Effects of the peak magnetic field position on Hall thruster discharge characteristics

Fan, Haotian; Li, Hong; Ding, Yongjie; Wei, Liqiu; Yu, Daren

doi:10.1016/j.asr.2020.06.036

Cited by 11 publications

(5 citation statements)

References 22 publications

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“…This means that more ions will bombard the anode surface, increasing the power deposition on the anode, which will lead to overheating or ablation of the anode, threatening the discharge stability and service life of the thruster. In the discharge test of HEP-100X with the same power level [30], there was a phenomenon of anode ablation caused by the anode surface being excessively close to the ionization zone. Therefore, not only discharge performance but also discharge reliability should be considered when selecting the optimal channel length.…”

Section: Simulation Results and Analysismentioning

confidence: 99%

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

Fan

Ding

et al. 2022

Plasma Sci. Technol.

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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 mN. 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-1350PM was defined, which serves as a reference for the optimization design of Hall thruster with large height-radius ratio. The short-channel 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.

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Section: Simulation Results and Analysismentioning

confidence: 99%

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

Fan

Ding

et al. 2022

Plasma Sci. Technol.

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“…The mass utilization efficiency (h m ) is an important parameter to evaluate the design of HT and represents the percentage of neutral atoms converted to ions, which is expressed in equation (6) [23,25].…”

Section: Fc Measurement Resultsmentioning

confidence: 99%

“…When r>10d (r and d represent the distance between the entrance hole of the probe and the exit plane of the thruster, and outer diameter of the thruster exit cross-section), the plasma plume can be considered to originate from the center of the thruster exit plane (a point source) [23]. The total ion current [24,25] is therefore equal to the integral over the ICD j i hemisphere, i.e.…”

Section: Plasma Diagnostic System (Pds)mentioning

confidence: 99%

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The far-field plasma characteristics of LHT40 low-power Hall thruster for commercial aerospace applications

Chen¹,

Zuo²,

Gao³

et al. 2021

Plasma Sci. Technol.

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To achieve a better insight into the far-field plasma spatial distribution and evolution characteristics of the 300 W class low-power Hall thruster (LHT) for commercial aerospace applications, a dedicated and integrated plasma diagnostic system composed of seventeen Faraday cups (FC) and two triple Langmuir probes (TLP) is established to investigate the timeaveraged in situ spatial distribution characteristics of far-field ions and electrons. The ion current density (ICD), plasma potential, plasma density, and electron temperature at 1000 mm downstream of 300 W class LHT for commercial aerospace applications in the azimuthal angle range of −90°to 90°were investigated under the conditions of different anode mass flow rates and discharge voltages. The results demonstrated that ICD, beam divergence angle, and mass utilization efficiency increased with increasing anode mass rate. The double-wings phenomenon was observed in the spatial distribution of ICD at large angles from the thruster axis, which is attributed to charge exchange collisions at increasing vacuum backpressure. The plasma electron temperature, electron density, and plasma potential parameters derived from the TLP decreased rapidly in the angle range from 0°to 30°and did not exhibit significant variations above 30°, which was also in good agreement with the results of the measured divergence angle of the FC. The discrepancy of average ion speed was calculated. The maximum error is better than 31.5% which checks the consistency between the TLP's results and that of FC to some extent.

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“…Lafleur et al studied transport effects of the electron drift instability in Hall-effect Thrusters [33]. Fan et al studied the effects of the peak magnetic field position on Hall thruster discharge characteristics [34]. Sekine et al investigated the spatially and temporally resolved ion flow measurements inside the plasma source of an inductive radio frequency plasma thruster [35].…”

Section: Oscillations and Instabilities In Hall Thrustersmentioning

confidence: 99%

Numerical Investigations of Electromagnetic Oscillations and Turbulences in Hall Thrusters Using Two Fluid Approach

Singh¹,

Vidhani²,

Tyagi³

2022

Plasma Science and Technology

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The first part of the contributed chapter discuss the overview of electric propulsion technology and its requirement in different space missions. The technical terms specific impulse and thrust are explained with their relation to exhaust velocity. The shortcoming of the Hall thrusters and its erosion problems of the channel walls are also conveyed. The second part of the chapter discuss the various waves and electromagnetic instabilities propagating in a Hall thruster magnetized plasma. The dispersion relation for the azimuthal growing waves is derived analytically with the help of magnetohydrodynamics theory. It is depicted that the growth rate of the instability increases with magnetic field, electron drift velocity and collisional frequency, whereas it is decreases with the initial drift of the ions.

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Effects of the peak magnetic field position on Hall thruster discharge characteristics

Cited by 11 publications

References 22 publications

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

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

The far-field plasma characteristics of LHT40 low-power Hall thruster for commercial aerospace applications

Numerical Investigations of Electromagnetic Oscillations and Turbulences in Hall Thrusters Using Two Fluid Approach

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