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The magnetoplasmadynamic thruster is a typical representative of the high-power electric propulsion device, and the magnetoplasmadynamics process is its core operating mechanism. In order to understand the influence of applied magnetic field on its operating characteristics, the particle-in-cell particle simulation method combined with the scale model based on the self-similarity criterion is used to simulate the operating process of magnetoplasmadynamic thruster with applied magnetic field. The reliability of the model and method are verified by comparing with the experimental results. The plasma characteristic parameter distribution of the thruster during ignition is analyzed, and the influence of external magnetic field and cathode current on the thruster performance are discussed. The research results show that the construction of the discharge arc between the cathode and anode is a key step for thruster ignition and efficient operation. A low-intensity magnetic field is not conducive to the construction of a stable discharge arc, while the plasma beam is concentrated near the axis and the main thrust generation mechanism is the self-field acceleration. The discharge arc between cathode and anode is stable by applying a high magnetic field, and the main mechanism of thrust generation is vortex acceleration, which causes the thrust and specific impulse to increase linearly with the strength of the external magnetic field. The efficiency of the thruster increases with cathode current and the applied magnetic field intensity increasing. The discharge voltage increases with the augment of cathode current, but first decreases and then increases with applied magnetic field intensity increasing.
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Keywords:
- magnetoplasmadynamic thruster /
- particle-in-cell /
- electric thruster
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Google Scholar
Tang H T, Wang Y B, Wei Y M 2018 J. Propul. Technol. 39 2401
Google Scholar
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Google Scholar
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[9] Rudolph L K 1981 Ph. D. Dissertation (Princeton: Princeton University)
[10] Heiermann J, Auweter-Kurtz M 2005 J. Propuls. Power 21 119
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Zhao B Q, Li Y, Zhou C, Wang G, Wang B J, Cong Y T 2021 J. Solid Rocket Technol. 44 233
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Google Scholar
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Google Scholar
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Google Scholar
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Google Scholar
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Google Scholar
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Google Scholar
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Google Scholar
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[21] 陈茂林, 夏广庆, 毛根旺 2014 物理学报 63 182901
Google Scholar
Chen M L, Xia G Q, Mao G W 2014 Acta Phys. Sin. 63 182901
Google Scholar
[22] Vahedi V, Surendra M 1995 Comput. Phys. Commun. 87 179
Google Scholar
[23] Szabo J J 2001 Ph. D. Dissertation (Cambridge: Massachusetts Institute of Technology)
[24] Khayms V 2000 Ph. D. Dissertation (Cambridge: Massachusetts Institute of Technology)
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Google Scholar
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图 1 AF-MPDT结构和工作原理示意图
Figure 1. Schematic of AF-MPDT structure and operating principle.
图 2 MPDT加速机理 (a)自身场加速; (b)霍尔加速; (c)涡旋加速
Figure 2. MPDT acceleration mechanism: (a) Self-field acceleration; (b) hall acceleration; (c) vortex acceleration.
图 3 MPDT几何结构与计算区域
Figure 3. MPDT geometry and simulation area.
图 4 Ar原子数密度分布和流线
Figure 4. The number density and streamlines of Ar.
图 5 电子数密度分布
Figure 5. Distribution of electron number density.
图 6 离子数密度分布
Figure 6. Distribution of ion number density
图 7 不同磁场强度下的电子数密度分布
Figure 7. Electron number density distribution with different applied magnetic field.
图 8 MPDT性能随外磁场的变化
Figure 8. MPDT performance changes with applied magnetic field.
图 9 仿真与实验结果对比
Figure 9. Comparison of simulation and experimental results.
图 10 不同阴极电流下的电子数密度分布
Figure 10. Distribution of electron number density under different cathode current
图 11 MPDT性能随阴极电流的变化
Figure 11. MPDT performance changes with cathode current.
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[1] Han X, Zhang Z, Chen Z Y, Marano M, Tang H B, Xao J B 2021 J. Phys. D: Appl. Phys. 54 135203
Google Scholar
[2] 汤海滨, 王一白, 魏延民 2018 推进技术 39 2401
Google Scholar
Tang H T, Wang Y B, Wei Y M 2018 J. Propul. Technol. 39 2401
Google Scholar
[3] Brushlinskii K V 1968 USSR Computational Mathematics and Mathematical Physics 8 135
Google Scholar
[4] Brushlinskii K V, Gerlakh N I, Morozov A I 1966 Fluid Dyn. 1 134
[5] Kimura I, Toki K, Tanaka M 1982 AIAA J. 20 889
Google Scholar
[6] Niewood E H 1993 Ph. D. Dissertation (Cambridge: Massachusetts Institute of Technology)
[7] Sheppard E J 1994 Ph. D. Dissertation (Cambridge: Massachusetts Institute of Technology)
[8] Caldo G, Choueiri E Y, Kelly A J, Jahn R G 1992 Proceedings of the 28th Joint Propulsion Conference and Exhibit, Nashville, July 6–8, 1992
[9] Rudolph L K 1981 Ph. D. Dissertation (Princeton: Princeton University)
[10] Heiermann J, Auweter-Kurtz M 2005 J. Propuls. Power 21 119
[11] 赵博强, 李永, 周成, 王戈, 王宝军, 丛云天 2021 固体火箭技术 44 233
Google Scholar
Zhao B Q, Li Y, Zhou C, Wang G, Wang B J, Cong Y T 2021 J. Solid Rocket Technol. 44 233
Google Scholar
[12] Sary G, Garrigues L, Boeuf J 2017 Plasma Sources Sci. Technol. 26 055007
Google Scholar
[13] Tahsini A M 2014 Appl. Mech. Mater. 598 239
Google Scholar
[14] Tskhakaya D, Matyash K, Schneider R, Taccogna F 2007 Contrib. Plasma Phys. 47 563
Google Scholar
[15] Tang H B, Cheng J, Liu C, York T M 2012 Phys. Plasmas 19 073108
Google Scholar
[16] Li M, Tang H B, Ren J X, York T M 2013 Phys. Plasmas 20 103502
Google Scholar
[17] Cheng J, Tang H B, York T M 2014 Phys. Plasmas 21 063501
Google Scholar
[18] Li J, Zhang Y, WU J J, Cheng Y Q, Du X R 2019 Energies 12 1579
Google Scholar
[19] Fradkin D B 1973 Ph. D. Dissertation (Princeton: Princeton University)
[20] Myers R M 1991. Proceedings of the 27th Joint Propulsion Conference, Sacramento, June 24–26, 1991
[21] 陈茂林, 夏广庆, 毛根旺 2014 物理学报 63 182901
Google Scholar
Chen M L, Xia G Q, Mao G W 2014 Acta Phys. Sin. 63 182901
Google Scholar
[22] Vahedi V, Surendra M 1995 Comput. Phys. Commun. 87 179
Google Scholar
[23] Szabo J J 2001 Ph. D. Dissertation (Cambridge: Massachusetts Institute of Technology)
[24] Khayms V 2000 Ph. D. Dissertation (Cambridge: Massachusetts Institute of Technology)
[25] Taccogna F, Longo S, Capiteli M, Schneider R 2005 Phys. Plasmas 12 053502
Google Scholar
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