Performance of a low-power cylindrical hall thruster

Kurt A. Polzin; Thomas E. Markusic; Boris J. Stanojev; Amado Dehoyos; Yevgeny Raitses; Artem Smirnov; Nathaniel J. Fisch

doi:10.2514/1.28595

Performance of a low-power cylindrical hall thruster

Kurt A. Polzin, Thomas E. Markusic, Boris J. Stanojev, Amado Dehoyos, Yevgeny Raitses, Artem Smirnov, Nathaniel J. Fisch

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25 Scopus citations

Abstract

The measured performance of a cylindrical Hall thruster operating at 100W input power was reported. A cylindrical geometry Hall thruster (CHT) was developed for low power applications. It has a cylindrical geometry which is critical for electron confinement because there is a large axial gradient in magnetic field over the cylindrical part. A CHT consists of a boron nitride channel, an annular anode, two electromagnet coils, a magnetic core and the propellant Xenon gas. Gas was injected through the anode into the short annular region of the thruster. Thrust was measured using a Variable amplitude hanging pendulum with exchange range thrust stand. Finally, it was concluded that CHT can easily be scaled down as per the power requirements while the conventional Hall thrusters cannot be because of their annular geometry and magnetic field optimization problem.

Original language	English (US)
Pages (from-to)	886-888
Number of pages	3
Journal	Journal of Propulsion and Power
Volume	23
Issue number	4
DOIs	https://doi.org/10.2514/1.28595
State	Published - 2007

All Science Journal Classification (ASJC) codes

Aerospace Engineering
Fuel Technology
Mechanical Engineering
Space and Planetary Science

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10.2514/1.28595

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title = "Performance of a low-power cylindrical hall thruster",

abstract = "The measured performance of a cylindrical Hall thruster operating at 100W input power was reported. A cylindrical geometry Hall thruster (CHT) was developed for low power applications. It has a cylindrical geometry which is critical for electron confinement because there is a large axial gradient in magnetic field over the cylindrical part. A CHT consists of a boron nitride channel, an annular anode, two electromagnet coils, a magnetic core and the propellant Xenon gas. Gas was injected through the anode into the short annular region of the thruster. Thrust was measured using a Variable amplitude hanging pendulum with exchange range thrust stand. Finally, it was concluded that CHT can easily be scaled down as per the power requirements while the conventional Hall thrusters cannot be because of their annular geometry and magnetic field optimization problem.",

author = "Polzin, {Kurt A.} and Markusic, {Thomas E.} and Stanojev, {Boris J.} and Amado Dehoyos and Yevgeny Raitses and Artem Smirnov and Fisch, {Nathaniel J.}",

note = "Funding Information: This work was performed under Space Act Agreement NAS8-05791 and supported by the NASA Marshall Space Flight Center (MSFC) Technology Transfer Office. Work performed by the Princeton Plasma Physics Laboratory coauthors were partially supported by the U.S. Air Force Office of Scientific Research. We gratefully acknowledge the contributions of the MSFC technical support staff: Doug Davenport, Tommy Reid, Doug Galloway, Keith Chavers, and Rondal Boutwell. We also extend our gratitude to students Benjamin Spaun, Chris Dodson, and Jeff Gross, and to Freida Lowery in the MSFC Business Development Office.",

year = "2007",

doi = "10.2514/1.28595",

language = "English (US)",

volume = "23",

pages = "886--888",

journal = "Journal of Propulsion and Power",

issn = "0748-4658",

publisher = "American Institute of Aeronautics and Astronautics Inc. (AIAA)",

number = "4",

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T1 - Performance of a low-power cylindrical hall thruster

AU - Polzin, Kurt A.

AU - Markusic, Thomas E.

AU - Stanojev, Boris J.

AU - Dehoyos, Amado

AU - Raitses, Yevgeny

AU - Smirnov, Artem

AU - Fisch, Nathaniel J.

N1 - Funding Information: This work was performed under Space Act Agreement NAS8-05791 and supported by the NASA Marshall Space Flight Center (MSFC) Technology Transfer Office. Work performed by the Princeton Plasma Physics Laboratory coauthors were partially supported by the U.S. Air Force Office of Scientific Research. We gratefully acknowledge the contributions of the MSFC technical support staff: Doug Davenport, Tommy Reid, Doug Galloway, Keith Chavers, and Rondal Boutwell. We also extend our gratitude to students Benjamin Spaun, Chris Dodson, and Jeff Gross, and to Freida Lowery in the MSFC Business Development Office.

PY - 2007

Y1 - 2007

N2 - The measured performance of a cylindrical Hall thruster operating at 100W input power was reported. A cylindrical geometry Hall thruster (CHT) was developed for low power applications. It has a cylindrical geometry which is critical for electron confinement because there is a large axial gradient in magnetic field over the cylindrical part. A CHT consists of a boron nitride channel, an annular anode, two electromagnet coils, a magnetic core and the propellant Xenon gas. Gas was injected through the anode into the short annular region of the thruster. Thrust was measured using a Variable amplitude hanging pendulum with exchange range thrust stand. Finally, it was concluded that CHT can easily be scaled down as per the power requirements while the conventional Hall thrusters cannot be because of their annular geometry and magnetic field optimization problem.

AB - The measured performance of a cylindrical Hall thruster operating at 100W input power was reported. A cylindrical geometry Hall thruster (CHT) was developed for low power applications. It has a cylindrical geometry which is critical for electron confinement because there is a large axial gradient in magnetic field over the cylindrical part. A CHT consists of a boron nitride channel, an annular anode, two electromagnet coils, a magnetic core and the propellant Xenon gas. Gas was injected through the anode into the short annular region of the thruster. Thrust was measured using a Variable amplitude hanging pendulum with exchange range thrust stand. Finally, it was concluded that CHT can easily be scaled down as per the power requirements while the conventional Hall thrusters cannot be because of their annular geometry and magnetic field optimization problem.

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JO - Journal of Propulsion and Power

JF - Journal of Propulsion and Power

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Performance of a low-power cylindrical hall thruster

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