Print Email Facebook Twitter Skin-Stiffener Separation in T-Stiffened Composite Specimens in Postbuckling Condition Title Skin-Stiffener Separation in T-Stiffened Composite Specimens in Postbuckling Condition Author Zou, D. (TU Delft Aerospace Structures & Computational Mechanics) Bisagni, C. (TU Delft Aerospace Structures & Computational Mechanics) Date 2018-07-01 Abstract An experimental and numerical investigation was conducted to study the skin-stiffener separation of single T-shape stiffener specimens in postbuckling condition. Three specimens were manufactured with a centrally located Teflon insert, and were loaded in compression until collapse. Deformation patterns and separation evolution were monitored during the tests. To measure the full-field displacements and the strain distributions of the specimens, a digital image correlation (DIC) system was used. Skin-stiffener separation was observed and measured with an ultrasound system. Finite-element (FE) analyses were conducted to capture interlaminar damage mechanism based on the virtual crack closure technique. The numerical analysis accurately predicted the postbuckling deformation and the skin-stiffener separation behavior. The close correlation between the experimental and numerical results allows for further exploitation of the strength reserve in the postbuckling region and wider design options for the next generation of composite aircraft designs. Subject Composite stiffened structuresCompressionPostbucklingSkin-stiffener separationTests To reference this document use: http://resolver.tudelft.nl/uuid:76db8555-bb0e-45aa-a433-3a2436ad99a8 DOI https://doi.org/10.1061/(ASCE)AS.1943-5525.0000849 ISSN 0893-1321 Source Journal of Aerospace Engineering, 31 (4) Part of collection Institutional Repository Document type journal article Rights © 2018 D. Zou, C. Bisagni Files PDF ASENG_2059_R2a.pdf 1.8 MB Close viewer /islandora/object/uuid:76db8555-bb0e-45aa-a433-3a2436ad99a8/datastream/OBJ/view