Analysis of Non-symmetric Laminates

Example 3.16 A unidirectional carbon hbre/PEEK laminate has the stacking sequence [O/SSa/—352]t- If it has an in-plane stress of = 100 MN/m applied, calculate the strains and curvatures in the global directions. The properties of the individual plies are 

Solution This stacking sequence is similar to that in Example 3.11 except that in this case the laminate is not symmetrical. As shown in Fig. 3.27, the centre line of the laminate is in the middle of one of the plies and 

The approach is the same as before. Q must be determined for each layer as shown below and thus the values in the A, B and D matrices. 

In this case [fl] 0 and so [a] and [d cannot be obtained by inverting the [A] and [D] matrices respectively. They must be obtained from 

The in-plane strains and the moments and curvatures are all linked in this non-symmetrical lamina and are obtained from 

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