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Calculate the resulting midplane strains and curvatures of a [0%/-45/902/+45/0] (the notation is from bottom to top ply) laminate loaded with a force Nx-150
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Calculate the resulting midplane strains and curvatures of a [0%/-45/902/+45/0] (the notation is from bottom to top ply) laminate loaded with a force Nx-150 kN/m. The plies are 0.375 mm thick and have the following stiffness properties: E 11-132 GPa, E 22=16 GPa, G12=4.5 GPa, v12=0.28 Calculate the resulting strains in the middle of the top and bottom plies.
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Laminate stacking sequence 045902450 Ply thickness 0375 mm Nx a...
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College Physics
Authors: Jerry D. Wilson, Anthony J. Buffa, Bo Lou
7th edition
9780321571113, 321601831, 978-0321601834
