초록 ▼

The system of the present application includes an engine and pylon arrangement for a tilt rotor aircraft in which the engine is fixed in relation to a wing portion of the aircraft, while the pylon is rotatable. The pylon supports a rotor hub having a plurality of rotor blades. Rotation of the pylon

The system of the present application includes an engine and pylon arrangement for a tilt rotor aircraft in which the engine is fixed in relation to a wing portion of the aircraft, while the pylon is rotatable. The pylon supports a rotor hub having a plurality of rotor blades. Rotation of the pylon allows the aircraft to selectively fly in a helicopter mode and an airplane mode, as well as any combination thereof.

대표청구항 ▼

1. A rotor system for a tilt rotor aircraft, the rotor system comprising: an outboard engine in a first fixed location on a wing member of the tilt rotor aircraft; anda prop-rotor pylon in power communication with the outboard engine, the prop-rotor pylon being configured to selectively rotate betwe

1. A rotor system for a tilt rotor aircraft, the rotor system comprising: an outboard engine in a first fixed location on a wing member of the tilt rotor aircraft; anda prop-rotor pylon in power communication with the outboard engine, the prop-rotor pylon being configured to selectively rotate between a vertical position and a horizontal position, the prop-rotor pylon comprising a plurality of rotor blades;an outboard input drive shaft coupled between the outboard engine and an outboard input gearbox; andan outboard gearbox drive shaft being perpendicular and directly connected to the outboard input drive shaft;wherein the prop-rotor pylon selectively rotates about the outboard gearbox drive shaft when orienting between the vertical position and the horizontal position. 2. The rotor system according to claim 1, wherein the outboard engine is located outboard of the prop-rotor pylon. 3. The rotor system according to claim 1, the prop-rotor pylon further comprising: a swashplate;a gearbox; anda nacelle fairing configured as an aerodynamic housing for the swashplate and the gearbox. 4. The rotor system according to claim 1, wherein the outboard gearbox drive shaft traverses through an interior of an outboard rib bearing, the outboard rib bearing providing rotational support for the prop-rotor pylon against a fixed outboard rib member. 5. The rotor system according to claim 1, the prop-rotor pylon further comprising: a nacelle fairing configured as an aerodynamic housing for internal components located therein;a fairing panel located aft of the nacelle fairing, the fairing panel being moveable between a closed position and an open position, the closed position providing aerodynamic efficiency when the prop-rotor pylon is the horizontal position, the open position providing clearance for the prop-rotor pylon to rotate into the vertical position. 6. The rotor system according to claim 1, further comprising: an inboard engine in a second fixed location on the wing member of the tilt rotor aircraft. 7. The rotor system according to claim 6, further comprising: an inboard input drive shaft coupled between the inboard engine and an inboard input gearbox; andan inboard gearbox drive shaft coupled between the inboard input gearbox and a gearbox located in the prop-rotor pylon. 8. The rotor system according to claim 7, further comprising: an accessory drive shaft coupled between the inboard input gearbox and an accessory input gearbox;an interconnect drive shaft coupled to the accessory input gearbox. 9. The rotor system according to claim 8, wherein the interconnect drive shaft is coupled to an accessory gearbox located in a fuselage portion of the aircraft. 10. The rotor system according to claim 8, wherein the interconnect drive shaft is coupled to a gearbox configured for drive a second prop-rotor pylon located on an opposite portion of the wing member. 11. A tilt rotor aircraft comprising: a fuselage;a wing member;an outboard engine in a first fixed location on the wing member of the tilt rotor aircraft; anda prop-rotor pylon powered by the outboard engine, the prop-rotor pylon being configured to selectively rotate between a vertical position and a horizontal position, the prop-rotor pylon comprising a plurality of rotor blades;an outboard input drive shaft coupled between the outboard engine and an outboard input gearbox; andan outboard gearbox drive shaft being perpendicular and directly connected to the outboard input drive shaft;wherein the prop-rotor pylon selectively rotates about the outboard gearbox drive shaft when orienting between the vertical position and the horizontal position. 12. The tilt rotor aircraft according to claim 11, wherein the outboard engine is located outboard of the prop-rotor pylon, the outboard engine and the prop-rotor pylon being located on an outboard portion of the wing member, the outboard portion being a selected distance from the fuselage. 13. The tilt rotor aircraft according to claim 11, the prop-rotor pylon further comprising: a swashplate;a gearbox; anda nacelle fairing configured as an aerodynamic housing for the swashplate and the gearbox. 14. The tilt rotor aircraft according to claim 11, wherein the outboard gearbox drive shaft traverses through an interior of an outboard rib bearing, the outboard rib bearing providing rotational support for the prop-rotor pylon against a fixed outboard rib member. 15. The tilt rotor aircraft according to claim 11, the prop-rotor pylon further comprising: a nacelle fairing configured as an aerodynamic housing for internal components located therein;a fairing panel located aft of the nacelle fairing, the fairing panel being moveable between a closed position and an open position, the closed position providing aerodynamic efficiency when the prop-rotor pylon is the horizontal position, the open position providing clearance for the prop-rotor pylon to rotate into the vertical position. 16. The tilt rotor aircraft according to claim 11, further comprising: an inboard engine in a second fixed location on the wing member of the tilt rotor aircraft. 17. The tilt rotor aircraft according to claim 16, further comprising: an inboard input drive shaft coupled between the inboard engine and an inboard input gearbox; andan inboard gearbox drive shaft coupled between the inboard input gearbox and a gearbox located in the prop-rotor pylon. 18. The tilt rotor aircraft according to claim 11, further comprising: a conversion actuator configured to selectively rotate the prop-rotor pylon.