Please analyze a laminated composite plate under tensile loads of equal to Nx=Ny=100N. - Layup: [0 0 0 0 90 90 90 90], (the laminate has 8 layers in total), Material properties: E 1_pr =50.6 GPa; E 2_pr =9.9 GPa; V12_pr =0.33; G12_pr =3.7 GPa; a1_pr=3.9e-6; a2_pr =49.7e-6; (Coefficients of thermal expansions) t pr=0.127mm (thickness of each layer) Q1. Using the analytic MATRIX calculations, please calculate the layers' stresses and strains of the laminate under loading cases A(mechanical) and B (thermal, if it is only under a temperature gradient of AT=-100°C.). Q2. For stress limits of the composite under consideration, use the following values for S-glass epoxy unidirectional composites: X (tensile)= 1.7 GPa, X (compressive)=-675 MPa, Y (tensile)= 35 MPa, Y (compressive)= -120 MPa, S (shear) =80 MPa, to consider an appropriate failure criterion.

Fig: 1