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Journal of Composite Materials
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Modeling Transversely Loaded Metal–Matrix Composites

S. Naboulsi

Department of Aeronautics and Astronautics, Air Force Institute of Technology, AFIT/ENY Bldg. 640, 2950 P St., Wright-Patterson Air Force Base, OH 45433-7765, USAsnabouls{at}afit.af.mil

The motivation behind the present work is to model the response of a transversely loaded unidirectional metal–matrix composite (MMC), which constitutes thermal residual stresses, debond, and viscoplasticity. Based on experimental observation of transversely loaded MMC, debond causes reductions in the global stiffness. To capture the influence of debond on the MMC response, a mechanism, which models the debond characteristics including the debond damage, is required, and it is the focus of the present investigation. A reduced order model to investigate transversely loaded MMC is presented. Its formulation is based on modeling the unit cell as a finite number of strips where an averaged approach is used to compute the global response of the MMC. The governing equations for the strips are based on a uniaxial thermo-mechanical assumption. A special debond mechanism between the fiber and matrix is included in the formulation. The constitutive relations incorporated in the model are the unified Bodner–Partom viscoplastic model and power law models. The technique is validated with experimental data for Ti–6Al–4V/SCS-6 composite under various operating temperatures and mechanically applied loads, and it shows good agreement.

Journal of Composite Materials, Vol. 37, No. 1, 55-72 (2003)
DOI: 10.1177/0021998303037001468
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