Critical assessment of a two-dimensional hybrid Hall thruster model: Comparisons with experiments

Bareilles, J.; Hagelaar, Gerjan; Garrigues, Laurent; Boniface, C.; Boeuf, Jean-Pierre; Gascon, Nicolas

doi:10.1063/1.1719022

Cited by 121 publications

(112 citation statements)

References 12 publications

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“…This low-energy peak was also observed in simulations of the Hall thruster using a two-dimensional hybrid (particle-in-cell/fluid) model and was attributed, in one case, to the dynamic shift between the ionization region and the acceleration region during the breathing mode cycle [26], and in another case to charge-exchange collisions between the ions in the beam and neutral xenon emitted by the hollow cathode [27]. In our measurements, this low-energy peak may also reflect the presence of charge-exchange collisions with nonionized xenon coming from the anode, because it appears to be weaker for operation at lower anode flow rates.…”

Section: Ion Energy Measurementmentioning

confidence: 75%

Experimental Characterization of a Micro-Hall Thruster

Ito

Gascon

Crawford

et al. 2007

Journal of Propulsion and Power

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The operation and performance of a micro-Hall thruster are characterized. The thruster is coaxial in design, with a 0.5 mm channel width and 4 mm outer diameter. The magnetic circuit includes a samarium cobalt permanent magnet generating approximately 0.7 T at the exit plane and 1 T inside the channel. Operation with a commercial hollow cathode neutralizer is achieved in the 10-40 W power range with an anode flow rate of 0:12-0:20 mg=s of xenon. The measured thrust is in the range of 0.6-1.6 mN for an anode flow rate of 0:17-0:20 mg=s and an applied voltage of 110-275 V. Anode thrust efficiency and specific impulse are in the range of 10-15% and 300-850 s, respectively, for the same conditions. Relatively broad ion energy distributions and large beam divergence are observed from an analysis of the plume using a retarding potential analyzer and ion current probe. The discharge exhibits the characteristic Hall thruster "breathing mode" instability in the 35-70 kHz frequency range.

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Section: Ion Energy Measurementmentioning

confidence: 75%

Experimental Characterization of a Micro-Hall Thruster

Ito

Gascon

Crawford

et al. 2007

Journal of Propulsion and Power

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“…6 Particularly, the quasi-one-dimensional hybrid PIC model called HPHall developed by Fife 7 was employed and improved by different institutes because of its robustness, accuracy, and low computational cost. [8][9][10] These models were also implemented for wall erosion and lifetime simulations. [11][12][13] However, it is necessary for these fluidbased models to use quasi-neutrality and Maxwellian electron energy distribution function (EEDF) assumptions throughout the calculation domain.…”

Section: Introductionmentioning

confidence: 99%

Kinetic particle simulation of discharge and wall erosion of a Hall thruster

Cho

Komurasaki²,

Arakawa

2013

Physics of Plasmas

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The primary lifetime limiting factor of Hall thrusters is the wall erosion caused by the ion induced sputtering, which is predominated by dielectric wall sheath and pre-sheath. However, so far only fluid or hybrid simulation models were applied to wall erosion and lifetime studies in which this non-quasi-neutral and non-equilibrium area cannot be treated directly. Thus, in this study, a 2D fully kinetic particle-in-cell model was presented for Hall thruster discharge and lifetime simulation. Because the fully kinetic lifetime simulation was yet to be achieved so far due to the high computational cost, the semi-implicit field solver and the technique of mass ratio manipulation was employed to accelerate the computation. However, other artificial manipulations like permittivity or geometry scaling were not used in order to avoid unrecoverable change of physics. Additionally, a new physics recovering model for the mass ratio was presented for better preservation of electron mobility at the weakly magnetically confined plasma region. The validity of the presented model was examined by various parametric studies, and the thrust performance and wall erosion rate of a laboratory model magnetic layer type Hall thruster was modeled for different operation conditions. The simulation results successfully reproduced the measurement results with typically less than 10% discrepancy without tuning any numerical parameters. It is also shown that the computational cost was reduced to the level that the Hall thruster fully kinetic lifetime simulation is feasible. V C 2013 AIP Publishing LLC. [http://dx

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“…In fluid and hybrid fluid-particle models, some investigators impose the anomalous Bohm conductivity inside the channel, 6 while others use only the near-wall conductivity 7 or a combination of both Bohm transport and wall collisions. [8][9][10][11][12] Full particle-in-cell (PIC) simulations 13,14 reveal turbulence increasing the cross-field transport. Some theoretical studies 15,16 suggest that due to the nonMaxwellian shape of the EDF in a Hall thruster, electron-wall collisions do not make a significant contribution to cross-field transport.…”

Section: Introductionmentioning

confidence: 99%

Electron Cross-field Transport in a Low Power Cylindrical Hall Thruster

Smirnov

Raitses

Fisch³

2004

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Conventional annular Hall thrusters become inefficient when scaled to low power. Cylindrical Hall thrusters, which have lower surface-to-volume ratio, are therefore more promising for scaling down. They presently exhibit performance comparable with conventional annular Hall thrusters. Electron cross-field transport in a 2.6 cm miniaturized cylindrical Hall thruster (100 W power level) has been studied through the analysis of experimental data and Monte Carlo simulations of electron dynamics in the thruster channel. The numerical model takes into account elastic and inelastic electron collisions with atoms, electron-wall collisions, including secondary electron emission, and Bohm diffusion. We show that in order to explain the observed discharge current, the electron anomalous collision frequency ν B has to be on the order of the Bohm value, ν B ≈ω c /16. The contribution of electron-wall collisions to cross-field transport is found to be insignificant.

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Critical assessment of a two-dimensional hybrid Hall thruster model: Comparisons with experiments

Cited by 121 publications

References 12 publications

Experimental Characterization of a Micro-Hall Thruster

Experimental Characterization of a Micro-Hall Thruster

Kinetic particle simulation of discharge and wall erosion of a Hall thruster

Electron Cross-field Transport in a Low Power Cylindrical Hall Thruster

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