|Autors: Todorov, M. D., Dobrev I.K., Massouh F., Velkova C.V.|
Title: AN INVESTUGATION OF THE MOTION OF A HELICOPTER ROTOR WITH FLAPPING AND LEAD/LAG HINGES IN HOVER
Keywords: helicopter, aeroelasticity, aerodynamics, structural dynamic
Abstract: A modelling of pattern helicopter rotor with flapping and lead/lag hinges in hover is presented in this paper. The coupled aeroelastic problem accounts for the mutual dependence between blade structure and rotor aerodynamics. The aerodynamic model uses Blade Element Momentum Theory (BEMT). BEMT gives good accuracy with respect to time cost. The structure model uses Finite Element Method (FEM). The investigation is based on the well-known solvers MATLAB and ANSYS. This modelling is also useful and applicable for airplane propellers, wind turbine rotors and airplane wings.
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Вид: публикация в национален форум