A Method for the Calculation of Large Deformations in Aeroelastic Applications

摘要

A modal-based method that calculates the geometric nonlinear effects in the regime of large deformations of wing-like structures is applied to the modeling of a highly flexible 3D wingbox of high aspect ratio. The proposed method features higher-order stiffness terms and calculates the nodal deformation field not only by normal modes but also by additional modal components. In this way, a nonlinear force-displacement relationship and a geometrically nonlinear displacement field are accounted for. Static and dynamic results for the two configurations are presented together with results from a nonlinear finite element solver. The validations highlight the capability of the method to capture the nonlinear effects and demonstrates its power to model a 3D wingbox structure made of composite shell elements with anisotropic material characteristics.