Static aeroelastic analysis including geometric nonlinearities based on Reduced Ordered Model (ROM)

In this paper, a method is proposed for modelling large deflection of wing by developing efficient reduced order model (ROM). The method can be used to solve the static aeroelastic problems of wing containing geometric nonlinearities and static aeroelastic trim problems of flexible aircraft containing geometric nonlinearities. Traditional methods of aeroelastic analysis can't reflect the nonlinear characteristics of structures, its result can't satisfy the precision demand of engineering analysis. The approach for structure modelling presented here is based on a combined modal/finite element (MFE) approach that describes the stiffness nonlinearities. We apply that structure modelling method as ROM to aeroelastic analysis. The results show static aeroelastic analysis of wing and static aeroelastic trim analysis of aircraft based on structure ROM can achieve a good agreement compared to analysis based on the finite element method (FEM) and experiment result. The methods in this paper is suitable for the preliminary design and the static aeroelastic analysis of the flexible aircraft with large-aspect-ratio wing efficiently.