Patent ID: 7607892

Claim:
A rotorcraft rotor comprising a hub and at least two blades hinged relative to the hub about respective pitch axes, about respective flap axes, and about respective lag axes, the three axes coinciding at a hinge center for each blade, each blade being secured to a respective pitch lever, the rotor including for each blade a pitch control rod connected to the pitch lever via a first ball joint, and a common lag damper structure centered substantially on the axis of rotation of the rotor and connected to each of the blades, wherein the lag damper structure is secured to a respective lateral projection of each blade via a respective single second ball joint that is sufficiently close to the first ball joint connecting the pitch rod to the pitch lever to ensure that the lag damper system is relatively or completely insensitive to flap oscillations of the hinged blades, and wherein the common damper structure is not secured to the hub, in which the damper structure comprises a plurality of identical damper units together with a strip common to a plurality of damper units and not secured to the hub, and in which the damper structure is secured to the pitch level of each blade.