Please analyze a laminated composite plate under tensile loads of equal to N_(x)=N_(y)=100N.
Layup: [00009090 90 90], (the laminate has 8 layers in total), Material properties:
E_(1)_(p)r=50.6GPa;E_(2)_(p)r=9.9GPa;v_(12)_(p)r=0.33;G_(12) _pr = =3.7GPa; alpha _(1)_()pr =3.9e-6; alpha _(2)_()pr = 49.7e-6; (Coefficients of thermal expansions) tpr=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 Delta T=-100deg C.).
Q2. For stress limits of the composite under consideration, use the following values for S-glass epoxy unidirectional composites:
x (tensile) =1.7GPa,x (compressive) =-675MPa,
Y (tensile) =35MPa,Y (compressive)= -120MPa,
S (shear) =80MPa, to consider an appropriate failure criterion.
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: E1 pr=50.6GPa;E2pr=9.9GPa;V12pr=0.33;G12pr=3.7GPa 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 T=-100C.).
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)=35MPa,Y(compressive)=-120 MPa
S(shear)=80 MPa,to consider an appropriate failure criterion.
