Patent ID: 8123483

Claim:
A rotorcraft ( 1 ) rotor comprising a hub ( 2 ) driven in rotation about an axis of rotation ( 100 ) oriented positively upwards relative to the rotorcraft, at least three blades ( 4 ) fastened to the hub ( 2 ) each via vertical flapping, drag, and pitch hinge ( 7 ), each blade ( 4 ) presenting a pitch variation axis ( 101 ), a leading edge (BA), and a trailing edge (BF), the rotor ( 1 ) further including inter-blade drag dampers each connected to two adjacent blades ( 4 ) respectively via at least two spherical joints ( 16 ) or ball joints, the two joints ( 16 ) connecting one blade ( 4 ) to two adjacent inter-blade drag dampers ( 15 ) being disposed on either side of the pitch variation axis ( 101 ) of the blade ( 4 ), wherein at least one of said joints ( 16 ) is offset above the plane P containing the pitch variation axis ( 101 ) and the vertical in the positive direction of the orthogonal axis ( 103 ) that is orthogonal to the plane P, the positive direction along said orthogonal axis ( 103 ) being oriented upwards relative to the rotorcraft.