Nonlinear modeling of the failure of a graphite epoxy under a three-point bending test

Abstract

The application of modeling theories and the choice of failure criteria are difficult in part because they are too varied and must be validated by biaxial tests, which are expensive to be performed. This article is devoted to the nonlinear modeling and failure criteria which are employed in the design and analysis of anisotropic materials. Indeed, in this work, a study of the macroscopic and microscopic behavior of a graphite epoxy under a three-point bending test is conducted, and the successive failures are also predicted. Experimentally, the damage progression and the effect of geometrical parameters are followed and identified in detail. The analytical modeling is based on a recently developed approximation for isotropic materials. This approximation is also valid for the studied quasi-isotropic laminated composite. A software program has been elaborated for the application of the most general failure criteria. The results obtained by this analytical modeling show a good correlation with those of the experimental study.

Flexural behaviour modelling of carbon/epoxy laminates using the puck-EWM approach

“…They used a mixed methodology based on a theoretical and experimental approach to developing a procedure for the selection and validation of the failure criterion. Y. Benbourass et al [16] have performed several three-point bending tests on a typical stacking sequence used in composite structures. The effect of different thickness ratios (l/h) on the behaviour and the failure modes of these specimens have been considered.…”

3D finite element analysis of laminated composites under three-point bending

“…The 3D FEA and 3D version of a Classical Laminate Theory (CLT) were adapted to examine the stress distribution under bending loads. Benbouras et al [21,22] used a recently established approximation formalism for isotropic materials to model the nonlinear behavior of laminated composite beams [21]. The global average stresses approach and the apparent flexural modulus method are used to obtain the laminate's equivalent longitudinal Young-modulus.…”

“…The global average stresses approach and the apparent flexural modulus method are used to obtain the laminate's equivalent longitudinal Young-modulus. A software program is developed to anticipate damage development using the most general failure criteria [22]. The authors [23] studied the successive failures and the effect of the thickness ratio on nonlinear behavior of a composites laminates reinforced with carbon/epoxy woven fabrics, It was discovered that successive failures are dependent on the stacking sequence, with orthogonal sequences having a considerable impact on plies delamination.…”

An analytical and experimental study of the nonlinear behaviour of a carbon/epoxy under a three-point bending test

“…Two methods are used to calculate the equivalent longitudinal Young-modulus of the laminate: (i) the global average stresses method and (ii) the apparent flexural modulus method. To predict the damage progression, Benbouras et al elaborated a software program for the application of the most general failure criteria [20]. Irhirane et al in [21][22][23] used two approaches: (i) the first one is based on the first-order shear deformation theory (FSDT) and (ii) the second is a finite element model.…”

“…However, these methods have an application complexity with a large number of unknowns to be determined. Benbouras et al [19, 20] modelled the nonlinear behaviour of the quasi-isotropic laminated composite by an approximation formalism that has been recently developed for isotropic materials [19]. Two methods are used to calculate the equivalent longitudinal Young-modulus of the laminate: (i) the global average stresses method and (ii) the apparent flexural modulus method.…”