* A [020/9020]s IM7/8552 Carbon/Epoxy laminate has the following lamina properties: E11 = 22.8 Msi, E22 = 1.3 Msi, 012 = 0.3, G12 = 0.8 Msi, a1 = 0, = 30 + 10-6- Laminate cure temperature is 350 F and ambient room temperature is 72 F. The cured ply thickness is 0.005 in. Use the classical lamination theory to calculate the deformation of the laminate and thermal residual stresses in the plies. Solution: Exx = Eyy = = = -0.0019.011= - 42 ksi, 022 = 7.6 ksi, 1- fiber direction, 2- transverse (90) direction. N PELL 90 40 D t ts 0.1"