Performance of a magnetic multipole line-cusp argon ion thruster

A 17 cm diameter line cusp ion thruster was evaluated with inert gases which are candidate propellants for on orbit and orbit transfer propulsion functions for Large Space Systems. A semiempirical relationship was generated to predict thruster beam current in terms of plasma parameters which would a...

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1. Verfasser:	Sovey, J. S.
Format:	Tagungsbericht
Sprache:	eng
Schlagworte:	Spacecraft Propulsion And Power
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creator	Sovey, J. S.
description	A 17 cm diameter line cusp ion thruster was evaluated with inert gases which are candidate propellants for on orbit and orbit transfer propulsion functions for Large Space Systems. A semiempirical relationship was generated to predict thruster beam current in terms of plasma parameters which would allow initial thruster optimization without ion extraction and the associated large vacuum facilities. The sensitivity of performance to changes in discharge electrode configurations and magnetic circuit was evaluated and is presented. After final optimization a propellant utilization efficiency of 0.9 at a discharge chamber power expenditure of about 260 w per beam ampere was obtained. These performance parameters are the highest yet achieved with argon propellant.
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S.</creatorcontrib><description>A 17 cm diameter line cusp ion thruster was evaluated with inert gases which are candidate propellants for on orbit and orbit transfer propulsion functions for Large Space Systems. A semiempirical relationship was generated to predict thruster beam current in terms of plasma parameters which would allow initial thruster optimization without ion extraction and the associated large vacuum facilities. The sensitivity of performance to changes in discharge electrode configurations and magnetic circuit was evaluated and is presented. After final optimization a propellant utilization efficiency of 0.9 at a discharge chamber power expenditure of about 260 w per beam ampere was obtained. 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S.</creatorcontrib><title>Performance of a magnetic multipole line-cusp argon ion thruster</title><description>A 17 cm diameter line cusp ion thruster was evaluated with inert gases which are candidate propellants for on orbit and orbit transfer propulsion functions for Large Space Systems. A semiempirical relationship was generated to predict thruster beam current in terms of plasma parameters which would allow initial thruster optimization without ion extraction and the associated large vacuum facilities. The sensitivity of performance to changes in discharge electrode configurations and magnetic circuit was evaluated and is presented. After final optimization a propellant utilization efficiency of 0.9 at a discharge chamber power expenditure of about 260 w per beam ampere was obtained. These performance parameters are the highest yet achieved with argon propellant.</description><subject>Spacecraft Propulsion And Power</subject><fulltext>true</fulltext><rsrctype>conference_proceeding</rsrctype><creationdate>1981</creationdate><recordtype>conference_proceeding</recordtype><sourceid>CYI</sourceid><recordid>eNrjZHAISC1Kyy_KTcxLTlXIT1NIVMhNTM9LLclMVsgtzSnJLMjPSVXIycxL1U0uLS5QSCxKz89TyATikoyi0uKS1CIeBta0xJziVF4ozc0g4-Ya4uyhm5dYnBifV1JUHG9oaWFoYGBoYGZpZExAGgDGXy1Y</recordid><startdate>19810101</startdate><enddate>19810101</enddate><creator>Sovey, J. S.</creator><scope>CYE</scope><scope>CYI</scope></search><sort><creationdate>19810101</creationdate><title>Performance of a magnetic multipole line-cusp argon ion thruster</title><author>Sovey, J. S.</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-nasa_ntrs_198100106923</frbrgroupid><rsrctype>conference_proceedings</rsrctype><prefilter>conference_proceedings</prefilter><language>eng</language><creationdate>1981</creationdate><topic>Spacecraft Propulsion And Power</topic><toplevel>online_resources</toplevel><creatorcontrib>Sovey, J. S.</creatorcontrib><collection>NASA Scientific and Technical Information</collection><collection>NASA Technical Reports Server</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Sovey, J. S.</au><format>book</format><genre>proceeding</genre><ristype>CONF</ristype><atitle>Performance of a magnetic multipole line-cusp argon ion thruster</atitle><date>1981-01-01</date><risdate>1981</risdate><abstract>A 17 cm diameter line cusp ion thruster was evaluated with inert gases which are candidate propellants for on orbit and orbit transfer propulsion functions for Large Space Systems. A semiempirical relationship was generated to predict thruster beam current in terms of plasma parameters which would allow initial thruster optimization without ion extraction and the associated large vacuum facilities. The sensitivity of performance to changes in discharge electrode configurations and magnetic circuit was evaluated and is presented. After final optimization a propellant utilization efficiency of 0.9 at a discharge chamber power expenditure of about 260 w per beam ampere was obtained. These performance parameters are the highest yet achieved with argon propellant.</abstract><cop>Legacy CDMS</cop><oa>free_for_read</oa></addata></record>
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subjects	Spacecraft Propulsion And Power
title	Performance of a magnetic multipole line-cusp argon ion thruster
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