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Test results for electron beam charging of flexible insulators and compositesFlexible solar-array substrates, graphite-fiber/epoxy - aluminum honeycomb panels, and thin dielectric films were exposed to monoenergetic electron beams ranging in energy from 2 to 20 keV in the Lewis Research Center's geomagnetic-substorm-environment simulation facility to determine surface potentials, dc currents, and surface discharges. The four solar-array substrate samples consisted of Kapton sheet reinforced with fabrics of woven glass or carbon fibers. They represented different construction techniques that might be used to reduce the charge accumulation on the array back surface. Five honeycomb-panel samples were tested, two of which were representative of Voyager antenna materials and had either conductive or nonconductive painted surfaces. A third sample was of Navstar solar-array substrate material. The other two samples were of materials proposed for use on Intelsat V. All the honeycomb-panel samples had graphite-fiber/epoxy composite face sheets. The thin dielectric films were 2.54-micrometer-thick Mylar and 7.62-micrometer-thick Kapton.
Document ID
19790015860
Document Type
Conference Paper
Authors
Staskus, J. V.
(NASA Lewis Research Center Cleveland, OH, United States)
Berkopec, F. D.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1979
Publication Information
Publication: Spacecraft Charging Technol., 1978
Subject Category
Spacecraft Design, Testing And Performance
Accession Number
79N24031
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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