Marín Vallejo, Juan CarlosGraciani Díaz, Enrique2025-11-202025-11-202022-021879-10850263-8223https://hdl.handle.net/11441/179242The increasingly widespread use of composite materials in structural elements of commercial aircrafts (Airbus 350, Boeing 787), has led to consider the design of wings in composite material. Finite Element (FE) models have been used as a numerical tool for analysis and design, due to the geometrical complexity of these elements, together with the anisotropic nature of the composite material. However, the structural design of elements made of composite laminates using FE models is very expensive in terms of time needed for processing the results and for introducing modifications. The use of simpler Strength of Materials (SM) models has shown to be very efficient for the design of wind turbine blades. The objective of this work is to investigate the feasibility of using these SM models for composite layered aircraft wing design. To this end, a specific model that considers the geometric characteristics of these structural elements (multicellular sections and presence of longitudinal spars and transverse stiffeners) has been developed. The application of the SM model on a specific geometry of a wing torsion box under a given loading condition has allowed us to successfully compare the results, in terms of longitudinal stress flows, with those obtained by a numerical FE model for the same problem, using equivalent discretization.application/pdf55 p.engAttribution-NonCommercial-NoDerivatives 4.0 Internationalhttp://creativecommons.org/licenses/by-nc-nd/4.0/CompositeThin-walled sectionAircraft wingBeam modelsFinite Element modelsinfo:eu-repo/semantics/articleinfo:eu-repo/semantics/openAccesshttps://doi.org/10.1016/j.compstruct.2021.115088