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Space environmental effects on LDEF composites: Leading graphite/epoxy panel, selected trailing edge specimensThe composite electronics-module cover for the leading edge (row D9) experiment M0003-8 was fabricated from T300 graphite/934 epoxy unidirectional prepreg tape in a multi-oriented layup. This panel contained thermal control coatings in three of the four quadrants with the fourth quadrant left uncoated as a control. The composite experienced different thermal cycling extremes in each quadrant due to the differing optical properties of the coatings. Results will be presented on microcracking and other Low Earth Orbital (LEO) effects on the coated panel substrate.
Document ID
19920018047
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Dursch, Harry (Boeing Co. Seattle, WA, United States)
George, Pete (Boeing Co. Seattle, WA, United States)
Hill, Sylvester (Boeing Co. Seattle, WA, United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1992
Publication Information
Publication: NASA. Langley Research Center, Second LDEF Post-Retrieval Symposium Abstracts
Subject Category
Composite Materials
Accession Number
92N27290
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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