Numerical study of a hollow cathode neutraliser by means of a zero-dimensional plasma model

Gurciullo, Antonio; Fabris, Andrea Lucca; Potterton, Thomas

doi:10.1016/j.actaastro.2020.05.006

Cited by 12 publications

(11 citation statements)

References 28 publications

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“…The PSAC-KE cathode is an open-end emitter cathode, hence, a double sheath may appear at the keeper orifice location, while the dynamics of the plasma environment in the emitter-keeper gap is yet to be studied. A reduction in the double sheath potential, as well as in the overall plasma resistance, can explain the trend of the discharge impedance [51]. The positive discharge impedance is observed at low mass flow rates.…”

Section: Cathode Standalone Operation and Discharge Mode Evaluationmentioning

confidence: 90%

A low-current LaB₆ open-end knife-edge emitter hollow cathode for low-power Hall thrusters

Potrivitu

2021

Plasma Sources Sci. Technol.

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Heated thermionic cathodes based on LaB 6 emitters are known to consume a relatively large amount of power during the heating part of the ignition phase. Miniaturized electric propulsion systems, and in particular low-power Hall thrusters, rely on the operation of self-sustained cathodes at low-current emission, typically below 1 A. At PSAC/SPC, an open-end knife-edge LaB 6 emitter hollow cathode was developed and tested, denoted herein as the PSAC-KE cathode. Here, a detailed description of the new model's design and comparison to the older version, the PSAC cathode, is included. Electrostatic simulations suggested that the open-end emitter geometry allowed for an enhanced electric field within the emitter region during cathode startup and steady-state operation as compared to the orificed emitter PSAC cathode. The PSAC-KE cathode's thermal management was improved based on iterative thermal simulations driven by different cathode geometries and various combinations of materials. The new cathode was tested with xenon in diode mode with an external anode and triode mode with the external anode and the keeper electrode. Furthermore, results from the coupling tests with a low-power Hall thruster are presented. Cathode performance was monitored over a range of anode current from 0.1 to 1 A, mass flow rates from 0.057 to 0.3 mg s −1 and keeper current of 0.05, 0.1, and 0.15 A. The cathode's thermal design was assessed with thermocouple measurements and compared with thermal simulations and results obtained for the PSAC cathode. The preliminary tests showed that the PSAC-KE cathode achieved ignition at low heating power below 35 W, self-sustained operation at 1 A when in standalone mode, and < 1 A when against a low-power Hall thruster.

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Section: Cathode Standalone Operation and Discharge Mode Evaluationmentioning

confidence: 90%

A low-current LaB₆ open-end knife-edge emitter hollow cathode for low-power Hall thrusters

Potrivitu

2021

Plasma Sources Sci. Technol.

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“…Using iterative methods where plasma properties are averaged, the plasma model solves conservation equations for mass, current, and power in two distinct areas -the insert and orifice regions. A full description of the model, including its core equations and computational sequence as well as a preliminary validation with respect to experimental data, is provided in [2]; here, we report a general overview and a summary of the key features. This model was previously exploited in a conventional hollow cathode neutraliser development at SSC.…”

Section: Zero-dimensional Plasma Model Simulationsmentioning

confidence: 99%

“…A zero-dimensional plasma model, previously developed at the Surrey Space Centre [2], is used to perform a numerical investigation exploring different geometrical configurations and operating regimes in As of late 2022, due to global supply chain limitations, the price of xenon per kilogram can be approximated to almost 9000 $/kg [5], while krypton is approximately four times cheaper than xenon. Despite being cheaper ($/kg) than xenon, krypton's lower atomic mass and higher ionisation potential may affect system performance.…”

Section: Introductionmentioning

confidence: 99%

Development of a Modular Hollow Cathode for Ground Testing of Plasma Thrusters

Ahmed

Karadag

Masillo

et al. 2023

Preprint

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“…Numerical simulating is another useful tool to better understand the plasma behaviors inside the hollow cathode. The modeling method of hollow cathode mainly includes a fluid model based on the continuum assumption [28][29][30][31] and kinetic approach, which treats plasma as individual particles [32,33]. Cao employed the particle-in-cell/Monte Carlo collisions (PIC/MCC) method to investigate the plasma parameters and power deposition on the different cathode walls [34,35].…”

Section: Introductionmentioning

confidence: 99%

Plasma behavior of a low current orificed hollow cathode using krypton propellant for electric thruster applications

Liu

Wang

et al. 2023

J. Phys. D: Appl. Phys.

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As a fundamental component, hollow cathode has been widely used in electric thruster applications. Krypton has be-come one of the ideal alternative propellant for hollow cathode due to its economy thus it is vital to understand the basic physical process of the discharge of Krypton-fed hollow cathode. This study set out to establish a two-dimensional fluid model coupled with the equations for gas flow and heat transfer allowing to obtain the self-consistent description of the cathode discharge. The anomalous collision term based on the formulations of Sagdeev and Galeev is considered in this model. The model is validated by comparing the simulated and measured plasma characteristic parameters and reasonable agreement is reached. The findings show that the discharge of the Krypton-fed hollow cathode is character-ized by the lower plasma density, higher electron temperature, and higher spatial electric potential compared with that of Xenon-fed hollow cathode and tends to present a higher plasma density in the cathode plume region when it is operat-ing with the diode configuration. The double layer formed at the keeper orifice is an important factor for the low elec-tron temperature distribution which is greatly affected by the keeper current. These findings add to our understanding of plasma behavior in the discharge of a low current Krypton-fed hollow cathode and support further development of cred-ible Krypton-fed hollow cathode.

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Numerical study of a hollow cathode neutraliser by means of a zero-dimensional plasma model

Cited by 12 publications

References 28 publications

A low-current LaB₆ open-end knife-edge emitter hollow cathode for low-power Hall thrusters

A low-current LaB₆ open-end knife-edge emitter hollow cathode for low-power Hall thrusters

Development of a Modular Hollow Cathode for Ground Testing of Plasma Thrusters

Plasma behavior of a low current orificed hollow cathode using krypton propellant for electric thruster applications

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Numerical study of a hollow cathode neutraliser by means of a zero-dimensional plasma model

Cited by 12 publications

References 28 publications

A low-current LaB6 open-end knife-edge emitter hollow cathode for low-power Hall thrusters

A low-current LaB6 open-end knife-edge emitter hollow cathode for low-power Hall thrusters

Development of a Modular Hollow Cathode for Ground Testing of Plasma Thrusters

Plasma behavior of a low current orificed hollow cathode using krypton propellant for electric thruster applications

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A low-current LaB₆ open-end knife-edge emitter hollow cathode for low-power Hall thrusters

A low-current LaB₆ open-end knife-edge emitter hollow cathode for low-power Hall thrusters