Oscillations of the Hall current in a Hall thruster with an anode layer

Ermilov, A. N.; Eroshenkov, V. F.; Novichkov, D. N.; Kovalenko, Yu. A.; Sapronova, T. M.; Chernyshev, T. V.; Shumilin, A. P.

doi:10.1134/s0018151x14030109

Cited by 6 publications

(3 citation statements)

References 4 publications

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“…In their work the selection of regularization parameters is posteriori, whereas our work tries to establish a method to predetermine the parameters without knowing how the current is distributed. Meanwhile, the Hall current magnitude and distribution can be affected by factors such as the discharge current, discharge voltage and so on [9,24,25], which means that a single constant regularization parameter satisfying all conditions is impossible. This suggests us to build different inverse magnetostatic problems and select the regularization parameters accordingly.…”

Section: Introductionmentioning

confidence: 99%

Utilizing the L-curve criterion for the inverse magnetostatic problem of Hall drift current estimation

Ren,

Zhou,

Wei

et al. 2024

J. Phys. D: Appl. Phys.

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Aiming at achieving the in-orbit diagnostic of Hall drift current, this study focuses on estimation through the indirect measurement methodology using a magnetic sensor array. It elaborates on the application of a pseudo-seminorm defined for the Hall drift current solution to address the inverse magnetostatic problems, which are formulated with a two-dimensional Tikhonov regularization constraint, and thereby offering a systematic approach to select regularization parameters. Our investigation discusses factors influencing the formation of the L-curve and the accuracy of the resultant solution obtained via the L-curve criterion. The results reveal that the formation of the defined pseudo-seminorm of the Hall drift current solution in the semi-logarithmic coordinate system is independent of the number of calibrating current elements or the number of magnetic sensors. This effectively resolves the issue of failing to generate an L-curve during regularization parameter selection. Furthermore, the study indicates that expanding the number of calibrating current elements – essentially increasing the unknown variables in the inverse magnetostatic equations – contributes to a significant enhancement in the accuracy of Hall drift current solutions. It also has extensibility to be applied to other areas where the contactless current measuring is required.

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Section: Introductionmentioning

confidence: 99%

Utilizing the L-curve criterion for the inverse magnetostatic problem of Hall drift current estimation

Ren,

Zhou,

Wei

et al. 2024

J. Phys. D: Appl. Phys.

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“…In a number of studies, the intrinsic field of the plasma is not taken into account when calculating the magnetic field of HETs. The typical average ratio between internal and external magnetic field lies in a range from one to ten percent [16][17][18][19][20][21]. Thus, this effect is considered to be small and (in most cases) does not account for simulations results.…”

Section: Introductionmentioning

confidence: 99%

On a force balance and role of cathode plasma in Hall effect thrusters

Chernyshev¹,

Krivoruchko²

2022

Plasma Sources Sci. Technol.

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The cathode plasma is a specific transition region in the Hall Effect Thruster (HET) discharge that localizes between the strongly magnetized acceleration layer (magnetic layer or B-layer) and non-magnetized exhaust plume. Cathode plasma provides a flow of electron current that supplies losses in the magnetic layer (due to ionization, excitation, electron-wall interactions, etc.). The electrons' transport in this region occurs in collisionless mode through the excitation of plasma instabilities. This effect is also known as "anomalous transport/conductivity". In this work, we present the results of a 2d (drift-plane) kinetic simulation of the HET discharge, including the outside region that contains cathode plasma. We discuss the process of cathode plasma formation and the mechanisms of "anomalous transport" inside it. We also analyze how fluid force balance emerges from collisionless kinetic approach. The acceleration mechanism in Hall Effect Thrusters (HETs) is commonly described in terms of force balance. Namely, the reactive force produced by accelerated ions has the same value as Ampère's force acting on a drift current loop. This balance written in integral form provides the basis for quantitative estimations of HETs' parameters and scaling models.

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“…The aforementioned previous work examined the electron-ion recombination pathways and HET behavior from a time-averaged analysis. The HET discharge plasma, however, is a dynamic system, resulting in fundamental plasma oscillatory modes that are not directly observable from time-averaged measurements [16][17][18][19][20][21][22][23][24][25][26][27][28]. The oscillatory plasma modes' types, frequencies, and spectral powers present in the discharge can impact HET stability and performance [20].…”

Section: Introductionmentioning

confidence: 99%

Electrical Facility Effects on Hall-Effect-Thruster Cathode Coupling: Discharge Oscillations and Facility Coupling

Walker¹,

Frieman²,

Walker³

et al. 2016

Journal of Propulsion and Power

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The physical mechanisms that govern the electrical interaction between the Hall-effect-thruster electrical circuit and the conductive vacuum-facility walls are not fully understood. As a representative test bed, an Aerojet Rocketdyne T-140 Hall-effect thruster is operated at 3.05 kW and a xenon mass flow rate of 11.6 mg∕s with a vacuum facility operating neutral pressure of 7.3 × 10 −6 torr, corrected for xenon. Two electrical witness plates, representative of the facility chamber walls, are placed 2.3 m radially outward from thruster centerline and 4.3 m axially downstream from the thruster exit plane. The cathode is radially translated from 18.1 to 77.8 cm away from the thruster centerline. At each cathode position, the discharge current and the electrical waveform of the radial and axial plates are simultaneously measured. As the cathode radial position changes from 18.1 to 77.8 cm from the thruster centerline, the discharge-current oscillation frequency decreases between 17 and 35% for the electrically grounded thruster-body case, and between 15 and 23% for the electrically floating thruster-body case. The analysis of the electron current collected by the radial plate suggests that electrons directly sourced from the cathode impinge on the radial plate at large cathode positions. Overall, the results of this work show that the chamber walls act as an artificial electrical boundary condition that keeps the Hall-effect-thruster plume plasma potential to within certain bounds.

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Oscillations of the Hall current in a Hall thruster with an anode layer

Cited by 6 publications

References 4 publications

Utilizing the L-curve criterion for the inverse magnetostatic problem of Hall drift current estimation

Utilizing the L-curve criterion for the inverse magnetostatic problem of Hall drift current estimation

On a force balance and role of cathode plasma in Hall effect thrusters

Electrical Facility Effects on Hall-Effect-Thruster Cathode Coupling: Discharge Oscillations and Facility Coupling

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