A 3D particle model for the plume CEX simulation

被引:7
作者
Lu, C. [1 ]
Qiu, P. [1 ]
Cao, Y. [1 ]
Zhang, T. P. [2 ]
Chen, J. J. [2 ]
机构
[1] Harbin Inst Technol, Shenzhen Grad Sch, Shenzhen, Peoples R China
[2] Lanzhou Inst Phys, Lanzhou, Gansu, Peoples R China
关键词
Ion thruster; plume; 3D particle model; IFE-PIC-MCC; SPACECRAFT; ENVIRONMENT; SMART-1;
D O I
10.1017/aer.2018.79
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
Charge Exchange (CEX) ion is the main factor causing the plume pollution. The distribution of CEX ions is determined by the distribution of beam ions and neutral atoms. Hence, the primary problem in the study of the plume is how to accurately simulate the distribution of beam ions and neutral atoms. At present, the most commonly used model utilised for the plume simulation is the analytical model proposed by Roy for the plume simulation of the NASA Solar Technology Application Readiness (NSTAR) ion thruster. However, this analytical model can only be applied to the ion beam with small divergence angles. In addition, the analytical model is no longer applicable to the simulation for the plume of a new type of ion thruster that appeared recently, which is called the annular ion thruster. In this paper, a 3D particle model is proposed for the plume simulation of ion thrusters consisting of the particle model for beam ions, the Direct SimulationMonte Carlo (DSMC) model for neutral atoms and the Immersed Finite Element-Particle In Cell-Monte Carlo Collision (IFE-PIC-MCC) model for CEX ions. Then, the plume of the NSTAR ion thruster is simulated by both Roy's model and the 3D particle model. The simulation results of both models are then compared with the experimental results. It is shown that the numerical results of the 3D particle model agree well with those of the analytical model and the experimental data. And this 3D particle model can also be used for other electric thrusters.
引用
收藏
页码:1425 / 1441
页数:17
相关论文
共 23 条
[1]  
Bird G., 1994, Molecular gas dynamics and the direct simulation monte carlo of gas flows, V508, P128
[2]   Numerical simulation of Hall thruster plasma plumes in space [J].
Boyd, Iain D. .
IEEE TRANSACTIONS ON PLASMA SCIENCE, 2006, 34 (05) :2140-2147
[3]   Monte Carlo simulation of neutral xenon flows in electric propulsion devices [J].
Boyd, ID ;
Van Gilder, DB ;
Liu, XM .
JOURNAL OF PROPULSION AND POWER, 1998, 14 (06) :1009-1015
[4]  
David O., 2004, 40 AIAA ASME SAE ASE, P3806
[5]  
Han D R., 2013, 49 AIAA ASME SAE ASE, DOI [10.2514/6.2013-3888, DOI 10.2514/6.2013-3888]
[6]   Three-dimensional immersed finite element methods for electric field simulation in composite materials [J].
Kafafy, R ;
Lin, T ;
Lin, Y ;
Wang, J .
INTERNATIONAL JOURNAL FOR NUMERICAL METHODS IN ENGINEERING, 2005, 64 (07) :940-972
[7]   Modelling ion propulsion plume interactions with spacecraft in formation flight [J].
Kafafy, R. ;
Cao, Y. .
AERONAUTICAL JOURNAL, 2010, 114 (1157) :417-426
[8]   Study of interspacecraft coulomb forces and implications for formation flying [J].
King, LB ;
Parker, GG ;
Deshmukh, S ;
Chong, JH .
JOURNAL OF PROPULSION AND POWER, 2003, 19 (03) :497-505
[9]   Modeling of plasma flow around SMART-1 spacecraft [J].
Markelov, Gennady ;
Gengembre, Eric .
IEEE TRANSACTIONS ON PLASMA SCIENCE, 2006, 34 (05) :2166-2175
[10]  
Patterson M, 2013, 48 AIAA ASME SAE ASE, DOI [10.2514/6.2012-3798, DOI 10.2514/6.2012-3798]