Carbon Back Sputter Modeling for Hall Thruster Testing

In support of wear testing for the Hall Effect Rocket with Magnetic Shielding (HERMeS) program, the back sputter from a Hall effect thruster plume has been modeled for the NASA Glenn Research Centers Vacuum Facility 5. The predicted wear at a near-worst case condition of 600 V, 12.5 kW was found to...

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Bibliographic Details
Published inNASA Center for AeroSpace Information (CASI). Misc. Resources
Main Authors Gilland, James H, Williams, George J, Burt, Jonathan M, Yim, John T
Format Web Resource
LanguageEnglish
Published Hampton NASA/Langley Research Center 27.07.2016
Subjects
Carbon
Computer simulation
Electromagnetism
Hall effect
Magnetic shielding
Mathematical models
Microbalances
Research facilities
Wear
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Summary:In support of wear testing for the Hall Effect Rocket with Magnetic Shielding (HERMeS) program, the back sputter from a Hall effect thruster plume has been modeled for the NASA Glenn Research Centers Vacuum Facility 5. The predicted wear at a near-worst case condition of 600 V, 12.5 kW was found to be on the order of 3 4 mkhour in a fully carbon-lined chamber. A more detailed numerical monte carlo code was also modified to estimate back sputter for a detailed facility and pumping configuration. This code demonstrated similar back sputter rate distributions, but is not yet accurately modeling the magnitudes. The modeling has been benchmarked to recent HERMeS wear testing, using multiple microbalance measurements. These recent measurements have yielded values, on the order of 1.5- 2 microns/khour.
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