稳态等离子体推进器羽流的粒子模拟  

The particle simulation of the plume flow exhausted from the stationary plasma thruster

作　　者：田东波[1] 沈青[1] 樊菁[1] 

机构地区：[1]中国科学院力学研究所高温气体动力学实验室,北京100080

出　　处：《空气动力学学报》2006年第4期425-429,共5页Acta Aerodynamica Sinica

摘　　要：利用结合了particle-in-cell方法的直接模拟Monte Carlo方法模拟了稳态等离子体推进器的羽流场。为了更真实地再现实验设备中的流动,模拟中包含了背压气体,并在计算中直接模拟,改变了以往的中性粒子平衡态的处理方式。为了匹配试验结果,修正了推进器出口处气流偏转角分布,并建议最大偏转半角取为20°。计算结果与现有的实验结果符合较好。In this paper, the stationary plasma thruster plume flow is simulated by using the direct simulation Monte Carlo method combined with the particle in cell method. In order to reproduce the flow conditions in the experimental facility more realistically, the backgnmnd gas is included and simulated directly and the neutral particles are treated separately not as the equilibrium state. The distribution of deflection angle at the thruster outlet is also modified to match with experimental results and the half deflection angle of 20° is suggested. The agreement of the simulation results with the experiment is good.

关 键 词：电推进 DSMC-PIC方法 中性粒子 偏转角 

分 类 号：V211.25[航空宇航科学与技术—航空宇航推进理论与工程]