Aeroelastic method to investigate nonlinear elastic wing structures

Abstract Stiffness directions of wing structures are already part the optimisation in aircraft design. Aircraft like A350 XWB and Boeing 787 mainly consist such composite material, whose stiffness can be optimised. To proceed with this optimisation, aim work is to modify optimise also linear stress-strain relation. On that account, Hooke’s law exchanged by a multi-linear formulation analyse any nonlinear elastic structural technology on structures. The structures, which used investigate behaviour, deduced from mid-range long-range configuration. These wings analysed an extended beam method coupled VLM solution calculate aeroelastical loading. proposed capable analysing structure technology. A degressive behaviour shows up good potential reduce bending moment one main drivers weight.