Development of a cathode for low-power Hall Effect Thruster

Panelli, Mario; Battista, Francesco; Smoraldi, Antonio; Fragiacomo, Manrico

doi:10.2514/6.2021-3387

Cited by 2 publications

(5 citation statements)

References 7 publications

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“…Particularly, the electron-neutral cross section has been updated in order to include only elastic collisions as suggested by Wordingham et al [14] and to take into account the most recent experimental data, a fit of which is proposed in Ref. [13].…”

Section: Definition and Assumptionsmentioning

confidence: 99%

“…The following subsections recall the equations presented in Ref. [13] and used to model the plasma in the three regions in which cathode's internal volume has been divided.…”

Section: Plasma Model Equationsmentioning

confidence: 99%

“…and the fit for the Maxwellian Average elastic electron-neutral cross section ([m 2 ]) proposed in Ref. [13] for Xenon is:…”

Section: Orificementioning

confidence: 99%

“…Also the Italian Aerospace Research Centre (CIRA) has developed its own design and analysis tools for Xenon fed OHCs (named PlasMCat) [13], that is based on Albertoni's et al model [6], whose plasma equations are corrected according to the suggestion by Wordingham et al [14] and cathode's internal pressure is computed by means of the empirical formula proposed by Taunay et al [15]. Moreover a proper plasma model is included for the cathode-keeper gap.…”

Section: Introductionmentioning

confidence: 99%

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Solution of Orifice Hollow Cathode Plasma Model Equations by Means of Particle Swarm Optimization

Coppola,

Panelli,

Battista

2024

Preprint

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Orificed Hollow Cathodes are electric devices necessary for the functioning of common plasma thrusters for space applications. From their reliability mainly depends the success of a spacecraft’s mission equipped by electric propulsion. The development of plasma models is crucial in the evaluation of plasma properties within the cathodes that are difficult to measure due to the small dimensions. Many models, based on non-linear system of plasma equations, have been proposed in the open literature. These are solved commonly by means of iterative procedures. This paper investigates the possibility to solve them by means of Particle Swarm Optimization method. The results of the validation tests confirm the expected trends for all the unknowns; the confidence bound of the discharge current as function of mass flow rate is very narrow (2÷5V), moreover the results match very well the experimental data except at the lowest mass flow rate (0.08mg/s) and discharge current (1A), where the computations underpredict the discharge current to the utmost by 40%; the highest data dispersion regards the plasma density in the emitter region (± 20 % of the average value) and the wall temperatures (± 50K respect to the average values) of orifice and insert; those of the others variables are very tiny.

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Section: Definition and Assumptionsmentioning

confidence: 99%

“…The following subsections recall the equations presented in Ref. [13] and used to model the plasma in the three regions in which cathode's internal volume has been divided.…”

Section: Plasma Model Equationsmentioning

confidence: 99%

“…and the fit for the Maxwellian Average elastic electron-neutral cross section ([m 2 ]) proposed in Ref. [13] for Xenon is:…”

Section: Orificementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Solution of Orifice Hollow Cathode Plasma Model Equations by Means of Particle Swarm Optimization

Coppola,

Panelli,

Battista

2024

Preprint

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“…Three different density cases correspond to different magnitudes of current, the n 0 = 10 19 m −3 case leads to a current about 0.27 A, which is in the range for the micro-thrusters of the cubestar [34]; the n 0 = 10 20 m −3 case leads to a current about 2.7 A, which is within the range for low-orbit satellites, geosynchronous orbit satellites, large and medium-sized communication satellites [35]; the n 0 = 10 21 m −3 case can reach a current about 27 A, which is within the range for high power missions [36], such as space cargo transportation, manned deep space exploration, etc.…”

Section: Effects Of the Plasma Number Densitymentioning

confidence: 99%

Electromagnetic particle-in-cell simulation on self-induced magnetic field by hollow cathode discharge

Wang,

Meng,

Zhao

et al. 2023

Plasma Sources Sci. Technol.

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Strong electron current density exits in hollow cathodes, but former numerical studies tend to only consider its electrostatic aspect and ignore its electromagnetic nature, due to the complex physics and the large computational cost. Among all the electromagnetic effects in hollow cathodes, the azimuthal magnetic field induced by the electron current plays the key role. In this work, for the first time fully kinetic particle-in-cell (PIC) simulations are conducted to study the induced magnetic field and relevant electromagnetic effects in hollow cathodes. It is found that the electron-ion instability could cause a significant drop of the induced magnetic field in a fraction of nanosecond. When the magnitude of the induced magnetic field is strong, its perturbation would disturbs the electron current density, and these mechanisms can only be captured by electromagnetic simulations.

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Development of a cathode for low-power Hall Effect Thruster

Cited by 2 publications

References 7 publications

Solution of Orifice Hollow Cathode Plasma Model Equations by Means of Particle Swarm Optimization

Solution of Orifice Hollow Cathode Plasma Model Equations by Means of Particle Swarm Optimization

Electromagnetic particle-in-cell simulation on self-induced magnetic field by hollow cathode discharge

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