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Issue: June 2006, page: 7
Finite element analysis predicts crack propagation in panels
One of the main failure modes for the skin of composite panels used on aircraft is buckling. Stringers are often bonded to the panel skins to help increase the buckling strength; however, if there is a defect in the bond between the stringer and the panel, the structure may still be weakened. Developing analysis tools that can accurately simulate the behaviour of composites in this application is therefore critical to the successful design and use of such structures.
