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Fatigue damage of notched boron/epoxy laminates under constant amplitude loadingFatigue damage in (0, + or - 45) and (0, + or - 45,90) boron/epoxy laminates was studied with X-ray radiography and scanning electron microscopy. In addition, limited tests for residual strength and stiffness were performed. The results of this study suggest that in boron/epoxy laminates the 45-degree plies play a key role in the fatigue process of boron/epoxy laminates that contain them. The fatigue process in the + or - 45-degree plies starts as intralaminar matrix cracks.
Document ID
19770010222
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Roderick, G. L. (NASA Langley Research Center Hampton, VA, United States)
Whitcomb, J. D. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
December 20, 1976
Subject Category
Composite Materials
Report/Patent Number
NASA-TM-X-73994
Report Number: NASA-TM-X-73994
Meeting Information
Meeting: ASTM Symp. on Fatigue of Filamentary Composites
Location: Denver
Start Date: November 15, 1976
End Date: November 18, 1976
Accession Number
77N17165
Funding Number(s)
PROJECT: RTOP 506-17-27-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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