Abstract
A new class of three-dimensional fibre-metal laminates (3D-FMLs) was introduced recently. It offers exemplary performance compared to 2D-FML and laminated composites counterparts, especially when impact loading is of concern. However, similarly to all slender laminate composites, this hybrid composite is also susceptible to buckling and delamination when subjected to in-plane axial loadings, especially if the load is applied suddenly (impact). This is because of the inherent nature and relatively weak interlaminar strength of laminated composites. Moreover, there exist no design equations for establishing the buckling capacity of 3D-FMLs. Therefore, a set of simple semi-empirical equations is developed and proposed to aid practicing engineers to quickly and reliably evaluate the static and dynamic buckling capacities of slender 3D-FML components. The equations are developed by adjusting Euler’s buckling equations to account for the complex 3D-sandwich nature of 3D-FMLs and their inherent initial geometric imperfection, length, and the applied energy. Moreover, a statistical approach is utilized to develop a simple equation for establishing the impact buckling capacity of 3D-FMLs. The approach is based on the Face Centred Central Composite Design (FCCCD), used to produce also a simple and practical regression-based equation for evaluating the impact buckling capacity.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Disclaimer: 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.