Hall推力器羽流数值模拟  

Numerical simulation of hall thruster plume

作　　者：钱中[1] 王平阳[1] 杜朝辉[1] 康小录 

机构地区：[1]上海交通大学航空航天工程系,上海200240 [2]上海航天动力机械研究所,上海200233

出　　处：《推进技术》2008年第1期93-97,共5页Journal of Propulsion Technology

基　　金：国家自然科学基金资助项目(50306013)

摘　　要：以稳态等离子体推力器(SPT)羽流流场为研究对象,基于直接蒙特卡罗模拟与粒子单元混合方法建立数值模型,模拟等离子体稳态流动,研究流场特性。将计算结果与实验数据相比较,并与同类推力器羽流参数进行比较,以保证仿真可靠性。研究表明,所建立的仿真模型能够较好地预测SPT羽流电子数密度和离子电流密度等参数。A numerical model, based on the direct simulation Monte Carlo and particle-in-cell hybrid method, was developed to simulate the steady flow of plasma and study the characteristics of the plume. The computational results were copared with both experimental data and plume parameters of a congener thruster to ensure the reliability of simulation. It indicated that the simulation model was able to well predict both electron number density and ion current density of plume of SPT.

关 键 词：稳态等离子推力器 羽流 蒙特卡罗法 粒子单元法 数值仿真 

分 类 号：V439[航空宇航科学与技术—航空宇航推进理论与工程]