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Inert gas ion thruster developmentTwo 12 cm magneto-electrostatic containment (MESC) ion thrusters were performance mapped with argon and xenon. The first, hexagonal, thruster produced optimized performance of 48.5to 79 percent argon mass utilization efficiencies at discharge energies of 240 to 425 eV/ion, respectively, Xenon mass utilization efficiencies of 78 to 95 percent were observed at discharge energies of 220 to 290 eV/ion with the same optimized hexagonal thruster. Changes to the cathode baffle reduced the discharge anode potential during xenon operation from approximately 40 volts to about 30 volts. Preliminary tests conducted with the second, hemispherical, MESC thruster showed a nonuniform anode magnetic field adversely affected thruster performance. This performance degradation was partially overcome by changes in the boundary anode placement. Conclusions drawn the hemispherical thruster tests gave insights into the plasma processes in the MESC discharge that will aid in the design of future thrusters.
Document ID
19800018923
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Ramsey, W. D. (Xerox Electro-Optical Systems Pasadena, CA, United States)
Date Acquired
September 4, 2013
Publication Date
March 1, 1980
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
XEOS-2372
IR-1
NASA-CR-159805
Accession Number
80N27424
Funding Number(s)
CONTRACT_GRANT: NAS3-21345
PROJECT: RTOP 506-55-32
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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