* A [020/9020]s IM7/8552 Carbon/Epoxy laminate has the following lamina properties: E11 = 22.8 Msi, E22...

 

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* 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, ₂ = 30 + 10-6-¹ 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" * 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, ₂ = 30 + 10-6-¹ 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. * 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, ₂ = 30 + 10-6-¹ 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" N PELL 90 40 D t ts 0.1"

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