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J series thruster thermal test resultsTest experience with J series ion thrusters have indicated that the present thruster design may result in excessive temperatures in areas which utilize organic materials such as wire insulation, with the resultant outgassing and potential contamination of insulating materials. Further, it appears that thermal data obtained with earlier thruster designs, such as the 700 series thruster, may not be directly applicable to the J series design. Two J series thrusters were fitted with thermocouples and critical temperatures measured for a variety of configurations and operating parameters. Completely enclosing the thruster to reduce facility contamination significantly increased temperatures prompting the selection of a compromise geometry for life testing. The operating parameter having the largest effect on temperatures was discharge power, while beam power affected little else than extraction system temperatures. Several off-normal operating modes were also investigated. Data believed to be sufficient to effectively modify existing thermal models were obtained from the tests.
Document ID
19830031263
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bechtel, R. T.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Dulgeroff, C. R.
(Hughes Research Laboratories Malibu, CA, United States)
Date Acquired
August 11, 2013
Publication Date
November 1, 1982
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 82-1906
Meeting Information
Meeting: Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference
Location: New Orleans, LA
Start Date: November 17, 1982
End Date: November 19, 1982
Sponsors: AIAA
Accession Number
83A12481
Distribution Limits
Public
Copyright
Other

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