Patent ID: 7850429

Claim:
A rotor for a helicopter, comprising: a hub rotating about a first axis, the hub comprising a radially inner cylindrical body and a radially outer tubular portion; a number of blades projecting from said hub in respective longitudinal directions lying in a plane crosswise to said first axis, each of said number of blades being connected to said hub so as to be movable at least about a second axis crosswise to said first axis and to one of said respective longitudinal directions; and a number of damping devices for damping vibration of said helicopter, and each interposed between one blade and said tubular portion of said hub; characterized in that each said number of damping devices comprises a separate plate member fixed, on one side, to said hub, and connected, on an opposite side, to said blade by elastic means; and in that said separate plate member, during movement of said blade, is flexible about a third axis parallel to said second axis and located close to the second axis; each said plate member being V-shaped, and comprising: a tip connected to the relative said blade; two diverging lateral branches originating from said tip; and an end, opposite to said tip, the tip being defined by free ends of said lateral branches and being connected to said tubular portion of said hub; said lateral branches of each said plate member being spaced from each other and defining together with said tip a cavity for receiving part of said tubular portion of said hub.