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modeling an iodine hall thruster plume in the iodine satellite (isat)An iodine-operated 200-W Hall thruster plume has been simulated using a hybrid-PIC model to predict the spacecraft surface-plume interaction for spacecraft integration purposes. For validation of the model, the plasma potential, electron temperature, ion current flux, and ion number density of xenon propellant were compared with available measurement data at the nominal operating condition. To simulate iodine plasma, various collision cross sections were found and used in the model. While time-varying atomic iodine species (i.e., I, I+, I2+) information is provided by HP Hall simulation at the discharge channel exit, the molecular iodine species (i.e., I2, I2+) are introduced as Maxwellian particles at the channel exit. Simulation results show that xenon and iodine plasma plumes appear to be very similar under the assumptions of the model. Assuming a sticking coefficient of unity, iodine deposition rate is estimated.
Document ID
20170001565
Document Type
Conference Paper
Authors
Choi, Maria
(NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
February 13, 2017
Publication Date
December 5, 2016
Subject Category
Spacecraft Propulsion and Power
Report/Patent Number
GRC-E-DAA-TN37710
Meeting Information
Liquid Propulsion (LPS) Meeting(Phoenix, AZ)
Funding Number(s)
WBS: WBS 762817.06.02.02.04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
Iodine
Hall Thruster Plume
Numerical Simulation

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