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The Hall-effect thruster has wide applications for commercial aerospace because of the high thrust density and simple structure. In order to further improve the performance of low-power Hall thruster and to solve the problem that the performance of low-power Hall thruster for low-orbit satellites is limited by the input power and maximum magnetic field intensity, the influence of radial magnetic field distribution in the discharge channel on the performance of the thruster is studied by numerical simulation and theoretical analysis in this work through changing the radial magnetic gradient on condition that the axial magnetic profile and the magnetic strength remain unchanged. The results show that the potential of the acceleration zone decreases with the increase of radial distance when the discharge parameters, propellant flow rate and axial magnetic field are unchanged. Therefore, the greater the radial magnetic field gradient near the inner wall of the thruster discharge channel, the greater the kinetic energy of the ions drifting along the axial direction to the thruster outlet, , and the greater the thrust of thruster. The research results of this work provide theoretical support for the magnetic field design and performance optimization of hall thrusters.
[1] 赵以德, 李娟, 吴宗海, 黄永杰, 李建鹏, 张天平 2020 物理学报 69 115203
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Zhao Y D, Li J, Wu Z H, Huang Y J, Li J P, Zhang T P 2020 Acta Phys. Sin. 69 115203
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Google Scholar
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Google Scholar
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Google Scholar
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Google Scholar
[20] Ellison C L, Raitses Y Fisch N J 2012 Phys. Plasmas 19 013503
Google Scholar
[21] Boeuf J P, Garrigues L 2018 Phys. Plasmas 25 061204
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Google Scholar
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Chen J B, Kang X L, Hang G R, Wang X 2019 J. Propul. Technol. 40 714
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图 1 计算区域和边界条件.
Figure 1. Simulation region and boundary conditions.
图 2 放电通道内磁场分布
Figure 2. Magnetic field distribution in discharge channel.
图 3 (a)推力和(b)比冲
Figure 3. The (a) thrust and (b) specific impulse.
图 4 (a)放电通道内磁场分布; (b)推力器出口处的径向磁场分布
Figure 4. (a) The magnetic field distribution in discharge channel; (b) radial distribution of magnetic field at thruster exit.
图 5 (a)推力和(b)比冲
Figure 5. The (a) thrust and (b) specific impulse.
图 6 (a)离子密度和(b)电子温度
Figure 6. The (a) ion density and (b) electron temperature.
图 7 (a)中性原子密度和(b)离子密度
Figure 7. The (a) neutral atom density and (b) ion density.
图 8 不同磁场强度下的电势沿着轴向的变化
Figure 8. Electric potential along the axial direction plotted for different magnetic strength.
图 9 不同径向位置处电势沿着轴向的变化
Figure 9. Electric potential along the axial direction plotted at various radii.
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[1] 赵以德, 李娟, 吴宗海, 黄永杰, 李建鹏, 张天平 2020 物理学报 69 115203
Google Scholar
Zhao Y D, Li J, Wu Z H, Huang Y J, Li J P, Zhang T P 2020 Acta Phys. Sin. 69 115203
Google Scholar
[2] 李建鹏, 荆伍银, 赵以德 2022 物理学报 71 015202
Google Scholar
Li J P, Jing W Y, Zhao Y D 2022 Acta Phys. Sin. 71 015202
Google Scholar
[3] Cusson S E, Dale E T, Jorns B A, Gallimore A D 2019 Phys. Plasmas 26 023506
Google Scholar
[4] Lubos B, Micheal K 2012 Phys. Plasmas 111 123302
Google Scholar
[5] Mikellides I G, Katz I, Hofer R R, Geobel D M 2013 Phys. Plasmas 102 023509
[6] Mikellides I G, Katz I, Hofer R R 2011 47th AIAA /ASME/SAE/ASEE Joint Propulsion Conference & Exhibit San Diego California, USA, July 31–August 03, 2011 p2011-5809-1
[7] Fruchtamn A, Fisch N J, Raitses Y 2001 Phys. Plasmas 8 1048
Google Scholar
[8] Karadag B, Cho S, Funaki I 2018 J. Appl. Phys. 123 153302
Google Scholar
[9] Hofer R R, Gallimore 2006 J. Propul. Power 22 732
Google Scholar
[10] Garrigues L, Hagelaar G J M, Bareilles J, Boniface C, Boeuf 2003 Phys. Plasmas 10 4886
Google Scholar
[11] Gawron D, Mazouffre S Sadeghi N Heron A 2008 Plasma Sources Sci. Technol. 17 025001
Google Scholar
[12] Andreussi T, Giannetti V, Leporini A. Saravia M M, Andrenucci M 2018 Plasma Phys. Control. Fusion 60 014015
Google Scholar
[13] Garrigues L, Boniface C, Hagelaar G J M, Boeuf J P 2008 Phys. Plasmas 15 114502
Google Scholar
[14] Perez-Luna J, Hagelaar G J M, Garrigues L, Boeuf J P 2007 Phys. Plasmas 14 113502
Google Scholar
[15] Kim V 1998 J. Propul. Power 5 736
[16] Ducrocq A, Adam J C, Heron A, Laval G 2006 Phys. Plasmas 13 102111
Google Scholar
[17] Choueiri E Y 2001 Phys. Plasmas 8 1411
Google Scholar
[18] Romadanov I, Raitses Y, Smolyakov A 2018 Plasma Sources Sci. Technol. 27 094006
Google Scholar
[19] Wei L Q, Li W B, Ding Y J, Yu D R 2018 Plasma Sci. Technol. 20 075502
Google Scholar
[20] Ellison C L, Raitses Y Fisch N J 2012 Phys. Plasmas 19 013503
Google Scholar
[21] Boeuf J P, Garrigues L 2018 Phys. Plasmas 25 061204
Google Scholar
[22] Hara K, Sekerak M J, Boyd I D 2014 J. Appl. Phys. 115 203304
Google Scholar
[23] Hara K, Sekerak M J, Boyd I D 2014 J. Appl. Phys. 21 122103
[24] Brown N P, Walker M L R 2020 Appl. Sci. 10 3775
Google Scholar
[25] 程佳兵, 康小录, 杭光荣, 王宣 2019 推进技术 40 714
Google Scholar
Chen J B, Kang X L, Hang G R, Wang X 2019 J. Propul. Technol. 40 714
Google Scholar
[26] 丁永杰, 扈延林, 颜世林, 李鸿, 李玉全, 蔡宁泊 2015 推进技术 36 795
Google Scholar
Ding Y J, Hu Y L, Yan S L, Li H, Li Y Q, Cai N B 2015 J. Propul. Technol. 36 795
Google Scholar
[27] 张旭, 于达仁 2013 高电压技术 39 1628
Google Scholar
Zhang X, Yu D R 2013 High Volt. Eng. 39 1628
Google Scholar
[28] 段萍, 宋继磊, 姜博瑞, 陈龙, 理文庆, 胡翔, 刘广睿 2020 推进技术 41 194
Google Scholar
Duan P, Song J L, Jiang B R, Chen L, Li W Q, Hu X, Liu G R 2020 J. Propul. Technol. 41 194
Google Scholar
[29] Harvey M L 2014 M. S. Dissertation (Florida: Embry-Riddle Aeronautical University)
[30] Choueiri E Y 2001 Phys. Plasmas 8 5025
Google Scholar
[31] Kornberg O 2007 M. S. Dissertation (Florida: Embry-Riddle Aeronautical University)
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