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霍尔推力器磁场位形及其优化的数值研究 被引量:2

Numerical study on Hall thruster magnetic configuration and its optimization
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摘要 基于麦克斯韦方程,在轴对称假设下建立了霍尔推力器磁场的数学模型.用有限差分方法对模型进行了离散.给出了数值求解模型的迭代法.通过对模型的数值求解,得到了相应的数值结果.通过对所得数值结果的分析,研究了磁场线圈电流变化对霍尔推力器磁场位形的影响.通过调整磁场线圈电流的大小找到了理想磁场位形.研究表明,对于理想磁场位形,内通道的磁镜比在3—3.5之间,外通道的磁镜比在0.4—0.9之间;增加磁场线圈的电流,出口的磁场强度随着增加,但不能增加磁镜比.通道内部的磁场强度几乎不随着磁场线圈电流的变化而变化. Based on Maxwell's equations,under axis-symmetric assumption,a mathematical model of the magnetic field of a Hall thruster is established. A finite difference method is used for discretizing the model. An iterative method for numerically solving the model is given. The numerical results are obtained. From analysis of the results,the effect of the current in the magnetic field coils on the magnetic configuration of a Hall thruster is investigated. Through adjusting the current,the ideal magnetic configurations are found. It was shown that,for ideal magnetic configuration,the magnetic mirror ratio in the inner channel is between 3 and 3. 5,and the magnetic mirror ratio in the outer channel is between 0. 4 and 0. 9. With the increasing of the current in the magnetic field coils,the magnetic field at the exit of the channel increases,but the magnetic mirror ratio cannot be increased. The magnetic field in the inner channel hardly changes with change of the currents in the magnetic field coils.
出处 《物理学报》 SCIE EI CAS CSCD 北大核心 2011年第2期496-501,共6页 Acta Physica Sinica
关键词 霍尔推力器 磁场位形 磁场线圈电流 磁镜比 Hall thruster magnetic configuration current in magnetic field coil magnetic mirror ratio
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  • 1魏合林,刘祖黎.磁场对直流辉光放电阴极鞘层中电子输运过程的影响[J].物理学报,1995,44(2):225-232. 被引量:8
  • 2Barral S, Makowski K, Peradzynski Z, Gascon N, Dudeck M 2003 Phys. Plasmas 10 4137
  • 3Taccogna F, Longo S, Capitelli M 2004 Phys. Plasmas, 11 1220
  • 4Taccogna F, Longo S, Capitelli International Electric Propulsion M 2005 Proceedings of the 29th Conference, Princeton (Electric Rocket Propulsion Society, Fairview Park, OH, 2005 ), Paper No IEPC-2005-012
  • 5Taccogna F, Longo S, Capitelli M 2005 Phys. Plasmas 12 093506
  • 6Morozov, Savel'ev V V 2002 Plasma Physics Reports 28 1017
  • 7Morozov, Savel' ev V V 2004 Plasma Physics Reports 30 299
  • 8Raitses Y et al 2005 Physics of Plasma 12 057104
  • 9Keidar M, Boyd I D, Beilis I I 2001 Physics of Plasmas 8 5315
  • 10Hobbs G D, Wesson J A 1967 Plasma of Physics 9 85

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  • 1丁永杰,于达仁,武志文.Parameters Distribution Along the Channel Axis in the Scaling Designed Stationary Plasma Thruster[J].Plasma Science and Technology,2006,8(6):716-719. 被引量:1
  • 2Joyner C R, Levack D, Borowski S K. Development of asmall nuclear thermal propulsion flight demonstrator conceptthat is scalable to human missions[C] / /48th AIAA/ ASME/SAE/ ASEE Joint Propulsion Conference & Exhibit. 2012:4207.
  • 3Meyer M, Johnson L, Palaszewski B, et al. In-space propul-sion systems roadmap, technology area 02 (TA02)[R/ OL].Office of the Chief technologist, Space Technology Roadmaps,2012. http:/ / www. nasa. gov/ pdf/501329main _ TA02-ID _rev3-NRC-wTASR. pdf.
  • 4Bérend N, Cliquet E, Ruault J M, et al. How fast can we goto Mars using high power electric propulsion? [C] / /48thAIAA/ ASME/ SAE/ ASEE Joint Propulsion Conference & Ex-hibit. 2012: 3889.
  • 5Vyacheslav Murashko, Alexander Koryakin, Arkadij Nyatin.State of the art and prospects of electric propulsion in Russia[C] / /28th International Electric Propulsion Conference,France, 2003: IEPC-2003-340.
  • 6Dankanich J W, Vondra B, Ilin A V. Fast transits to mars u-sing electric propulsion[C] / /46th AIAA/ ASME/ SAE/ ASEEJoint Propulsion.
  • 7Nishiyama K, Hosoda S, Ueno K, et al. Development andtesting of the hayabusa2 ion engine system[C] / / Joint Confer.ence of 30th International Symposium on Space Technologyand Science, 34th International Electric Propulsion Confer.ence and 6th Nano.satellite Symposium, Hyogo.Kobe, Japan,2015: IEPC.2015.333 / ISTS.2015.b.333.
  • 8Lewis R A, Pérez.Luna J, Coombs N, et al. Qualification ofthe T6 thruster for bepicolombo[C] / / Joint Conference of 30thInternational Symposium on Space Technology and Science,34th International Electric Propulsion Conference and 6thNano.satellite Symposium, Hyogo.Kobe, Japan, 2015: IEPC.2015.132 / ISTS.2015.b.132.
  • 9Snyder J S, Goebel D M, Polk J E, et al. Results of a 2000hour wear test of the NEXIS ion engine[C] / /29th Interna.tional Electric Propulsion Conference,Princeton,USA,2005:IEPC-2005-281.
  • 10Polk J E, Brinza D, Kakuda R Y, et al. Demonstration of theNSTAR ion propulsion system on the deep space one mission[C] / /27th International Electric Propulsion Conference, Pas.adena, USA, 2001:IEPC.2001.075.

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