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Design of a cusped field plasma thruster

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dc.contributor.advisor Paulo Lozano. en_US Conte, Joseph Richard, III en_US
dc.contributor.other Massachusetts Institute of Technology. Dept. of Mechanical Engineering. en_US 2012-09-13T18:55:36Z 2012-09-13T18:55:36Z 2012 en_US 2012 en_US
dc.description Thesis (S.B.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 2012. en_US
dc.description Pages 46-85 printed landscape format. Cataloged from PDF version of thesis. en_US
dc.description Includes bibliographical references (p. 44-45). en_US
dc.description.abstract A plasma space propulsion thruster has been designed. It is classified as a Cusped Field Thruster (CFT), which refers to the geometry of the magnetic field that influences the flow of electrons and ions. The thruster was modeled after an original Diverging Cusped Field Thruster (DCFT) developed at MIT's Space Propulsion Laboratory. There are several improvements (including a flat downstream separatrix) that are aimed at increasing performance. In general, plasma thrusters have applications in satellite trajectory adjustment and deep space probes because of their superior fuel efficiency compared to chemical thrusters. en_US
dc.description.statementofresponsibility by Joseph Richard Conte, III. en_US
dc.format.extent 85 p. en_US
dc.language.iso eng en_US
dc.publisher Massachusetts Institute of Technology en_US
dc.rights M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission. en_US
dc.rights.uri en_US
dc.subject Mechanical Engineering. en_US
dc.title Design of a cusped field plasma thruster en_US
dc.type Thesis en_US S.B. en_US
dc.contributor.department Massachusetts Institute of Technology. Dept. of Mechanical Engineering. en_US
dc.identifier.oclc 807127388 en_US

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