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Configuration effects on satellite charging responseThe response of various spacecraft configurations to a charging environment in sunlight was studied using the NASA Charging Analyzer Program code. The configuration features geometry, type of stabilization, and overall size. Results indicate that sunlight charging response is dominated by differential charging effects. Shaded insulation charges negatively result in the formation of potential barriers which suppress photoelectron emission from sunlit surfaces. Sunlight charging occurs relatively slowly: with 30 minutes of charging simulations, in none of the configurations modeled did the most negative surface cell reach half its equilibrium potential in eclipse.
Document ID
19800006941
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Purvis, C. K. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1980
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NASA-TM-81397
E-307
Report Number: NASA-TM-81397
Report Number: E-307
Meeting Information
Meeting: Aerospace Sci. Meeting
Location: Pasadena, CA
Country: United States
Start Date: January 14, 1980
End Date: January 16, 1980
Sponsors: AIAA
Accession Number
80N15200
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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