Effects of cathode electron emission on Hall thruster discharge

Yevgeny Raitses; Erik Granstedt; Artem Smirnov; Enrique Merino; Nathaniel J. Fisch

Effects of cathode electron emission on Hall thruster discharge

Yevgeny Raitses, Erik Granstedt, Artem Smirnov, Enrique Merino, Nathaniel J. Fisch

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

Abstract

Low power cylindrical and annular geometry Hall thrusters are operated in a non-self-sustained regime with different thermionic cathode-neutralizers. The enhancement of the electron emission with a keeper current for the hollow cathode and with a wire heating for the filament cathode leads to a significant (up to 30%) narrowing of the plasma plume and increase of the energetic ion fraction. For the cylindrical Hall thruster, the observed variations of the plasma potential, electron temperature, and plasma density with the keeper current suggest that the electron emission from the cathode can affect the electron cross-field transport and the ionization in the thruster channel.

Original language	English (US)
Title of host publication	44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
State	Published - 2008
Event	44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit - Hartford, CT, United States Duration: Jul 21 2008 → Jul 23 2008

Publication series

Name	44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

Other

Other	44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
Country/Territory	United States
City	Hartford, CT
Period	7/21/08 → 7/23/08

All Science Journal Classification (ASJC) codes

Aerospace Engineering
Control and Systems Engineering
Space and Planetary Science
General Energy
Electrical and Electronic Engineering
Mechanical Engineering

Cite this

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title = "Effects of cathode electron emission on Hall thruster discharge",

abstract = "Low power cylindrical and annular geometry Hall thrusters are operated in a non-self-sustained regime with different thermionic cathode-neutralizers. The enhancement of the electron emission with a keeper current for the hollow cathode and with a wire heating for the filament cathode leads to a significant (up to 30%) narrowing of the plasma plume and increase of the energetic ion fraction. For the cylindrical Hall thruster, the observed variations of the plasma potential, electron temperature, and plasma density with the keeper current suggest that the electron emission from the cathode can affect the electron cross-field transport and the ionization in the thruster channel.",

author = "Yevgeny Raitses and Erik Granstedt and Artem Smirnov and Enrique Merino and Fisch, {Nathaniel J.}",

year = "2008",

language = "English (US)",

isbn = "9781563479434",

series = "44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit",

booktitle = "44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit",

note = "44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit ; Conference date: 21-07-2008 Through 23-07-2008",

}

TY - GEN

T1 - Effects of cathode electron emission on Hall thruster discharge

AU - Raitses, Yevgeny

AU - Granstedt, Erik

AU - Smirnov, Artem

AU - Merino, Enrique

AU - Fisch, Nathaniel J.

PY - 2008

Y1 - 2008

N2 - Low power cylindrical and annular geometry Hall thrusters are operated in a non-self-sustained regime with different thermionic cathode-neutralizers. The enhancement of the electron emission with a keeper current for the hollow cathode and with a wire heating for the filament cathode leads to a significant (up to 30%) narrowing of the plasma plume and increase of the energetic ion fraction. For the cylindrical Hall thruster, the observed variations of the plasma potential, electron temperature, and plasma density with the keeper current suggest that the electron emission from the cathode can affect the electron cross-field transport and the ionization in the thruster channel.

AB - Low power cylindrical and annular geometry Hall thrusters are operated in a non-self-sustained regime with different thermionic cathode-neutralizers. The enhancement of the electron emission with a keeper current for the hollow cathode and with a wire heating for the filament cathode leads to a significant (up to 30%) narrowing of the plasma plume and increase of the energetic ion fraction. For the cylindrical Hall thruster, the observed variations of the plasma potential, electron temperature, and plasma density with the keeper current suggest that the electron emission from the cathode can affect the electron cross-field transport and the ionization in the thruster channel.

UR - http://www.scopus.com/inward/record.url?scp=77957841377&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=77957841377&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:77957841377

SN - 9781563479434

T3 - 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

BT - 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

T2 - 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

Y2 - 21 July 2008 through 23 July 2008

ER -

Effects of cathode electron emission on Hall thruster discharge

Abstract

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All Science Journal Classification (ASJC) codes

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