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The influence of lay-up and thickness on composite impact damage and compression strengthThe effects of composite stacking sequence, thickness, and percentage of zero-degree plies on the size, shape, and distribution of delamination through the laminate thickness and on residual compression strength following impact were studied. Graphite/epoxy laminates were impacted with an 0.5 inch diameter aluminum sphere at a specific low or high velocity. Impact damage was measured nondestructively by ultrasonic C-scans and X-radiography and destructively by the deply technique, and compression strength tests were performed. It was found that differences in compression failure strain due to stacking sequence were small, while laminates with very low percentages of zero-degree plies had similar failure loads but higher failure strains than laminates with higher percentages of zero-degree plies. Failure strain did not correlate with planar impact damage area, and delaminations in impact regions were associated with matrix cracking.
Document ID
19850048095
Document Type
Conference Paper
Authors
Guynn, E. G. (NASA Langley Research Center; Kentron International, Inc. Aerospace Technologies Div., Hampton, VA, United States)
Obrien, T. K. (NASA Langley Research Center; U.S. Army, Research and Technology Laboratories, Hampton VA, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1985
Subject Category
COMPOSITE MATERIALS
Report/Patent Number
AIAA PAPER 85-0646
Meeting Information
Structures, Structural Dynamics, and Materials Conference(Orlando, FL)
Distribution Limits
Public
Copyright
Other