中国空间科学技术

中国空间科学技术 ›› 2024, Vol. 44 ›› Issue (1): 99-105.doi: 10.16708/j.cnki.1000-758X.2024.0011

• 论文 • 上一篇    下一篇

放电通道长径比对霍尔推力器性能的影响

李春波，郭宁，杨三祥，高俊，雪佳强   

  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
  • 发布日期:2024-02-01 出版日期:2024-02-25

Effects of discharge channel aspect ratio on performance of Hall thruster

LI Chunbo，GUO Ning，YANG Sanxiang，GAO Jun，XUE Jiaqiang   

  1. Science and Technology on Vacuum Technology and Physics Laboratory，Lanzhou Institute of Physics，Lanzhou 730000，China
  • Online:2024-02-01 Published:2024-02-25

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摘要： 为了获得霍尔推力器放电通道长度与宽度的最佳匹配关系，提升推力器性能，以兰州空间技术物理研究所研制的LHT-70霍尔推力器为研究对象，利用一维流体模型，研究了阳极工质流率对比冲、推力的影响，并通过与试验数据比对，验证了模型的合理性。在此基础上，研究了放电通道长径比α（长度与宽度的比值）对霍尔推力器性能的影响。结果表明，随着放电通道长径比的增加，电子温度降低，电子密度增加，电离率上升，离子密度增加，但由于中性原子密度与离子壁面损失增大，工质利用率下降；放电通道出口处电势降、比冲、推力和效率先增大后减小。由工质利用率、比冲、推力和效率随放电通道长径比增加而变化的趋势可知，在固定放电通道体积与内径，增加长度时，当放电通道长径比介于1.80~2.05，霍尔推力器性能达到最优。研究结果将为霍尔推力器的优化设计提供理论指导。

关键词: 霍尔推力器, 放电通道长径比, 放电特性, 性能参数, 流体模拟

Abstract: To obtain the optimal matching relationship between the length and width of the discharge channel of the Hall thruster and to improve the thruster performance，a one-dimensional fluid model relying on the LHT-70 Hall thruster developed by the Lanzhou Institute of Physics was used to study the influence of the anode propellant flow rate on specific impulse and thrust，and the rationality of the model was verified by comparing it with the experimental data.On this basis，the effect of the discharge channel aspect ratio α（the ratio of length to width）on the performance of the Hall thruster was studied.The results show that with the increase of the discharge channel aspect ratio，the electron temperature decreases，the electron density increases，the ionization rate increases，and the ion density increases.However，due to the increase in neutral atom density and ion wall loss，the propellant utilization rate decreases.The potential drop at the exit of the discharge channel，the specific impulse，thrust and efficiency first increase and then decrease.It can be seen from the trend of propellant utilization rate，specific impulse，thrust and efficiency changing with the increase of the discharge channel aspect ratio that when the volume and internal radius of the discharge channel are fixed，the length is increased，and the discharge channel aspect ratio is 1.80~2.05，the performance of the Hall thruster reaches the optimum.The results will provide theoretical guidance for the optimal design of Hall thrusters.

Key words: Hall thrusters, discharge channel aspect ratio, discharge characteristics, performance parameters, fluid simulation