In a typical structural application of a composite, multiple layers (or laminae) of unidirectional composites are stacked together at various angles to form a laminate. The stacking sequence and orientations of the individual layers give the laminate designer additional ‘degrees of freedom’ to ‘tailor’ or optimize the design with respect to strength, stiffness, buckling load, vibration response, panel flutter or other desired performance objective.


Individual Layer Unit Width Classical Lamination Theory Symmetric Laminate Panel Flutter 
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Copyright information

© Society for Experimental Mechanics 1989

Authors and Affiliations

  • Charles W. Bert

There are no affiliations available

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