Abstract Aeroelastic oscillations of a rotating blade as a thin-walled beam with restrained strains of bending, transverse shear, and torsion are considered. Aerodynamic loads on the blade performing the forced harmonic oscillations at helicopter hovering are determined according to the nonstationary theory of a two-dimensional flow past blade cross-sections without taking into account the vortex wake of other main rotor blades. The influence of blade anisotropy on its dynamic and propulsive characteristics is estimated in the case of prescribed variation of the root section angle of twist.
Forced aeroelastic oscillations of a rotating anisotropic helicopter main rotor blade at hovering
Russian Aeronautics (Iz VUZ) ; 56 , 3 ; 303-313
2013-07-01
11 pages
Article (Journal)
Electronic Resource
English
Forced aeroelastic oscillations of a rotating anisotropic helicopter main rotor blade at hovering
Online Contents | 2013
|Hovering rotor computations using an aeroelastic blade model
Online Contents | 2012
|Hovering model helicopter rotor testing
NTRS | 1984
|