Characteristics and Performances of a 100-W Hall Thruster for Microspacecraft

Mazouffre, S.; Grimaud, Lou

doi:10.1109/tps.2017.2786402

Cited by 29 publications

(13 citation statements)

References 28 publications

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“…This is a possible indirect explanation of the measured decrease in the wall and anode temperatures of only between 30 to 60 Celsius degrees passing from the US to the MS configuration [24].…”

Section: B Performance Analysismentioning

confidence: 90%

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Operation of a low-power Hall thruster: comparison between magnetically unshielded and shielded configuration

Garrigues

Santhosh

Grimaud

et al. 2019

Plasma Sources Sci. Technol.

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HAL is a multi-disciplinary open access archive for the deposit and dissemination of scientific research documents, whether they are published or not. The documents may come from teaching and research institutions in France or abroad, or from public or private research centers. L'archive ouverte pluridisciplinaire HAL, est destinée au dépôt et à la diffusion de documents scientifiques de niveau recherche, publiés ou non, émanant des établissements d'enseignement et de recherche français ou étrangers, des laboratoires publics ou privés.

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Section: B Performance Analysismentioning

confidence: 90%

“…No magnetic field optimization on that specific thruster has been performed. The ISCT-class HTs have been extensively characterized [8], [23], [24]. The axial ion velocity distribution in several key areas has been measured by LIF spectroscopy [8].…”

Section: The Isct-200 Hall Thrustermentioning

confidence: 99%

Operation of a low-power Hall thruster: comparison between magnetically unshielded and shielded configuration

Garrigues

Santhosh

Grimaud

et al. 2019

Plasma Sources Sci. Technol.

Self Cite

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“…Hall-effect thrusters are one kind of electric thrusters which uses a plasma discharge with magnetized electrons to ionize a gas and accelerate ions [8]. Figure 2 presents a schematic of a Hall-effect thruster.…”

Section: Hall-effect Thruster Technology and Exotrail's Thrustermentioning

confidence: 99%

Electric Propulsion For Small Satellites Orbit Control And Deorbiting : The Example Of A Hall Effect Thruster

Lascombes

2018

2018 SpaceOps Conference

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Electric propulsion technologies for small satellites enable their operators to develop new high delta-V missions thanks to their high specific impulse. Exotrail has developed software tools to assess the impact of low-thrust propulsion maneuvers on small satellites operation. Using these tools, two missions are analyzed in this article: very low Earth orbit station keeping, and post-launch secondary injection involving altitude change and inclination correction followed by deorbitation. Finally, the impact of the high thrust-to-power ratio provided by the Hall-effect thrusters developed by Exotrail is analyzed. This analysis is done from a customer point of view by quantifying the fuel mass and mission duration differences compared with other technologies.

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“…where e t is the total specific energy, e t ¼ e in þ B 2 2 0 , e in ¼ f p, ð ÞþV 2 2, f( p, ) is the real gas state function, which is calculated using the model in Cheng and Xia, 15 q is the thermal flux, Q rad is the radiation loss, calculated using optical thin model, 16 $ is the tensor of viscous stress, and r is the electrical conductivity.…”

Section: Plasma Fluid Modelmentioning

confidence: 99%

“…The electric thrusters are characterized by high specific impulse and long lifetime; the system design is strongly affected by the ionization and acceleration principles. Two problems appear that limit the performance of thrusters in practice: one is the space charge limit in ion thruster; 1 the other is the electrode corruption, occurring nearly in all particle emission type thrusters, 2 and the upper limit of thrust density is determined consequently. To overcome these problems, the pulsed inductive thruster (PIT) is a promising choice.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of flow properties of the pulsed inductive thruster considering plasma electrical characteristics

Cheng

Xia

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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The pulsed inductive thruster accelerates the propellant by the repulsion between inductive coil and current sheet. To accurately investigate the acceleration characteristics in the first half period of pulsed inductive discharge and the energy needed to generate effective impulse, an unsteady magnetohydrodynamics model is developed, in which the coil-plasma boundary condition is improved by plasma electrical model, and the electrical conductivity is calculated using gas kinetic method. The analysis of plasma electrical characteristics shows confining of particles in the beginning and acceleration of the current sheet after ionization process is completed, leaving behind the low-density residual plasma, with negligible contribution to the total impulse. The impulse at high voltage decreases monotonically after peak value is reached, showing effective impulse generation in the first half period, especially before the decoupling distance is reached.

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Characteristics and Performances of a 100-W Hall Thruster for Microspacecraft

Cited by 29 publications

References 28 publications

Operation of a low-power Hall thruster: comparison between magnetically unshielded and shielded configuration

Operation of a low-power Hall thruster: comparison between magnetically unshielded and shielded configuration

Electric Propulsion For Small Satellites Orbit Control And Deorbiting : The Example Of A Hall Effect Thruster

Numerical investigation of flow properties of the pulsed inductive thruster considering plasma electrical characteristics

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