# STRESS AND FAILURE ANALYSIS OF A COMPOSITE MATERIAL SYSTEM Academic Essay

1. Write down the fibre and matrix material properties according to the selections. (1%) 2. Calculate the longitudinal Youngs modulus of the unidirectional lamina, E1 , using the mechanics of materials model. Assume there is no void in the composite. (1%) 3. Calculate the major Poissons ratio of the unidirectional lamina, ?? 12 , using the mechanics of materials model. (1%) 4. Calculate the transverse Youngs modulus of the unidirectional lamina, E2 , using the Halpin-Tsai equations. Assume the lamina is with square array of circular fibres. Note: Use E2 f instead of E f . (2%) 5. Calculate the in plane shear modulus of the unidirectional lamina, G12 , using the HalpinTsai equations and the Hewitt-Malherbe modification. (2%) 6. Calculate the longitudinal tensile strength of the unidirectional lamina, u ?? 1t . (2%) 7. Calculate the transverse tensile strength of the unidirectional lamina, u ?? 2t , using the maximum tensile stress criterion. Neglect the residual stresses in the matrix. Note: Use E2 f instead of E f . (2%) 8. Calculate the transverse compressive strength of the unidirectional lamina, u ?? 2c . Neglect the residual stresses in the matrix. (1%) 9. Calculate the in plane shear strength of the unidirectional lamina, u 12 ?? . (2%) 10.Write a table of the elastic and strength properties of the unidirectional lamina, including E1 , E2 , ?? 12 , G12 , u ?? 1t , u ?? 1c , u ?? 2t , u ?? 2c and u 12 ?? . Assume the longitudinal compressive strength u t u ?? 1c ?® ?? 1 . (1%) 11.Find the reduced compliance matrix [S] of the unidirectional lamina. (3%) 12.Find the reduced stiffness matrix [Q] of the unidirectional lamina. (2%) SCHOOL of ENGINEERING Page vi of vii 13.Draw the stacking sequence of the laminate to be studied according to the selections. (1%) 14.Draw the flowchart for the first / second ply failure analysis of the laminate based on the maximum stress failure theory. (4%) 15.Find the transformed reduced stiffness matrices ( ) [ ] Q k for each layer k . Note: ( 4 ) ( ) 4 4 1 2 2 2 1 2 1 1 2 2 6 6 Q ?® Q ?? Q ?? Q s c ?? Q c ?? s . (6%) 16.Find the laminate stiffness matrices [A], [B] and [D]. (6%) 17.Calculate the unit forces acting on an element of the cylindrical shell, ??N?®x??y . Nx ?® ?? xh, Ny ?® ?? yh and Nxy ?®?? xyh ; ??M?®x??y can be considered as zero in this case. (3%) 18.Calculate the mid-plane strains in the laminate, ?? ?®x??y 0 ? . (3%) 19.Calculate the curvatures in the laminate, ?????®x??y . (3%) 20.Calculate the global strains, ?? ?®x??y ? , at the surfaces of each lamina. (3%) 21.Calculate the global stresses, ?????®x??y , at the surfaces of each lamina. (3%) 22.Draw figures and show the variations of the global strains and the global stresses through the thickness of the laminate. (12%) 23.Find the local stresses, ?????®1??2 , at the surfaces of each lamina. (3%) 24.Find the maximum value of S0 for the first ply failure. State which layer, which surface is damaged for the first ply failure, and what failure mode is it. Use the maximum stress failure theory. (11%) 25.Find the maximum value of S0 for the second-ply failure of the laminate. State which layer, which surface and what failure mode it is for the second-ply failure in the laminate. Use the fully discounted method. Use the maximum stress failure theory. (12%) 26.Clarity and neatness of the coursework will possess 10% of the full marks PLACE THIS ORDER OR A SIMILAR ORDER WITH US TODAY AND GET AN AMAZING DISCOUNT