭宁,邱家稳,顾佐等.20cm氙离子发动机空心阴极3000h寿命试验[J].真空与低温,2006,12(4):204-207.
[2]Hanson W B,Zuccaro D R,Lip p ineott C R,et a1.The retarding p otential analy zer on Atmosp here Exp lorer-C.Radio Sci,1973,8:333.
[3]Hanson W B,Sanatani S,Zuccaro D R.The M artian ionosp hereas observed by the Vikin g retardin g p otential analy zers.J Geop hy s Res,1977,82(28):4351~4363.
[4]Knudsen W C,Sp enner K,Bakke J,et a1.Pioneer venus orbiter p lanar retarding p otential analy zer p lasma exp eriment.IEEE Transactions On Geoscience and Remote Sensing,1980,GE-18(1):54~59.
[5]Rich F J.Users guide for the topside ionosp heric p lasma monitor(SSIES,SSIES-2 and SSIES-3)on sp acecraft of the Defense M eteorological Satellite Program.Air Force Phillip s Laboratory,Hanscom AFB,M A,1994,1125.
[6]Knudsen W C.Evaluation and demonstration of the use of retarding p otential analy zers for measuring several ionosp heric quantities[J].J.Geop hys.Res.,71:4669-4678.
[7]颜则东,杨生胜,孔风连.深空电推进阻滞势分析仪探测方法研究[J].真空与低温,2014,20(1):29-33.
[8]马亚莉,薛玉雄,陈益锋等.电推力器羽流离子能谱测试仪设计及在轨数据分析[J].真空与低温,2014,20(2):90-93.
[9]孙明明,顾佐,郭宁等.电推进系统空心阴极热特性研究进展[J].真空与低温,2010,16(2):113-117.
[10]郭宁,邱家稳,顾佐等.20cm氙离子发动机空心阴极3000h寿命试验[J].真空与低温,2006,12(4):204-207.