Concepts for improving the damage tolerance of composite compression panelsThe results of an experimental evaluation of graphite-epoxy composite compression panel impact damage tolerance and damage propagation arrest concepts are reported. The tests were conducted on flat plate specimens and blade-stiffened structural panels such as those used in commercial aircraft wings, and the residual strength of damaged specimens and their sensitivity to damage while subjected to in-plane compression loading were determined. Results suggest that matrix materials that fail by delamination have the lowest damage tolerance, and it is concluded that alternative matrix materials with transverse reinforcement to suppress the delamination failure mode and yield the higher-strain value transverse shear crippling mode should be developed.
Document ID
19810048421
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Rhodes, M. D. (NASA Langley Research Center Hampton, VA, United States)
Williams, J. G. (NASA Langley Research Center Structures and Dynamics Div., Hampton, Va., United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1981
Subject Category
Composite Materials
Meeting Information
Meeting: Conference on Fibrous Composites in Structural Design