Control of the electric-field profile in the Hall thruster

Fruchtman, A.; Fisch, Nathaniel J.; Raitses, Yevgeny

doi:10.1063/1.1343508

Cited by 79 publications

(54 citation statements)

References 17 publications

(9 reference statements)

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“…The important implications of this work include: one, that the theoretical modeling of thruster processes need to account better for the sheath physics in the presence of secondary electron emission, and particularly for kinetic effects such as the depletion of the electron EDF; and, two, that in light of the effects on the electron temperature, by adjusting voltages 40,41 or material properties 42 where V is the probe potential with respect to the surrounding plasma, N e is the electron density in the unperturbed plasma, and A p is the probe collection area and m is the electron mass. This current is completely independent of the sheath size, which is not the case for the ion current to the attracting probe.…”

Section: Discussionmentioning

confidence: 99%

Space charge saturated sheath regime and electron temperature saturation in Hall thrusters

et al. 2005

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Secondary electron emission in Hall thrusters is predicted to lead to space charge saturated wall sheaths resulting in enhanced power losses in the thruster channel.Analysis of experimentally obtained electron-wall collision frequency suggests that the electron temperature saturation, which occurs at high discharge voltages, appears to be caused by a decrease of the Joule heating rather than by the enhancement of the electron energy loss at the walls due to a strong secondary electron emission.2

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Section: Discussionmentioning

confidence: 99%

Space charge saturated sheath regime and electron temperature saturation in Hall thrusters

et al. 2005

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“…3,4 The use of segmented electrodes along the thruster channel can provide additional control of the plasma flow in a Hall thruster. [5][6][7][8] The plume narrowing effect measured for molybdenum and carbon electrodes at low discharge voltages (≤300 V) 6,7 was attributed to the reduced voltage drop outside the channel exit. 6 This effect on the voltage drop has been attributed to the lower secondary electron emission (SEE) of the electrode materials compared to that of a boron nitride ceramic and due to a shorting of the plasma electric field through the conductive electrodes.…”

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confidence: 99%

Operation of a segmented Hall thruster with low-sputtering carbon-velvet electrodes

Raitses¹,

Staack²,

Dunaevsky³

et al. 2006

Journal of Applied Physics

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Carbon fiber velvet material provides exceptional sputtering resistance properties exceeding those for graphite and carbon composite materials. A 2kW Hall thruster with segmented electrodes made of this material was operated in the discharge voltage range of 200–700V. The arcing between the floating velvet electrodes and the plasma was visually observed, especially, during the initial conditioning time, which lasted for about 1h. The comparison of voltage versus current and plume characteristics of the Hall thruster with and without segmented electrodes indicates that the magnetic insulation of the segmented thruster improves with the discharge voltage at a fixed magnetic field. The observations reported here also extend the regimes wherein the segmented Hall thruster can have a narrower plume than that of the conventional nonsegmented thruster.

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“…It was found that, like in some other models, 10 at large temperatures all of the propellant is ionized in a very short region near the anode, and at the smaller temperatures the propellant utilization,…”

Section: Solutionmentioning

confidence: 99%

Hall Thruster Modeling with a Given Temperature Profile

Dorf

Semenov

Raitses

et al. 2002

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A quasi one-dimensional steady-state model of the Hall thruster is presented. For given mass flow rate, magnetic field profile and discharge voltage the unique solution can be constructed, assuming that the thruster operates in one of the two regimes: with or without the anode sheath. It is shown that for a given temperature profile the applied discharge voltage uniquely determines the operating regime: for discharge voltages greater than a certain value, the sheath disappears. That result is obtained over a wide range of incoming neutral velocities, channel lengths and widths and cathode plane locations. A good correlation between the quasi 1-D model and experimental results can be achieved by selecting an appropriate temperature profile. We also show how the presented model can be used to obtain a two-dimensional potential distribution.

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Control of the electric-field profile in the Hall thruster

Cited by 79 publications

References 17 publications

Space charge saturated sheath regime and electron temperature saturation in Hall thrusters

Space charge saturated sheath regime and electron temperature saturation in Hall thrusters

Operation of a segmented Hall thruster with low-sputtering carbon-velvet electrodes

Hall Thruster Modeling with a Given Temperature Profile

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