径向磁场对霍尔推力器性能影响的数值模拟研究  

Numerical study of the effect of radial magnetic field on performance of Hall thruster

作　　者：杨三祥 王倩楠[1] 高俊[1] 贾艳辉[1] 耿海[1] 郭宁[1] 陈新伟 袁兴龙 张鹏[1] Yang San-Xiang;Wang Qian-Nan;Gao Jun;Jia Yan-Hui;Geng Hai;Guo Ning;Chen Xin-Wei;Yuan Xing-Long;Zhang Peng(Science and Technology on Vacuum Technology and Physics Laboratory,Lanzhou Institute of Physics,Lanzhou 730000,China)

机构地区：[1]兰州空间技术物理研究所真空技术与物理重点实验室,兰州730000

出　　处：《物理学报》2022年第10期216-224,共9页Acta Physica Sinica

基　　金：甘肃省自然科学基金(批准号:20JR10RA478);甘肃省杰出青年基金(批准号:21JR7RA744)资助的课题。

摘　　要：霍尔推力器由于推力密度大、结构简单等特点,在商业航天领域具有广泛的应用前景.为了进一步提升小功率霍尔推力器的性能,克服低轨卫星用小功率霍尔推力器性能受限于输入功率和最大磁场强度的问题,本文利用数值模拟和理论分析方法研究了霍尔推力器放电通道中径向磁场分布对推力器性能的影响.在轴向磁场分布和最大径向磁场强度一定的情况下,通过改变径向磁场梯度实现径向磁场对推力器性能影响的研究.结果表明,在放电参数、推进剂流率以及轴向磁场不变的情况下,加速区的电势随着径向距离的增加而减小.因此,靠近推力器放电通道内壁侧的径向磁场梯度越大,离子沿着轴向漂移到达推力器出口的动能越大,推力器的推力越大.本文的研究结果为霍尔推力器的磁场设计,性能优化提供了理论支撑.The Hall-effect thruster has wide applications for commercial aerospace because of the high thrust density and simple structure.In order to further improve the performance of low-power Hall thruster and to solve the problem that the performance of low-power Hall thruster for low-orbit satellites is limited by the input power and maximum magnetic field intensity,the influence of radial magnetic field distribution in the discharge channel on the performance of the thruster is studied by numerical simulation and theoretical analysis in this work through changing the radial magnetic gradient on condition that the axial magnetic profile and the magnetic strength remain unchanged.The results show that the potential of the acceleration zone decreases with the increase of radial distance when the discharge parameters,propellant flow rate and axial magnetic field are unchanged.Therefore,the greater the radial magnetic field gradient near the inner wall of the thruster discharge channel,the greater the kinetic energy of the ions drifting along the axial direction to the thruster outlet,,and the greater the thrust of thruster.The research results of this work provide theoretical support for the magnetic field design and performance optimization of hall thrusters.

关 键 词：霍尔推力器 数值研究 径向磁场 加速区 

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]