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

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plasma Science and Technology 2022年第2期24卷 1-9页

作者： Haotian FAN Yongjie DING Chunjin MO Liqiu WEI Hong LI Daren YU plasma propulsion lab Institute of Advanced PowerHarbin Institute of TechnologyHarbin 150001People's Republic of China Key laboratory of Aerospace plasma propulsion Ministry of Industry and Information TechnologyHarbin 150001People's Republic of China

In this study,the neutral gas distribution and steady-state discharge under different discharge channel lengths were studied via numerical *** results show that the channel with a length of 22 mm has the advantage of comprehensive discharge *** this time,the magnetic field intensity at the anode surface is 10%of the peak magnetic field *** 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 *** outward movement of the main ionization zone also reduces the ion loss on the wall ***,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 *** excessively short-channel will greatly reduce the voltage utilization *** thrust is reduced to a minimum of 46.1 m ***,because the anode surface is excessively close to the main ionization zone,the discharge reliability is also difficult to *** 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 *** 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

Effect of low-frequency oscillation on performance of Hall thrusters

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plasma Science and Technology 2018年第7期20卷 139-144页

作者： Liqiu WEI Wenbo LI Yongjie DING Daren YU lab of plasma propulsion Harbin Institute of Technology（HIT）Harbin 150001People＇s Republic of China lab of Electric Drive ＆ propulsion Technology Harbin Institute of Technology（HIT）Harbin 150001People＇s Republic of China

In this paper, a direct connection between the discharge current amplitude and the thruster performance is established by varying solely the capacitance of the filter unit of the Hall thrusters. To be precise, the variation characteristics of ion current, propellant utilization efficiency, and divergence angle of plume at different low-frequency oscillation amplitudes are measured. The findings demonstrate that in the case of the propellant in the discharge channel just meets or falls below the full ionization condition, the increase of low-frequency oscillation amplitude can significantly enhance the ionization degree of the neutral gas in the channel and increase the thrust and anode efficiency of thruster. On the contrary, the increase in the amplitude of low-frequency oscillation will lead to increase the loss of plume divergence, therefore the thrust and anode efficiency of thruster decrease.

关键词： Hall thruster low-frequency oscillation performance filter

Hybrid–PIC simulation of sputtering product distribution in a Hall thruster

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plasma Science and Technology 2017年第10期19卷 44-51页

作者： Xifeng CAO Guanrong HANG Hui LIU Yingchao MENG Xiaoming LUO Daren YU lab of plasma propulsion Mail Box 458 Harbin Institute of Technology （HIT） Harbin 150001 People＇s Republic of China Shanghai Institute of Space propulsion Shanghai 201112 People＇s Republic of China

Hall thrusters have been widely used in orbit correction and the station-keeping of geostationary satellites due to their high specific impulse, long life, and high reliability. During the operating life of a Hall thruster, high-energy ions will bombard the discharge channel and cause serious erosion. As time passes, this sputtering process will change the macroscopic surface morphology of the discharge channel, especially near the exit, thus affecting the performance of the ***, it is necessary to carry out research on the motion of the sputtering products and erosion process of the discharge wall. To better understand the moving characteristics of sputtering products, based on the hybrid particle-in-cell（PIC） numerical method, this paper simulates the different erosion states of the thruster discharge channel in different moments and analyzes the moving process of different particles, such as B atoms and B~＋ ions. In this paper,the main conclusion is that B atoms are mainly produced on both sides of the channel exit, and B~＋ ions are mainly produced in the middle of the channel exit. The ionization rate of B atoms is approximately 1%.

关键词： Hall thruster sputtering erosion hybrid–PIC

Matching characteristics of magnetic field configuration and chamfered channel wall in a magnetically shielded Hall thruster

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plasma Science and Technology 2021年第10期23卷 72-80页

作者： Zhaoyu Wang Hong Li Chao Zhong Yanlin Hu Yongjie Ding Liqiu Wei Daren Yu lab of plasma propulsion Harbin Institute of TechnologyHarbin 150001People's Republic of China Key laboratory of Aerospace plasma propulsion Ministry of Industry and Information TechnologyHarbin 150001People's Republic of China Beijing Institute of Control Engineering Beijing 100190People's Republic of China

To date, the selection of the magnetic field line used to match the chamfered inner and outer channel walls in a magnetically shielded Hall thruster has not been quantitatively studied. Hence, an experimental study was conducted on a 1.35 k W magnetically shielded Hall thruster with a xenon propellant. Different magnetic field lines were chosen, and corresponding tangentially matched channel walls were manufactured and utilized. The results demonstrate that high performance and a qualified anti-sputtering effect cannot be achieved simultaneously. When the magnetic field lines that match the chamfered wall have a strength at the channel centerline of less than 12% of the maximum field strength, the channel wall can be adequately protected from ion sputtering. When the magnetic field lines have a strength ratio of 12%–20%, the thruster performance is high. These findings provide the first significant quantitative design reference for the match between the magnetic field line and chamfered channel wall in magnetically shielded Hall thrusters.

关键词： magnetically shielded Hall thruster magnetic field line chamfered channel wall tangent matching

Numerical study of the effect of aft-loaded magnetic field on multiple ionizations in Hall thruster

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plasma Science and Technology 2022年第7期24卷 45-52页

作者： Demai ZENG Hong LI Jinwen LIU Yongjie DING Liqiu WEI Daren YU Wei MAO lab of plasma propulsion Harbin Institute of TechnologyHarbin 150001People's Republic of China Key laboratory of Aerospace plasma propulsion Ministry of Industry and Information TechnologyHarbin 150001People's Republic of China Qingdao Haier Smart Technology Qingdao 266100People's Republic of China Beijing Institute of Control Engineering Beijing 100190People's Republic of China

It is assumed that the shift of a strong magnetic field region with a positive gradient from exit plane to outside, namely the transit from a normal loaded magnetic field to an aft-loaded one, enhances the multiple ionization process in the magnetically shielded Hall thruster. To confirm this conjecture, a comparative study is carried out numerically with a particle-in-cell method. The simulation results prove that compared with the normal loaded magnetic field, the application of aft-loaded magnetic field enhances the multiple ionization process. This study further analyzes the ionization characteristics of the transition from low-charged ions to high-charged ions under two magnetic field conditions and the influence of the magnetic strength of aft-loaded magnetic field on the multiple ionization characteristics. The study described herein is useful for understanding the discharge characteristics of Hall thruster with an aft-loaded magnetic field.

关键词： Hall thruster aft-loaded magnetic field multiple ionization electron temperature

Influence of heating on the discharge characteristics of a hollow cathode

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plasma Science and Technology 2020年第1期22卷 15-23页

作者： Yanlin HU Zhongxi NING Xiaoyu LIU Yanfeng CHU Wei MAO Yan SHEN Ximing ZHU Beijing Institute of Control Engineering Beijing 100080People's Republic of China plasma propulsion lab Institute of Advanced PowerHarbin Institute of TechnologyHarbin 150001People's Republic of China

Hollow cathodes are widely used as electron sources and neutralizers in ion and Hall electric *** applications such as commercial aerospace and gravitational wave detection require hollow cathodes with a very wide discharge current *** this paper,a heater is used to compensate for the temperature drop of the emitter at low *** self-sustained current can be extended from 0.6 to 0.1 A with a small discharge oscillation and ion energy when the flow rate is *** is also beneficial for long-life ***,when the discharge current is high(>1 A),heating can cause discharge oscillation,discharge voltage and ion energy to increase,f urther,combined with a rapid decline of pressure inside the cathode and an increase in the temperature in the cathode orifice plate,electron emission in die orifice and outside the orifice increases and the plasma density in the orifice *** leads to a change in the cathode discharge mode.

关键词： electric propulsion hollow cathode discharge oscillation heater extended operation range

Simulation study of the influence of leak electrons on the discharge characteristics of a cusped field thruster

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plasma Science and Technology 2019年第4期21卷 115-122页

作者： Hui LIU Xiang NIU Huan WU Daren YU lab of plasma propulsion.Harbin Institute of Technology(HIT) Harbin 150001.People's Republic of China Department of Mechanical and Aerospace Engineering University of CaliforniaLos AngelesCA 90095.United States of America

Previous studies have shown that leak electro ns in cusped field thrusters can move along the channel axis to the anode after crossing the magnetic cusp on the *** this paper,a onedimensional fluid model is built along two typical electron paths to study the influence of leak electrons on the discharge characteristics of a cusped field thruster,considering the electron temperature *** is found that the frequencies of low-frequency oscillations increase with a decrease in the proportion of leak electrons,which is related to an increase in the ion speed in the *** results show that the position of the peak electron temperature is near the magnetic cusp on the exit and the position of the peak electron density is located downstream from the middle magnetic *** a decrease in the proportion of the leak electrons,the peak electron temperature and peak electron density decrease and the position of the peak electron density moves away from the exit,which is related to a decrease in the potential fall on the exit and an increase in confinement of electrons to the middle magnetic cusp.

关键词： leak electrons cusped field thruster low-frequency oscillations electron lemperature,ionization

Magnet stage optimization of 5 kW multi-cusped field thruster

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plasma Science and Technology 2020年第9期22卷 128-138页

作者： Peng HU Daren YU Yan SHEN Beijing Institute of Control Engineering Beijing 100094People's Republic of China lab of Advanced Space propulsion Beijing 100094People’s Republic of China Beijing Engineering Research Center of Efficient and Green Aerospace propulsion Technology Beijing 100094People’s Republic of China plasma propulsion laboratory of Harbin Institute of Technology Harbin 150001People's Republic of China School of Aeronautics and Astronautics Sun Yat-sen UniversityGuangzhou 510006People's Republic of China

The multi-cusped field thruster is a unique electric thruster device,which has many advantages such as long lifetime,large-range thrust throttling ability,high thrust density,and low *** thruster employs several alternating polarity permanent magnets to create a periodic magnetic field with several *** studies have indicated that the basic ionization and acceleration processes are directly related to the electron motion behavior,which mainly depends on the magnetic field *** magnet number and magnet stage length are two key magnetic field parameters that have important effects on the thruster *** this paper,both the magnet number and magnet stage length parameters are studied for the optimization of a 5 k W multi-cusped field *** results indicate that the three-stage thruster has a better electron confinement than the two-stage *** has lower ion energy loss at the wall,and shows a higher ionization ***,the three-stage magnetic field is a superior magnetic field ***,the three-stage magnetic field simulation results indicate that an optimal accelerating electric field distribution and ionization region distribution could be obtained when the magnet length ratio is 78:25:20.

关键词： multi-cusped field magnet number magnet length performance optimization

Influence of the position relationship between the cathode and magnetic separatrix on the discharge process of a Hall thruster

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plasma Science and Technology 2024年第1期26卷 74-81页

作者：曹希峰麻洪宁夏国俊刘辉赵方舟王宇航陈巨辉 School of Mechanical and Power Engineering Harbin University of Science and TechnologyHarbin 150001People’s Republic of China Shanghai Institute of Satellite Engineering Shanghai 20040People’s Republic of China lab of plasma propulsion Harbin Institute of TechnologyHarbin 150001People’s Republic of China

Previous studies have shown that there is an obvious coupling relationship between the installation location of the external cathode and the magnetic separatrix in the plume region of a Hall *** this paper,the particle-in-cell simulation method is used to compare the thruster discharge process under the conditions of different position relationships between the cathode and the magnetic *** comparing the distribution of electron conduction,potential,plasma density and other microscopic parameters,we try to explain the formation mechanism of the discharge *** simulation results show that the cathode inside and outside the magnetic separatrix has a significant effect on the distribution of potential and plasma *** the cathode is located on the outer side of the magnetic separatrix,the potential above the plume region is relatively low,and there is a strong potential gradient above the plume *** potential gradient is more conducive to the radial diffusion of ions above the plume,which is the main reason for the strong divergence of the *** distribution of ion density is also consistent with the distribution of *** the cathode is located on the outer side of the magnetic separatrix,the radial diffusion of ions in the plume region is ***,by comparing the results of electron conduction,it is found that the traiectories of electrons emitted from the cathode are significantly different between the inner and outer sides of the magnetic *** is mainly because the electrons are affected by the magnetic mirror effect of the magnetic tip,which makes it difficult for the electrons to move across the magnetic *** is the main reason for the difference in potential *** this paper,the simulation results of macroscopic parameters under several conditions are also compared,and they are consistent with the experimental *** cathode is located on the inner side of the ma

关键词： Hall thruster cathode magnetic separatrix