Modeling of Geometrically Nonlinear Aeroelasticity of Advanced Aircraft Wings in Incompressible Flow

摘要

To model advanced aircraft wing structures undergoing moderately large deflections, a linear thin-walled anisotropic beam model, which incorporates a number of nonclassical effects, including elastic couplings, transverse shear strain effect, warping inhibition, and three-dimensional(3-D) strain effect, has been extended by considering geometric nonlin-earities. Linear unsteady aerodynamics theory in incompressible flow is used to derive the aerodynamic loads. With the aid of Lagrangian-Eulerian relations, the aeroelastic system is formulated via the extended Hamilton's Principle. Various structural couplings in the governing system are specifically discussed and some conclusions are drawn.