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Double ion production in mercury thrustersThe development of a model which predicts doubly charged ion density is discussed. The accuracy of the model is shown to be good for two different thruster sizes and a total of 11 different cases. The model indicates that in most cases more than 80% of the doubly charged ions are produced from singly charged ions. This result can be used to develop a much simpler model which, along with correlations of the average plasma properties, can be used to determine the doubly charged ion density in ion thrusters with acceptable accuracy. Two different techniques which can be used to reduce the doubly charged ion density while maintaining good thruster operation, are identified as a result of an examination of the simple model. First, the electron density can be reduced and the thruster size then increased to maintain the same propellant utilization. Second, at a fixed thruster size, the plasma density, temperature and energy can be reduced and then to maintain a constant propellant utilization the open area of the grids to neutral propellant loss can be reduced through the use of a small hole accelerator grid.
Document ID
19760015211
Acquisition Source
Legacy CDMS
Document Type
Thesis/Dissertation
Authors
Peters, R. R. (Colorado State Univ. Fort Collins, CO, United States)
Date Acquired
September 3, 2013
Publication Date
April 1, 1976
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-CR-135019
Accession Number
76N22299
Funding Number(s)
CONTRACT_GRANT: NGR-06-002-112
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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