Start >> Lamination Theory >> Engineering Inplane Stiffness
The calculator computes the laminate inplane stiffness in terms of effective Young's modulus, Poisson's ratio, and shear modulus. Note that this representation is strictly correct only for orthotropic laminates. An orthotropic laminate requires that the number of plus theta angle plies equals the number of minus theta angle plies
Enter the layer material properties as a list {Ex, Ey, Gxy, nuxy}:
Enter a stacking sequence {theta1, theta2, ...}: Help on advanced stack entry
Check to tabulate expanded stacking sequence
Page History Notes
Copyright Materials Sciences Corporation, 2001