Abstract
The objective of this chapter is the macromechanical analysis for a laminate consisting of two (bimaterial) or more laminae subjected to in–plane loads of tension, compression, shear, bending, and torsion. The analysis is conducted with the plane stresses assumption in the elastic regime. We derive stress–strain relationships in the local and global axes of each lamina (ply) using transformation of strains and stresses leading to the global response of the laminate and the related overall stiffness and compliance matrices. We calculate stresses and strains in each oriented or unidirectional ply considering the stacking position and loading configuration. The effects of the laminate coupling stiffness components on its global response is highlighted for particular stacking sequences.
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