磁路对30cm离子推力器性能影响研究

推进技术 ›› 2016, Vol. 37 ›› Issue (1): 193-200.

• 电推进和其它推进 • 上一篇

磁路对30cm离子推力器性能影响研究

吴先明,张天平,陈娟娟,龙建飞,孙明明

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:吴先明，男，博士生，工程师，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(9140c550206130c5503)。

Study on Effects of Magnetic Circuit on Performance of 30cm Diameter Ion Thruster

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

Published:2021-08-15

摘要/Abstract

摘要： 为了研究磁路结构对与新型GEO平台配套的30cm离子推力器(LIPS-300)性能的影响，采用PIC-MCC数值模拟方法对LIPS-300在其典型工作点下的放电损耗和束流平直度进行了研究，其中输入磁场采用有限元软件Maxwell计算得到，另外还利用Maxwell研究了磁体尺寸对侧壁磁环对产生的磁场等值线的影响。结果表明在LIPS-300的典型工作点下，4极场推力器比3极场推力器放电损耗高3%，分别是164W/A和160W/A，束流平直度高30%，分别为0.65和0.50。利用较厚较窄的磁环能够获得更大的无场区体积。因此，采用4极场将获得更好的推力器性能，采用较大厚度/宽度比的磁体有利于推力器束流平直度的改进。

关键词: 离子推力器；磁路；PIC-MCC；放电损耗；束流平直度

Abstract: In order to study the effects of magnetic circuit on the performance of 30cm diameter ion thruster(LIPS-300)which matches the new type of GEO satellite platform，PIC-MCC numerical simulation method was used to study LIPS-300’s discharge loss and beam flatness under its typical operating point. The magnetic field input of PIC-MCC simulation was calculated using infinite element software Maxwell. It was also used to study the effects of different magnet sizes on the magnetic contour produced by side-wall magnet pair. The obtained results indicate that under LIPS-300’s typical operating point，4 pole field thruster’s discharge loss is higher than that of 3 pole field by 3%. They are 164W/A and 160W/A，respectively. The 4 pole field thruster’s beam flatness is larger than that of 3 pole field thruster by 30%. They are 0.65 and 0.50，respectively. More field free volume can be obtained by utilization of thicker and narrower magnet. So，the thruster can achieve better performance by applying 4 pole magnetic field and moderately large thickness/width ratio of the magnet is beneficial to the improvement of the beam flatness.

Key words: Ion thruster；Magnetic circuit；PIC-MCC；Discharge loss；Beam flatness

吴先明,张天平,陈娟娟,龙建飞,孙明明. 磁路对30cm离子推力器性能影响研究[J]. 推进技术, 2016, 37(1): 193-200.

WU Xian-ming,ZHANG Tian-ping,CHEN Juan-juan,LONG Jian-fei,SUN Ming-ming. Study on Effects of Magnetic Circuit on Performance of 30cm Diameter Ion Thruster[J]. Journal of Propulsion Technology, 2016, 37(1): 193-200.

参考文献

[1] Wirz R,Goebel D. Ion Thruster Discharge Performance per Magnetic Field Topography[R]. AIAA 2006-4487.
[2] Sengupta A. Experimental Investigation of Discharge Plasma Magnetic Confinement in a NSTAR Ion Thruster[C]. Arizona: 41st Joint Propulsion Conference, 2005.
[3] Sengupta A. Experimental and Analytical Investigation of a Modified Ring Cusp NSTAR Engine[C]. Princeton: 29th International Electric Propulsion Conference, 2005.
[4] Sanghera1 A S, De Turris D J. Performance Characterization of a 15-cm Ion Thruster with Simulated Beam Extraction[R]. AIAA 2007-5219.
[5] Ogunjobi T A, Menart J A. Computational Study of Ring-Cusp Magnet Configurations that Provide Maximum Electron Confinement[R]. AIAA 2006-4489.
[6] Deshpande S S, Ogunjobi T A, Menart J A. Computational Study of Magnet Placement on the Discharge Chamber of an Ion Engine[R]. AIAA 2005-4254.
[7] Ogunjobi T A. Computational Study of Ring-Cusp Magnet Configurations that Provide Maximum Electron Confinement[D]. Ohio: Wright State University, 2004.
[8] 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): 991-996. (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): 991-996.)
[9] 贾艳辉, 张天平, 李小平. 离子推力器加速栅寿命概率性分析[J]. 推进技术2011, 32(6): 766-769. (JIA Yan-hui, ZHANG Tian-ping, LI Xiao-ping, et al. Probabilistic Evaluation of Ion Thruster Accelerator Grid Life[J]. Journal of Propulsion Technology, 2011, 32(6):766-769.)
[10] Mahalingam S. Particle Based Plasma Simulation for an Ion Engine Discharge Chamber[D]. Ohio: Wright State University, 2007.
[11] Mahalingam S, Yongjun Choi, John Loverich, et al. Fully Coupled Electric Field/PIC-MCC Simulation Results of the Plasma in the Discharge Chamber of an Ion Engine[R]. AIAA 2011-6071.
[12] 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粒子模拟[J]. 推进技术, 2012, 33(1): 143-149. (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, 33(1): 143-149.)
[13] 陈娟娟. 离子推力器放电室工作性能的理论模型分析与数值计算模拟研究[D]. 兰州:兰州空间技术物理研究所, 2013.
[14] Leung K, Hershkowitz N, MacKenzie K. Plasma Confinement By Localized Cusps[J]. Physics of Fluids, 1976(7): 1045–1053.
[15] Goebel D M, Wirz R E, Katz I. Analytical Ion Thruster Discharge Performance Model[J]. Journal of Propulsion and Power, 2007, 23(5): 1055-1067.
[16] Beattie J R, Matossian J N. Inert-Gas Ion Thruster Technology[R]. NASA 3-23860.　(编辑:朱立影)　　　　　*　收稿日期:2014-09-17；修订日期:2014-11-03。基金项目:真空低温技术与物理重点实验室基金(9140c550206130c5503)。作者简介:吴先明,男,博士生,工程师,研究领域为空间电推进技术。E-mail: wxm0511@163.com

磁路对30cm离子推力器性能影响研究

Study on Effects of Magnetic Circuit on Performance of 30cm Diameter Ion Thruster

PDF

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 0

编辑推荐

Metrics

本文评价