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Sputter erosion and deposition in the discharge chamber of a small mercury ion thrusterA 5-cm diameter mercury ion thruster similar to one tested for 9715 hours was operated approximately 400 hrs each at discharge voltages of 36.6, 39.6, and 42.6 V, with corresponding discharge propellant utilizations of 58, 68, and 70 percent. The observed sputter erosion rates of the internal thruster parts and the anode weight gain rate all rose rapidly with discharge voltage and were roughly in the ratio of 1:3:5 for the three voltages. The combined weight loss of the internal thruster parts nearly balanced the anode weight gain. Hg+2 ions apparently caused most of the observed erosion.
Document ID
19740027938
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Power, J. L.
(NASA Lewis Research Center Cleveland, Ohio, United States)
Date Acquired
August 7, 2013
Publication Date
October 1, 1973
Subject Category
Propulsion Systems
Report/Patent Number
AIAA PAPER 73-1109
Meeting Information
Meeting: Electric Propulsion Conference
Location: Lake Tahoe, NV
Start Date: October 31, 1973
End Date: November 2, 1973
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
74A10688
Distribution Limits
Public
Copyright
Other

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