Optimization of a wall-less Hall thruster

Vaudolon, Julien; Mazouffre, S.; Hénaux, Carole; Harribey, Dominique; Rossi, Alberto

doi:10.1063/1.4932196

Cited by 57 publications

(35 citation statements)

References 19 publications

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“…From top to bottom: t=0μs, t=0.44μs, t=0.87μs, t=1.31μs. n e is normalized by 12 2.3 10 ⋅ cm -3 , n Xe -by 13 1.2 10 ⋅ cm -3 , P ionby 18…”

Section: Simulation Resultsmentioning

confidence: 99%

“…The ISCT200 thruster can be operated in the standard (ST) and the wall-less (WL) configurations. The wall-less configuration is a recent and original approach to decrease plasma-wall interactions, hence prolonging the thruster lifetime [12,13]. The principle is to entirely shift the ionization and acceleration regions outside the cavity.…”

Section: Isct200-wl Hall Thrustermentioning

confidence: 99%

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Rotating spoke instabilities in a wall-less Hall thruster: simulations

Matyash¹,

Schneider²,

Mazouffre³

et al. 2019

Plasma Sources Sci. Technol.

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The low-frequency rotating plasma instability (spoke) in the ISCT200 thruster operating in the wall-less configuration was simulated with a 3 dimensional PIC MCC code. In the simulations an m = 1 spoke rotating with a velocity of 6.5 km/s in the ExB direction was observed. The rotating electron density structure in the spoke is accompanied by a strongly depleted region of the neutral gas, which clearly shows that the spoke instability is of an ionization nature, similar to the axial breathing mode oscillations. In the simulation the electron cross-field transport through the spoke core was caused by diffusion in the highfrequency (4-10 MHz), short-scale (3 mm) electric field oscillations. These short-scale oscillations play a crucial role in the thruster discharge as over 70% of the electron current to the anode originates from the spoke core. The rest of the current originates from the spoke front where the electron cross-field transport toward the anode is due to the ExB drift in the spoke macroscopic azimuthal electric field.

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“…From top to bottom: t=0μs, t=0.44μs, t=0.87μs, t=1.31μs. n e is normalized by 12 2.3 10 ⋅ cm -3 , n Xe -by 13 1.2 10 ⋅ cm -3 , P ionby 18…”

Section: Simulation Resultsmentioning

confidence: 99%

Section: Isct200-wl Hall Thrustermentioning

confidence: 99%

Rotating spoke instabilities in a wall-less Hall thruster: simulations

Matyash¹,

Schneider²,

Mazouffre³

et al. 2019

Plasma Sources Sci. Technol.

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“…Electric propulsion has been identified as a promising technology for primary propulsion in deep-space scientific missions. [1][2][3] Among many types of electric propulsion engines, Hall effect thrusters stand out by its current state of the art, being developed and tested for over 50 years. 1,4 Recently, improvements and variations in those devices, like in the magnetic source, [5][6][7][8] in the wall shaping, 2,3 in the propellant gas distribution, 9 and in the number of acceleration channels, 10 have made long space travels using Hall thrusters closer to become a reality.…”

Section: Introductionmentioning

confidence: 99%

“…Therefore, a key issue in order to increase the thrust power and the overall thruster efficiency is to maximize the gas ionization by the electrons in the acceleration channel. [1][2][3][5][6][7] Most of the basic analyses of particle dynamics on Hall thrusters are based on models that consider a one dimensional electron flow. [14][15][16][17] In such a case, the electron dynamics is integrable, being characterized by the presence of periodic orbits.…”

Section: Introductionmentioning

confidence: 99%

Single electron dynamics in a Hall thruster electromagnetic field profile

Marini

Pakter

2017

Physics of Plasmas

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In this work, the single electron dynamics in a simplified three dimensional Hall thruster model is studied. Using Hamiltonian formalism and the concept of limiting curves, one is able to determine confinement conditions for the electron in the acceleration channel. It is shown that as a given parameter of the electromagnetic field is changed, the particle trajectory may transit from regular to chaotic without affecting the confinement, which allows one to make a detailed analysis of the role played by the chaos. The ionization volume is also computed, which measures the probability of an electron to ionize background gas atoms. It is found that there is a great correlation between chaos and increased effective ionization volume. This indicates that a complex dynamical behavior may improve the device efficiency by augmenting the ionization capability of each electron, requiring an overall lower electron current.

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“…The performance level of a WL ion accelerator strongly depends upon the anode geometry. In order to prevent large electron losses at the anode, a magnetic barrier must be created by making the magnetic field lines parallel to the anode surface, 68 as illustrated in Fig. 9.…”

Section: -63mentioning

confidence: 99%

Space micropropulsion systems for Cubesats and small satellites: From proximate targets to furthermost frontiers

Levchenko

Bazaka

Ding

et al. 2018

Applied Physics Reviews

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256

104

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Rapid evolution of miniaturized, automatic, robotized, function-centered devices has redefined space technology, bringing closer the realization of most ambitious interplanetary missions and intense near-Earth space exploration. Small unmanned satellites and probes are now being launched in hundreds at a time, resurrecting a dream of satellite constellations, i.e., wide, all-covering networks of small satellites capable of forming universal multifunctional, intelligent platforms for global communication, navigation, ubiquitous data mining, Earth observation, and many other functions, which was once doomed by the extraordinary cost of such systems. The ingression of novel nanostructured materials provided a solid base that enabled the advancement of these affordable systems in aspects of power, instrumentation, and communication. However, absence of efficient and reliable thrust systems with the capacity to support precise maneuvering of small satellites and CubeSats over long periods of deployment remains a real stumbling block both for the deployment of large satellite systems and for further exploration of deep space using a new generation of spacecraft. The last few years have seen tremendous global efforts to develop various miniaturized space thrusters, with great success stories. Yet, there are critical challenges that still face the space technology. These have been outlined at an inaugural International Workshop on Micropropulsion and Cubesats, MPCS-2017, a joint effort between Plasma Sources and Application Centre/Space Propulsion Centre (Singapore) and the Micropropulsion and Nanotechnology Lab, the G. Washington University (USA) devoted to miniaturized space propulsion systems, and hosted by CNR-Nanotec—P.Las.M.I. lab in Bari, Italy. This focused review aims to highlight the most promising developments reported at MPCS-2017 by leading world-reputed experts in miniaturized space propulsion systems. Recent advances in several major types of small thrusters including Hall thrusters, ion engines, helicon, and vacuum arc devices are presented, and trends and perspectives are outlined.

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Optimization of a wall-less Hall thruster

Cited by 57 publications

References 19 publications

Rotating spoke instabilities in a wall-less Hall thruster: simulations

Rotating spoke instabilities in a wall-less Hall thruster: simulations

Single electron dynamics in a Hall thruster electromagnetic field profile

Space micropropulsion systems for Cubesats and small satellites: From proximate targets to furthermost frontiers

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