Patent ID: 8590833

Claim:
A rotary-wing aircraft rotor with constant velocity drive, comprising: a rotor mast driven in rotation about a longitudinal axis; a hub connected to said mast by a constant velocity drive mechanism and by a tilting arrangement, the constant velocity drive mechanism having: a differential mechanism configured to split static torque while allowing relative movement in a plane perpendicular to the longitudinal axis of the mast, the differential mechanism having: a first disk; a second disk; a third disk; and a connecting pin having a longitudinal axis parallel to the longitudinal axis of the mast, the connecting pin being configured to hinge to the first disk, the second disk, and the third disk by a three ball joint connection centered about the longitudinal axis of the connecting pin; wherein the first disk, the second disk, and the third disk are placed one above another and are coaxial about the longitudinal axis of the mast; wherein the first disk is positioned between the second disk and the third disk; and wherein the second disk and the third disk are driven by the first disk via the connecting pin; wherein the tilting arrangement allows pivoting movement of the hub about a flapping axis converging with the axis of the mast and perpendicular to said axis of the mast in such a way that said hub is capable of being driven in constant velocity rotation by said mast about a geometrical axis of rotation of the hub which may be inclined in any direction about the axis of the mast; at least two blades, each linked to said hub by a coupling retaining and hinging the blade in pitch; and two driving devices configured to drive the hub and spaced from the differential mechanism along the axis of the mast.