13th International Conference on Fracture June 16–21, 2013, Beijing, China -5- of fiber layer thickness H. Figure 3. Cure cycle of the splices in a fiber metal laminate Table 1. Material properties of the materials in the spliced fiber metal laminate Materials E1 E2 E3 ν12 ν13 ν23 G12 Aluminum 72000 72000 72000 0.33 0.33 0.33 27067.67 Epoxy Resin 3200 3200 3200 0.49 0.49 0.49 1073.83 Composite 24600 24600 24600 0.025 0.363 0.025 1145 Table 2. Thermal expansion coefficients of the materials in the spliced fiber metal laminate Materials α1(/°C) α2(/°C) α3(/°C) Aluminum 1.881×10-5 1.881×10-5 1.881×10-5 Epoxy Resin 5×105 5×105 5×105 Composite 6.443×10-6 41.482×10-6 6.443×10-6 4. Fracture criterion of splices in a fiber metal laminate Due to the symmetric feature of the structure, only one fourth of the structure is considered in the analysis. Fig. 7 illustrates the structure for FEM analysis and its boundary conditions. To solve the stress fields at the interface edge o, a 5-node super wedge tip element is used at this point, around which two-dimensional four-node element elements are used. Plane strain assumption is used in all numerical calculations. Figure 4. Tensile test apparatus of the spliced fiber metal laminate
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