Fatigue performance of aircraft panels with novel skin buckling containment features

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To increase structural efficiency of stiffened panels in an aircraft, it is plausible to introduce skin buckling containment features to increase the local skin stability and thus static strength performance. Introducing buckling containment features may also significantly influence the fatigue crack growth performance of the stiffened panel. This study focuses on the experimental demonstration of panel durability with skin bay buckling containment features. Through a series of fatigue crack growth tests on integrally machined aluminium alloy stiffened panels, the potential to simultaneously improve static strength performance and crack propagation behaviour is demonstrated. The introduction of prismatic buckling containment features which have yielded significant static strength performance gains have herein demonstrated potential fatigue life gains of up to + 63 per cent.
Original languageEnglish
Pages (from-to)791-806
Number of pages16
JournalProceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
Issue number7
Publication statusPublished - Jul 2011

ASJC Scopus subject areas

  • Aerospace Engineering
  • Mechanical Engineering


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