## 留言板

 引用本文: 任军学, 王艳, 仇钎, 等 . 离子发动机羽流二维轴对称数值模型与验证[J]. 北京航空航天大学学报, 2011, 37(12): 1498-1503.
Ren Junxue, Wang Yan, Qiu Qian, et al. Validation of two-dimensional axisymmetric plume model for ion thruster[J]. Journal of Beijing University of Aeronautics and Astronautics, 2011, 37(12): 1498-1503. (in Chinese)
 Citation: Ren Junxue, Wang Yan, Qiu Qian, et al. Validation of two-dimensional axisymmetric plume model for ion thruster[J]. Journal of Beijing University of Aeronautics and Astronautics, 2011, 37(12): 1498-1503. (in Chinese)

## 离子发动机羽流二维轴对称数值模型与验证

###### 作者简介:任军学(1980-),男,湖北随州人,讲师,rjx_buaa@sina.com.
• 中图分类号: V 439.4

## Validation of two-dimensional axisymmetric plume model for ion thruster

• 摘要: 为了解离子发动机羽流特别是交换电荷离子(CEX,Charge-Exchange)的分布和流动特性,建立了离子发动机羽流的物理模型,采用粒子网格(PCI,Particle in Cell)方法对2种型号的离子发动机羽流场进行数值模拟计算,与其地面实验数据进行对比分析.结果表明:在CEX离子密度大小及分布、电势的大小及最大电势梯度的位置、CEX离子流动角方面,模拟结果同实验结果符合得相当好.在电势结构方面,由于舱壁电势的影响,模拟结果同实验结果相比有一些差别.羽流模型和计算结果为相关羽流实验和数值模拟研究提供参考.

•  [1] 陈琳英,宋仁旺.离子推力器羽流特性及其污染分析[J].上海航天,2005(4):36-40 Chen Linying, Song Renwang.Analysis on plume contamination and its characteristic of ion thruster[J].Aerospace Shanghai,2005(4):36-40(in Chinese) [2] Samanta R L Roy.Numerical simulation of ion thruster plume backflow for spacecraft contamination assessment .Boston: Department of Aeronautics and Astronautics, Massachusetts Institute of Technology,1995 [3] Kaufman H R.Charge-exchange plasma generated by an ion thruster .NASA CR-13844,1976 [4] Carruth M R,Brady M E.Measurement of the charge-exchange plasma flow from an ion thruster[J].Journal of Spacecraft, 1981,8(5):457-461 [5] Samanta Roy R L, Hastings D E,Taylor S.Three-dimensional plasma particle-in-cell calculations of ion thruster backflow contamination[J].Journal of Computational Physics, 1996,128(1):6-18 [6] Wang J, Brinza D,Young M.Three-dimensional particle simulations of ion propulsion plasma environment for deep space 1[J].Journal of Spacecraft and Rockets, 2001,38(3):433-438 [7] Passaro A, Vicini A,Biagioni L.3-D computation of plasma thruster plumes .AIAA paper 04-3632,2004 [8] Wang J, Cao Y, Kafafy R, et al.Simulations of ion thruster plume-spacecraft interactions on parallel supercomputer[J].IEEE Transactions on Plasma Science, 2006,34(5):2148-2158 [9] Roussel J F,Rogier F,Dufour G,et al.SPIS modeling capabilities,achievements and prospects //Proceedings of 10th Spacecraft Charging Technology Conference.Biarriz,France: ,2007 [10] Muranaka T,Hosoda S,Kim J H,et al.Development of multi-utility spacecraft charging analysis tool (MUSCAT)[J].IEEE Transactions on Plasma Science,2008,36(5):2336-2349 [11] 贺碧蛟,张建华,蔡国飙.稳态等离子体推进器羽流场数值模拟[J].北京航空航天大学学报, 2005, 31(9):1010-1013 He Bijiao, Zhang Jianhua, Cai Guobiao.Numerical simulation of stationary plasma thruster plume[J].Journal of Beijing University of Aeronautics and Astronautics, 2005,31(9):1010-1013(in Chinese)

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##### 出版历程
• 收稿日期:  2010-08-06
• 刊出日期:  2012-12-30

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