Abstract
The aeroelastic stability of a composite hingeless rotor blade, idealized as a laminated thin-walled box-beam, has been investigated using a finite element formulation based on Hamilton’s principle. First-order shear deformation theory and quasi-steady aerodynamic theory have been employed for the analysis. In order to consider the sectional distribution of shear stresses for the box-beam in an effective manner, Timoshenko beam assumption has been made and the formula of shear correction factor of isotropic box section has been used to describe the motion. Three dimensional stress analysis of composite box-beam by using a detailed finite element analysis program has been performed to identify the distribution of shear of the box section and to correlate the results of shear correction factor of isotropic material with that of composite material. Free vibration tests of rotating composite box-beams have showed fairly good agreement between the current results and the experimental data. Transverse shear behavior on the aeroelastic stability has been studied for a specific box-beam configuration. The results displayed in this article have revealed that the transverse shear coupling has a significant role on the flutter boundary of the rotor, especially in case of anti-symmetric configuration.
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