A comprehensive approach to the continuous damage of materials is formulated within the framework of thermodynamic reasoning. Particular emphasis is put on the application to composites. The starting point lies in the assumption that damage evolution can be described at the macroscopic scale by mean
Micromechanical approach to damage mechanics of composite materials with fabric tensors
โ Scribed by G.Z. Voyiadjis; Z.N. Taqieddin; P.I. Kattan
- Publisher
- Elsevier Science
- Year
- 2007
- Tongue
- English
- Weight
- 498 KB
- Volume
- 38
- Category
- Article
- ISSN
- 1359-8368
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โฆ Synopsis
The purpose of this study is to apply continuum damage mechanics -introduced through the concept of fabric tensors -to composite materials within the framework of the theory of elasticity. A directional data model of damage mechanics for composite materials will be developed using fabric tensors. The introduction of fabric tensors into the analysis of damage of composite materials will allow for an enhanced and better understood physical meaning of damage. The micromechanical approach will be used here to relate the damage effect through fabric tensors to the behavior of composite materials. In this approach, damage mechanics is introduced separately to the constituents of the composite material through different constituents' damage effect tensors. The damaged properties of the composite system as a whole can then be obtained by proper homogenization of the damaged properties of the constituents.
The derivation of a generalized formulation of damage evolution will be shown here in a mathematically consistent manner that is based on sound thermodynamic principles. Numerical examples will be presented to show applicability. In addition, damage evolution for the one-dimensional tension case is also illustrated.
๐ SIMILAR VOLUMES
The first ply failure in composite laminates are studied by 3-D fracture mechanic approach. The fracture model is based on a crack embedded in one of the inner layers. Numeriil results for the case of "angle ply" laminates are based on a general 3-D finite difference progtam. Stress intensi~ factor