Aeroelastic and local buckling optimisation of a variable-angle-tow composite wing-box structure

Benefiting from curved fibre paths, variable-angle-tow (VAT) composites feature a larger design space than traditional straight-fibre reinforced plastics. Herein, an optimisation framework of full-scale wing-box structure with VAT-fibre is presented, aiming at minimised mass and optimised local buckling performance under realistic aeroelastic loading conditions. Local analyses on individual subsections the wing are performed refined finite-element models by extracting running loads analysis entire structure. Using this global–local approach, conducted static failure, aeroelastic, manufacturing constraints to obtain structural parameters for straight- composite architectures. By optimising wing-skin thicknesses, paths wing-spar geometry simultaneously via genetic algorithm, potential benefit VAT explored. In addition, continuous tow shearing (CTS) process, which introduces layer thickness variations as tows steered, A reduction 12.5% 13.2% obtained using constant-thickness variable-thickness CTS designs, respectively, compared baseline quasi-isotropic design. The distribution also suggests that critical failure mode in specific regions, therefore needs be included during optimisation.