You conduct a mechanical test on a composite laminate specimen with a lay-up of [0/60/- 60/90]s...

 

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You conduct a mechanical test on a composite laminate specimen with a lay-up of [0/60/- 60/90]s and a rectangular cross-section of 30 mm (width) x 8 mm (thickness). Each ply is the same thickness and each ply is the same material. The specimen was subjected to in-plane deformation and constrained such that only deformation in the x-direction was permitted. A design axial strain of & = 0.002 was applied with the y- and xy-directions constrained. Part A (30): Assuming E1 = 100 GPa, E2 = 15 GPa, G12 = 8 GPa, V12 = 0.30, calculate the ply-by-ply stresses and strains in each ply's local coordinate system. Part B (60): Calculate safety factors for each ply using non-interactive theories (maximum stress, maximum strain), and interactive theories (Tsai-Hill, Tsai-Wu failure theory with the Hoffman's criterion), using the following failure strength information for this material: (of)ult=1300 MPa (of uit = 1100MPa Jult (12)ult = 58 MPa ( )ult - = 244 MPa ()uit = = 40 MPa Part C (10): Calculate the maximum strain, &x, that can be applied using the most conservative failure theory. Bonus (10): Calculate the average in-plane stresses (x, y, xy) for the entire laminate resulting from the applied design strains. You conduct a mechanical test on a composite laminate specimen with a lay-up of [0/60/- 60/90]s and a rectangular cross-section of 30 mm (width) x 8 mm (thickness). Each ply is the same thickness and each ply is the same material. The specimen was subjected to in-plane deformation and constrained such that only deformation in the x-direction was permitted. A design axial strain of & = 0.002 was applied with the y- and xy-directions constrained. Part A (30): Assuming E1 = 100 GPa, E2 = 15 GPa, G12 = 8 GPa, V12 = 0.30, calculate the ply-by-ply stresses and strains in each ply's local coordinate system. Part B (60): Calculate safety factors for each ply using non-interactive theories (maximum stress, maximum strain), and interactive theories (Tsai-Hill, Tsai-Wu failure theory with the Hoffman's criterion), using the following failure strength information for this material: (of)ult=1300 MPa (of uit = 1100MPa Jult (12)ult = 58 MPa ( )ult - = 244 MPa ()uit = = 40 MPa Part C (10): Calculate the maximum strain, &x, that can be applied using the most conservative failure theory. Bonus (10): Calculate the average in-plane stresses (x, y, xy) for the entire laminate resulting from the applied design strains.

Answer rating: 100% (QA)

Part A 30 Ply 1 0 deg x1 x 0002 y1 v12x1 0003 xy1 0 x1 E1x1 1000002 200 MPa y1 E2y1 150003 45 MPa xy... View the full answer