Abstract
The behaviour of a thin tensioned sheet with an opening has been the subject of a number of recent investigations. In this type of problem, as in an aircraft structure, a skin carries all or some of the in-plane load as well as a lateral pressure load. Failure often results from the development of fatigue cracks which propagate from a stress concentration at the cut-out being subjected to structural vibration excited by acoustic pressure fluctuations. The Comet disaster in 1954 was due to the structural failure of the pressure cabin, brought about by the development of fatigue cracks from high stress concentration regions around the corners of the windows. The cases of statically tensioned, uniaxially and biaxi-ally loaded plates having a central crack subjected to acoustic excitation have been studied. These investigations were concerned with the basic features of plate vibration; i.e., mode shapes at a resonance frequency, the resonance frequency versus load behaviour and the crack propagation rates.
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