TY - GEN

T1 - A direct micromechanical failure analysis of textile composites

AU - Karkkainen, R. L.

AU - Sankar, B. V.

AU - Tzeng, J. T.

N1 - Copyright:
Copyright 2013 Elsevier B.V., All rights reserved.

PY - 2005

Y1 - 2005

N2 - A micromechanical analysis of the representative volume element (RVE) of a plain weave textile composite has been performed using the finite element method. Two alternate methods for predicting failure envelopes are presented: a parametric ellipse-fitting scheme which accurately predicts trends in failure envelopes for a given failure space, as well as the formulation of a robust 27-term quadratic failure criterion to predict failure under any general plate loading conditions. A previous study by the authors extended a method, known as the Direct Micromechanics Method (DMM), to develop failure envelopes for a plain-weave textile composite under plane stress in terms of applied macroscopic stresses. The importance of consideration of stress gradient effects over the relatively large RVE dimensions of a textile microgeometry was illustrated, and it is assumed that the stress state is not uniform across the RVE. This is unlike most stiffness and strength models, which start with the premise that an RVE is subjected to a uniform stress or strain. The stress state is defined in terms of the well-known laminate theory load matrices [N], [M], i.e.force and moment resultants. Assuming that micro level failure criteria for the yarn and matrix are known, failure envelopes for a plain-weave textile composite have been constructed using the microstresses from finite element analysis of the RVE. The parametric ellipse-fitting method for predicting failure envelopes was found to agree with DMM results to within a few percent. The quadratic failure criterion was found to agree with DMM results within an average deviation of 9.3%, but the method is more robust in terms of its ability to accommodate general 6D plate loading conditions.

AB - A micromechanical analysis of the representative volume element (RVE) of a plain weave textile composite has been performed using the finite element method. Two alternate methods for predicting failure envelopes are presented: a parametric ellipse-fitting scheme which accurately predicts trends in failure envelopes for a given failure space, as well as the formulation of a robust 27-term quadratic failure criterion to predict failure under any general plate loading conditions. A previous study by the authors extended a method, known as the Direct Micromechanics Method (DMM), to develop failure envelopes for a plain-weave textile composite under plane stress in terms of applied macroscopic stresses. The importance of consideration of stress gradient effects over the relatively large RVE dimensions of a textile microgeometry was illustrated, and it is assumed that the stress state is not uniform across the RVE. This is unlike most stiffness and strength models, which start with the premise that an RVE is subjected to a uniform stress or strain. The stress state is defined in terms of the well-known laminate theory load matrices [N], [M], i.e.force and moment resultants. Assuming that micro level failure criteria for the yarn and matrix are known, failure envelopes for a plain-weave textile composite have been constructed using the microstresses from finite element analysis of the RVE. The parametric ellipse-fitting method for predicting failure envelopes was found to agree with DMM results to within a few percent. The quadratic failure criterion was found to agree with DMM results within an average deviation of 9.3%, but the method is more robust in terms of its ability to accommodate general 6D plate loading conditions.

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M3 - Conference contribution

AN - SCOPUS:84871012141

SN - 9781622762828

T3 - 20th Technical Conference of the American Society for Composites 2005

SP - 2220

EP - 2239

BT - 20th Technical Conference of the American Society for Composites 2005

T2 - 20th Technical Conference of the American Society for Composites 2005

Y2 - 7 September 2005 through 9 September 2005

ER -