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Environmental Testing of the NEXT PM1R Ion EngineThe NEXT propulsion system is an advanced ion propulsion system presently under development that is oriented towards robotic exploration of the solar system using solar electric power. The subsystem includes an ion engine, power processing unit, feed system components, and thruster gimbal. The Prototype Model engine PM1 was subjected to qualification-level environmental testing in 2006 to demonstrate compatibility with environments representative of anticipated mission requirements. Although the testing was largely successful, several issues were identified including the fragmentation of potting cement on the discharge and neutralizer cathode heater terminations during vibration which led to abbreviated thermal testing, and generation of particulate contamination from manufacturing processes and engine materials. The engine was reworked to address most of these findings, renamed PM1R, and the environmental test sequence was repeated. Thruster functional testing was performed before and after the vibration and thermal-vacuum tests. Random vibration testing, conducted with the thruster mated to the breadboard gimbal, was executed at 10.0 Grms for 2 min in each of three axes. Thermal-vacuum testing included three thermal cycles from 120 to 215 C with hot engine re-starts. Thruster performance was nominal throughout the test program, with minor variations in a few engine operating parameters likely caused by facility effects. There were no significant changes in engine performance as characterized by engine operating parameters, ion optics performance measurements, and beam current density measurements, indicating no significant changes to the hardware as a result of the environmental testing. The NEXT PM1R engine and the breadboard gimbal were found to be well-designed against environmental requirements based on the results reported herein. The redesigned cathode heater terminations successfully survived the vibration environments. Based on the results of this test program and confidence in the engineering solutions available for the remaining findings of the first test program, specifically the particulate contamination, the hardware environmental qualification program can proceed with confidence
Document ID
20080013225
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Snyder, John S.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Anderson, John R.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
VanNoord, Jonathan L.
(NASA Glenn Research Center Cleveland, OH, United States)
Soulas, George C.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
August 24, 2013
Publication Date
January 1, 2007
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
E-16280
IEPC-2007-276
NASA/TM-2008-215058
Report Number: E-16280
Report Number: IEPC-2007-276
Report Number: NASA/TM-2008-215058
Meeting Information
Meeting: 30th International Electric Propulsion Conference (IEPC 2007)
Location: Florence
Country: Italy
Start Date: September 17, 2007
End Date: September 20, 2007
Sponsors: Centrospazio, Electric Rocket Propulsion Society, ALTA S.p.A.
Funding Number(s)
WBS: WBS 346620.04.05.03.11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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