Application of hollow anodes in a Hall thruster with double-peak magnetic fields

Ding, Yongjie; Sun, Haonan; Li, Peng; Wei, Liqiu; Su, Haijun; Peng, Wuji; Li, Hong; Yu, Daren

doi:10.1088/1361-6463/aa7bbf

Cited by 24 publications

(13 citation statements)

References 20 publications

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“…The simulation and experimental results indicate the indented U-shape hollow anode can further improve the thrust, specific impulse, and efficiency. [33][34][35] Moreover, two lower-power Hall thrusters designed by the Harbin Institute of Technology with power levels of 10-20 W and 50-100 W, using two permanent magnet rings, yielded also quite high anode efficiency at preliminary tests. In addition, 1.35 kW and 5 kW largerpower Hall thrusters using a permanent magnet have been designed and tested at Harbin Institute of Technology, providing a maximum efficiency of up to 65%.…”

Section: Coaxial Hall Thrusters With Permanent Magnetsmentioning

confidence: 98%

“…27 With the aim of improving the performance and lifetime of lower power Hall thrusters, Harbin Institute of Technology has done some research work on the channel wall material 28 and on anode design. [33][34][35] As the ionization occurs in the channel and acceleration occurs in the plume, the simulation and experimental results indicate that maximum electron temperature can be found in the plume zone, while the electron temperature in the channel is relatively low. The secondary electron emission yield of the channel material will have a small but measurable effect on the performance of the thruster, which was verified experimentally.…”

Section: Coaxial Hall Thrusters With Permanent Magnetsmentioning

confidence: 99%

“…Recently, Harbin Institute of Technology designed a cylindrical permanent-magnet Hall thruster with a low power of 50-100 W. 53 The magnetic field distribution in the channel is guided by the magnetically insulated anode, altering the intersection status of the magnetic field line passing through the anode and the wall.…”

Section: Miniaturized Cylindrical Hall Thrustersmentioning

confidence: 99%

“…The design relies upon a two-peak magnetic field topology obtained with permanent magnets only and an extended anode. 27,33 This unconventional design can be seen as a hybrid approach between the MS and WL concepts, as the discharge is largely outside of the chamber and walls are magnetically protected from the charged-particle flux. Numerous works reveal a high thrust level and efficiency around 30% at low power.…”

Section: -63mentioning

confidence: 99%

See 3 more Smart Citations

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

Levchenko

Bazaka

Ding

et al. 2018

Applied Physics Reviews

Self Cite

267

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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Section: Coaxial Hall Thrusters With Permanent Magnetsmentioning

confidence: 98%

Section: Coaxial Hall Thrusters With Permanent Magnetsmentioning

confidence: 99%

Section: Miniaturized Cylindrical Hall Thrustersmentioning

confidence: 99%

Section: -63mentioning

confidence: 99%

See 2 more Smart Citations

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

Levchenko

Bazaka

Ding

et al. 2018

Applied Physics Reviews

Self Cite

267

104

View full text Add to dashboard Cite

show abstract

“…[19][20][21][22][23] However, novel materials are urgently needed to build the most advanced, miniaturized spacecraft. Electric propulsion is very attractive and could replace cold gas propulsion and chemical propulsion due to favorable parameters, such as high specific impulse, availability of miniaturized versions, and a wide range of applications.…”

Section: Introductionmentioning

confidence: 99%

3D‐Printed Multilayered Reinforced Material System for Gas Supply in CubeSats and Small Satellites

et al. 2019

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Further development of the near-Earth satellite infrastructure as well as plans for colonization of the Moon and Mars require innovative materials and technologies to produce efficient space assets capable of active functioning for several years. Therefore, the development of compact and efficient devices has bloomed exponentially. Critical components of such devices, propulsion systems that include thrusters, and feed and power systems, have to be efficient and compact. Moreover, these systems shall be simple and cheap, to satisfy the need for thousands of small satellites planned to be launched in the near future. Herein, the design of a 3D-printed, reinforced multilayered material system for gas supply to be used in CubeSats and small satellites of a 1U (10 Â 10 Â 11.3 cm) form factor is described. The main objective of the system is to provide 0.1 standard cubic centimeter per minute (sccm) of propellant to the thruster. To achieve that, a material system is designed for a propellant tank of %50 Â 100 mm.

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Particle‐in‐cell simulation of the effect of curved magnetic field on wall bombardment and erosion in a hall thruster

Liu

Hu³

et al. 2019

Contributions to Plasma Physics

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A curved, convex towards the channel bottom magnetic field is an important feature of an advanced Hall thruster that allows confining the plasma flow in the channel center, reducing the divergence angle of the ejected ion beam, and improving the discharge performance. In this article, the discharge behaviour of a Hall thruster in magnetic fields with different degrees of curvature is simulated with a particle‐in‐cell numerical method, and the effect of curved magnetic field on the ion bombardment and wall erosion and the associated mechanisms are studied and analysed. The results show that, as the curvature of the magnetic field increases, the propellant ionization becomes more confined at the channel center, the potential drop inside the channel decreases, and the acceleration region shifts outside the channel, which lead to the attenuation of the ion energy bombarding the wall and the deviation of the bombardment angle from the optimal sputtering angle. Conversely, the ion flux bombarding the wall near the channel exit increases. Nevertheless, the bombardment energy and angle are the dominant factors for the wall erosion, and the wall erosion rate clearly decreases with the increasing curvature of the magnetic field. These findings are closely related to the behaviour of electron conduction under a curved magnetic field; the relevant mechanisms are clarified in this article.

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Application of hollow anodes in a Hall thruster with double-peak magnetic fields

Cited by 24 publications

References 20 publications

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

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

3D‐Printed Multilayered Reinforced Material System for Gas Supply in CubeSats and Small Satellites

Particle‐in‐cell simulation of the effect of curved magnetic field on wall bombardment and erosion in a hall thruster

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