ABSTRACT
The flexural stiffness of symmetric sandwich laminates with honeycomb core and multidirectional composite facing will be covered. The strain in the laminate is assumed to be proportional to the curvature. Flexural stiffness can then be defined in terms of the modulus and compliance and the moment-curvature relation. The contribution of the core and the effect of stacking sequence on the flexural modulus can be described by explicit formulas. For design optimization the components of modulus are therefore easier to use than those of compliance and equivalent engineering constants. https://s3-euw1-ap-pe-df-pch-content-public-p.s3.eu-west-1.amazonaws.com/9780203750148/388f19dd-fb28-47ec-8e98-b8cab140a50c/content/page167_a.tif"/>
