Efficient prediction of aeroelastic behaviour including geometric non-linearities

A procedure for developing efficient aeroelastic Reduced Order Models (ROMs) for aerospace structures containing geometric non-linearities is described. The structural modelling is based upon a combined modal/Finite Element approach that describes the non-linear stiffening effects from results of non-linear static analyses for a range of prescribed inputs. Once the structural ROM has been defined, it is coupled to the aerodynamic model. The aeroelastic model can then be used to predict the dynamic aeroelastic behaviour of the defined structure. The methodology is demonstrated on the aeroelastic model of a flexible high-aspect ratio wing.