Rotor hub with blade-to-blade dampers attached to the pitch change axis

An aircraft, comprising:

• a fuselage;
• a powerplant;
• a mast coupled to the powerplant;
• and
• a rotor assembly, comprising:
• a yoke coupled to the mast and being configured to rotate about a mast axis, the yoke defining a plurality of bearing pockets;
• a plurality of rotor blade assemblies, each rotor blade assembly comprising:
• a rotor blade;
• a bearing, wherein the bearing is at least partially disposed within one of the plurality of bearing pockets, the bearing forming a lead-lag hinge with a lead-lag axis that is substantially parallel to the mast axis, a flap hinge with a flap axis that is substantially perpendicular to and intersects the lead-lag axis, and a pitch change hinge with a pitch change axis that is substantially perpendicular to and intersects both the lead-lag axis and the flap axis;
• and
• a blade grip, the blade grip coupling the rotor blade to the bearing, the blade grip including a shaft between the yoke and the rotor blade, wherein the shaft intersects the pitch change axis;
• and
• a plurality of damper assemblies, each of the plurality of damper assemblies including a first end and a second end, the first end of each of the plurality of damper assemblies and the second end of an adjacent damper assembly both being connected to a single concentric rod end bearing, each concentric rod end bearing comprising a ball and concentric inner and outer races, each race being connected to either the first end of one of the damper assemblies or to the second end of an adjacent damper assembly, each of the concentric rod end bearings being coupled to the shaft of one of the plurality of blade grips such that a center point of the ball of each of the concentric rod end bearings is approximately coincident to the pitch change axis of each of the plurality of rotor blade assemblies.