Investigation into the ionization and acceleration regions shift in a Hall thruster channel

Shashkov, Andrey; Lovtsov, A. S.; Tomilin, D. A.

doi:10.1140/epjd/e2019-90641-y

Cited by 9 publications

(8 citation statements)

References 11 publications

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“…Consequently, the ionization region moves upstream as well (see figures 15 and 16), thereby further reducing the divergence angle. This observation aligns well with the prior findings [47][48][49].…”

Section: Findings and Discoursesupporting

confidence: 93%

Optimization of magnetic field design for Hall thrusters based on a genetic algorithm

TAN 谭,

HANG 杭,

WANG 王

2024

Plasma Sci. Technol.

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Magnetic field design is essential for the operation of Hall thrusters. This study focuses on utilizing a genetic algorithm to optimize the magnetic field configuration of SPT70. A 2D hybrid PIC-DSMC and channel-wall erosion model are employed to analyze the plume divergence angle and wall erosion rate, while a Farady probe measurement and laser profilometry system are set up to verify the simulation results. The results demonstrate that the genetic algorithm contributes to reducing the divergence angle of the thruster plumes and alleviating the impact of high-energy particles on the discharge channel wall，reducing the erosion by 5.5% and 2.7%, respectively. Further analysis indicates that the change from a divergent magnetic field to a convergent magnetic field, combined with the upstream shift of the ionization region, contributes to the improving the operation of the Hall thruster.

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Section: Findings and Discoursesupporting

confidence: 93%

Optimization of magnetic field design for Hall thrusters based on a genetic algorithm

TAN 谭,

HANG 杭,

WANG 王

2024

Plasma Sci. Technol.

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“…The thruster KM-88 with centerline 88 mm [59] and 15 mm height of the discharge channel [54] was modeled. The simulation domain was 2.5 times longer than the discharge chamber length.…”

Section: The Results and Their Analysismentioning

confidence: 99%

“…In the case where > z z , 6 the conductivity coefficient becomes constant = a f . 6 The coefficients z j and f j were calculated in the 1D3V hybrid model [9,54] using the adjustment of the anomalous conductivity profile to experimentally measure the operating parameters described in detail in [55]. Figure 4 shows the anomalous collision frequency profile in comparison with classical collision frequencies and the electron cyclotron frequency.…”

Section: Boltzmann Integralsmentioning

confidence: 99%

Numerical study of viscosity and heat flux role in heavy species dynamics in Hall thruster discharge

Shashkov¹,

Tomilin²,

Kravchenko³

et al. 2022

Plasma Sci. Technol.

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Two-dimensional with three-dimensional velocity space axisymmetric hybrid-PIC model of Hall thruster discharge called Hybrid2D has been developed. Particle-in-cell (PIC) method was used for neutrals and ions (heavy species) and fluid dynamics on magnetic-field-aligned (MFA) mesh was used for electrons. Time saving method for heavy species moments interpolation on MFA mesh was developed. The method implies using regular rectangle and irregular triangle meshes, connected to each other on preprocessing stage. Electron fluid model takes into account neither inertia terms nor viscous terms and includes electron temperature equation with heat flux term. The developed model was used to calculate all heavy species moments up to the third one in 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 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 cold non-viscous fluid when the sole aim of the modeling is the calculation of the operating parameters or distribution of the local parameters along the centerline of the discharge channel, because the magnitude of the viscosity and the temperature gradient terms is negligible in the centerline. However, when simulations’ focus is either on the radial divergence of the plume or on magnetic poles erosion, 3 components of ion temperature should be taken into consideration. The non-diagonal terms of ions’ pressure tensor have lower impact than diagonal terms. According to the study, zero heat flux condition could be used for closing the ions equation system in calculated geometry.

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“…The optimized Hall thruster with a hollow magnetic anode is called PlaS [13][14][15][16], which represents a series of Hall thrusters of different powers. Hollow magnetic anode technology was also applied to a series of KM Hall thrusters [17,18] developed by the Keldysh Research Centre in Russia.…”

Section: Introductionmentioning

confidence: 99%

Improving the specific impulse of Hall thrusters using a wide channel design

Liu,

Li,

Jiang

et al. 2024

J. Phys. D: Appl. Phys.

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This paper proposes increasing the width of the discharge channel to improve the specific impulse of Hall thrusters. In our study, we significantly increased the achievable channel width by optimizing the magnetic circuit topology, and the design freedom of the Hall thruster was improved. A prototype of a wide-channel high-specific-impulse Hall thruster was designed and experimentally verified. The effects of channel width on the discharge process and the characteristics of an aft-loaded magnetic field Hall thruster were investigated. The high-intensity luminous region did not diffuse radially with an increase in the channel width, and the plasma was always concentrated near the channel centerline. A wider channel is more conducive for improving the propellant utilization efficiency, thereby effectively improving the specific impulse of the Hall thruster. By optimizing the discharge channel width, the upper limit of the discharge voltage was increased, and the maximum specific impulse was increased from 3170 to 3794 s, a relative improvement of 20%. The effect of the specific impulse improvement at the same discharge voltage was analyzed and discussed. The results of this study are significant for the design of high-specific-impulse Hall thrusters.

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Investigation into the ionization and acceleration regions shift in a Hall thruster channel

Cited by 9 publications

References 11 publications

Optimization of magnetic field design for Hall thrusters based on a genetic algorithm

Optimization of magnetic field design for Hall thrusters based on a genetic algorithm

Numerical study of viscosity and heat flux role in heavy species dynamics in Hall thruster discharge

Improving the specific impulse of Hall thrusters using a wide channel design

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