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Non-Contact Thermal Characterization of NASA's HERMeS Hall ThrusterThe thermal characterization test of NASA's 12.5-kW Hall Effect Rocket with Magnetic Shielding has been completed. This thruster was developed to support a number of potential Solar Electric Propulsion Technology Demonstration Mission concepts, including the Asteroid Redirect Robotic Mission concept. As a part of the preparation for this characterization test, an infrared-based, non-contact thermal imaging system was developed to measure the temperature of various thruster surfaces that are exposed to high voltage or plasma. An in-situ calibration array was incorporated into the setup to improve the accuracy of the temperature measurement. The key design parameters for the calibration array were determined in a separate pilot test. The raw data from the characterization test was analyzed though further work is needed to obtain accurate anode temperatures. Examination of the front pole and discharge channel temperatures showed that the thruster temperature was driven more by discharge voltage than by discharge power. Operation at lower discharge voltages also yielded more uniform temperature distributions than at higher discharge voltages. When operating at high discharge voltage, increasing the magnetic field strength appeared to have made the thermal loading azimuthally more uniform.
Document ID
20150021868
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Huang, Wensheng
(NASA Glenn Research Center Cleveland, OH United States)
Kamhawi, Hani
(NASA Glenn Research Center Cleveland, OH United States)
Myers, James L.
(Vantage Partners, LLC Brook Park, OH, United States)
Yim, John T.
(NASA Glenn Research Center Cleveland, OH United States)
Neff, Gregory
(University of Western Michigan Kalamazoo, MI, United States)
Date Acquired
November 25, 2015
Publication Date
July 27, 2015
Subject Category
Propellants And Fuels
Energy Production And Conversion
Report/Patent Number
AIAA Paper 2015-3920
GRC-E-DAA-TN24829
Meeting Information
Meeting: AIAA/SAE/ASEE Joint Propulsion Conference
Location: Orlando, FL
Country: United States
Start Date: July 27, 2015
End Date: July 29, 2015
Sponsors: American Society for Engineering Education (ASEE), Society of Automotive Engineers, Inc., American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 729200.06.03.05
CONTRACT_GRANT: NNC12BA01B
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
Hall Thrusters
Ground Tests
Electric Propulsion
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