Stress intensity factor solution for cracks in panels with arbitrarily located stringers

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DOIResolve DOI: http://doi.org/10.2514/1.C032159
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TypeArticle
Journal titleJournal of Aircraft
ISSN0021-8669
Volume50
Issue6
Pages17871805; # of pages: 19
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 constitutive 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. For the tested cases, the difference between the stress intensity factors calculated using the new closed-form solution and the linear static finite-element analysis results were within 4%. 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. © 2012 AIAA.
Publication date
LanguageEnglish
AffiliationNational Research Council Canada (NRC-CNRC); Aerospace (AERO-AERO)
Peer reviewedYes
NPARC number21270932
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Record identifier5f898a7f-9eb4-45e2-b484-b33427dd241d
Record created2014-02-18
Record modified2016-05-09
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