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Results of a XIPS© 25-cm thruster discharge cathode wear test

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dc.contributor.author Polk, James E.
dc.contributor.author Goebel, Dan M.
dc.contributor.author Tighe, William
dc.date.accessioned 2014-09-03T21:53:22Z
dc.date.available 2014-09-03T21:53:22Z
dc.date.issued 2009-09-20
dc.identifier.citation 31st International Electric Propulsion Conference, Ann Arbor, Michigan, September 20-24, 2009 en_US
dc.identifier.clearanceno 09-3472
dc.identifier.uri http://hdl.handle.net/2014/44682
dc.description.abstract The Xenon Ion Propulsion System (XIPS©) 25-cm thruster produced by L-3 Communications Electron Technologies, Inc. offers a number of potential benefits for planetary missions, including high efficiency and high Isp over a large power throttling range and availability from an active product line. The thruster is qualified for use on commercial communications satellites, which have requirements differing from those for typical planetary missions. In particular, deep space missions require longer service life over a broad range of throttling conditions. A XIPS © discharge cathode assembly was subjected to a long duration test to extend operating experience at the maximum power point and at throttled conditions unique to planetary mission applications. A total of 16079 hours were accumulated at conditions corresponding to the full power engine operating point at 4.2 kWe, an intermediate power point at 2.76 kWe and the minimum power point at 0.49 kWe. Minor performance losses and cathode keeper erosion were observed at the full power point, but there were no changes in performance and negligible erosion at the intermediate and minimum power points. 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, 2009 en_US
dc.subject cathode en_US
dc.subject electric propulsion en_US
dc.title Results of a XIPS© 25-cm thruster discharge cathode wear test en_US
dc.type Presentation en_US


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