霍尔推力器等离子体羽流粒子模拟  

Particle Simulation of Plasma Plume of a Hall Thruster

作　　者：钱中[1] 康小录 王平阳[1] 杜朝辉[1] 

机构地区：[1]上海交通大学机械与动力工程学院,上海200240 [2]上海空间推进研究所,上海200233

出　　处：《上海航天》2009年第4期43-46,共4页Aerospace Shanghai

基　　金：国家自然科学基金(50306013)

摘　　要：建立了霍尔推力器羽流仿真模型,用单元粒子-直接模拟蒙特卡罗(PIC-DSMC)混合方法对SPT-7推力器的流场进行数值模拟,分析背压、扩张角和电子温度对流场的影响。结果表明:背压粒子增加了回流区内离子和高速粒子,加重羽流污染。SPT-70推力器羽流出口处扩张角约为30°。实验数据验证了仿真模型的正确和方法的可行,对电推力器及其羽流污染等的研究有一定的参考价值。An emulation model of Hall thruster plume was set up in this paper. The flow field of the thruster was simulated with the particle-in-cell （PIC-DSMC） hybrid method. The effect of background pressure, divergence angle and electron temperature on flow field were analyzed. The results showed that background pressure particles would lead to an increase of ion number and high speed particle number in the backflow region, which would aggravate the contamination of plume. And the divergence angle of plume at thruster exit was about 30 degree. The correct of the simulation model and the feasibility of the method were validated by the experiment data, which was referable for the research of electric thrusters and their plume contamination.

关 键 词：稀薄等离子体 羽流 单元粒子 直接模拟蒙特卡罗 背压 扩张角 电子温度 

分 类 号：TM386[电气工程—电机]