On the analysis of composite structures with material and geometric non-linearities

摘要

If major weight saving is to be realised it is essential that composites be used in "primary" structural components, i.e., wing and fuselage skins. To this end it is essential that analytical tools be developed to ensure that composite structures meet the FAA damage tolerance certification requirements. For stiffened composite panels one potential failure mechanism is the separation of the skin from the stiffeners; resulting from excessive "through the thickness" stresses.