离子推力器空心阴极分区均布模型研究

推进技术 ›› 2017, Vol. 38 ›› Issue (8): 1900-1906.

离子推力器空心阴极分区均布模型研究

谷增杰¹,郭宁¹,贾艳辉¹,谢侃²,杨威¹,冯杰¹,孙运奎¹

兰州空间技术物理研究所真空技术与物理国防科技重点实验室，甘肃兰州 730000,兰州空间技术物理研究所真空技术与物理国防科技重点实验室，甘肃兰州 730000,兰州空间技术物理研究所真空技术与物理国防科技重点实验室，甘肃兰州 730000,北京理工大学宇航学院，北京 100081,兰州空间技术物理研究所真空技术与物理国防科技重点实验室，甘肃兰州 730000,兰州空间技术物理研究所真空技术与物理国防科技重点实验室，甘肃兰州 730000,兰州空间技术物理研究所真空技术与物理国防科技重点实验室，甘肃兰州 730000

发布日期:2021-08-15
作者简介:谷增杰，男，硕士生，研究领域为空间电推进技术与工程。

Numerical Study on a Regional Uniform Model for Ion Thruster Hollow Cathode

National Key Laboratory of Science and Technology on Vacuum Technology ＆ Physics，Lanzhou Institute of Physics，Lanzhou 730000，China,National Key Laboratory of Science and Technology on Vacuum Technology ＆ Physics，Lanzhou Institute of Physics，Lanzhou 730000，China,National Key Laboratory of Science and Technology on Vacuum Technology ＆ Physics，Lanzhou Institute of Physics，Lanzhou 730000，China,School of Aerospace Engineering，Beijing Institute of Technology，Beijing 100081，China,National Key Laboratory of Science and Technology on Vacuum Technology ＆ Physics，Lanzhou Institute of Physics，Lanzhou 730000，China,National Key Laboratory of Science and Technology on Vacuum Technology ＆ Physics，Lanzhou Institute of Physics，Lanzhou 730000，China and National Key Laboratory of Science and Technology on Vacuum Technology ＆ Physics，Lanzhou Institute of Physics，Lanzhou 730000，China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究空心阴极结构尺寸和工况参数对放电性能的影响规律，基于发射体区和孔腔区等离子体参数均布假设，建立了一种不依赖试验和经验参数的适用于节流型空心阴极的分区均布数学模型。以LHC-5L空心阴极为算例，仿真结果与空心阴极试验结果对比表明，当输入参数在一定范围之内，计算所得放电电压误差优于20%，发射体温度误差优于15%，放电电压等参数随放电电流、工质流率、关键结构尺寸的变化趋势与试验结果基本一致，证明该模型可以用于预测空心阴极放电性能，为空心阴极结构参数选择和设计优化提供依据。

关键词: 电推进；空心阴极；放电特性；建模仿真；性能试验

Abstract: Aimed at understanding the regulations about how hollow cathode geometry features and working conditions affect its discharge characteristics，a regional uniform model suitable for orificed hollow cathode is presented and the method is based on hypothesis that plasma parameters are uniform for both insert and orifice region. Neither preliminary experimental dates nor empirical dates are needed for the model calculation input parameters. The model was used for calculating the discharge characteristics parameters for LHC-5L hollow cathodes. Compared with the test results，the error of calculated discharge voltage is less than 20% and the error of calculated emitter temperature is less than 15%. The variation tendency of calculated discharge voltage and emitter temperature with discharge current，xenon flow rate and geometry features are basically consistent with the tests. The results from the tests show that the model is qualified for forecasting discharge characteristics and could serve the hollow cathode design optimization and geometry parameters selection.

Key words: Electric propulsion；Hollow cathode；Discharge characteristic；Modeling and simulation；Performance test

谷增杰,郭宁,贾艳辉,谢侃,杨威,冯杰,孙运奎. 离子推力器空心阴极分区均布模型研究[J]. 推进技术, 2017, 38(8): 1900-1906.

GU Zeng-jie¹,GUO Ning¹,JIA Yan-hui¹,XIE Kan²,YANG Wei¹,FENG Jie¹,SUN Yun-kui¹. Numerical Study on a Regional Uniform Model for Ion Thruster Hollow Cathode[J]. Journal of Propulsion Technology, 2017, 38(8): 1900-1906.

参考文献

[1] 郭宁, 顾佐, 邱家稳, 等. 空心阴极在空间技术中的应用[J]. 真空, 2005, 42(5): 32-35.
[2] 杨福全, 江豪成, 张天平, 等. 20cm离子推力器飞行试验工作性能评价[J]. 推进技术, 2016, 37(4): 783-787. (YANG Fu-quan, JIANG Hao-cheng, ZHANG Tian-ping, et al. Flight Test Performance Evaluation of 20cm Ion Thruster[J]. Journal of Propulsion Technology, 2016, 37(4): 783-787.)
[3] 田立成, 高俊, 李兴坤, 等. LHT-100自励磁霍尔推力器热特性测试和热真空实验研究[J]. 推进技术, 2016, 37(4): 793-800. (TIAN Li-cheng, GAO Jun, LI Xing-kun, et al. Experimental Study of Thermal Characteristics and Thermal Vacuum of LHT-100 Self-Excited Hall Thruster[J]. Journal of Propulsion Technology, 2016, 37(4): 793-800.)
[4] Angelo Niko [Grubi?i?]. Microthrusters Based on the T5 and T6 Hollow Cathode[D]. Southampton: University of Southampton, 2009.
[5] 田立成, 石红, 李娟, 等. 航天器表面充电仿真计算和电位主动控制技术[J]. 航天器环境工程, 2012, 29(2): 144-149.
[6] Derek M Blash. The Effects of a Realistic Hollow Cathode Plasma Contactor Model on the Simulation of Bare Electrodynamic Tether Deorbit System[D]. Fort Collins: Colorado State University, 2013.
[7] Ioannis G Mikellides, Ira Katz, Dan M Goebel, et al. Theoretical Model of a Hollow Cathode Plasma for the Assessment of Insert and Keeper Lifetimes[R]. AIAA 2005-4234.
[8] Ioannis G Mikellides, Ira Katz, Dan M Goebel, et al.Theoretical Model of a Hollow Cathode Insert Plasma[R]. AIAA 2004-3817.
[9] Ioannis G Mikellides, Ira Katz, Dan M Goebel. Numerical Simulation of the Hollow Cathode Discharge Plasma Dynamics[C]. Princeton: 29th International Electric Propulsion Conference, 2005.
[10] Riccardo Albertoni, Daniela Pedrini, Fabrizio Paganucci, et al. A Reduced-Order Model for Thermionic Hollow Cathodes [J]. IEEE Transactions on Plasma Science, 2013, 41(7): 1731-1745.
[11] Riccardo Albertoni, Daniela Pedrini, Fabrizio Paganucci, et al. Experimental Characterization of a LaB6 Hollow Cathode for Low-Power Hall Effect Thrusters[C]. Cologne: Space Propulsion, 2014.
[12] Dan M Goebel, Ira Katz. Fundamentals of Electric Propulsion: Ion and Hall Thrusters [M]. New York: Wiley, 2008.
[13] Salhi A, Turchi P J. A First-Principles Model for Orificed Hollow Cathode Operation[R]. AIAA 92-3742
[14] Matthew T Domonkos. A Particle and Energy Balance Model of the Orificed Hollow Cathode[R]. AIAA 2002-4240.
[15] Ira Katz, John R Anderson, James E Polk, et al. One-Dimensional Hollow Cathode Model [J]. Journal of Propulsion and Power, 2003, 19(4): 595-600.
[16] Daniela Pedrini, Riccardo Albertoniy, Fabrizio Paganucci. Theoretical Model of a Lanthanum Hexaboride Hollow Cathode[C]. Washington: 33th International Electric Propulsion Conference, 2013.
[17] Korkmaz O, Celik M. Global Numerical Model for the Assessment of the Effect of Geometry and Operation Conditions on Insert and Orifice Region Plasmas of a Thermionic Hollow Cathode Electron Source[J]. Plasma Phys, 2014, 54(10): 838-850.
[18] Daniela Pedrini, RiccardoAlbertoni , Fabrizio Paganucci, et al. Modeling of LaB6 Hollow Cathode Performance and Life Time[C]. Beijing: 64th International Astronautical Conference, 2014.
[19] 张天平, 刘乐柱, 贾艳辉. 电推进系统空心阴极产品试验技术[J]. 火箭推进, 2010, 36(1): 58-62.
[20] 郭宁, 邱家稳, 顾佐, 等. 20cm氙离子发动机空心阴极3000h寿命试验[J]. 真空与低温, 2006, 12(4): 204-206.
[21] 郭宁, 江豪成, 顾佐. 离子发动机空心阴极寿命预测[J]. 真空, 2009, 46(4): 83-85.(编辑:史亚红)　　　　　　　　　　　　　　收稿日期:2016-05-16；修订日期:2016-06-22。作者简介:谷增杰,男,硕士生,研究领域为空间电推进技术与工程。E-mail:guzengjie@foxmail.com