Flutter characteristics of a composite wing containing an arbitrary concentrated mass

The bending- Torsional flutter characteristics of a composite wing containing an arbitrary concentrated mass are presented. The wing performs as a classical beam. The governing equations are determined via Lagrange’s principle. In order to exactly consider the spanwise and chordwise location and properties of concentrated mass, the generalized function theory is used. The unsteady incompressible aerodynamics based on Wagner’s function is considered for determining the aerodynamic loads. The general laminate composite theory is used for modeling the effects of ply angles on the flutter characteristics. The Ritz method is subsequently applied to convert the partial differential equations into a set of ordinary differential equations. Dirac delta function is used in order to precisely consider the location and properties of the engine mass. Moreover, the numerical results are compared with the published results and excellent agreement is observed. The numerical simulations indicating the significant effects of the sweep angle, mass value and location and the ply angles on the flutter boundaries are presented