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.
Aeroelastic Tailoring of Helicopter Blades
Contributed by the Design Engineering Division of ASME for publication in the JOURNAL OF COMPUTATIONAL AND NONLINEAR DYNAMICS. Manuscript received March 12, 2014; final manuscript received May 1, 2014; published online April 9, 2015. Assoc. Editor: José L. Escalona.
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Cornette, D., Kerdreux, B., Michon, G., and Gourinat, Y. (November 1, 2015). "Aeroelastic Tailoring of Helicopter Blades." ASME. J. Comput. Nonlinear Dynam. November 2015; 10(6): 061001. https://doi.org/10.1115/1.4027717
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