Due to recent interest in using composites for primary structural components of commercial aircraft, there is a need to develop methodology for the fail-safe design of large composite panels. An economical fail-safe structure must sustain a high groos stress with a large damaged zone such as a two-bay-crack. The purpose of this paper is to derive analytical formulae for the stress distribution ahead of a large damaged zone in a curved composite panel. The stress distribution is linked with either a stress intensity factor or a stress concentration factor since they can be easily obtained from Handbooks. The derived formulae are based on Lekhnitskii's solution with two extra assumptions and are verified by both experiments and finite element analysis. The derived formulae can also be applied to the design of buffer strips in composite curve panels.
Formulae for the stress distribution ahead of a damaged zone in composite curved panels
Formel für die Spannungsverteilung vor dem beschädigten Bereich einer gekrümmten Verbundwerkstoffplatte
1995
11 Seiten, 19 Bilder, 3 Tabellen, 17 Quellen
Aufsatz (Konferenz)
Englisch
Formulae for the Stress Distribution Ahead of A Damages Zone in Composite Curved Panels
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