Article ID Journal Published Year Pages File Type
253780 Composite Structures 2008 7 Pages PDF
Abstract

The aeroelastic stability of an aircraft wing modeled as an anisotropic composite thin-walled beam in an incompressible flow is investigated. The wing is built-up as a single-cell box beam whose central point is noncoincident with the mid-chord of the profile. The effects of material anisotropy, transverse shear, warping inhibition, nonuniform torsional model and rotary inertia are considered in the structural model. The unsteady incompressible aerodynamics based on Wagner’s function is used to determine the aerodynamic loads. The effects of the offset between reference axis and the mid-chord (“a” parameter), fiber orientation and sweep angle on stability boundary are considered, their effects on the stability boundary are discussed and a number of important conclusions are drawn.

Related Topics
Physical Sciences and Engineering Engineering Civil and Structural Engineering
Authors
, , ,