Improved stress intensity factor solution for cracks in panels with arbitrarily located stringers

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DOIResolve DOI: http://doi.org/10.2514/6.2012-1699
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TypeArticle
Proceedings title53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Series titleCollection of Technical Papers
Conference53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, 23 April 2012 through 26 April 2012, Honolulu, HI
ISSN0273-4508
ISBN9781600869372
Article numberAIAA 2012-1699
SubjectA-center; Closed form solutions; Crack location; Edge cracks; Linear statics; Poisson's effects; Cracks; Locks (fasteners); Stress intensity factors; Structural dynamics; Stringers
AbstractThis paper presents a stress intensity factor solution for cracks located in panels reinforced with arbitrarily located stringers. The new solution was developed by modifying the constituting equations of a solution for symmetrically and periodically spaced stringers with riveted rigid fasteners. The new solution supports arbitrary stringer locations with respect to the crack location, includes the capability to model compliant fasteners, improves the accuracy of the equivalent stringer compliance by considering Poisson's effect, and allows the fasteners to be arbitrarily located within each stringer. The stress intensity factors calculated using the new closed-form solution were compared to linear static finite element analysis results and very good agreement was obtained for the tested cases. Through two examples for the CC-130 aircraft, it was shown that the closed-form solution developed for a center crack in an infinite sheet could also be used to model an edge crack growing in a relatively large panel.
Publication date
PublisherAmerican Institute of Aeronautics and Astronautics
LanguageEnglish
AffiliationNational Research Council Canada (NRC-CNRC); Aerospace
Peer reviewedYes
NPARC number21269191
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Record identifierfe6d58d2-0fcc-4f51-87a4-53811e359713
Record created2013-12-12
Record modified2017-06-06
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