离子发动机羽流二维轴对称数值模型与验证

任军学; 王艳; 仇钎; 汤海滨

离子发动机羽流二维轴对称数值模型与验证

1.
北京航空航天大学宇航学院, 北京 100191
2. 北京空间机电研究所, 北京 100190

基金项目: 国家自然科学基金资助项目(10805004,10705003)

详细信息

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
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- 被引次数: 0
出版历程
- 收稿日期: 2010-08-06
- 网络出版日期: 2012-12-30

Validation of two-dimensional axisymmetric plume model for ion thruster

1.
School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
2. Beijing Institute of Space Mechanics & Electricity, Beijing 100190, China

摘要

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.
- 离子发动机 /
- 羽流 /
- 粒子网格 /
- 交换电荷离子 /
- 数值模拟
Abstract: In order to understand the distribution and flow characteristic of ion plume especially the charge-exchange (CEX) ions, the ion thruster plume model was established and a numerical simulation using the particle-in-cell method was adopted to obtain CEX ions distribution in the plume. The calculation results were compared with the experimental results for the plume fields of two ion thrusters. It agrees well between calculation results and experimental results of CEX ions density distribution, magnitude of electrical potential, position of maximum electrical potential grads, CEX ion flow angle. Structures of electrical potential have somewhat differences because the experimental result is influenced by the vacuum tank wall. The ion thruster plume model and calculation results help for experimental and numerical simulation study of plume.
- ion engine /
- plume /
- particle in cell /
- charge-exchange ions /
- numerical simulation

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参考文献(1)

[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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