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Advanced ion thruster researchA simple model describing the discharge chamber performance of high strength, cusped magnetic field ion thrusters is developed. The model is formulated in terms of the energy cost of producing ions in the discharge chamber and the fraction of ions produced in the discharge chamber that are extracted to form the ion beam. The accuracy of the model is verified experimentally in a series of tests wherein the discharge voltage, propellant, grid transparency to neutral atoms, beam diameter and discharge chamber wall temperature are varied. The model is exercised to demonstrate what variations in performance might be expected by varying discharge chamber parameters. The results of a study of xenon and argon orificed hollow cathodes are reported. These results suggest that a hollow cathode model developed from research conducted on mercury cathodes can also be applied to xenon and argon. Primary electron mean free paths observed in argon and xenon cathodes that are larger than those found in mercury cathodes are identified as a cause of performance differences between mercury and inert gas cathodes. Data required as inputs to the inert gas cathode model are presented so it can be used as an aid in cathode design.
Document ID
19840011399
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Wilbur, P. J. (Colorado State Univ. Fort Collins, CO, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1984
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NAS 1.26:168340
NASA-CR-168340
Accession Number
84N19467
Funding Number(s)
PROJECT: RTOP 506-55-22
CONTRACT_GRANT: NGR-06-002-112
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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