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An Investigation on the Accuracy of Delamination Analysis Predictions for Unidirectional Laminate ConfigurationsThe state-of-the-art methodologies for predicting delamination growth in composite laminates make use of the concept of mixed-mode fracture mechanics. In mixed-mode fracture approaches the individual Mode I, Mode II and Mode III components of the strain energy release rate (SERR) need to be determined under general loading conditions. Through the use of mixed-mode fracture, the individual components are used in combination with the critical strain energy release rates (interlaminar fracture toughnesses) for each fracture mode in a mixed mode criterion in order to predict delamination extension. These interlaminar fracture toughnesses are traditionally obtained by testing of unidirectional laminate coupons. This work presents an investigation on the accuracy of Double Cantilever Beam (DCB), End Notch Flexure (ENF) and Mixed-Mode Bending (MMB) delamination analysis predictions by comparing measured total strain-energy release rates obtained experimentally to results for structural analysis from closed-form expressions, shell finite element analysis, and continuum two-dimensional (2D) and three-dimensional (3D) (solid) finite element analysis.
Document ID
20200003101
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Patrick Enjuto
(Boeing (United States) Chicago, Illinois, United States)
Gerald E Mabson
(Boeing (United States) Chicago, Illinois, United States)
Hangki Lee
(Boeing (United States) Chicago, Illinois, United States)
Ronald Krueger
(National Institute of Aerospace Hampton, Virginia, United States)
James Ratcliffe
(Langley Research Center Hampton, Virginia, United States)
Date Acquired
April 29, 2020
Subject Category
Composite Materials
Report/Patent Number
NF1676L-35125
Report Number: NF1676L-35125
Meeting Information
Meeting: 2020 AIAA SciTech Forum
Location: Orlando, FL
Country: US
Start Date: January 6, 2020
End Date: January 10, 2020
Sponsors: American Institute of Aeronautics and Astronautics
Funding Number(s)
WBS: 826611.04.07.01
Distribution Limits
Public
Copyright
Portions of document may include copyright protected material.
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