The laminate described in Problem 7.15 has laminae that are \(0.25 \mathrm{~mm}\) thick and the stiffness matrix associated with the \(0^{\circ}\) lamina is given by

If a single bending moment per unit length \(M_{x}=0.1 \mathrm{GPa} \mathrm{mm} 2\) is applied to the laminate,

(a) determine the stresses associated with the \(x\) - and \(y\)-axes on the top surface of the laminate and

(b) determine the stresses associated with the \(x\) - and \(y\)-axes on the middle surface of the laminate.

Problem 7.15

A symmetric [0/90/0] laminate is \(0.75 \mathrm{~mm}\) thick and its full compliance matrix is given below:

where the units of the matrix are

Determine the following effective engineering constants for the laminate, giving both magnitude and units;

(a) the effective longitudinal Young's modulus, \(E_{x^{\prime}}(\mathrm{b})\) the effective transverse Young's modulus, \(E_{y^{\prime}}(\mathrm{c})\) the effective in-plane shear modulus, \(G_{x y}(\mathrm{~d})\) the effective longitudinal Poisson's ratio, \(v_{x y}\) and

(e) the effective flexural modulus, \(E_{\mathrm{fx}}\).

Transcribed Image Text:

138.8 2.7 0 [Q] = 2.7 8.965 0 GPa 0 0 7.1