Page 240 - Plastics Engineering

Mechanical Behaviour of Composites 223

X - strains X - stresses
-0.378% 0

0 0.378% 0 13.25

Y - strains Y - stresses
Fig. 3.26 Stresses and strains, Example 3.15

3.13 Analysis of Non-symmetric Laminates
Example 3.16 A unidirectional carbon fibre/PEEK laminate has the stacking
sequence [0/352/-352]~. If it has an in-plane stress of a, = 100 MN/m2
applied, calculate the strains and curvatures in the global directions. The
properties of the individual plies are
El = 145 GN/m2, E2 = 15 GN/m2, G12 = 4 GN/m2, u12 = 0.278

Each ply has a thickness of 0.1 mm.