Helicopter rotor

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.