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Abstract Aircraft composites structures are typically made using stiffened skin construction as it provides a minimum weight solution to many design problems. However, designers are reluctant to allow composite stiffened… Click to show full abstract
Abstract Aircraft composites structures are typically made using stiffened skin construction as it provides a minimum weight solution to many design problems. However, designers are reluctant to allow composite stiffened structures to operate in the post-buckled load regimes due to their poor inter-laminar properties. The post-buckling response of cocured composite stiffened panels is explored by experiments and numerical simulations. An integrated progressive damage finite element model is presented which captures inter and intra-laminar failures in panels. Detailed analysis of measured experimental structural responses in terms of strain, deformations, the failure mode is carried out and validated from the numerical analysis.
Journal Title: Mechanics of Advanced Materials and Structures
Year Published: 2019
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