Flexible aircrafts tend to undergo large deformation under aerodynamic forces, as a result, structural geometric nonlinearity occurs. The linear small deformation theory cannot give accurate results for analysis of static aeroelasticity. Fluid structure coupling method based on three dimensional RANs Navier-Stokes equations and nonlinear static equation is used for static aeroelastic analysis with structural geometric nonlinearity. The mentioned approach adopts nonlinear incremental finite element method to solve nonlinear static equation with assembled structure stiffness matrix. Moreover, RBF method is used for data interpolation and mesh deformation. Based on multi-material wing finite element model, the numerical simulations were made to analyse the static aeroelastic behavior. The comparisons of twist angles, vertical displacements, spanwise displacements and life coefficients between linear and nonlinear structure were made. The results show that geometric nonlinearity cannot be neglected for predicting accurate static aeroelastic behavior for large flexible airplanes.
Key words
static aeroelastic analysis /
geometric nonlinearity /
flexible aircrafts
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