LIPS-200离子推力器放电室出口离子密度分布研究

推进技术 ›› 2018, Vol. 39 ›› Issue (5): 1194-1200.

• 电推进和其它推进 • 上一篇

LIPS-200离子推力器放电室出口离子密度分布研究

龙建飞,张天平,吴辰宸,李娟,贾艳辉

兰州空间技术物理研究所真空技术与物理重点实验室，甘肃兰州 730000,兰州空间技术物理研究所真空技术与物理重点实验室，甘肃兰州 730000,兰州空间技术物理研究所真空技术与物理重点实验室，甘肃兰州 730000,兰州空间技术物理研究所真空技术与物理重点实验室，甘肃兰州 730000,兰州空间技术物理研究所真空技术与物理重点实验室，甘肃兰州 730000

发布日期:2021-08-15
作者简介:龙建飞，男，博士，研究领域为空间电推进技术。
基金资助:
真空低温技术与物理重点实验室基金(9140C55026150C55013)。

Study on Ion Density Distribution in Discharge Chamber Exit of LIPS-200 Ion Thruster

Science and Technology on Vacuum Technology and Physics Laboratory，Lanzhou Institute of Physics，Lanzhou 730000，China,Science and Technology on Vacuum Technology and Physics Laboratory，Lanzhou Institute of Physics，Lanzhou 730000，China,Science and Technology on Vacuum Technology and Physics Laboratory，Lanzhou Institute of Physics，Lanzhou 730000，China,Science and Technology on Vacuum Technology and Physics Laboratory，Lanzhou Institute of Physics，Lanzhou 730000，China and Science and Technology on Vacuum Technology and Physics Laboratory，Lanzhou Institute of Physics，Lanzhou 730000，China

Published:2021-08-15

摘要/Abstract

摘要： 为了明确国内200 mm口径离子推力器放电室出口(即栅极上游附近)离子密度径向分布，采用实验与数值仿真相结合的方法对LIPS-200推力器放电室出口离子密度进行研究。应用法拉第筒分别测试推力器栅极下游50mm和100mm位置处束流特性，结合经验模型计算出栅极出口(z=0mm)束流离子径向分布。在此基础上，通过栅极数值模拟仿真，分析出栅极系统透过率随栅孔电流变化关系，进而反推计算出放电室出口离子密度径向分布。结果显示:放电室出口离子密度平均值约为9.0×1017m-3，最大值约为1.54×1018m-3，最小值约为4.6×1017m-3；离子密度径向分布具有较好的中心轴对称性，离子密度从中心处沿着径向先缓慢减小，在径向位置约为50mm时出现快速下降；对比放电室出口与栅极出口离子密度径向分布发现，中心位置两者相差最大，边缘处相差最小。

关键词: LIPS-200推力器；离子密度分布；法拉第探针；数值计算

Abstract: In order to clarify the ion density distribution in discharge chamber exit of a 200mm diameter ion thruster， the ion density distribution in the discharge chamber exit of the LIPS-200 thruster is analyzed and discussed based on the combination of experiment and numerical simulation. The beam characteristics at 50mm and 100mm downstream of the accelerator grid are measured by a Faraday cup， and then the ion current radial distribution in the accelerator grid exit is calculated combined with empirical model. Further， the relationship between grid system transmittance and the grid current is obtained by optics system numerical simulation. At last the ion density radial distribution in the discharge chamber exit is calculated. The results show that the average ion density in discharge chamber exit is 9.0×1017m-3， the maximum is 1.54×1018m-3 and the minimum is 4.6×1017m-3. The ion density radial distribution has a good central axial symmetry， ion density decrease slowly from the center along the radial direction and drop rapidly near the radial position of 50mm. Compared with the ion density in the discharge chamber exit and accelerator grid exit， there are the largest difference at the center but the smallest at the edges.

Key words: LIPS-200 thruster；Ion density distribution；Faraday probe；Numerical simulation

龙建飞,张天平,吴辰宸,李娟,贾艳辉. LIPS-200离子推力器放电室出口离子密度分布研究[J]. 推进技术, 2018, 39(5): 1194-1200.

LONG Jian-fei,ZHANG Tian-ping,WU Chen-chen,LI Juan,JIA Yan-hui. Study on Ion Density Distribution in Discharge Chamber Exit of LIPS-200 Ion Thruster[J]. Journal of Propulsion Technology, 2018, 39(5): 1194-1200.

参考文献

[1] ZHANG Tian-ping, WANG Xiao-yong, JIANG Hao-cheng. Initial Flight Test Results of the LIPS-200 Electric Propulsion System on SJ-9A Satellite[C]. Washington DC: 33th International Electric Propulsion Conference, 2013.
[2] 郑茂繁, 江豪成. 改善离子推力器束流均匀性的方法[J]. 推进技术, 2011, 32(6): 763-769. (ZHENG Mao-fan, JIANG Hao-cheng. Method of Improving Beam Current Profile for Ion Thruster[J]. Journal of Propulsion Technology, 2011, 32(6): 763-769.)
[3] 周志成, 王敏, 仲小清, 等. 口径离子推力器寿命模型及评估[J]. 真空科学与技术学报, 2015, 35(9): 1088-1093.
[4] Noushkam N, Basak D, Glogowski M, et al. Sputtering Effects of Xenon Ion Thruster Plume on Common Spacecraft Materials[R]. AIAA 2015-4642.
[5] Brophy J, Wilbur P. Simple Performance Model for Ring and Line Cusp Ion Thrusters[R]. AIAA 85-1736.
[6] Wirz R, Goebel D. Effects of Magnetic Field Topography on Ion Thruster Discharge Performance [J]. Plasma Sources Science and Technology, 2008, 17(3).
[7] Othmer C, Glassmeier K H, Motschmann U, et al. Numerical Simulation of Ion Thruster-Induced Plasma Dynamics—the Model and Initial Results[J]. Advances in Space Research, 2002, 29(9): 1357-1362.
[8] 陈娟娟, 张天平, 刘明正, 等. LIPS-200 离子推力器放电室原初电子动力学行为的数值模拟研究[J]. 推进技术, 2015, 36(1): 155-161. (CHEN Juan-juan, ZHANG Tian-ping, LIU Ming-zheng, et al. Investigation on Dynamical Behavior of Primary Electrons in LIPS-200 Ion Thruster Discharge Chamber[J]. Journal of Propulsion Technology, 2015, 36(1): 155-161.)
[9] 孙安邦, 毛根旺, 夏广庆, 等. 离子推力器放电腔内等离子体流动规律的全离子模型[J]. 推进技术, 2012, 24(10): 2469-2473. (SUN An-bang, MAO Gen-wang, XIA Guang-qing, et al. Full Particles Model of Plasma Flow for Ion Thruster Discharge Chamber[J]. Journal of Propulsion Technology, 2012, 24(10): 2469-2473.)
[10] Herman D A, Gallimore A D. Discharge Chamber Plasma Structure of a 30cm NSTAR-Type Ion Engine[R]. AIAA 2004-3794.
[11] Carruth M R. A Review of Studies on Ion Thruster Beam and Charge-Exchange Plasmas[R]. AIAA 82-1944.
[12] 李娟, 楚豫川, 曹勇. 离子推力器羽流场模拟以及Mo+CEX沉积分析[J]. 推进技术, 2012, 33(1): 131-138. (LI Juan , CHU Yu-chuan , CAO Yong. Numerical Simulations of Ion Thruster Plume Contamination Interactions on Spacecraft[J]. Journal of Propulsion Technology, 2012, 33(1): 131-138.)
[13] Roy R S, Hastings D, Gastonis N. Ion-Thruster Plume Modeling for Backflow Contamination[J]. Journal of Spacecraft and Rockets, 1996, 33(33): 525-534.
[14] Reynolds T W. Mathematical Representation of Current Density Profiles from Ion Thruster[R]. AIAA 71-693.
[15] 商圣飞, 顾左, 贺碧蛟, 等. 离子推力器束流密度分布模型[J]. 真空科学与技术学报, 2015, 35(12): 1414-1419.
[16] Zhang Z, Tang H B, Ren J X, et al. Calibrating Ion Density Profile Measurements in Ion Thruster Beam Plasma[J]. American Institute of Physics, 2016, 87(11).
[17] 贾艳辉, 张天平, 郑茂繁, 等. 离子推力器栅极系统电子反流阈值的数值分析[J]. 推进技术, 2012, 33(6): 991-998. (JIA Yan-hui, ZHANG Tian-ping, ZHENG Mao-fan, et al. Numerical Analysis for Electron Backstreaming Accelerator Grid Limited Voltage for 20 cm Xe Ion Thruster Grid System[J]. Journal of Propulsion Technology, 2012, 33(6): 991-998.)
[18] 陈琳英, 江豪成, 郑茂繁. 离子推力器束流密度分布测量[J]. 真空与低温, 2007, 13(3): 155-160.
[19] Hofer R R, Walker M, Gallimore A D. A Comparison of Nude and Collimated Faraday Probes for Use with Hall Thrusters[R]. IEPC-2001-020.
[20] Okawa Y, Takegahara H, Tachinabana T. Numerical Analysis of Ion Beam Extraction Phenomena in an Ion Thruster[R]. IEPC-2001-097.　　　　　　　　　　　　　*　收稿日期:2017-04-16；修订日期:2017-06-06。基金项目:真空低温技术与物理重点实验室基金(9140C55026150C55013)。作者简介:龙建飞,男,博士,研究领域为空间电推进技术。E-mail: ljf510@163.com(编辑:梅瑛)

LIPS-200离子推力器放电室出口离子密度分布研究

Study on Ion Density Distribution in Discharge Chamber Exit of LIPS-200 Ion Thruster

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