US 4,255,084 AGranted

Device for damping the vibrations of a rotary-wing aircraft rotor

AssigneeSociete Nationale Industrielle et Aerospatiale

InventorsRene L. Mouille, Gerard C. L. Genoux, Marc A. Declercq, Jean-Luc M. Leman, Robert J. Suzzi

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Abstract

The invention relates to a device for damping the vibrations of the rotor of a rotary-wing aircraft. This device comprises a flapping weight concentrated near the rotor axis and at least three resiliently deformable elements, such as helical springs. The deformable elements are radially biassed in directions regularly distributed around the rotor axis. The inner ends of the deformable elements directly bear on the flapping weight. Their outer ends directly bear on rigid structure elements, rigidly secured to the rotor hub, so that the biassed deformable elements apply statically balanced centripetal thrusts to the flapping weight.

Claims14

Dependent claims

A resonator device for damping the vibrations of a rotary-wing aircraft rotor having a hub, the device comprising:

a flapping weight disposed at the top of the rotor hub and concentrated near the rotor axis;
means for returning said weight resiliently towards an inoperative position centred on such axis, said means comprising at least three resiliently deformable elements, which are each radially biassed in directions distributed regularly around the rotor axis, the inner ends of said elements directly bearing on said flapping weight;
and
rigid structure elements, rigidly secured to the rotor hub, the outer ends of said resiliently deformable elements bearing on said structure elements so as to apply statically balanced centripetal thrusts to said flapping weight.

1 more element

Dependencies are inferred from the claim text.