Patent ID: 8297549
Filing Date: 2012-10-30
Classification: B64C

Abstract:
1. A rotor for a helicopter, comprising: a drive shaft rotating about a first axis; a hub angularly integral with said drive shaft about said first axis; at least two blades projecting from said hub, on the opposite side to said first axis, and extending along respective second axes crosswise to said first axis; each said blade being movable with respect to said hub and the other said blades about a respective fourth axis parallel to said first axis, about the respective said second axis, and about a respective third axis crosswise to said first and respective second axis; and a number of first dampers for damping vibration associated with at least oscillation of the relative said blades about the respective said fourth axes; said first dampers being connected to one another and each to a relative blade; said blades rotating, in use, collectively about said first axis together with said hub; characterized in that at least one said first damper is located between said first axis and said fourth axis of the relative blade, in a radial direction with respect to said first axis; said rotor further comprising a second damper interposed between said hub and at least one said first damper.