HW2-solution - Aerospace Structural Composites I Homework 2...

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Aerospace Structural Composites I Homework 2 Anirban Chaudhuri 1. Material A has Young's modulus of 10 million psi, and a shear modulus of 3.7 million psi. Material B has a Young's modulus of 20 million psi, and a Poisson's ratio of 0.5. Design a laminate made of the two materials, with total thickness of 0.5 inches, with maximum Young modulus, so that its Poisson's ratio is not larger than 0.4. Solution: E A = 10e6 psi, G A = 3.7e6 psi; E B = 20e6 psi, B = 0.5; h = 0.5 in. Poisson’s ratio for the material A, A = E A /(2G A ) – 1 = 0.3514 [considering isotropic material] Let the thickness of material A be t A . So, the thickness of material B is t B = h – t A . The terms in A-matrix for the composite are shown in equation (1). 11 22 22 12 11 AB AA BB EE A At t Att     …(1) Now, the effective Young’s modulus of the laminate has to be maximized, so that the effective Poisson’s ratio is not greater than 0.4. The optimization problem that needs to be solved is given in equation (2) with the design variable as t A . , 0.4 A eff t eff E Subject to Max …(2) where, 2 11 22 12 22 12 22 1 eff eff A E hA A A    The above optimization problem is then solved in MATLAB using the fmincon command. The code used to solve the problem is given in the Appendix I. After solving the optimization problem, the thickness of material A is found to be 0.4139 in. Thus the thickness of material B is 0.0861 in .
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This note was uploaded on 06/06/2011 for the course EAS 4240 taught by Professor Peterifju during the Spring '08 term at University of Florida.

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HW2-solution - Aerospace Structural Composites I Homework 2...

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