A [0/90/0]s laminate consisting of 0.25 -mm-thick unidirectional AS/3501 carbon/epoxy laminae is subjected to tensile uniaxial loading along the x-direction. Using the maximum strain criterion, find the loads corresponding to first ply failure and subsequent ply failures; then plot the load-strain curve up to failure. Assume all ply stiffnesses equal to zero for failed plies. Typical Values of Lamina Engineering Constants for Several Composites Having Fiber Volume Fraction vf Typical Values of Lamina Strengths for Several Composites at Room Temperature