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Quasi-static and Fatigue Delamination at Tape/Fabric InterfacesThe relationship between quasi-static and fatigue delamination of a fabric/tape interface is examined experimentally and numerically.Mixed-mode bending tests were conducted using specimens in which a mid-plane delamination is bound between a ply of 0-degree unidirectional tape and a 0-degree fabric ply of the same material system. The experimental results indicate that delaminations tend to migrate towards the constraining ply that is on the compressive side of the laminate in bending, and that the fracture toughness for a fabric-constrained delamination is almost twice that of a tape-constrained delamination. A cohesive model based on superposition of bilinear laws was used to account for these differences in measured properties. Fatigue analyses were conducted with a cohesive damage model that uses an idealization of stress-life diagrams used in engineering design. The fatigue model is shown to be capable of predicting the steady-state rate of delamination propagation described by the Paris law, as well as the initial transients that depend on the quasi-static R-curve effects. The analysis results help quantify the effects of fracture toughness and R-curves on the rates of delamination propagation in fatigue.
Document ID
20200002784
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Davila, Carlos G.
(NASA Langley Research Center Hampton, VA, United States)
Ratcliffe, James
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
April 20, 2020
Publication Date
January 6, 2020
Subject Category
Composite Materials
Report/Patent Number
NF1676L-33239
Report Number: NF1676L-33239
Meeting Information
Meeting: AIAA SciTech 2020
Location: Orlando, FL
Country: United States
Start Date: January 6, 2020
End Date: January 10, 2020
Sponsors: American Institute of Aeronautics and Astronautics (AIAA)
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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