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dc.contributor.authorSeneviratne, Waruna P.
dc.contributor.authorSaseendran, Vishnu
dc.contributor.authorShafie, Mohamed Z.
dc.contributor.authorTomblin, John S.
dc.date.accessioned2021-12-16T18:18:56Z
dc.date.available2021-12-16T18:18:56Z
dc.date.issued2021-09-01
dc.identifier.citationSeneviratne, Waruna & Saseendran, Vishnu & Shafie, Mohamed & Tomblin, John. (2021). Skin/Stringer Interface Damage Characterization of Stiffened Composite Structures. 10.12783/asc36/35929.en_US
dc.identifier.issn978-171383759-6
dc.identifier.urihttps://doi.org/10.12783/asc36/35929
dc.identifier.urihttps://soar.wichita.edu/handle/10057/22407
dc.descriptionClick on the DOI link to access the conference paper (may not be free).en_US
dc.description.abstractWith stiffened composite panels being widely used in aerostructures, critical failure mechanics of the skin/stringer interface need to be thoroughly understood. The interface is design critical and must demonstrate the ability to sustain design limit load throughout the service life. Buckling and out-of-plane deformations, localized in a stiffened panel can initiate separation at the interface. In addition, presence of inherent manufacturing flaws or operational impact events can lead to premature separation and result in failure. Hence, to ensure structural integrity, thorough damage characterization of skin/stringer interface must be performed. The general building block certification approach used for analysis and test validation does not contain standardized test methods beyond the coupon level. In this study, a Seven-Point Bend (7PB) based test methodology is employed to induce localized buckling-based skin separation. The 7PB methodology is utilized to evaluate panels fabricated using both co-bonding and secondary-bonding methods. The experimental work is complimented by a cohesive zone model (CZM) where the disbond initiation and progressive damage growth at the skin/stringer interface is simulated. Delamination is observed at the interface, originating centrally and progressing asymmetrically along the length of the stringer until failure occurred. The zero-thickness cohesive elements based model implemented within this work was able to capture damage initiation and predicted the final damage map. The 7PB test methodology is demonstrated to be robust and can be introduced as a standard test practice to evaluate sub-elements.en_US
dc.description.sponsorshipThis research was funded by the FAA William J Hughes Technical Center, in Atlantic City, NJ, under Cooperative Agreement Number 12-C-AM-WISU. The authors would like to thank Dr. Larry Ilcewicz and Ms. Cindy Ashforth of the FAA Seattle Aircraft Certification Office as well as Dr. Ahmet Oztekin of the FAA William J. Hughes Technical Center for their technical guidance. The authors would also like to thank the NIAR Composites and Structures Laboratory staff for their support in fabrication, testing, and data reduction. Facts and opinions are solely the personal statements of the authors and do not necessarily represent the views of the sponsoring agency.en_US
dc.language.isoen_USen_US
dc.publisherDEStech Publicationsen_US
dc.relation.ispartofseriesASC 36th Technical Conference, 2021;
dc.subjectStringeren_US
dc.subjectCohesive modelen_US
dc.subjectDelaminationen_US
dc.subjectCurved panelen_US
dc.subjectFracture toughnessen_US
dc.subjectCertificationen_US
dc.subjectImpacten_US
dc.subject7PBen_US
dc.titleSkin/stringer interface damage characterization of stiffened composite structuresen_US
dc.typeConference paperen_US
dc.rights.holder© 2021 36th Technical Conference of the American Society for Composites 2021: Composites Ingenuity Taking on Challenges in Environment-Energy-Economy, ASC 2021. All rights reserved.en_US


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