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A Finite Element Model For Structural And Aeroelastic Analysis Of Rotary Wings With Advanced Blade Geometry
Publié en 2010
Objective of this paper is the development and implementation of a finite element model, in a COMSOL Multiphysics context, for the prediction of the aeroelastic behavior of rotor blades. In particular, the attention is focused on new generation blades characterized by curved elastic axes, with the presence of tip sweep and anhedral angles. The blade structural model implemented is based on nonlinear flap-lag-torsion beam equations valid for slender, homogeneous, isotropic, non-uniform, twisted blades undergoing moderate displacements. To validate the model implemented, several analyses are performed reproducing reliable results available in literature.
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