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Post-Test Inspection of NASA's Evolutionary Xenon Thruster Long-Duration Test Hardware: Discharge and Neutralizer CathodesThe NEXT Long-Duration Test is part of a comprehensive thruster service life assessment intended to demonstrate overall throughput capability, validate service life models, quantify wear rates as a function of time and operating condition, and identify any unknown life-limiting mechanisms. The test was voluntarily terminated in February 2014 after demonstrating 51,184 hours of high-voltage operation, 918 kg of propellant throughput, and 35.5 MN-s of total impulse. The post-test inspection of the thruster hardware began shortly afterwards with a combination of non-destructive and destructive analysis techniques, and is presently nearing completion. This paper presents relevant results of the post-test inspection for both discharge and neutralizer cathodes. Discharge keeper erosion was found to be significantly reduced from what was observed in the NEXT 2 kh wear test and NSTAR Extended Life Test, providing adequate protection of vital cathode components throughout the test with ample lifetime remaining. The area of the discharge cathode orifice plate that was exposed by the keeper orifice exhibited net erosion, leading to cathode plate material building up in the cathode-keeper gap and causing a thermally-induced electrical short observed during the test. Significant erosion of the neutralizer cathode orifice was also found and is believed to be the root cause of an observed loss in flow margin. Deposition within the neutralizer keeper orifice as well as on the downstream surface was thicker than expected, potentially resulting in a facility-induced impact on the measured flow margin from plume mode. Neutralizer keeper wall erosion on the beam side was found to be significantly lower compared to the NEXT 2 kh wear test, likely due to the reduction in beam extraction diameter of the ion optics that resulted in decreased ion impingement. Results from the post-test inspection have led to some minor thruster design improvements.
Document ID
20170000955
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Shastry, Rohit
(NASA Glenn Research Center Cleveland, OH United States)
Soulas, George C.
(NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
January 31, 2017
Publication Date
July 25, 2016
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
GRC-E-DAA-TN33394
Report Number: GRC-E-DAA-TN33394
Meeting Information
Meeting: AIAA/SAE/ASEE Joint Propulsion Conference
Location: Salt Lake City, UT
Country: United States
Start Date: July 25, 2016
End Date: July 27, 2016
Sponsors: American Society for Electrical Engineers, American Inst. of Aeronautics and Astronautics, Society of Automotive Engineers, Inc.
Funding Number(s)
WBS: WBS 336763.01.05.02.04.05.01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
Electric Propulsion
Lifetime
Ion Thrusters
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