Performance and Characterization of a Neutral Beam Propulsion Technology Demonstrator
A neutral beam propulsion technology demonstrator has been fabricated and tested. It uses gas diffusion neutralization to create a globally neutral plasma from an ion source. Thrust measurements for the neutral beam demonstrate that thrust at the very low 100 μN levels produced by this system can b...
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| Veröffentlicht in: | Journal of spacecraft and rockets 2020-09, Vol.57 (5), p.1061-1068 |
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| container_end_page | 1068 |
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| container_issue | 5 |
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| container_title | Journal of spacecraft and rockets |
| container_volume | 57 |
| creator | DeCicco, Anthony J Hartzell, Christine M Adams, Robert B Polzin, Kurt A Leps, Thomas J |
| description | A neutral beam propulsion technology demonstrator has been fabricated and tested. It uses gas diffusion neutralization to create a globally neutral plasma from an ion source. Thrust measurements for the neutral beam demonstrate that thrust at the very low 100 μN levels produced by this system can be measured during thermal drift of the variable amplitude hanging pendulum with extended range thrust stand. The beam energy, which exhibits good quantitative agreement with the thrust measurements, is measured as a function of neutralizer gas flow rate using a graphite calorimeter. A Faraday cup is used to measure the neutralization of the beam. These measurements generally exhibit quantitative agreement with predictive analytical and numerical models. Losses owing to the use of a grounded metal neutralizer are discussed, and it is quantitatively demonstrated through thrust, neutralization, and calorimetry measurements that the neutralizer is the source of the performance losses. |
| doi_str_mv | 10.2514/1.A34651 |
| format | Article |
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It uses gas diffusion neutralization to create a globally neutral plasma from an ion source. Thrust measurements for the neutral beam demonstrate that thrust at the very low 100 μN levels produced by this system can be measured during thermal drift of the variable amplitude hanging pendulum with extended range thrust stand. The beam energy, which exhibits good quantitative agreement with the thrust measurements, is measured as a function of neutralizer gas flow rate using a graphite calorimeter. A Faraday cup is used to measure the neutralization of the beam. These measurements generally exhibit quantitative agreement with predictive analytical and numerical models. Losses owing to the use of a grounded metal neutralizer are discussed, and it is quantitatively demonstrated through thrust, neutralization, and calorimetry measurements that the neutralizer is the source of the performance losses.</description><identifier>ISSN: 0022-4650</identifier><identifier>EISSN: 1533-6794</identifier><identifier>DOI: 10.2514/1.A34651</identifier><language>eng</language><publisher>Reston: American Institute of Aeronautics and Astronautics</publisher><subject>Flow velocity ; Gas flow ; Gaseous diffusion ; Ion sources ; Neutral beams ; Numerical models ; Pendulums ; Technology demonstrator</subject><ispartof>Journal of spacecraft and rockets, 2020-09, Vol.57 (5), p.1061-1068</ispartof><rights>This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. All requests for copying and permission to reprint should be submitted to CCC at ; employ the eISSN to initiate your request. See also AIAA Rights and Permissions .</rights><rights>This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the eISSN 1533-6794 to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp.</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><cites>FETCH-LOGICAL-a246t-86a8abff65cacf97c3ccf8bb2e343bb883f94fbeb3fa2421b35d2a754d53ee553</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,780,784,27923,27924</link.rule.ids></links><search><creatorcontrib>DeCicco, Anthony J</creatorcontrib><creatorcontrib>Hartzell, Christine M</creatorcontrib><creatorcontrib>Adams, Robert B</creatorcontrib><creatorcontrib>Polzin, Kurt A</creatorcontrib><creatorcontrib>Leps, Thomas J</creatorcontrib><title>Performance and Characterization of a Neutral Beam Propulsion Technology Demonstrator</title><title>Journal of spacecraft and rockets</title><description>A neutral beam propulsion technology demonstrator has been fabricated and tested. It uses gas diffusion neutralization to create a globally neutral plasma from an ion source. Thrust measurements for the neutral beam demonstrate that thrust at the very low 100 μN levels produced by this system can be measured during thermal drift of the variable amplitude hanging pendulum with extended range thrust stand. The beam energy, which exhibits good quantitative agreement with the thrust measurements, is measured as a function of neutralizer gas flow rate using a graphite calorimeter. A Faraday cup is used to measure the neutralization of the beam. These measurements generally exhibit quantitative agreement with predictive analytical and numerical models. Losses owing to the use of a grounded metal neutralizer are discussed, and it is quantitatively demonstrated through thrust, neutralization, and calorimetry measurements that the neutralizer is the source of the performance losses.</description><subject>Flow velocity</subject><subject>Gas flow</subject><subject>Gaseous diffusion</subject><subject>Ion sources</subject><subject>Neutral beams</subject><subject>Numerical models</subject><subject>Pendulums</subject><subject>Technology demonstrator</subject><issn>0022-4650</issn><issn>1533-6794</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2020</creationdate><recordtype>article</recordtype><recordid>eNpl0E1LAzEQBuAgCtYq-BMCInjZmu9mj7V-QtEe2vMySRO7ZXdTk91D_fVuWcGDp4GZZ2bgReiakgmTVNzTyYwLJekJGlHJeaamuThFI0IYy_o-OUcXKe0IoUqrfITWSxd9iDU01mFoNni-hQi2dbH8hrYMDQ4eA353XRuhwg8OaryMYd9V6ThcObttQhU-D_jR1aFJvWpDvERnHqrkrn7rGK2fn1bz12zx8fI2ny0yYEK1mVagwXivpAXr86nl1nptDHNccGO05j4X3jjDfb_AqOFyw2AqxUZy56TkY3Qz3N3H8NW51Ba70MWmf1kwIYRSmmrSq7tB2RhSis4X-1jWEA8FJcUxtIIWQ2g9vR0olAB_x_65H0ana1E</recordid><startdate>20200901</startdate><enddate>20200901</enddate><creator>DeCicco, Anthony J</creator><creator>Hartzell, Christine M</creator><creator>Adams, Robert B</creator><creator>Polzin, Kurt A</creator><creator>Leps, Thomas J</creator><general>American Institute of Aeronautics and Astronautics</general><scope>AAYXX</scope><scope>CITATION</scope><scope>7TB</scope><scope>8FD</scope><scope>FR3</scope><scope>H8D</scope><scope>L7M</scope></search><sort><creationdate>20200901</creationdate><title>Performance and Characterization of a Neutral Beam Propulsion Technology Demonstrator</title><author>DeCicco, Anthony J ; Hartzell, Christine M ; Adams, Robert B ; Polzin, Kurt A ; Leps, Thomas J</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-a246t-86a8abff65cacf97c3ccf8bb2e343bb883f94fbeb3fa2421b35d2a754d53ee553</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2020</creationdate><topic>Flow velocity</topic><topic>Gas flow</topic><topic>Gaseous diffusion</topic><topic>Ion sources</topic><topic>Neutral beams</topic><topic>Numerical models</topic><topic>Pendulums</topic><topic>Technology demonstrator</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>DeCicco, Anthony J</creatorcontrib><creatorcontrib>Hartzell, Christine M</creatorcontrib><creatorcontrib>Adams, Robert B</creatorcontrib><creatorcontrib>Polzin, Kurt A</creatorcontrib><creatorcontrib>Leps, Thomas J</creatorcontrib><collection>CrossRef</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>Engineering Research Database</collection><collection>Aerospace Database</collection><collection>Advanced Technologies Database with Aerospace</collection><jtitle>Journal of spacecraft and rockets</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>DeCicco, Anthony J</au><au>Hartzell, Christine M</au><au>Adams, Robert B</au><au>Polzin, Kurt A</au><au>Leps, Thomas J</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Performance and Characterization of a Neutral Beam Propulsion Technology Demonstrator</atitle><jtitle>Journal of spacecraft and rockets</jtitle><date>2020-09-01</date><risdate>2020</risdate><volume>57</volume><issue>5</issue><spage>1061</spage><epage>1068</epage><pages>1061-1068</pages><issn>0022-4650</issn><eissn>1533-6794</eissn><abstract>A neutral beam propulsion technology demonstrator has been fabricated and tested. 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Losses owing to the use of a grounded metal neutralizer are discussed, and it is quantitatively demonstrated through thrust, neutralization, and calorimetry measurements that the neutralizer is the source of the performance losses.</abstract><cop>Reston</cop><pub>American Institute of Aeronautics and Astronautics</pub><doi>10.2514/1.A34651</doi><tpages>8</tpages></addata></record> |
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| source | Alma/SFX Local Collection |
| subjects | Flow velocity Gas flow Gaseous diffusion Ion sources Neutral beams Numerical models Pendulums Technology demonstrator |
| title | Performance and Characterization of a Neutral Beam Propulsion Technology Demonstrator |
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