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Performance investigation of a low-power Hall thruster fed on iodine propellant
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作者 徐宗琦 王平阳 +2 位作者 蔡东升 谭睿 姜文静 《Plasma Science and Technology》 SCIE EI CAS CSCD 2024年第6期140-148,共9页
The common propellants used for electric thrusters, such as xenon and krypton, are rare, expensive,and difficult to acquire. Solid iodine attracts much attention with the advantages of low cost,extensive availability,... The common propellants used for electric thrusters, such as xenon and krypton, are rare, expensive,and difficult to acquire. Solid iodine attracts much attention with the advantages of low cost,extensive availability, low vapor pressure, and ionization potential. The performance of a lowpower iodine-fed Hall thruster matched with a xenon-fed cathode is investigated across a broad range of operation conditions. Regulation of the iodine vapor's mass flow rates is stably achieved by using a temperature control method of the iodine reservoir. The thrust measurements are finished utilizing a thrust target during the tests. Results show that thrust and anode-specific impulse increase approximately linearly with the increasing iodine mass flow rate.At the nominal power of 200 W class, iodine mass flow rates are 0.62 and 0.93 mg/s, thrusts are7.19 and 7.58 m N, anode specific impulses are 1184 and 826 s, anode efficiencies are 20.8%and 14.5%, and thrust to power ratios are 35.9 and 37.9 m N/k W under the conditions of 250 V,0.8 A and 200 V, 1.0 A, respectively. The operating characteristics of iodine-fed Hall thruster are analyzed in different states. Further work on the measurements of plasma characteristics and experimental optimization will be carried out. 展开更多
关键词 electric propulsion hall thruster iodine propellant thrust measurement operating characteristics
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Growth mechanism and characteristics of electron drift instability in Hall thruster with different propellant types
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作者 陈龙 阚子晨 +4 位作者 高维富 段萍 陈俊宇 檀聪琦 崔作君 《Chinese Physics B》 SCIE EI CAS CSCD 2024年第1期511-522,共12页
The existence of a significant electron drift instability(EDI) in the Hall thruster is considered as one of the possible causes of the abnormal increase in axial electron mobility near the outlet of the channel. In re... The existence of a significant electron drift instability(EDI) in the Hall thruster is considered as one of the possible causes of the abnormal increase in axial electron mobility near the outlet of the channel. In recent years, extensive simulation research on the characteristics of EDI has been conducted, but the excitation mechanism and growth mechanism of EDI in linear stage and nonlinear stage remain unclear. In this work, a one-dimensional PIC model in the azimuthal direction of the thruster near-exit region is established to gain further insights into the mechanism of the EDI in detail, and the effects of different types of propellants on EDI characteristics are discussed. The changes in axial electron transport caused by EDI under different types of propellants and electromagnetic field strengths are also examined. The results indicate that EDI undergoes a short linear growth phase before transitioning to the nonlinear phase and finally reaching saturation through the ion Landau damping. The EDI drives a significant ion heating in the azimuthal direction through electron–ion friction before entering the quasi-steady state, which increases the axial mobility of the electrons. Using lighter atomic weight propellant can effectively suppress the oscillation amplitude of EDI, but it will increase the linear growth rate, frequency, and phase velocity of EDI. Compared with the classical mobility, the axial electron mobility under the EDI increases by three orders of magnitude, which is consistent with experimental phenomena. The change of propellant type is insufficient to significantly change the axial electron mobility. It is also found that the collisions between electrons and neutral gasescan significantly affect the axial electron mobility under the influence of EDI, and lead the strength of the electric field to increase and the strength of the magnetic field to decrease, thereby both effectively suppressing the axial transport of electrons. 展开更多
关键词 hall thruster electron drift instability axial electron mobility particle-in-cell simulation
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Influence of the position relationship between the cathode and magnetic separatrix on the discharge process of a Hall thruster
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作者 曹希峰 麻洪宁 +4 位作者 夏国俊 刘辉 赵方舟 王宇航 陈巨辉 《Plasma Science and Technology》 SCIE EI CAS CSCD 2024年第1期74-81,共8页
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 thruster.In this paper,the... 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 thruster.In 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 separatrix.By comparing the distribution of electron conduction,potential,plasma density and other microscopic parameters,we try to explain the formation mechanism of the discharge difference.The simulation results show that the cathode inside and outside the magnetic separatrix has a significant effect on the distribution of potential and plasma density.When 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 region.This 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 plume.The distribution of ion density is also consistent with the distribution of potential.When the cathode is located on the outer side of the magnetic separatrix,the radial diffusion of ions in the plume region is enhanced.Meanwhile,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 separatrix.This 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 separatrix.This is the main reason for the difference in potential distribution.In this paper,the simulation results of macroscopic parameters under several conditions are also compared,and they are consistent with the experimental results.The cathode is located on the inner side of the magnetic separatrix,which can effectively reduce the plume divergence angle and improve the thrust.In this paper,the cathode moves from R=50 mm to R=35 mm along the radial direction,the thrust increases by 3.6 mN and the plume divergence angle decreases by 23.77%.Combined with the comparison of the ionization region and the peak ion density,it is found that the main reason for the change in thrust is the change in the radial diffusion of ions in the plume region. 展开更多
关键词 hall thruster CATHODE magnetic separatrix
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Thrust estimate method of an on-orbit Hall thruster using Hall drift current
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作者 Ziying REN Liqiu WEI +5 位作者 Zexin LIU Yanlin HU Liang HAN Hong LI Yongjie DING Xiufeng ZHONG 《Plasma Science and Technology》 SCIE EI CAS CSCD 2024年第12期150-159,共10页
In order to realize the thrust estimation of the Hall thruster during its flight mission,this study establishes an estimation method based on measurement of the Hall drift current.In this method,the Hall drift current... In order to realize the thrust estimation of the Hall thruster during its flight mission,this study establishes an estimation method based on measurement of the Hall drift current.In this method,the Hall drift current is calculated from an inverse magnetostatic problem,which is formulated according to its induced magnetic flux density detected by sensors,and then the thrust is estimated by multiplying the Hall drift current with the characteristic magnetic flux density of the thruster itself.In addition,a three-wire torsion pendulum micro-thrust measurement system is utilized to verify the estimate values obtained from the proposed method.The errors were found to be less than 8%when the discharge voltage ranged from 250 V to 350 V and the anode flow rate ranged from 30 sccm to 50 sccm,indicating the possibility that the proposed thrust estimate method could be practically applied.Moreover,the measurement accuracy of the magnetic flux density is suggested to be lower than 0.015 mT and improvement on the inverse problem solution is required in the future. 展开更多
关键词 thrust estimation hall effect thruster hall drift current inverse problem Tikhonov regularization
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Experimental and numerical simulation study of the effect for the anode positions on the discharge characteristics of 300W class low power Hall thrusters
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作者 陈新伟 高俊 +5 位作者 杨三祥 耿海 郭宁 顾左 杨俊泰 张宏 《Plasma Science and Technology》 SCIE EI CAS CSCD 2023年第1期100-110,共11页
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 ... 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. 展开更多
关键词 low-power hall thruster discharge characteristics PIC-MCC simulation anode positions
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Numerical study of viscosity and heat flux role in heavy species dynamics in Hall thruster discharge
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作者 Andrey SHASHKOV Alexander LOVTSOV +1 位作者 Dmitri TOMILIN Dmitrii KRAVCHENKO 《Plasma Science and Technology》 SCIE EI CAS CSCD 2023年第1期165-180,共16页
A two-and three-dimensional velocity space axisymmetric hybrid-PIC model of Hall thruster discharge called Hybrid2D has been developed.The particle-in-cell(PIC) method was used for neutrals and ions(heavy species),and... A two-and three-dimensional velocity space axisymmetric hybrid-PIC model of Hall thruster discharge called Hybrid2D has been developed.The particle-in-cell(PIC) method was used for neutrals and ions(heavy species),and fluid dynamics on a magnetic field-aligned(MFA) mesh was used for electrons.A time-saving method for heavy species moment interpolation on a MFA mesh was developed.The method comprises using regular rectangle and irregular triangle meshes,connected to each other on a pre-processing stage.The electron fluid model takes into account neither inertia terms nor viscous terms and includes an electron temperature equation with a heat flux term.The developed model was used to calculate all heavy species moments up to the third one in a stationary case.The analysis of the viscosity and the heat flux impact on the force and energy balance has shown that for the calculated geometry of the Hall thruster,the viscosity and the heat flux terms have the same magnitude as the other terms and could not be omitted.Also,it was shown that the heat flux is not proportional to the temperature gradient and,consequently,the highest moments should be calculated to close the neutral fluid equation system.At the same time,ions can only be modeled as a cold non-viscous fluid when the sole aim of modeling is the calculation of the operating parameters or distribution of the local parameters along the centerline of the discharge channel.This is because the magnitude of the viscosity and the temperature gradient terms are negligible at the centerline.However,when a simulation’s focus is either on the radial divergence of the plume or on magnetic pole erosion,three components of the ion temperature should be taken into consideration.The non-diagonal terms of ion pressure tensor have a lower impact than the diagonal terms.According to the study,a zero heat flux condition could be used to close the ion equation system in calculated geometry. 展开更多
关键词 hall thruster hybrid-PIC model moments of distribution function magnetic-field-aligned mesh
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Study of beam divergence and thrust vector eccentricity characteristics of the Hall thruster based on dual Faraday probe array planes and its applications
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作者 陈新伟 赵勇 +11 位作者 田恺 高俊 孙明明 孙新锋 郭宁 张宏 王尚民 冯杰 陈焘 耿海 杨俊泰 史楷 《Plasma Science and Technology》 SCIE EI CAS CSCD 2023年第5期104-115,共12页
The accurate knowledge of the thrust vector eccentricity and beam divergence characteristics of Hall thrusters are of significant engineering value for the beneficial integration and successful application of Hall thr... The accurate knowledge of the thrust vector eccentricity and beam divergence characteristics of Hall thrusters are of significant engineering value for the beneficial integration and successful application of Hall thrusters on spacecraft.For the characteristics of the plume bipolar diffusion due to the annular discharge channel of the Hall thruster,a Gaussian-fitted method for thrust vector deviation angle and beam divergence of Hall thrusters based on dual Faraday probe array planes was proposed in respect of the Hall thruster beam characteristics.The results show that the ratios of the deviation between the maximum and minimum values of the beam divergence angle and the thrust vector eccentricity angle using a Gaussian fit to the optimized Faraday probe dual plane to the mean value are 1.4%and 11.5%,respectively.The optimized thrust vector eccentricity angle obtained has been substantially improved,by approximately 20%.The beam divergence angle calculated using a Gaussian fitting to the optimized Faraday probe dual plane is approximately identical to the non-optimized one.The beam divergence and thrust vector eccentricity angles for different anode mass flow rates were obtained by averaging the beam divergence and thrust vector eccentricity angles calculated by the dual-plane,Gaussian-fitted ion current density method for different cross-sections.The study not only allows for an immediate and effective tool for determining the design of thrust vector adjustment mechanisms of spacecraft with different power Hall thrusters but also for characterizing the 3D spatial distribution of the Hall thruster plume. 展开更多
关键词 hall thruster beam divergence thrust vector eccentricity dual Faraday probe array planes
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Influence of neutral gas supply position on wall erosion of Hall thruster studied by particle-in-cell simulation
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作者 曹希峰 夏国俊 +2 位作者 刘辉 陈巨辉 于达仁 《Plasma Science and Technology》 SCIE EI CAS CSCD 2023年第5期184-192,共9页
In this work,we have carried out a simulation study on the discharge process of Hall thrusters under the conditions of different neutral gas radial supply positions based on the particle-in-cell(PIC)and Monte Carlo co... In this work,we have carried out a simulation study on the discharge process of Hall thrusters under the conditions of different neutral gas radial supply positions based on the particle-in-cell(PIC)and Monte Carlo collision(MCC)methods.This paper compares the two-dimensional(2D)distributions of neutral gas,plasma and wall erosion-related parameters under different neutral gas supply positions.The comparison results show that the change of the neutral gas supply position affects the radial distribution uniformity of the neutral gas and plasma in the channel.From the comparison of the density peaks,it can be found that the neutral gas density and the plasma density peak under the upper gas supply condition are relatively low,and the plasma density peak is 22.49%lower than the density peak under the middle gas supply condition.Meanwhile,as the radial position of the gas supply moves from the lower gas supply to the upper gas supply,the position of the ionization zone also gradually moves toward the anode.The results of erosion-related parameter distribution comparison show that the change of gas supply location has an obvious influence on erosion rate and erosion range.In terms of erosion rate,the wall erosion rate is relatively low under the upper gas supply condition,and the peak erosion rates of the inner and outer walls are 33.3%and 29.9%lower than those under the other two conditions.In terms of erosion range,as the gas supply position moves from the lower gas supply position to the upper gas supply position,the erosion range gradually increases from5 to 7.5 mm. 展开更多
关键词 hall thruster neutral gas wall erosion
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Experimental Study on the Effects of Magnetic Field Configuration near the Channel Exit on the Plume Divergence of Hall Thrusters 被引量:3
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作者 于达仁 李杰 +2 位作者 李鸿 李勇 江滨浩 《Plasma Science and Technology》 SCIE EI CAS CSCD 2009年第6期714-720,共7页
Experimental investigations into the effects of the magnetic field configuration near the channel exit on the plume of Hall thrusters were conducted. The magnetic field configuration near the channel exit is character... Experimental investigations into the effects of the magnetic field configuration near the channel exit on the plume of Hall thrusters were conducted. The magnetic field configuration near the channel exit is characterized by the inclination angle between the magnetic field lines and the thruster radial direction. Different inclination angles were obtained by varying the current ratio in the coils. The plume divergence angles were measured by a dual-directed probe. The results showed that the plume divergence angle increased obviously with the increase in the magnitude of the inclination angle near the channel exit. Therefore, in order to optimize the magnetic field for reducing plume divergence, the magnitude of the inclination angle should be reduced as much as possible. It suggests that the magnetic field configuration near the channel exit is another important factor that affects plume divergence. 展开更多
关键词 hall thruster plume divergence magnetic field configuration inclination angle
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Influence of channel length on discharge performance of anode layer Hall thruster studied by particle-in-cell simulation 被引量:3
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作者 Xi-Feng Cao Hui Liu +3 位作者 Wen-Jia Jiang Zhong-Xi Ning Run Li Da-Ren Yu 《Chinese Physics B》 SCIE EI CAS CSCD 2018年第8期368-373,共6页
Hall thruster has the advantages of simple structure, high specific impulse, high efficiency, and long service life, and so on. It is suitable for spacecraft attitude control, North and South position keeping, and oth... Hall thruster has the advantages of simple structure, high specific impulse, high efficiency, and long service life, and so on. It is suitable for spacecraft attitude control, North and South position keeping, and other track tasks. The anode layer Hall thruster is a kind of Hall thruster. The thruster has a longer anode area and a relatively short discharge channel. In this paper, the effect of the channel length on the performance of the anode layer Hall thruster is simulated by the PIC simulation method. The simulation results show that the change of the channel length has significant effect on the plasma parameters, such as potential and plasma density and so on. The ionization region mainly concentrates at the hollow anode outlet position, and can gradually move toward the channel outlet as the channel length decreases. The collision between the ions and the wall increases with the channel length increasing. So the proper shortening of the channel length can increase the life of the thruster. Besides, the results show that there is a best choice of the channel length for obtaining the best performance. In this paper, thruster has the best performance under a channel length of 5 mm. 展开更多
关键词 anode layer hall thruster channel length POTENTIAL
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Simulation study on the influence of magnetic field in the near-anode region on anode power deposition of ATON-type Hall thruster 被引量:3
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作者 Hongbo SU Hong LI +4 位作者 Yongjie DING Liqiu WEI Xu ZHANG Chaoying ZHOU Daren YU 《Plasma Science and Technology》 SCIE EI CAS CSCD 2020年第9期106-113,共8页
The highest deposition of power and temperature is always near the cusp of the ATON-type Hall thruster.This shows that when there are electrons gathering at the cusp,the distribution of heat load will be uniform,which... The highest deposition of power and temperature is always near the cusp of the ATON-type Hall thruster.This shows that when there are electrons gathering at the cusp,the distribution of heat load will be uniform,which will potentially damage the reliability.Therefore,we optimize the magnetic field near the anode.We changed the magnetic field characteristics in the near-anode region with an additional magnetic screen,and performed numerical simulation with particle-incell simulation.The simulation results show that the magnetic field of the thruster with the additional magnetic screen can alleviate the over-concentration of power deposition on the anode and reduce the power deposition in the anode by 20%,while ensuring that the overall magnetic field characteristics do not change significantly. 展开更多
关键词 hall thruster magnetic field near-anode power deposition
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Effect of Anode Magnetic Shield on Magnetic Field and Ion Beam in Cylindrical Hall Thruster 被引量:2
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作者 赵杰 唐德礼 +3 位作者 耿少飞 王世庆 柳建 许丽 《Plasma Science and Technology》 SCIE EI CAS CSCD 2010年第1期109-112,共4页
Numerical simulation of the effect of the anode magnetic shielding on the magnetic field and ion beam in a cylindrical Hall thruster is presented. The results show that after the anode is shielded by the magnetic shie... Numerical simulation of the effect of the anode magnetic shielding on the magnetic field and ion beam in a cylindrical Hall thruster is presented. The results show that after the anode is shielded by the magnetic shield, the magnetic field lines near the anode surface are obviously convex curved, the ratio of the magnetic mirror is enhanced, the width of the positive magnetic field gradient becomes larger than that without the anode magnetic shielding, the radial magnetic field component is enhanced, and the discharge plasma turbulence is reduced as a result of keeping the original saddle field profile and the important role the other two saddle field profiles play in restricting electrons. The results of the particle in cell (PIC) numerical simulation show that both the ion number and the energy of the ion beam increase after the anode is shielded by the magnetic shield. In other words, the specific impulse of the cylindrical Hall thruster is enhanced. 展开更多
关键词 cylindrical hall thruster anode magnetic shield magnetic field line magnetic mirror ratio saddle magnetic field profile ion beam
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Effect of Segmented Electrode Length on the Performances of an Aton-Type Hall Thruster 被引量:2
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作者 段萍 边兴宇 +3 位作者 曹安宁 刘广睿 陈龙 殷燕 《Plasma Science and Technology》 SCIE EI CAS CSCD 2016年第5期525-530,共6页
The influences of the low-emissive graphite segmented electrode t)laeed near the channel exit on the discharge characteristics of a Hall thruster are studied using the particle- in-cell method. A two-dimensional phys... The influences of the low-emissive graphite segmented electrode t)laeed near the channel exit on the discharge characteristics of a Hall thruster are studied using the particle- in-cell method. A two-dimensional physical model is established according to the Hall thruster discharge channel configuration. The effects of electrode length on the potential, ion density, electron temperature, ionization rate and discharge current are investigated. It is found that, with tile increasing of the segmented electrode length, the equipotential lines bend towards the channel exit. and approximately parallel to the wall at the channel surface, the radial velocity and radial flow of ions are increased, and the electron temperature is also enhanced. Due to the conductive characteristic of electrodes, the radial electric field and the axial electron conductivity near the wall are enhanced, and the probability of the electron-atom ionization is reduced, which leads to the degradation of the ionization rate in the discharge channel. However, the interaction between electrons and the wall enhances the near wall conductivity, therefore the discharge current grows along with the segmented electrode length, and the performance of the thruster is also affected. 展开更多
关键词 hall thruster segmented electrodes PARTICLE-IN-CELL ionization rate
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Low-frequency oscillations in Hall thrusters 被引量:2
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作者 魏立秋 韩亮 +1 位作者 于达仁 郭宁 《Chinese Physics B》 SCIE EI CAS CSCD 2015年第5期117-126,共10页
In this paper, we summarize the research development of low-frequency oscillations in the last few decades. The findings of physical mechanism, characteristics and stabilizing methods of low-frequency oscillations are... In this paper, we summarize the research development of low-frequency oscillations in the last few decades. The findings of physical mechanism, characteristics and stabilizing methods of low-frequency oscillations are discussed. It shows that it is unreasonable and incomplete to model an ionization region separately to analyze the physical mechanism of low-frequency oscillations. Electro-dynamics as well as the formation conditions of ionization distribution play an important role in characteristics and stabilizing of low-frequency oscillations. Understanding the physical mechanism and characteristics of low- frequency oscillations thoroughly and developing a feasible method stabilizing this instability are still important research subjects. 展开更多
关键词 low-frequency oscillations plasma discharge hall thrusters
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Experimental and numerical investigation of a Hall thruster with a chamfered channel wall 被引量:1
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作者 Hong Li Guo-Jun Xia +4 位作者 Wei Mao Jin-Wen Liu Yong-Jie Ding Da-Ren Yu Xiao-Gang Wang 《Chinese Physics B》 SCIE EI CAS CSCD 2018年第10期484-494,共11页
A discharge channel with a chamfered wall not only has application in the design of modern Hall thrusters, but also exists where the channel wall is eroded, and so is a common status for these units. In this paper, th... A discharge channel with a chamfered wall not only has application in the design of modern Hall thrusters, but also exists where the channel wall is eroded, and so is a common status for these units. In this paper, the laws and mechanisms that govern the effect of the chamfered wall on the performance of a Hall thruster are investigated. By applying both experimental measurement and particle-in-cell simulation, it is determined that there is a moderate chamfer angle that can further improve the optimal performance obtained with a straight channel. This is because the chamfering of the wall near the channel exit can enhance ion acceleration and effectively reduce ion recombination on the wall, which is favorable to the promotion of the thrust and efficiency. However, the chamfer angle should not be too large; otherwise, both the density of the propellant gas and the distribution of the plasma potential in the channel are influenced, which is undesirable for efficient propellant utilization and beam concentration. Therefore, it is suggested that the chamfer shape of the channel wall is an important factor that must be carefully considered in the design of Hall thrusters. 展开更多
关键词 hall thruster chamfered wall discharge performance physical mechanism
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Effect of Magnetic Mirror on the Asymmetry of the Radial Profile of Near-Wall Conductivity in Hall Thrusters 被引量:1
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作者 于达仁 刘辉 付海洋 《Plasma Science and Technology》 SCIE EI CAS CSCD 2009年第3期314-320,共7页
Considering the actual magnetic field configuration in a Hall thruster, the effect of magnetic mirror on the radial profile of near-wall conductivity (NWC) is studied in this paper. The plasma electron dynamic proce... Considering the actual magnetic field configuration in a Hall thruster, the effect of magnetic mirror on the radial profile of near-wall conductivity (NWC) is studied in this paper. The plasma electron dynamic process is described by the test particle method. The Monte Carlo scheme is used to solve this model. The radial profile of electron mobility is obtained and the role of magnetic mirror in NWC is analysed both theoretically and numerically. The numerical results show that the electron mobility peak due to NWC is inversely proportional to the magnetic mirror ratio and the asymmetry of electron mobility along the radial direction gets greater when the magnetic mirror is considered. This effect indicates that apart from the disparity in the magnetic field strength, the difference in the magnetic mirror ratio near the inner and outer walls would actually augment the asymmetry of the radial profile of NWC in Hall thrusters. 展开更多
关键词 magnetic mirror effect near-wall conductivity asymmetrical profile hall thruster
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Effect of low-frequency oscillation on performance of Hall thrusters 被引量:1
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作者 Liqiu WEI Wenbo LI +1 位作者 Yongjie DING Daren YU 《Plasma Science and Technology》 SCIE EI CAS CSCD 2018年第7期139-144,共6页
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 var... 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. 展开更多
关键词 hall thruster low-frequency oscillation PERFORMANCE FILTER
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Investigation of short-channel design on performance optimization effect of Hall thruster with large height–radius ratio 被引量:1
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作者 Haotian FAN Yongjie DING +3 位作者 Chunjin MO Liqiu WEI Hong LI Daren YU 《Plasma Science and Technology》 SCIE EI CAS CSCD 2022年第2期1-9,共9页
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 a... 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. 展开更多
关键词 hall thruster large height-radius ratio short-channel design discharge performance numerical simulation
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Characteristics of a Sheath with Secondary Electron Emission in the Double Walls of a Hall Thruster 被引量:1
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作者 段萍 李肸 +2 位作者 沈鸿娟 陈龙 鄂鹏 《Plasma Science and Technology》 SCIE EI CAS CSCD 2012年第9期837-841,共5页
In order to investigate the effects of secondary electrons, which are emitted from the wall, on the performance of a thruster, a one-dimensional fluid model of the plasma sheath in double walls is applied to study the... In order to investigate the effects of secondary electrons, which are emitted from the wall, on the performance of a thruster, a one-dimensional fluid model of the plasma sheath in double walls is applied to study the characteristics of a magnetized sheath. The effects of secondary electron emission (SEE) coefficients and trapping coefficients, as well as magnetic field, on the structure of the plasma sheath are investigated. The results show that sheath potential and wall potential rise with the increment of SEE coefficient and trapping coefficient which results in a reduced sheath thickness. In addition, magnetic field strength will influence the sheath potential distributions. 展开更多
关键词 hall thruster magnetized sheath secondary electron
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Particle-in-cell simulation for the effect of magnetic cusp on discharge characteristics in a cylindrical Hall thruster 被引量:1
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作者 Sheng-Tao Liang Hui Liu Da-Ren Yu 《Chinese Physics B》 SCIE EI CAS CSCD 2018年第4期341-345,共5页
The cylindrical Hall thruster has the good prospect of serving as a miniaturized electric propulsion device.A 2 D-3 V particle-in-cell plus Monte Carlo(PIC-MCC) method is used to study the effect of the magnetic cus... The cylindrical Hall thruster has the good prospect of serving as a miniaturized electric propulsion device.A 2 D-3 V particle-in-cell plus Monte Carlo(PIC-MCC) method is used to study the effect of the magnetic cusp on discharge characteristics of a cylindrical Hall thruster.The simulation results show that the main ionization region and the main potential drop of the thruster are located at the upstream of the discharge channel.When the magnetic cusp moves toward the anode side,the main ionization region is compressed and weakened,moving upstream correspondingly.The ionization near the cusp is enhanced,and the interaction between the plasma and the wall increases.The simulation results suggest that the magnetic cusp should be located near the channel exit. 展开更多
关键词 cylindrical hall thruster PIC-MCC method magnetic cusp
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