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• W4302009633 endingPage "116268" @default.
• W4302009633 startingPage "116268" @default.
• W4302009633 abstract "Contemporary computational analysis of modern aircraft structures demands rapid and efficient, yet accurate enough tools for the conceptual and preliminary design stages. On that front, a novel optimisation framework, utilising low-cost numerical tools for sizing composite materials aircraft wings subject to stiffness, strength and dynamic aeroelastic constraints is proposed herein. The structural representation of the numerical model is based on the well-established equivalent-plate methodology, capable of reducing the size and computational cost of the associated problem. An equivalent-plate model of a modern transport aircraft wing is developed and compared to its equivalent 3D Finite Element Method model. Results by means of natural frequencies and modes, indicate excellent accordance between the numerical models. An optimisation framework is then presented, with the ply thicknesses of a baseline lay-up being assigned as design variables. The developed framework succeeds to guide the mass of the wing to a minimum while satisfying the constraints under a critical loading scenario. Optimal lay-ups for the skins, spar webs and ribs as well as spar and rib caps dimensions are obtained. The presented optimisation framework, exhibiting high accuracy and efficiency, constitutes a robust numerical tool for the early design stages of composite aircraft wings." @default.
• W4302009633 created "2022-10-06" @default.
• W4302009633 creator A5013937389 @default.
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• W4302009633 date "2023-01-01" @default.
• W4302009633 modified "2023-10-18" @default.
• W4302009633 title "Efficient structural optimisation of composite materials aircraft wings" @default.
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• W4302009633 doi "https://doi.org/10.1016/j.compstruct.2022.116268" @default.
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