초록 ▼

A rotor system for tilt rotor aircraft comprises an engine disposed at a first fixed position on a wing member, and a prop-rotor pylon mechanically coupled to the engine along a drive path extending through the wing member. The engine is disposed adjacent a fuselage of the tilt rotor aircraft, and t

A rotor system for tilt rotor aircraft comprises an engine disposed at a first fixed position on a wing member, and a prop-rotor pylon mechanically coupled to the engine along a drive path extending through the wing member. The engine is disposed adjacent a fuselage of the tilt rotor aircraft, and the prop-rotor pylon is configured to selectively rotate between a vertical position and a horizontal position. The prop-rotor pylon is coupled to a plurality of rotor blades.

대표청구항 ▼

1. A rotor system for tilt rotor aircraft, the rotor system comprising: an engine disposed at a first fixed position above a wing member, wherein the engine is disposed adjacent to and above a fuselage of the tilt rotor aircraft, wherein the wing member is rotatable coupled to the fuselage, and the

1. A rotor system for tilt rotor aircraft, the rotor system comprising: an engine disposed at a first fixed position above a wing member, wherein the engine is disposed adjacent to and above a fuselage of the tilt rotor aircraft, wherein the wing member is rotatable coupled to the fuselage, and the wing member is configured to rotate relative to the fuselage and align a width of the wing member with a longitudinal axis of the fuselage; anda prop-rotor pylon mechanically coupled to the engine along a drive path extending through the wing member, wherein the prop-rotor pylon is configured to selectively rotate between a vertical position and a horizontal position, and wherein the prop-rotor pylon is coupled to a plurality of rotor blades. 2. The rotor system of claim 1, wherein the engine comprises an intake and an exhaust, and wherein the engine is oriented so that the exhaust is canted away from the fuselage. 3. The rotor system of claim 1, wherein the drive path comprises a drive shaft extending through the wing member, and wherein the drive shaft is coupled to the engine through an inboard gearbox. 4. The rotor system of claim 3, wherein the inboard gearbox comprises a spiral bevel gearset. 5. The rotor system of claim 3, wherein the drive shaft is coupled to the prop-rotor pylon through a gearbox, and wherein the prop-rotor pylon is configured to selectively rotate along an axis of the gearbox. 6. The rotor system of claim 1, wherein the prop-rotor pylon is rotatably coupled to the wing member by a spindle. 7. The rotor system of claim 1, further comprising an interconnect drive shaft mechanically coupled to the engine, wherein the interconnect drive shaft is mechanically coupled to a second prop-rotor pylon. 8. The tilt rotor system of claim 1, further comprising a conversion actuator coupled to the wing member at a first point and to the prop-rotor pylon at a second point, wherein the conversion actuator is configured to selectively rotate the prop-rotor pylon between the vertical position and the horizontal position. 9. The rotor system of claim 1, wherein the plurality of ribs extend aft of a trailing edge of the wing member. 10. The rotor system of claim 1, further comprising a torque box formed by a plurality of ribs in the wing member, wherein the engine is mounted to the wing member using the torque box. 11. The rotor system of claim 10, further comprising a plurality of cross members extending between the plurality of ribs. 12. The rotor system of claim 10, wherein the plurality of ribs comprises two ribs extending between an aft spar and aft cove spar under the engine. 13. The rotor system of claim 10, further comprising a plurality of links coupling the engine at a mid-mount location to the torque box. 14. The rotor system of claim 10, further comprising a torque tube coupling the engine to a gearbox coupled to an aft spar. 15. A tilt rotor aircraft comprising: a fuselage;a wing member rotatably coupled to the fuselage, wherein the wing member is configured to rotate relative to the fuselage and align a width of the wing member with a longitudinal axis of the fuselage;an engine disposed at a first fixed position above the wing member, wherein the engine is disposed adjacent to and above the fuselage; anda prop-rotor pylon mechanically coupled to the engine along a drive path, wherein the prop-rotor pylon is configured to selectively rotate between a vertical position and a horizontal position. 16. The tilt rotor aircraft of claim 15, wherein the prop-rotor pylon is rotatably coupled to the wing member by a spindle. 17. The tilt rotor aircraft of claim 15, wherein the drive path is configured to disengage from the engine or the prop-rotor pylon when the wing member rotates relative to the fuselage. 18. The tilt rotor aircraft of claim 15, further comprising a conversion actuator coupled to the wing member at a first point and to the prop-rotor pylon at a second point, wherein the conversion actuator is configured to selectively rotate the prop-rotor pylon between the vertical position and the horizontal position. 19. The tilt rotor aircraft of claim 15, wherein the plurality of ribs extend aft of a trailing edge of the wing member. 20. The tilt rotor aircraft of claim 15, further comprising a torque box formed by a plurality of ribs in the wing member, wherein the engine is mounted to the wing member using the torque box. 21. A tilt rotor aircraft comprising: a fuselage;a wing member coupled to the fuselage, wherein the wing member is configured to rotate relative to the fuselage and align a width of the wing member with a longitudinal axis of the fuselage;a plurality of engines located at fixed positions above the wing member, wherein each of the engines of the plurality of engines is disposed adjacent to and above the fuselage;a plurality of prop-rotor pylons rotatably coupled to the wing member, wherein each prop-rotor pylon is configured to selectively rotate between a vertical position and a horizontal position, and wherein each of the prop-rotor pylons is mechanically coupled to at least one of the plurality of engines; anda plurality of torque boxes, each torque box formed by a plurality of ribs in the wing member, wherein each engine is mounted to the wing member by a respective torque box. 22. The tilt rotor aircraft of claim 21, wherein each engine of the plurality of engines is mechanically coupled to each prop-rotor pylon of the plurality of prop-rotor pylons. 23. The tilt rotor aircraft of claim 21, further comprising an interconnect drive shaft mechanically coupling the plurality of engines. 24. The tilt rotor aircraft of claim 21, further comprising a conversion actuator coupled to the wing member at a first point and to the prop-rotor pylon at a second point, wherein the conversion actuator is configured to selectively rotate the prop-rotor pylon between the vertical position and the horizontal position. 25. The tilt rotor aircraft of claim 21, wherein, for each torque box, the plurality of ribs extend aft of a trailing edge of the wing member.