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Determination of CTOD C in Fibre Metal Laminates by ASTM and Schwalbe Methods

DOI: 10.1590/S1516-14392002000200006

Keywords: fibre metal laminates, crack tip opening displacement, composites.

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fibre metal laminates (fmls) have arisen as a demand of the aeronautical industry to use thin sheets with high resistance to fatigue crack growth, high damage tolerance, corrosion resistance and high specific strength. considering these requirements, fmls are an advantageous choice when compared to metal alloys currently used. in order to employ fmls in aircraft structures, designers must hold a deep knowledge of a wide set of their properties including fracture toughness. the aim of this work was to evaluate the available methodologies to measure fracture toughness at instability (ctodc) in unidirectional fibre metal laminates reinforced with aramid fibres (arall?). to achieve this, tests were performed to obtain traditional and schwalbe ctods by using experimental astm based techniques, especially adapted to these laminates. results achieved point out that schwalbe method is more appropriate and also that there are differences between both ctod parameters.


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