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NEXT Long-Duration Test Neutralizer Performance and Erosion CharacteristicsThe NASA's Evolutionary Xenon Thruster (NEXT) program is developing the next-generation ion propulsion system with significant enhancements beyond the state-of-the-art to provide future NASA science missions with enhanced capabilities at a low total development cost. A Long-Duration Test (LDT) was initiated in June 2005, to verify the NEXT propellant throughput capability to a qualification-level of 450 kg, 1.5 times the anticipated throughput requirement of 300 kg per thruster based on mission analyses. As of September 2, 2009, the thruster has accumulated 24,400 hr of operation with extensive durations at the following input powers: 6.9, 4.7, 1.1, and 0.5 kW. The thruster has processed 434 kg of xenon, surpassing the NASA Solar Technology Application Readiness (NSTAR) program thruster propellant throughput demonstrated during the extended life testing of the Deep Space 1 flight spare ion thruster and approaching the NEXT development qualification throughput goal of 450 kg. The NEXT LDT has demonstrated a total impulse of 16.1 10(exp 6zzz0 N s; the highest total impulse ever demonstrated by an ion thruster. A reduction in neutralizer flow margin has been the only appreciable source of thruster performance degradation. The behavior of the neutralizer is not easily predicted due to both erosion and deposition observed in previous wear tests. Spot-to-plume mode transition flow data and in-situ erosion results for the LDT neutralizer are discussed. This loss of flow margin has been addressed through a combination of a design change in the prototype-model neutralizer to increase flow margin at low emission current and to update the NEXT throttle table to ensure adequate flow margin as a function of propellant throughput processed. The new throttle table will be used for future LDT operations. The performance of the NEXT LDT neutralizer is consistent with that observed for long-life hollow cathodes. The neutralizer life-limiting failure modes are progressing as expected and the neutralizer data indicate none of the neutralizer failures are imminent.
Document ID
20100002896
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Herman, Daniel A.
(ASRC Aerospace Corp. Cleveland, OH, United States)
Soulas, George C.
(NASA Glenn Research Center Cleveland, OH, United States)
Patterson, Michael J.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
August 25, 2013
Publication Date
December 1, 2009
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
IEPC-2009-154
E-17098
NASA/TM-2009-215838
Report Number: IEPC-2009-154
Report Number: E-17098
Report Number: NASA/TM-2009-215838
Meeting Information
Meeting: 31st International Electric Propulsion Conference (IEPC 2009)
Location: Ann Arbor, MI
Country: United States
Start Date: September 20, 2009
End Date: September 24, 2009
Sponsors: CU Aerospace, L-3 Communications Corp, EDA, Inc., Busek (J.) Co., Inc., Michigan Univ., Air Force Office of Scientific Research, Bolling AFB, Electric Rocket Propulsion Society, Aerojet
Funding Number(s)
WBS: WBS 346620.04.08.02.02.01
Distribution Limits
Public
Copyright
Public Use Permitted.
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