Abstract
Finite element analysis of carbon-epoxy (Unidirectional lamina) composite laminate is carried out for stress-strain relationship in the rectangular cross-section utilizing ANSYS 14.2. Tsai-Wu failure theory based on (Goldenblat and Koponov’s work) in-plane stress for maximum stress-strain in laminate are incorporated in the analysis. The final analysis gives the maximum stress and maximum strain in the composite laminate. ANSYS ACP is employed to model composite plate of three lamina using 60 degree angle lamina of carbon-epoxy (UD). Under investigation it is found that the layer wise maximum strain is 6.2406e−04 which is in the first layer and maximum stress is 41.946 MPa which is in the second layer. Also shear strain is 4.9813e−04 and shear stress is 13.01 MPa.
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