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A Progressive Damage Methodology for Residual Strength Predictions of Notched Composite PanelsThe translaminate fracture behavior of carbon/epoxy structural laminates with through-penetration notches was investigated to develop a residual strength prediction methodology for composite structures. An experimental characterization of several composite materials systems revealed a fracture resistance behavior that was very similar to the R-curve behavior exhibited by ductile metals. Fractographic examinations led to the postulate that the damage growth resistance was primarily due to fractured fibers in the principal load-carrying plies being bridged by intact fibers of the adjacent plies. The load transfer associated with this bridging mechanism suggests that a progressive damage analysis methodology will be appropriate for predicting the residual strength of laminates with through-penetration notches. A progressive damage methodology developed by the authors was used to predict the initiation and growth of matrix cracks and fiber fracture. Most of the residual strength predictions for different panel widths, notch lengths, and material systems were within about 10% of the experimental failure loads.
Document ID
19980201405
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Coats, Timothy W. (National Academy of Sciences - National Research Council Hampton, VA United States)
Harris, Charles E. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1998
Subject Category
Composite Materials
Report/Patent Number
NASA/TM-1998-207646
NAS 1.15:207646
L-17729
Funding Number(s)
PROJECT: RTOP 538-13-11-05
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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