Patent ID: 8336815

Claim:
A constant-velocity drive system for a rotary-wing aircraft rotor, the constant-velocity drive system comprising: a differential torque-splitting mechanism configured to interface with a mast about a longitudinal mast axis of rotation, the differential torque-splitting mechanism having: a drive disk located coaxial with the mast axis of rotation and configured to be integral in rotation with the mast; an inner driven member having: an inner base portion coaxial with the mast axis and adjacent the drive disk; an inner riser portion coaxial with the mast axis and extending away from the inner base portion; and inner drive arms extending from the inner riser portion generally radially and spaced a substantial distance along the mast axis away from the inner base portion; an outer driven member comprising: an outer base portion coaxial with the mast axis and adjacent the drive disk; an outer riser portion coaxial with the mast axis and extending from the outer base portion and toward the inner drive arms; and outer drive arms extending generally radially from the outer riser portion and spaced along the mast axis away from the outer base portion; and triple joint pins each having three joint connections, each joint connection pivotally engaging the drive disk, the inner base portion, or the outer base portion; and a gimbal mechanism configured to be driven in rotation by the inner drive arms and the outer drive arms, the gimbal mechanism being configured to connect with a rotor hub for allowing the rotor hub to gimbal with respect to the mast wherein the gimbal mechanism is axially displaced from the differential torque-splitting mechanism such that the gimbal mechanism rotates about a first rotational plane relative a second rotational plane of the torque-splitting mechanism.