Patent ID: 8141812

Claim:
A transmission for a rotary-wing aircraft, the transmission comprising: at least one differential torque-splitting mechanism adapted for interfacing with a shaft about a longitudinal shaft axis of rotation, each differential torque-splitting mechanism comprising: a drive disk coaxial with the shaft axis of rotation and adapted to be integral in rotation with the shaft; a first driven member coaxial with the shaft axis and generally adjacent the drive disk; a second driven member coaxial with the shaft axis and generally adjacent the drive disk; and at least one pin, each pin pivotally engaging each of the drive disk, the first driven member, and the second driven member, wherein the first driven member is configured to drive at least one first transfer gear and the second driven member is configured to drive at least one second transfer gear; wherein each first transfer gear and each second transfer gear supply torque to a bull gear associated with a rotor mast; wherein at least one of the pins further comprising: opposing end ball joints; and a central cylindrical joint having a central cylindrical joint axis; wherein the central cylindrical joint pivotally engages the drive disk; wherein the central cylindrical joint axis is substantially radial to the shaft axis; and wherein the at least one pin is configured for translation along the central cylindrical joint axis.