Аннотация
In this study, the classical flutter and dynamic response of a helicopter tapered rotating blade with angular velocity (Ω) and forward flight speed (Un) in subsonic compressible flow are investigated. The composite blade was modeled as an anisotropic thin-walled composite beam with the Circumferentially Asymmetric Stiffness (CAS) structural model to establish proper coupling between pitch and flap. Also, the structural model takes into account a group of non-classical effects; such as the transverse shear, the material anisotropy, warping inhibition, etc. The analysis of classical flutter in helicopters necessitates the use of unsteady aerodynamics. The Aerodynamic Strip Method based on Indicial Function in unsteady subsonic compressible flow is used to simulate compressible unsteady aerodynamic effects. As a result, the Extended Galerkin's Method (EGM) and the Separation of Variables Method are used to obtain the coupled and linear Governing System of Dynamic Equations. Solving the aforementioned equations of motion in the time domain, the aeroelastic responses of the Tapered Composite Rotor Blade can be computed