Abstract
The postbuckling compressive strength and collapse phenomena of composite laminated cylindrical panels with various fiber angles and width-to-length ratios are characterized by the nonlinear finite element method. For the iteration and load increment along the postbuckling equilibrium path, a modified arc-length method in which the effect of stress unloading due to failure can be considered is introduced. In the progressive failure analysis, the maximum stress criterion and complete unloading model are used. Validity of present finite element results are verified by experiment for [0 3 /90] S cylindrical panel and [0/90/±45] S plate. The postbuckling compressive strength of composite laminated cylindrical panels is independent of the initial buckling stress but high in the panel with large value of the bending stiffness in axial direction. In several of the cylindrical panels, it is observed that the prebuckling compressive failures occur and directly result in collapse before buckling.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
