Tilt rotor aircraft with fixed engine arrangement
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.
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; and
a 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; and
an 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; and
a 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; and
an 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; and
a 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; and
an 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; and
a 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; and
an 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.