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Magnetoelectrostatic thruster physical geometry testsInert gas tests are conducted with several magnetoelectrostatic containment discharge chamber geometries. The configurations tested include three discharge chamber lengths; three boundary magnet patterns; two different flux density magnet materials; hemispherical and conical shaped thrusters having different surface-to-volume ratios; and two and three grid ion optics. Argon mass utilizations of 60 to 79% are attained at 210 to 280 eV/ion in different test configurations. Short hemi thruster configurations are found to produce 70 to 92% xenon mass utilization at 185 to 220 eV/ion.
Document ID
19810045162
Document Type
Conference Paper
Authors
Ramsey, W. D.
(Xerox Electro-Optical Systems Pasadena, Calif., United States)
Date Acquired
August 11, 2013
Publication Date
April 1, 1981
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 81-0753
Meeting Information
Meeting: International Electric Propulsion Conference
Location: Las Vegas, NV
Country: US
Start Date: April 21, 1981
End Date: April 23, 1981
Sponsors: DGLR, AIAA, Japan Society for Aeronautical and Space Sciences
Accession Number
81A29566
Funding Number(s)
CONTRACT_GRANT: NAS3-21345
Distribution Limits
Public
Copyright
Other

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