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Inner Front Pole Cover Erosion in the 12.5 kW HERMeS Hall Thruster Over a Range of Operating Conditions

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dc.contributor.author Polk, James E.
dc.contributor.author Lobbia, Robert
dc.contributor.author Barriault, Arthur
dc.contributor.author Guerrero, Pablo
dc.contributor.author Mikellides, Ioannis
dc.contributor.author Lopez Ortega, Alejandro
dc.date.accessioned 2020-03-20T21:11:06Z
dc.date.available 2020-03-20T21:11:06Z
dc.date.issued 2017-10-10
dc.identifier.citation 35th International Electric Propulsion Conference, Atlanta, Georgia, October 8-12, 2017 en_US
dc.identifier.clearanceno CL#17-5281
dc.identifier.uri http://hdl.handle.net/2014/47707
dc.description.abstract Erosion characteristics on the cover of the inner front pole in a 12.5 kW Hall thruster were measured over a wide range of operating conditions in tests of 6 to 14 hours duration using an accelerated test method and a very sensitive radioactive tracer-based erosion diagnostic. The operating points included the nominal 300 - 600 V conditions on a constant 20.8 A throttle curve, but included additional conditions at other currents spanning the throttling envelope and measurements at varying magnetic eld strength, facility pressure, and discharge voltage oscillation amplitude. The results show that the 300 V condition produces the highest wear rates on the 20.8 A throttle curve, but that rates actually increase with decreasing current. The wear rate was insensitive to discharge voltage ripple, but increased monotonically with magnetic eld strength, particularly near the inner radius of the pole cover. The inner region was also sensitive to facility pressure, showing lower rates at a higher pressure level. Separate experiments in which the energy distributions of ions generated by the hollow cathode were measured suggest that the cathode plume may be a source of energetic ions responsible for some of the erosion trends, in addition to ions originating in the thruster plume. The Hall thruster simulation code Hall2De is able to reproduce the erosion characteristics observed at 600 V, 20.8 A, but cannot currently match the rates measured at lower voltages and currents. en_US
dc.description.sponsorship NASA/JPL en_US
dc.language.iso en_US en_US
dc.publisher Pasadena, CA: Jet Propulsion Laboratory, National Aeronautics and Space Administration, 2017 en_US
dc.title Inner Front Pole Cover Erosion in the 12.5 kW HERMeS Hall Thruster Over a Range of Operating Conditions en_US
dc.type Preprint en_US


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