a) Describe the progressive failure process which would occur in a symmetric cross-ply laminate loaded in fatigue by an Nx. In this discussion you should include comments related to local delaminations near free edges and the stresses which would cause these. b) Briefly explain the approach (equations will suffice) to determine Young's Modulus for a multilayer composite laminate in the x-direction (Ex). c) In ultimate laminate failure theory we replace the stiffness in the 1 direction with Q11 and replace all other non-zero stiffness Q values with a small number (e.g. 1). Briefly explain (1-2 sentences) why reducing all but the Q11 values is an acceptable approach.