= 2. A 4-ply composite laminate with lay-up sequence of [0/-15/+25/+45] is subjected to loads: Nx Ny =50 kN/m and Ns=25 kN/m. No moments are applied, so Mx, My and Ms are zero. Assume that each lamina is 2 mm thick. Write a MATLAB code to find the following: a. Extensional, coupling, and flexural stiffness matrices A, B and D from equations 4.56 & 4.67) b. Mid-plane strains and curvatures c. Strains and stresses at the top surface of the 25° ply (Hint - start d. Calculate the percentage of load Nx, Ny, and Ns taken by each ply (take ply stress or load values at the middle of that ply). Verify your solution by checking if the sums of Nx Ny and Ns from all plies equal the total applied values. S Use the properties for E glass/Epoxy lamina from table A.4, page 377 of the textbook. Please ignore the v21 value (0.06) provided. If you use the provided v12 and v21 in the Appendix, it will make the Q matrix non-symmetric. So please calculate v21 using the provided v12=0.28 and Betti's reciprocal theorem. For Q2, calculate the safety factors for each ply as per the Tsai Hill criterion. Which ply will break first according to this analysis? HINT: Use section 9.5 as a guide for sequence of steps (except in this assignment use Tsai Hill instead of Tsai Wu)

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