A symmetric [0/90/0] laminate is 0.75mm thick (0.25mm thick for each lamina) and it is full compliance matrix is given below: [ ]^-1=[ ] in which,A'=[ ] [GPa mm]^-1, B' = 0, D' = [ ] [GPa mm^3]^-1. o 0 4.016 and the stiffness matrix associated with th 0 degree lamina is [Q]=[ ]GPa If the single bending moment per unit length Mx=0.1GPa MM^2 is applied to the laminate,
(a) determine the stresses associated with the x and y axes on the top surface of the laminate and
(b) determine the stresses with the x and y axes on the middle surface of the laminate.
A [0/90/0], laminate consisting of AS/3501 carbon/epoxy lamiae is subjected to uni-axial loading along the x-direction. Use the Maximum Strain Criterion to find the loads corresponding to first ply failure and ultimate laminate failure; then plot the load-strain curve up to failure. For AS/3501 carbon/epoxy lamiae, the lamina engineering constants are: E1=138GPa, E2 = 9GPa, G12 = 6.9GPa, v12 = 0.3, vf = 0.65 .The thickness of each lamina is 0.25mm.