稳态等离子体推力器羽流数值模拟  

Numerical simulation on plume of a stationary plasma thruster

作　　者：钱中[1] 王平阳[1] 杜朝辉[1] 康小录 

机构地区：[1]上海交通大学机械与动力工程学院航空航天系,上海200030 [2]上海航天动力机械研究所,上海200233

出　　处：《固体火箭技术》2008年第5期484-488,共5页Journal of Solid Rocket Technology

基　　金：国家自然科学基金资助项目(No.50306013)

摘　　要：以国内研制的稳态等离子体推力器羽流为研究对象,建立了基于粒子单元法和直接蒙特卡罗模拟法的数值仿真模型,简化了电子动量方程,运用Boltzmann关系式求解了等离子体电势,研究了羽流电子数密度、离子电流密度及流场温度分布。通过与实验数据和已有数值结果对比,以验证模型和编制的程序。研究表明,羽流出口下游0.3-1.0 m处的羽流中心电子数密度约为2.5×10^16-5×10^15m^-3,电流密度约为65-1 A/m^2。文中工作对分析等离子体羽流污染具有参考意义。Taking plume of the stationary plasma thruster manufactured by China as research object, a numerical simulation model was derived based on particle-in-cell and direct simulation Monte-Carlo hybrid method. The electron momentum equation was simplified. Boltzmann relational expression was used for solving plasma potential. The electron number density of the plume, ion current density, and temperature distribution of flow field were investigated. Then the model and the program were verified by comparison of calculation results, experimental data and existing numerical results. The investigation results show that the electron number density of plume center at a distance of exit downstream 0.3 - 1.0 m is about 2.5 × 10^16 - 5 × 10^5 m^- 3, and current density is about 65 - 1 A/m^2. The above conclusion can provide the reference for analyzing contamination of plasma plume.

关 键 词：电推力器 等离子体羽流 粒子单元法(PIC) 直接蒙特卡罗模拟法(DSMC) 

分 类 号：V439[航空宇航科学与技术—航空宇航推进理论与工程]