Accession Number N20130013161
Title Prediction of Composite Laminate Strength Properties Using a Refined Zigzag Plate Element.
Publication Date Apr 2013
Media Count 12p
Personal Author A. Barut A. Tessler E. Madenci
Abstract This study presents an approach that uses the refined zigzag element, RZE(exp2,2) in conjunction with progressive failure criteria to predict the ultimate strength of composite laminates based on only ply-level strength properties. The methodology involves four major steps: (1) Determination of accurate stress and strain fields under complex loading conditions using RZE(exp2,2)-based finite element analysis, (2) Determination of failure locations and failure modes using the commonly accepted Hashin's failure criteria, (3) Recursive degradation of the material stiffness, and (4) Non-linear incremental finite element analysis to obtain stress redistribution until global failure. The validity of this approach is established by considering the published test data and predictions for (1) strength of laminates under various off-axis loading, (2) strength of laminates with a hole under compression, and (3) strength of laminates with a hole under tension.
Keywords Composite materials
Compressive strength
Degradation
Failure analysis
Failure modes
Finite element method
Laminates
Stiffness
Stress analysis


 
Source Agency National Aeronautics and Space Administration
NTIS Subject Category 71F - Composite Materials
Corporate Author National Aeronautics and Space Administration, Hampton, VA. Langley Research Center.
Document Type Conference proceedings
Title Note N/A
NTIS Issue Number 1323
Contract Number N/A

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