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dc.contributor.advisorEpp, Chirold
dc.contributor.authorSinclair, Brian C.
dc.date.accessioned2012-03-14T17:33:11Z
dc.date.available2012-03-14T17:33:11Z
dc.date.issued2005-12
dc.identifier.urihttp://hdl.handle.net/10945/1821
dc.description.abstractNASAâ s VAriable Specific Impulse Magnetoplasma Rocket Engine (VASIMR) will provide a highly efficient propulsion source that can dramatically reduce Martian transit times, provide for more abort contingencies, and protect astronauts from space radiation with its highly radiation-absorbent hydrogen fuel. The VASIMR is still in its developmental infancy and requires many years of research before its initial operational capability. Much is still unknown about the complex plasma interactions in the exhaust. A Langmuir probe was designed, constructed, and operated to determine current density radial profiles and total particle flux at various stages in the exhaust of VASIMR. The Langmuir probe results proved that the exhaustâ s radial profile is Gaussian, experimentally validated predictions of magnetic field line dragging, and verified the ionization efficiency of VASIMR.en_US
dc.format.extentxiv, 91 p. : col. ill. ;en_US
dc.publisherMonterey, California. Naval Postgraduate Schoolen_US
dc.rightsApproved for public release, distribution unlimiteden_US
dc.subject.lcshLangmuir probesen_US
dc.subject.lcshRocket enginesen_US
dc.subject.lcshPhysicsen_US
dc.subject.lcshEngineeringen_US
dc.titleLangmuir probe diagnostics of the VASIMR engineen_US
dc.typeThesisen_US
dc.contributor.secondreaderBrophy, Christopher
dc.contributor.corporateNaval Postgraduate School (U.S.).
dc.contributor.departmentMechanical and Astronautical Engineering
dc.identifier.oclc63117675
etd.thesisdegree.nameM.S.en_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineAstronautical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US
etd.verifiednoen_US


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