Investigation of short-channel design on performance optimization effect of Hall thruster with large height–radius ratio  

作　　者：Haotian FAN Yongjie DING Chunjin MO Liqiu WEI Hong LI Daren YU 范昊天;丁永杰;牟春锦;魏立秋;李鸿;于达仁(Plasma Propulsion Lab,Institute of Advanced Power,Harbin Institute of Technology,Harbin 150001,People's Republic of China;Key Laboratory of Aerospace Plasma Propulsion,Ministry of Industry and Information Technology,Harbin 150001,People's Republic of China)

机构地区：[1]Plasma Propulsion Lab,Institute of Advanced Power,Harbin Institute of Technology,Harbin 150001,People's Republic of China [2]Key Laboratory of Aerospace Plasma Propulsion,Ministry of Industry and Information Technology,Harbin 150001,People's Republic of China

出　　处：《Plasma Science and Technology》2022年第2期1-9,共9页等离子体科学和技术（英文版）

基　　金：This work is funded by the Defense Industrial Technology Development Program(No.JCKY2019603B005);National Natural Science Foundation of China(Nos.52076054,51777045);the Hunan Science and Technology Innovation Project(No.2019RS1102).

摘　　要：In this study,the neutral gas distribution and steady-state discharge under different discharge channel lengths were studied via numerical simulations.The results show that the channel with a length of 22 mm has the advantage of comprehensive discharge performance.At this time,the magnetic field intensity at the anode surface is 10%of the peak magnetic field intensity.Further analysis shows that the high-gas-density zone moves outward due to the shortening of the channel length,which optimizes the matching between the gas flow field and the magnetic field,and thus increases the ionization rate.The outward movement of the main ionization zone also reduces the ion loss on the wall surface.Thus,the propellant utilization efficiency can reach a maximum of 96.8%.Moreover,the plasma potential in the main ionization zone will decrease with the shortening of the channel.The excessively short-channel will greatly reduce the voltage utilization efficiency.The thrust is reduced to a minimum of 46.1 m N.Meanwhile,because the anode surface is excessively close to the main ionization zone,the discharge reliability is also difficult to guarantee.It was proved that the performance of Hall thrusters can be optimized by shortening the discharge channel appropriately,and the specific design scheme of short-channel of HEP-1350 PM was defined,which serves as a reference for the optimization design of Hall thruster with large height–radius ratio.The shortchannel design also helps to reduce the thruster axial dimension,further consolidating the advantages of lightweight and large thrust-to-weight ratio of the Hall thruster with large height–radius ratio.

关 键 词：Hall thruster large height-radius ratio short-channel design discharge performance numerical simulation 

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] O441[理学—电磁学]