Magnetic field configurations on thruster performance in accordance with ion beam characteristics in cylindrical Hall thruster plasmas

Kim, Holak; Choe, Wonho; Lee, Seung Hun; Park, Sanghoo

doi:10.1063/1.4978532

Cited by 21 publications

(11 citation statements)

References 19 publications

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“…To investigate the topic of this study, the particle-in-cell numerical program, which was developed by our laboratory independently was applied to simulate the discharge process, 18) and the availability of this simulation model has been proved experimentally. 19) An adequate amount of positive research results on HETs 13,[19][20][21] CHTs 10,11,22) and cusped field thrusters, 23) have been achieved using this numerical program.…”

Section: Pic Model Descriptionmentioning

confidence: 98%

“…6,7) To solve the problem of the service life of a small power thruster, Raitses proposed a new cylindrical Hall thruster (CHT), 8) effectively solving the problem of increasing the surface-to-volume ratio, and then carried out a series of studies on experimental phenomena such as the difference in the magnetic field configuration near the anode region of the CHT, multivalent ionization, and spoke oscillation. [9][10][11] Harbin Institute of Technology designed and proposed a 50-100 W low-power CHT. They used the magnetically insulated anode structure to optimize the magnetic field in the discharge channel and carried out a series of studies on its magnetic field, performance, and service life.…”

Section: Introductionmentioning

confidence: 99%

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Study on the influence of magnetic mirror ratio on the erosion of the bottom channel of cylindrical Hall thruster with magnetically insulated anode

Hu¹,

Mao³

et al. 2020

Jpn. J. Appl. Phys.

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A cylindrical Hall thruster with a magnetically insulated anode structure was found experimentally to experience erosion sputtering at the bottom of the ceramic channel. In this study, a Particle-In-Cell numerical simulation was used to analyze the influence of the magnetic mirror effect on the ion current density, ion energy, and deposition power density bombardment at the bottom of the discharge channel. The research findings show that, as the magnetic mirror ratio grows, the stronger magnetic mirror effect confines the ions in the boron nitride channel, leading to a decrease in the ion current density and ion energy bombarding the bottom of discharge bottom. Further statistics show that the deposition power density decreases as the magnetic mirror ratio grows, indicating that increasing the magnetic mirror ratio can effectively alleviate the erosion sputtering at the bottom.

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Section: Pic Model Descriptionmentioning

confidence: 98%

Section: Introductionmentioning

confidence: 99%

Study on the influence of magnetic mirror ratio on the erosion of the bottom channel of cylindrical Hall thruster with magnetically insulated anode

Hu¹,

Mao³

et al. 2020

Jpn. J. Appl. Phys.

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“…The Hall thruster has the advantages of simple structure, high specific impulse, high efficiency and long life. It is suitable for spacecraft attitude control, north-south position maintenance and other on-orbit missions [1][2][3][4][5]. The structure of a Hall thruster is shown in figure 1.…”

Section: Introductionmentioning

confidence: 99%

Influence of neutral gas supply position on wall erosion of Hall thruster studied by particle-in-cell simulation

Cao¹,

Xia²,

Liu³

et al. 2023

Plasma Sci. Technol.

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In this work, we have carried out the simulation study on the discharge process of Hall thruster under the conditions of different neutral gas radial supply positions based on particle-in-cell method (PIC) and Monte Carlo collision method (MCC). This paper compares the two-dimensional (2D) distributions of neutral gas, plasma and the distributions of wall erosion related parameters under different neutral gas supply positions. The comparison results show that the change of the neutral gas supply position will affect 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 comparison results of erosion related parameter distribution show that the change of gas supply location has 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 inner and outer walls are 33.3% and 29.9% lower than those under the other two conditions. In terms of erosion range, the gas supply position moves from the lower gas supply position to the upper gas supply position, the erosion range gradually increases from 5 to 7.5 mm.

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“…The Hall thruster is an electric propulsion device, which has been widely used in satellite location maintenance, attitude adjustment, orbit change, resistance compensation, and many interplanetary missions. [1][2][3][4][5] The principle of Hall thruster is to use an orthogonal electromagnetic field to ionize the propellant gas and accelerate the ions to generate thrust. As the propellant gas, xenon and krypton are generally used.…”

Section: Introductionmentioning

confidence: 99%

Research of influence of the additional electrode on Hall thruster plume by particle-in-cell simulation*

Cao¹,

Liu²,

Yu³

2020

Chinese Phys. B

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Hall thruster is an electric propulsion device for attitude control and position maintenance of satellites. The discharge process of Hall thruster will produce divergent plume. The plume will cause erosion, static electricity, and other interference to the main components, such as solar sailboard, satellite body, and thruster. Therefore, reducing the divergence of the plume is an important content in the research of thruster plume. The additional electrode to the plume area is a way to reduce the divergence angle of the plume, but there are few related studies. This paper uses the particle-in-cell (PIC) simulation method to simulate the effect of the additional electrode on the discharge of the Hall thruster, and further explains the effect mechanism of the additional electrode on parameters such as the electric field and plume divergence angle. The simulation results show that the existence of the additional electrode can enhance the potential near the additional position. The increase of the potential can effectively suppress the radial diffusion of ions, and effectively reduce the plume divergence angle. The simulation results show that when the additional electrode is 30 V, the half plume divergence angle can be reduced by 18.21%. However, the existence of additional electric electrode can also enhance the ion bombardment on the magnetic pole. The additional electrode is relatively outside, the plume divergence angle is relatively small, and it can avoid excessive ion bombardment on the magnetic pole. The research work of this paper can provide a reference for the beam design of Hall thruster.

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Magnetic field configurations on thruster performance in accordance with ion beam characteristics in cylindrical Hall thruster plasmas

Cited by 21 publications

References 19 publications

Study on the influence of magnetic mirror ratio on the erosion of the bottom channel of cylindrical Hall thruster with magnetically insulated anode

Study on the influence of magnetic mirror ratio on the erosion of the bottom channel of cylindrical Hall thruster with magnetically insulated anode

Influence of neutral gas supply position on wall erosion of Hall thruster studied by particle-in-cell simulation

Research of influence of the additional electrode on Hall thruster plume by particle-in-cell simulation*

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