Patent ID: 8496435

Claim:
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 opposite sides of said first axis and elongated along respective second axes crosswise to said first axis, each said blade being movable with respect to said hub and to the other said blade about a respective third axis crosswise to the respective said second axis; a number of dampers for damping oscillation of respective said blades about the respective said third axes, and which comprise respective first portions movable integrally with the respective said blades about the respective said third axes; said dampers comprising respective second portions connected elastically to the respective first portions and functionally to each other; said second portions of said dampers being connected rigidly to one another; and a number of rigid rods interposed each between respective pair of said second portions of a respective pair of adjacent said dampers and alternating with said blades about said first axis: each said damper comprising two second portions and being connected to two adjacent dampers; one second portion of each damper being connected by one relative rod to a respective second portion of one of said adjacent dampers; the other second portion of each damper being connected by the other relative rod to a respective second portion of the other of said adjacent dampers.