Buckling and compressive strength of laminates with optimized fibre-steering and layer-stacking for aerospace applications
Abstract
The primary objective of design in aerospace composites is to minimize weight for a given loading requirement. For thin laminates subject to compression, this means ensuring sufficient buckling stiffness whilst maintaining material strength in the presence of in-service damage. In effect, stress levels (i.e. applied running load/laminate thickness) are maximized subject to buckling and strength requirements. Where buckling stresses for lightly loaded (thin) panels are relatively low, increased stiffening could be used to reduce effective panel widths but this comes with increased ...
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