Patent ID: 9126678
Filing Date: 2015-09-08
Classification: B64C

Abstract:
1. A rotor system for tilt rotor aircraft, the rotor system comprising: an engine disposed at a first fixed location on a wing member; a prop-rotor pylon mechanically coupled to the engine along a first drive path, wherein the prop-rotor pylon is rotatably mounted on a spindle, wherein the prop-rotor pylon is configured to selectively rotate about a rotational axis of the spindle between a vertical position and a horizontal position; a gearbox disposed in the first drive path, wherein the gearbox comprises a rotational shaft configured to at least partially transmit a rotation of the engine to the prop-rotor pylon, wherein a rotational axis of the rotational shaft is aligned with the rotational axis of the spindle; and an interconnect drive shaft passing through the wing member, wherein the prop-rotor pylon is mechanically coupled to the interconnect drive shaft along a second drive path, wherein a rotational axis of the interconnect drive shaft is aligned with the rotational axis of the spindle; wherein the interconnect drive shaft is disconnected from the rotational shaft included in the gearbox causing the first drive path and the second drive path to independently engage a prop-rotor gearset.