Experimental and numerical simulation study of the effect for the anode positions on the discharge characteristics of 300W class low power Hall thrusters  

作　　者：陈新伟 高俊 杨三祥 耿海 郭宁 顾左 杨俊泰 张宏 Xinwei CHEN;Jun GAO;Sanxiang YANG;Hai GENG;Ning GUO;Zuo GU;Juntai YANG;Hong ZHANG(Science and Technology on Vacuum Technology and Physics Laboratory,Lanzhou Institute of Physics,Lanzhou 730000,People's Republic of China)

机构地区：[1]Science and Technology on Vacuum Technology and Physics Laboratory,Lanzhou Institute of Physics,Lanzhou 730000,People's Republic of China

出　　处：《Plasma Science and Technology》2023年第1期100-110,共11页等离子体科学和技术（英文版）

基　　金：National Natural Science Foundation of China (No.12005087);Science and Technology Program of Gansu Province (Nos.2006ZCTF0054, HTKJ2019KL510003,and 20JR10RA478)。

摘　　要：Low-power Hall thruster(LHT) generally has poor discharge efficiency characteristics due to the large surface-to-volume ratio.Aiming to further refine and improve the performance of 300 W class LHT in terms of thrust and efficiency,and to obtain the most optimal operating point,the experimental study of the discharge characteristics for three different anode positions was conducted under the operation of various discharge voltages(100-400 V) and anode mass flow rates(0.65 mg·s-1and 0.95 mg·s-1).The experimental results indicated that the thruster has the most excellent performance in terms of thrust and efficiency etc at a channel length of 27 mm for identical operating conditions.In addition,particle in cell simulations,employed to reveal the underlying physical mechanisms,show that the ionization and acceleration zone is pushed downwards towards the channel exit as the anode moves towards the exit.At the identical operating point,when the channel length is reduced from 32 to 27 mm,the ionization and acceleration zone moves towards the exit,and the parameters such as thrust and efficiency increase due to the high ionization rate,ion number density,and axial electric field.When the channel length is further moved to 24 mm,the parameters in terms of thrust(F) and efficiency(ηa) are reduced as a result of the decreasing ionization efficiency(ηm) and the larger plume divergence angle(α).In this paper,the results indicated that an optimum anode position(ΔL=27 mm) exists for the optimum performance.

关 键 词：low-power Hall thruster discharge characteristics PIC-MCC simulation anode positions 

分 类 号：V439.4[航空宇航科学与技术—航空宇航推进理论与工程]