Investigations of a laboratory model Hall thruster

J. Ashkenazy; Y. Raitses; G. Appelbaum

doi:10.2514/6.1995-2673

Investigations of a laboratory model Hall thruster

J. Ashkenazy
, Y. Raitses
, G. Appelbaum

Research output: Contribution to conference › Paper › peer-review

10 Scopus citations

Abstract

A laboratory model Hall thruster was constructed and operated in the test facility recently assembled at Soreq for electric thrusters research. The thruster, intended to serve as a tool to study and investigate Hall thruster technology, was operated at various values of the discharge voltage, propellant mass flow rate and coils current (magnetic field strength) at an input power of up to 1.2kW. Electrical properties and thrust were measured, from which the thruster discharge characteristics, specific impulse and efficiency, at the various operating points, were deduced. In these experiments, an efficiency larger than 50% and a specific impulse of up to 2000s were obtained.

Original language	English (US)
DOIs	https://doi.org/10.2514/6.1995-2673
State	Published - 1995
Externally published	Yes
Event	31st Joint Propulsion Conference and Exhibit, 1995 - San Diego, United States Duration: Jul 10 1995 → Jul 12 1995

Conference

Conference	31st Joint Propulsion Conference and Exhibit, 1995
Country/Territory	United States
City	San Diego
Period	7/10/95 → 7/12/95

All Science Journal Classification (ASJC) codes

Energy Engineering and Power Technology
Electrical and Electronic Engineering
Mechanical Engineering
Control and Systems Engineering
Aerospace Engineering

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10.2514/6.1995-2673

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title = "Investigations of a laboratory model Hall thruster",

abstract = "A laboratory model Hall thruster was constructed and operated in the test facility recently assembled at Soreq for electric thrusters research. The thruster, intended to serve as a tool to study and investigate Hall thruster technology, was operated at various values of the discharge voltage, propellant mass flow rate and coils current (magnetic field strength) at an input power of up to 1.2kW. Electrical properties and thrust were measured, from which the thruster discharge characteristics, specific impulse and efficiency, at the various operating points, were deduced. In these experiments, an efficiency larger than 50\% and a specific impulse of up to 2000s were obtained.",

author = "J. Ashkenazy and Y. Raitses and G. Appelbaum",

note = "Publisher Copyright: {\textcopyright} 1995, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.; 31st Joint Propulsion Conference and Exhibit, 1995 ; Conference date: 10-07-1995 Through 12-07-1995",

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doi = "10.2514/6.1995-2673",

language = "English (US)",

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TY - CONF

T1 - Investigations of a laboratory model Hall thruster

AU - Ashkenazy, J.

AU - Raitses, Y.

AU - Appelbaum, G.

PY - 1995

Y1 - 1995

N2 - A laboratory model Hall thruster was constructed and operated in the test facility recently assembled at Soreq for electric thrusters research. The thruster, intended to serve as a tool to study and investigate Hall thruster technology, was operated at various values of the discharge voltage, propellant mass flow rate and coils current (magnetic field strength) at an input power of up to 1.2kW. Electrical properties and thrust were measured, from which the thruster discharge characteristics, specific impulse and efficiency, at the various operating points, were deduced. In these experiments, an efficiency larger than 50% and a specific impulse of up to 2000s were obtained.

AB - A laboratory model Hall thruster was constructed and operated in the test facility recently assembled at Soreq for electric thrusters research. The thruster, intended to serve as a tool to study and investigate Hall thruster technology, was operated at various values of the discharge voltage, propellant mass flow rate and coils current (magnetic field strength) at an input power of up to 1.2kW. Electrical properties and thrust were measured, from which the thruster discharge characteristics, specific impulse and efficiency, at the various operating points, were deduced. In these experiments, an efficiency larger than 50% and a specific impulse of up to 2000s were obtained.

UR - https://www.scopus.com/pages/publications/84964489693

UR - https://www.scopus.com/pages/publications/84964489693#tab=citedBy

U2 - 10.2514/6.1995-2673

DO - 10.2514/6.1995-2673

M3 - Paper

AN - SCOPUS:84964489693

T2 - 31st Joint Propulsion Conference and Exhibit, 1995

Y2 - 10 July 1995 through 12 July 1995

ER -

Investigations of a laboratory model Hall thruster

Abstract

Conference

All Science Journal Classification (ASJC) codes

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