An aircraft wing skin panel which can be modeled as a semi-infinite plate, has an edge crack
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Question:
An aircraft wing skin panel which can be modeled as a semi-infinite plate, has an edge crack of length 0.25 mm and is subjected to typical cyclic service loads. The component of those loads that act to propagate the crack can be simplified to constant amplitude stress loading of 200 N/mm 2 normal to the crack. If the panel is made from a metal alloy with fracture toughness of 3000 N/mm 1/2 and a crack growth rate of 35 × 10 -15 (ΔC) 4 mm/cycle, determine the maintenance interval required to detect the crack before it grows to half its critical length.
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