Fundamentals of Stationary Plasma Thruster Theory

Морозов, А. И.; Savelyev, V. V.

doi:10.1007/978-1-4615-4309-1_2

Cited by 294 publications

(219 citation statements)

References 3 publications

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“…Illustrative curves of voltage versus current characteristics measured in stable and unstable regimes for both thruster configurations are shown in Fig 14. Although the discharge current for the annular thruster in the stable regime is somewhat smaller than for the cylindrical, its ratio to the equivalent gas flow current corrected for the background pressure effect is almost 3 times higher than the corresponding ratios for large annular and cylindrical Hall thrusters, 1 .1-1.5 [1,7]. Thus, there is a significant fraction of the axial electron current in the total discharge current for both miniaturized thruster configurations.…”

Section: Thruster Operation and V-i Characteristicsmentioning

confidence: 89%

“…A significant axial electric field is established in the vicinity of the maximum radial magnetic field, typically near the thruster exhaust. The length of the acceleration region and its location relative to the magnetic field distribution depends mainly on the electron mobility and can be strongly affected by material properties of the channel walls, namely, conductivity and secondary electron emission [1]. However, a simple exchange of the channel materials, for example, from ceramic to metal, does not necessarily lead to changes in the beam divergence.…”

Section: Introductionmentioning

confidence: 99%

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Studies of Non-Conventional Configuration Closed Electron Drift Thrusters

Raitses¹,

Staack²,

Smirnov³

et al. 2001

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In this paper we review recent results obtained for segmented electrode and cylindrical Hall thrusters. A low sputtering graphite segmented electrode, placed at the exit of the annular thruster, is shown to affect the plasma potential distribution in the ceramic channel. This effect appears to be correlated with an observed plume reduction compared to a conventional, nonsegmented thruster. In preliminary experiments a 3 cm thruster was operated in the 50-200 W power range. Two operating regimes, stable and oscillating, were observed and investigated.

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Section: Thruster Operation and V-i Characteristicsmentioning

confidence: 89%

Section: Introductionmentioning

confidence: 99%

Studies of Non-Conventional Configuration Closed Electron Drift Thrusters

Raitses¹,

Staack²,

Smirnov³

et al. 2001

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“…In a conventional Hall thruster 4 , the axial electric and radial magnetic fields are applied in an annular channel. The magnetic field is large enough to lock the electrons in the azimuthal E× B drift, but small enough to leave the ion trajectories almost unaffected.…”

Section: Introductionmentioning

confidence: 99%

Parametric investigation of miniaturized cylindrical and annular Hall thrusters

Smirnov¹,

Raitses²,

Fisch³

2002

Journal of Applied Physics

118

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Conventional annular Hall thrusters become inefficient when scaled to low power. An alternative approach, a 2.6-cm miniaturized cylindrical Hall thruster with a cusp-type magnetic field distribution, was developed and studied. Its performance was compared to that of a conventional annular thruster of the same dimensions. The cylindrical thruster exhibits discharge characteristics similar to those of the annular thruster, but it has a much higher propellant ionization efficiency. Significantly, a large fraction of multicharged xenon ions might be present in the outgoing ion flux generated by the cylindrical thruster. The operation of the cylindrical thruster is quieter than that of the annular thruster. The characteristic peak in the discharge current fluctuation spectrum at 50-60 kHz appears to be due to ionization instabilities. In the power range 50-300 W, the cylindrical and annular thrusters have comparable efficiencies (15-32%) and thrusts (2.5-12 mN). For the annular configuration, a voltage less than 200 V was not sufficient to sustain the discharge at low propellant flow rates. The cylindrical thruster can operate at voltages lower than 200V, which suggests that a cylindrical thruster can be designed to operate at even smaller power. * Electronic mail: asmirnov@pppl.gov 2

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“…For a single-stage conventional Hall thruster, the electrons can gain thermal energy sufficient for ionization by diffusing towards the anode. Acquiring a relatively high electron temperature (10)(11)(12)(13)(14)(15)(16)(17)(18)(19)(20) eV), they can also escape along the magnetic field lines [1]. The use of concave magnetic field lines might reduce this defocusing effect on the ion flux [1,2].…”

Section: Introductionmentioning

confidence: 99%

“…Acquiring a relatively high electron temperature (10)(11)(12)(13)(14)(15)(16)(17)(18)(19)(20) eV), they can also escape along the magnetic field lines [1]. The use of concave magnetic field lines might reduce this defocusing effect on the ion flux [1,2]. Indeed, mostly through optimization of the magnetic field profile, state-of-the art Hall thrusters now operate with efficiencies (the ratio of the jet power to the input electric power) 50-60% and thrust densities larger than space-charge-limited ion engines [1][2][3].…”

Section: Introductionmentioning

confidence: 99%

Parametric Investigations of Non-Conventional Hall Thruster

Raitses¹,

Fisch²

2001

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Hall thrusters might better scale to low power with non-conventional geometry. A 9 cm cylindrical, ceramic-channel, Hall thruster with a cusp-type magnetic field distribution has been investigated. It exhibits discharge characteristics similar to conventional coaxial Hall thrusters, but does not expose as much channel surface. Significantly, its operation is not accompanied by large amplitude discharge low frequency oscillations.2

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Fundamentals of Stationary Plasma Thruster Theory

Cited by 294 publications

References 3 publications

Studies of Non-Conventional Configuration Closed Electron Drift Thrusters

Studies of Non-Conventional Configuration Closed Electron Drift Thrusters

Parametric investigation of miniaturized cylindrical and annular Hall thrusters

Parametric Investigations of Non-Conventional Hall Thruster

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