Aeroelastic Tailoring of Helicopter Blades

Abstract : The dynamic loads transmitted from the rotor to the airframe are responsible for vibrations, discomfort and alternate stress on components. A new and promising way to minimize vibration is to reduce dynamic loads at their source by performing an aeroelastic optimization of the rotor. This optimization uses couplings between the flapwise-bending motion and the torsion motion. The impacts of elastic couplings (composite anisotropy) and inertial couplings (center-of-gravity offset) on blade dynamic behavior and on dynamic loads are evaluated in this paper. First, analytical results, based on a purely linear modal approach, are given to understand the influence of these couplings on blade dynamic behavior. Then, a complete nonlinear aeroelastic model of the rotor, including elastic and inertial couplings, is derived. Finally, this last model is used to improve a simplified but representative blade (homogeneous beam with constant chord) and results are presented.
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Contributor : Pierre Naegelen <>
Submitted on : Tuesday, December 11, 2018 - 12:18:40 PM
Last modification on : Tuesday, October 22, 2019 - 5:20:44 PM

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  • HAL Id : hal-01951219, version 1

Citation

Donatien Cornette, Benjamin Kerdreux, Guilhem Michon, Yves Gourinat. Aeroelastic Tailoring of Helicopter Blades. Journal of Computational and Nonlinear Dynamics, 2015, 10 (6), pp.061001--061001--12. ⟨hal-01951219⟩

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