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Non-Contact Thermal Characterization of NASA's HERMeS Hall ThrusterThe Thermal Characterization Test of NASAs 12.5-kW Hall thruster is being completed. This thruster is being developed to support of a number of potential Solar Electric Propulsion Technology Demonstration Mission concepts, including the Asteroid Redirect Robotic Mission concept. As a part of this test, an infrared-based, non-contact thermal imaging system was developed to measure Hall thruster surfaces that are exposed to high voltage or harsh environment. To increase the accuracy of the measurement, a calibration array was implemented, and a pilot test was performed to determine key design parameters for the calibration array. The raw data is analyzed in conjunction with a simplified thermal model of the channel to account for reflection. The reduced data will be used to refine the thruster thermal model, which is critical to the verification of the thruster thermal specifications. The present paper will give an overview of the decision process that led to identification of the need for a non-contact temperature diagnostic, the development of said diagnostic, the measurement results, and the simplified thermal model of the channel.
Document ID
Document Type
Huang, Wensheng (NASA Glenn Research Center Cleveland, OH United States)
Kamhawi, Hani (NASA Glenn Research Center Cleveland, OH United States)
Meyers, 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 28, 2015
Subject Category
Spacecraft Propulsion and Power
Report/Patent Number
Meeting Information
AIAA/SAE/ASEE Joint Propulsion Conference(Orlando, FL)
Funding Number(s)
WBS: WBS 729200.06.03.05
Distribution Limits
Public Use Permitted.
Electric Propulsion
Hall Thrusters
Ground Tests

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