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Extended Performance 8-cm Mercury Ion ThrusterA slightly modified 8-cm Hg ion thruster demonstrated significant increase in performance. Thrust was increased by almost a factor of five over that of the baseline thruster. Thruster operation with various three grid ion optics configurations; thruster performance as a function of accelerator grid open area, cathode baffle, and cathode orifice size; and a life test of 614 hours at a beam current of 250 mA (17.5 mN thrust) are discussed. Highest thruster efficiency was obtained with the smallest open area accelerator grid. The benefits in efficiency from the low neutral loss grids were mitigated, however, by the limitation such grids place on attainable ion beam current densities. The thruster components suffered negligible weight losses during a life test, which indicated that operation of the 8-cm thruster at extended levels of thrust and power is possible with no significant loss of lifetime.
Document ID
19830005886
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mantenieks, M. A.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1981
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NAS 1.15:83029
E-1464
NASA-TM-83029
AIAA PAPER 82-1913
Report Number: NAS 1.15:83029
Report Number: E-1464
Report Number: NASA-TM-83029
Report Number: AIAA PAPER 82-1913
Meeting Information
Meeting: Intern. Elec. Propulsion Conf.
Location: New Orleans
Start Date: November 17, 1982
End Date: November 19, 1982
Sponsors: AIAA, Japan Soc. for Aeron. and Space Sci., Deut. Gesselschaft fuer Luft und Raumfahrt
Accession Number
83N14157
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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