Effect of magnetic field configuration on the multiply charged ion and plume characteristics in Hall thruster plasmas

Kim, Holak; Lim, Yong‐Kon; Choe, Wonho; Park, Sanghoo; Seon, Jongho

doi:10.1063/1.4918654

Cited by 28 publications

(25 citation statements)

References 20 publications

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“…The design of a CHT leads potentially to smaller wall losses. Below 200 W, CHT have performances similar to conventional HT with a higher propellant utilization and larger fraction of multiply-charged ions [125].…”

Section: Variations Of the Hall Thrustermentioning

confidence: 91%

Electric propulsion for satellites and spacecraft: established technologies and novel approaches

Mazouffre

2016

Plasma Sources Sci. Technol.

429

263

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This contribution presents a short review of electric propulsion technologies for satellites and spacecraft. Electric thrusters, also termed ion or plasma thrusters, deliver a low thrust level compared to their chemical counterparts, but they offer significant advantages for in-space propulsion as energy is uncoupled to the propellant, therefore allowing for large energy densities. Although the development of EP goes back to the 1960's, the technology potential has just begun to be fully exploited because of the increase in the available power aboard spacecrafts, as demonstrated by the very recent appearance of all-electric communication satellites. This article first describes the fundamentals of EP: momentum conservation and the ideal rocket equation, specific impulse and thrust, figures of merit and a comparison with chemical propulsion. Subsequently, the influence of the power source type and characteristics on the mission profile is discussed. Plasma thrusters are classically grouped into three categories according to the thrust generation process: electrothermal, electrostatic and electromagnetic devices. The three groups, along with the associated plasma discharge and energy transfer mechanisms, are presented via a discussion of long-standing technologies like arcjet thrusters, MPD thrusters, pulsed plasma thrusters, ion engines as well as Hall thrusters and variants. More advanced concepts and new approaches for performance improvement are discussed afterwards: magnetic shielding and wall-less configurations, negative ion thrusters, and plasma acceleration with a magnetic nozzle. Finally, various alternative propellant options are analyzed and possible research paths for the near future are examined.

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Section: Variations Of the Hall Thrustermentioning

confidence: 91%

Electric propulsion for satellites and spacecraft: established technologies and novel approaches

Mazouffre

2016

Plasma Sources Sci. Technol.

429

263

View full text Add to dashboard Cite

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“…1(a), which is a typical cylindrical Hall thruster. Details can be found in previous papers [11,13]. The discharge channel is 50 mm in diameter and 24 mm in depth.…”

Section: Methodsmentioning

confidence: 99%

“…The schematic diagram of the Hall thruster used for the study is illustrated in figure 1(a), which is a typical cylindrical Hall thruster. Details can be found in previous papers [11,13]. The discharge channel is 50 mm in diameter and 24 mm in depth.…”

Section: Methodsmentioning

confidence: 99%

Structure of the ion acceleration region in cylindrical Hall thruster plasmas

Doh¹,

Kim²,

Lee³

et al. 2022

J. Phys. D: Appl. Phys.

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We investigated the structure of the ion acceleration region and the shape of the ion velocity distribution function in cylindrical Hall thruster plasmas, using laser-induced fluorescence spectroscopy on Xe II metastable ions. On the thruster axis, the acceleration front is located deeper than a half-length of the discharge channel length, and the acceleration region reaches up to 3 times the discharge channel length (several centimeters) away from the channel exit, regardless of the discharge condition. It is noteworthy that ion acceleration mostly (more than 70%) takes place outside the discharge channel. The ion velocity distribution function is close to a single Gaussian inside the discharge channel. It however becomes substantially asymmetric when moving downstream. Double Gaussian distributions including cold and hot ion groups was in good agreement with the measured ion velocity distributions downstream with an R-squared greater than 0.995.

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“…Acceleration of charged ions using static electric fields (Wilbur, Rawlin & Beattie 1998; Tajmar & Wang 2000; Kim et al. 2005; Wirz & Goebel 2008; Ortega & Mikellides 2016) and current-carrying quasi-neutral plasmas using electromagnetic Lorentz forces (Paccani, Chiarotti & Deininger 2015; Ichihara et al. 2016) are types of electrostatic and electromagnetic acceleration, respectively.…”

Section: Introductionmentioning

confidence: 99%

“…There is not significant plasma ionization or an electromagnetic field to accelerate the plasma. Acceleration of charged ions using static electric fields (Wilbur, Rawlin & Beattie 1998;Tajmar & Wang 2000;Kim et al 2005;Wirz & Goebel 2008;Ortega & Mikellides 2016) and current-carrying quasi-neutral plasmas using electromagnetic Lorentz forces (Paccani, Chiarotti & Deininger 2015;Ichihara et al 2016) are types of electrostatic and electromagnetic acceleration, respectively. Electric propulsion that employs multiple acceleration mechanisms is called a mixed-type system.…”

Section: Introductionmentioning

confidence: 99%

Performance investigation of a high-temperature and power Hall-effect electric propulsion

Lu²,

Wang³

et al. 2019

J. Plasma Phys.

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This paper discusses a detailed computational analysis that illustrated the influences of the magnetic field and external potential on the performance of a high-temperature Hall-effect electric thruster. Uniform and non-uniform magnetic field configurations were examined. The Lorentz force in the $x$ direction, acting on the plasma, was shown to substantially enhance the flow velocity in the non-uniform magnetic field, which indicated that the non-uniform magnetic field was more suitable for Hall-effect electromagnetic acceleration. The static temperature increased with the external potential, especially near the region of cathode. This increment in gas temperature, together with the effect of the Lorentz force, results in the enhancement of the velocity at the front and back of the cathode. However, the Mach number and gas density decreased due to static temperature increases caused by the conversion of more electric power into internal energy. The thrust increased eventually with the increase of the average exit velocity.

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Effect of magnetic field configuration on the multiply charged ion and plume characteristics in Hall thruster plasmas

Cited by 28 publications

References 20 publications

Electric propulsion for satellites and spacecraft: established technologies and novel approaches

Electric propulsion for satellites and spacecraft: established technologies and novel approaches

Structure of the ion acceleration region in cylindrical Hall thruster plasmas

Performance investigation of a high-temperature and power Hall-effect electric propulsion

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