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Forced aeroelastic oscillations of a rotating anisotropic helicopter main rotor blade at hovering

  • Structural Mechanics and Strength of Flight Vehicles
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Russian Aeronautics (Iz VUZ) Aims and scope Submit manuscript

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.

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Authors and Affiliations

  1. Moscow Aviation Institute (State Technical University), Moscow, Russia

    T. V. Grishanina

  2. Institute of Applied Mechanics, Russian Academy of Sciences, Moscow, Russia

    F. N. Shklyarchuk

Authors
  1. T. V. Grishanina
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  2. F. N. Shklyarchuk
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Original Russian Text © N.V. Grishanina, F.N. Shklyarchuk, 2013, published in Izvestiya VUZ. Aviatsionnaya Tekhnika, 2013, No. 3, pp. 66–72.

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Grishanina, T.V., Shklyarchuk, F.N. Forced aeroelastic oscillations of a rotating anisotropic helicopter main rotor blade at hovering. Russ. Aeronaut. 56, 303–313 (2013). https://doi.org/10.3103/S1068799813030136

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  • DOI: https://doi.org/10.3103/S1068799813030136

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