羽流区磁场对霍尔推力器性能影响的二维模拟研究

杨三祥; 赵以德; 代鹏; 李建鹏; 耿海; 杨俊泰; 贾艳辉; 郭宁

doi:10.7498/aps.73.20241331

摘要

磁场作为霍尔推力器的关键设计参数之一, 其通过直接影响电子输运、中性原子电离、等离子体分布等微观行为, 间接影响推力器的宏观性能. 目前, 针对霍尔推力器磁场影响的研究更多的是关注放电通道内磁场大小以及分布的影响, 而对羽流区磁场的影响研究相对较少. 基于此, 本文利用二维粒子-流体混合模型研究了霍尔推力器羽流区的轴向磁场分布对推力器性能的影响. 结果表明, 在放电通道内轴向磁场分布不变的情况下, 改变羽流区的轴向磁场梯度对推力具有显著的影响. 放电通道中的电势降随着羽流区轴向磁场梯度的减小而减小, 羽流区电场以及放电通道中的离子数密度峰值则随着羽流区轴向磁场梯度的减小而增加. 增加羽流区的磁感应强度, 有助于推力器性能的提升. 更明确地说, 羽流区的磁场梯度存在一个临界值, 当羽流区轴向磁场梯度大于临界值时, 推力随羽流区轴向磁场梯度的减小而增加. 当羽流区轴向磁场梯度小于临界值时, 推力随羽流区轴向磁场梯度的减小而轻微的减小. 通过对不同羽流区磁场分布下的等离子体电势、电场、离子数密度, 以及电离率分布的比较表明, 羽流区磁场通过影响电子迁移率改变电场的分布, 而电场分布的改变则会对推力产生影响. 本文的研究结果将对霍尔推力器性能优化, 以及磁场设计提供理论支撑.

关键词:

Abstract

As one of the key design parameters of Hall thruster, magnetic field indirectly influences the macroscopic performance of the thruster by directly affecting electron transport, neutral atom ionization, plasma distribution and other microscopic behaviors. At present, the research on the influence of Hall thruster’s magnetic field focuses mostly on the size and distribution of the magnetic field in the discharge channel, but less on the influence of the plume magnetic field on the thruster. Based on this, the effect of plume region axial magnetic field profile on the performance of Hall thruster is studied by using two-dimensional hybrid simulation. The research results show that the axial magnetic field gradient in the plume region has a significant influence on the thruster performance, when the magnetic field characteristics (magnetic field topology and magnetic field intensity) in the discharge channel remain unchanged. The potential drop in the discharge channel decreases with the axial magnetic field gradient in the plume region decreasing. However, the electric field in the plume region and the peak ion number density in the discharge channel increase with the axial magnetic field gradient in the plume region decreasing. Overall, the performance of the thruster is improved by increasing the magnetic field strength in the plume region. More specifically, there is a critical value of axial magnetic field gradient in the plume region. When the axial magnetic field gradient in the plume region is greater than the critical value, the thrust increases with the axial magnetic field gradient decreasing. When the axial magnetic field gradient of the plume region is less than the critical value, the thrust decreases slightly with the axial magnetic field gradient decreasing. The comparison of plasma potential, electric field, ion number density, and ionization rate distribution under different magnetic field distributions in the plume region shows that the effect of plume magnetic field on thrust is to affect the spatial electric field distribution by affecting the mobility of electrons, thus causing the thrust to change due to electric field. The research results of this paper will provide theoretical support for improving the performance of hall thrusters and designing magnetic fields.

Keywords:

作者及机构信息

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　730000

通信作者: 耿海, marineen115@163.com

基金项目: 国家重点研发计划(批准号: 2021YFC2202704)、国家自然科学基金(批准号: 62201238)、甘肃省杰出青年基金(批准号: 21JR7RA744)和甘肃省自然科学基金(批准号: 22JR5RA789, 22JR5RA787)资助的课题.

Authors and contacts

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

Corresponding author: Geng Hai, marineen115@163.com

Funds: Project supported by the National Key R&D Program of China (Grant No. 2021YFC2202704), the National Natural Science Foundation of China (Grant No. 62201238), the Outstanding Youth Fund of Gansu Province, China (Grant No. 21JR7RA744), and the Natural Science Foundation of Gansu Province, China (Grant Nos. 22JR5RA789, 22JR5RA787).

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参考文献

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施引文献

图 1 粒子-流体混合模型计算流程图

Fig. 1. Calculation flowchart of the particle-fluid hybrid model.

下载: 全尺寸图片幻灯片

图 2 计算域及边界条件

Fig. 2. Calculation domain and boundary conditions.

下载: 全尺寸图片幻灯片

图 3 (a) ${\alpha _1}$和(b) ${\alpha _2}$对轴向磁场分布的影响.

Fig. 3. Influences of (a) ${\alpha _1}$ and (b) ${\alpha _2}$ on the magnetic field distribution.

下载: 全尺寸图片幻灯片

图 4 ${\alpha _1} = 0.35$时${\alpha _2}$对推力的影响

Fig. 4. Influence of ${\alpha _2}$ on the thrust at ${\alpha _1} = 0.35$.

下载: 全尺寸图片幻灯片

图 5 ${\alpha _1} = 0.35$时${\alpha _2}$对电势(a)和电场(b)分布的影响

Fig. 5. Influence of ${\alpha _2}$ on potential (a) and electric field (b) at ${\alpha _1} = 0.35$.

下载: 全尺寸图片幻灯片

图 6 ${\alpha _1} = 0.35$时${\alpha _2}$对离子产生速率(a)和离子密度的影响(b)

Fig. 6. Influence of ${\alpha _2}$ on ion production rate (a) and ion number density (b) at ${\alpha _1} = 0.35$.

下载: 全尺寸图片幻灯片

图 7 不同${\alpha _2}$时电势的分布

Fig. 7. Potential distribution for different ${\alpha _2}$.

下载: 全尺寸图片幻灯片

图 8 不同${\alpha _2}$时轴向电场的分布

Fig. 8. Axial electric field distribution for different ${\alpha _2}$.

下载: 全尺寸图片幻灯片

图 9 不同${\alpha _2}$时离子数密度的分布

Fig. 9. Ion number density distribution for different ${\alpha _2}$.

下载: 全尺寸图片幻灯片

[1]	Mazouffre S 2016 Plasma Sources Sci. Technol. 25 033002 Google Scholar
[2]	Li W B, Ding Y J, Wei L Q, Han L, Yu D R 2017 Vacuum 136 77 Google Scholar
[3]	Taccogna F, Minelli P, Capitelli M, Longo S 2012 Am. Instit. Phys. 1501 1390 Google Scholar
[4]	Raitses Y, Fisch N J 2001 Phys. Plasmas 8 2579 Google Scholar
[5]	Shitrit S, Ashkenazy J, Appelbaum G, Warshavsky A 2008 IEEE Trans. Plasma Sci. 36 2025 Google Scholar
[6]	Gawron D, Mazouffre S, Sadeghi N, Héron A 2008 Plasma Sources Sci. Technol. 17 025001 Google Scholar
[7]	Shmelev A V, Lovtsov A S 2012 Tech. Phys. Lett. 38 544 Google Scholar
[8]	Hofer R R, Geoibel D M, Mikellides I G, Katz I, 2014 J. Appl. Phys. 115 043304 Google Scholar
[9]	Li H, Fan H T, Liu X Y, Ding M H, Ding Y J, Wei L Q, Yu D R, Wang X G 2019 Vacuum 162 78 Google Scholar
[10]	Garrigues L, Hagelarr G J M, Bareilles J, Boniface C, Boeuf J P 2003 Phys. Plasmas 10 4886 Google Scholar
[11]	Sommier E, Allis M K, Cappelli M A 2005 The 29^th International Electric Propulsion Conference Princeton NJ, USA, October 31–November 4, 2005 IEPC-2005-189
[12]	Ahedo E, Antón A, Garmendia I, Caro I 2007 The 30^th International Electric Propulsion Conference Florence, Italy, September 17–20, 2007 IEPC-2007-067
[13]	Boniface C, Garrigues L, Hagelaar G J M, Boefu J P 2006 Appl. Phys. Lett. 89 161503 Google Scholar
[14]	Hara K, Sekerak M J, Boyd I D, Gallimore A D 2014 J. Appl. Phys. 115 203304 Google Scholar
[15]	Perales-Dĺaz J, Domĺnguez-Vázquez Fajardo P, Ahedo E, Faraji F, Reza M, Andreussi T 2022 J. Appl. Phys. 131 103302 Google Scholar
[16]	Jiang Y W, Tang H B, Ren J X, Li M, Cao J B 2018 J. Phys. D: Appl. Phys. 51 1627 Google Scholar
[17]	Liu J W, Li H, Hu Y L, Liu X Y, Ding Y J, Wei L Q, Yu D R, Wang X G 2019 Contrib. Plasma Phys. 59 e201800001 Google Scholar
[18]	杨三祥, 王倩楠, 高俊, 贾艳辉, 耿海, 郭宁, 陈新伟, 袁兴龙, 张鹏 2022 物理学报 71 105201 Google Scholar Yang S X, Wang Q N, Gao J, Jia Y H, Geng H, Guo N, Chen X W, Yuan X L, Zhang P 2022 Acta Phys. Sin. 71 105201 Google Scholar
[19]	Keidar M, Boyd I D 1999 J. Appl. Phys. 86 4786 Google Scholar
[20]	Mikellides I G, Katz I, Mandell M J, Snyder J S 2001 37^th AIAA/ASME/SAE/AHS/ASEE Joint Propulsion Conference & Exhibit Salt Lake City, Utah, July 8–11, 2001 AIAA-2001-3505
[21]	Boyd I D, Yim J M 2004 J. Appl. Phys. 95 4575 Google Scholar
[22]	Raitses Y, Gaysoso J C, Merino E, Fisch N J 2010 46^th AIAA/ASME/SAE/AHS/ASEE Joint Propulsion Conference & Exhibit Nashville, TN, July 25–28, 2010 AIAA-2010-6621
[23]	Hu P, Liu H, Mao W, Yu D R, Gao Y Y 2015 Phys. Plasmas 22 103502 Google Scholar
[24]	Kim H, Lim Y, Choe W, Park S, Seon J 2015 Appl. Phys. Lett. 106 154103 Google Scholar
[25]	Singh S, Malik H K 2023 J. Astrophys. Astr. 44 3 Google Scholar
[26]	Hofer R R, Gallimore A D 2006 J. Propul. Power 22 721 Google Scholar
[27]	Hofer R R, Gallimore A D 2006 J. Propul. Power 22 732 Google Scholar
[28]	Henaux C, Vilamot R, Garrigues L, Harribey D 2012 20^th International Conferences on Electrical Machines Marseille, France, September 2–5, 2012 p2533
[29]	Domonkos M T, Gallimore A D, Marrese C M, Haas J M 2000 J. Propul. Power 16 91 Google Scholar
[30]	Liang R, Gallimore A D 2011 49^th AIAA Aerospace Sciences Meeting Kissimmee, Florida, January 4–7, 2011 AIAA-2011-1016
[31]	Adam J C, Héron A, Laval G 2004 Phys. Plasma 11 295 Google Scholar
[32]	Lafleur T, Martorelli R, Chabert P, Bourdon A 2018 Phys. Plasma 25 061202 Google Scholar
[33]	Coche P, Garrigues L 2014 Phys. Plasmas 21 023503 Google Scholar
[34]	Chen L, Kan Z C, Gao W F, Duan P, Chen J Y, Tan C Q, Cui Z J 2024 Chin. Phys. B 33 015203 Google Scholar
[35]	Yu D R, Qing S W, Liu H, Li H 2011 Contrib. Plasma Phys. 51 955 Google Scholar
[36]	Yu D R, Song M, Liu H, Ding Y J, Li H 2012 Phys. Plasmas 19 033503 Google Scholar
[37]	Szabo J, Warner N, Martinez-Sanchez M, Batishchev O 2014 J. Propuls. Power 30 197 Google Scholar
[38]	Taccogna F, Minelli P 2018 Phys. Plasmas 25 061208 Google Scholar
[39]	Garrigues L, Hagelarr G J M, Boniface C, Boeuf J P 2004 Appl. Phys. Lett. 85 5460 Google Scholar
[40]	Kawashima R, Hara K, Komurasaki K 2018 Plasma Sources Sci. Technol. 27 035010 Google Scholar
[41]	Katz I, Jongeward G, Davis V, et al. 2001 37th AIAA/ASME/SAE/AHS/ASEE Joint Propulsion Conference & Exhibit Salt Lake City, Utah, July 8–11, 2001 AIAA-2001-3355
[42]	Kawashima R, Komurasaki K, Schönherr T Koizumi H 2016 54^th AIAA Aerospace Sciences Meeting San Diego, California, USA, January 4–8, 2016 AIAA-2016-2159
[43]	Kawashima R, Wang Z X, Chamarthi A S 2018 55^th AIAA Aerospace Sciences Meeting Kissimmee, Florida, January 8–12, 2018 AIAA-2018-0175
[44]	Hofer R R, Mikellides I G, Katz I, Goebel D M 2007 43^rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference Honolulu, Hawaii, April 23–26, 2007 AIAA-2007-5267
[45]	Manzella D, Jankovsky R, Elliott F, Mikellides I, Jongeward G, Allen D 2001 27^th International Electric Propulsion Conference Pasadena, CA, October 15–19, 2001 IEPC-2001-044
[46]	Andreussi T, Giannetti V, Leporini A, Saravia M M, Andrenucci M 2017 Plasma Phys. Control. Fusion. 60 014015 Google Scholar
[47]	Fujita D, Kawashima R, Ito Y, Akagi S, Suzuki J, Schonherr T, Koizumi H, Komurasaki K 2014 Vacuum 10 159 Google Scholar

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羽流区磁场对霍尔推力器性能影响的二维模拟研究