Finite Element Modeling and Vibration Analysis of Aeroelastic Wing Structures

Abstract

This paper presents an aeroelastic formulation and implementation of coupled aeroelastic bending-torsion equations using the finite-element method and conducts modal analysis of symmetric and anti-symmetric aeroelastic modes of flexible aircraft wing structures.. The computational method is used to develop an aeroelastic model which is capable of computing static and dynamic wing aeroelastic deflections under a coupled bending-torsion motion. The wing aeroelastic model is derived from a one-dimensional structural dynamic theoretical framework and is coupled with aircraft rigid-body longitudinal states. The contribution of the propulsive forces and moments to wing aeroelasticity is accounted in the aeroelastic model. An eigenvalue analysis of the generalized linear aeroelastic system allows for the determination of aeroelastic l frequencies, damping, and mode shapes. The computation is iterated until the solution converges within a specified error tolerance. Simulations are performed using geometry and material properties of a wing structure of a Generic Transport Model (GTM) to demonstrate the capability of the aeroelastic model.