The aeroelastic behavior of composite fin in subsonic regime using FEM/BEM model

In this study the elastic structure of a composite plate, is modeled using FEM by means of Reissner-Mindlin first-order shear deformable theory. This formulation is transformed into a modal representation form that is then assembled with the equations of aerodynamic to obtain the governing equations of the coupled system. The FEM model of structure is modified using experimental results by means of modal updating method. The governing equations of incompressible potential flow are derived using BEM based reduced order method and the generalized force of each structural mode is derived. The flutter and divergence characteristics of composite fin with various laminate lay up are studied and compared with those of the metal fin.

کلیدواژه ها:

Aeroelastic instability ، modal ، reduced order ، boundary element ، finite element