Simulation of a helicon plasma source in a magnetoplasma rocket engine  

作　　者：Zhenyu YANG Wei FAN Jianguo WEI Xianwei HAN 杨振宇;范威;魏建国;韩先伟(Shaanxi Key Laboratory of Plasma Physics and Applied Technology,Xi'an 710100,People's Republic of China)

机构地区：[1]Shaanxi Key Laboratory of Plasma Physics and Applied Technology,Xi'an 710100,People's Republic of China

出　　处：《Plasma Science and Technology》2022年第7期53-62,共10页等离子体科学和技术（英文版）

基　　金：supported by the Shaanxi Key Laboratory of Plasma Physics and Applied Technology。

摘　　要：The helicon plasma source,which generates high thrust and high impulse,is of vital importance for magnetoplasma rocket engines.In this work,a multi-component,two-dimensional,axisymmetric fluid model coupled with an electromagnetic field was developed to model the helicon discharge.The simulation results demonstrate that:(i)the discharge mode changes twice—each conversion is accompanied by a plasma density jump and an electron temperature peak in the discharge;(ii)when the input current increases,the plasma density increases,and ionization occurs faster;(iii)the background magnetic field clearly enhances the discharge;(iv)the plasma density may be smaller if the discharge has not entered the wave mode.

关 键 词：space propulsion MPRE helicon plasma source discharge mode conversion 

分 类 号：V439.2[航空宇航科学与技术—航空宇航推进理论与工程]