Energy model and mechanisms of acceleration layer formation for Hall thrusters

Baranov, Vladimir; Nazarenko, Yu. S.; Petrosov, V. A.; Vasin, A. I.; Yashnov, Yu. M.

doi:10.2514/6.1997-3047

Cited by 8 publications

(8 citation statements)

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“…The ion current lost to the dielectric walls is ≈15% of the ion current on the FS boundary. This value is similar to the ratio obtained in conventional medium-power Hall thrusters of 10% [30]. The lifetime of the thruster is dependent on the ratio of the dielectric wall thickness to the ion current density near the walls.…”

Section: Two-dimensional Effectssupporting

confidence: 85%

Investigation of two discharge configurations in the CAMILA Hall thruster by the particle-in-cell method

Kronhaus

Kapulkin

Guelman

et al. 2012

Plasma Sources Sci. Technol.

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The CAMILA (co-axial magneto-isolated longitudinal anode) concept was introduced to improve the ionization efficiency in low-power Hall thrusters. With relatively large coaxial anode surfaces and longitudinal magnetic strength, the CAMILA represents a significant departure from conventional Hall thrusters. In order to investigate the physical processes inside the CAMILA thruster, a two-dimensional particle-in-cell simulation of the thruster channel is used. The discharge parameters are analysed in two magnetic configurations: simplified CAMILA with a conventional magnetic field and full CAMILA with strengthened longitudinal component of the magnetic field. The simulation is fully kinetic with electrons, ions and gas atoms (xenon) represented as particles. Electron-neutral interactions are included together with particle-boundary interactions such as recombination and secondary emission. In addition, dielectric boundaries float and the cathode is represented as a free-space boundary, emitting electrons to satisfy quasi-neutrality on its surface. The high anode efficiency, observed in experiments, can be explained by several mechanisms found in this work. In the simplified case (magnetic configuration similar to the experiments) a focusing potential is created near the anode-dielectric boundary that directs ions away from the walls. It is created due to a combination of anode placement, in parallel with the channel, penetration of the plasma inside the anode cavity and the shape of magnetic force lines. Simulated steady-state results show good agreement with experimental measurements. In the full CAMILA case we demonstrate that the ionization region is found in the anode cavity. The electric field inside the anode cavity is substantial and it is directed towards the anode cavity centreline. Electrons are heated sufficiently to reach a high degree of ionization inside the anode cavity while ion currents to the anode surfaces are reduced significantly.

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Section: Two-dimensional Effectssupporting

confidence: 85%

Investigation of two discharge configurations in the CAMILA Hall thruster by the particle-in-cell method

Kronhaus

Kapulkin

Guelman

et al. 2012

Plasma Sources Sci. Technol.

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“…25 and 26 demonstrate excellent agreement with the currently accepted structure of the ionization and acceleration regions within the SPT-100 discharge chamber. Baranov et al 15 have recently developed a comprehensive 15 model of the acceleration layer formation within the Hall thruster. This model was used to predict plasma parameters such as electron temperature, plasma density, collision frequencies, and electric field within the acceleration region of a Hall thruster very similar to the SPT-100.…”

Section: B Ion Temperaturementioning

confidence: 99%

Ion-Energy Diagnostics in an SPT-100 Plume from Thrust Axis to Backflow

King

Gallimore

2004

Journal of Propulsion and Power

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Of primary concern with the integration of Hall thrusters on conventional satellite designs is the possible damaging effect of high-energy exhaust ions impinging upon spacecraft surfaces. This paper reports on measurements of plasma ion-energy distributions within the plume of an SPT-100 Hall thruster using a custom-designed molecular beam mass spectrometer. With this instrument ion energy was measured over a complete 360-deg circumference about the thruster at 0.5-m radius from the exit plane and over a total inclusive arc of 260 deg at 1.0-m radius. These data uncovered the existence of high-energy ions departing the thruster at angles exceeding 90 deg from the thrust vector and continuing well into the backflow region of the plume. Through an analysis of the energy structure the evidence of charge-exchange collisions occurring between plume ions and background neutrals was documented; such collisions produced anomalous distributions of ions having voltages greater than that applied to the thruster discharge.

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“…For example, the azimuthal uniformity of the number density at the propellant distributor exit plane has been studied in detail [11][12][13] as an important parameter to obtain efficient performance of the thruster.…”

Section: A Lif Velocimetry In Xeimentioning

confidence: 99%