Convertible tiltrotor aircraft

Patent metadata

Field	Value
Publication number	US-9701406-B2
Application number	US-201414566844-A
Country	US
Kind code	B2
Filing date	Dec 11, 2014
Priority date	Dec 11, 2014
Publication date	Jul 11, 2017
Grant date	Jul 11, 2017

Abstract

A rotorcraft includes a proprotor coupled to the wing and a pusher propeller. Power is transferred from the proprotor to the pusher propeller with the use of a torque splitter. The torque splitter contains several gears, including a ring gear which rotates on an axis. The power outputted by the torque splitter is increased or decreased by selectively slowing down the rotation of the ring gear by the use of a clamp.

First claim

The invention claimed is:

1. A rotorcraft, comprising:
a body;
a wing coupled to the body;
an engine;
a first proprotor coupled to the wing, the first proprotor comprising:
a plurality of blades;

a shaft defining a first axis in mechanical communication with the first proprotor, wherein the shaft is configured to selectively rotate around the first axis;
a pusher propeller; and
a torque splitter comprising:
a sun gear;
a ring gear;
a planet carrier in mechanical communication with the shaft;
a plurality of planetary gears, each in mechanical communication with the planet carrier and the ring gear and the sun gear; and
a clamp associated with the ring gear, the clamp being configured to selectively prevent rotation of the ring gear.

2. The rotorcraft of claim 1 , wherein the clamp is configured to selectively apply a frictional force on the ring gear.

3. The rotorcraft of claim 1 , wherein a transfer of power from the engine to the shaft decreases as the clamp allows an increase to a rotational speed of the ring gear.

4. The rotorcraft of claim 1 , wherein a transfer of power from the engine to the pusher propeller increases as the clamp allows an increase to a rotational speed of the ring gear.

5. The rotorcraft of claim 1 , wherein a transfer of power from the engine to the shaft increases as the clamp decreases a rotational speed of the ring gear.

6. The rotorcraft of claim 1 , wherein a transfer of power from the engine to the pusher propeller decreases as the clamp decreases a rotational speed of the ring gear.

7. The rotorcraft of claim 1 , further comprising:
a shaft clamp associated with the shaft, the shaft clamp configured to selectively be engaged and to decrease a rotational speed of the shaft.

8. The rotorcraft of claim 1 , wherein the ring gear further comprises:
a disk coupled to a perimeter of the ring gear; and
wherein the clamp is associated with the disk.

9. The rotorcraft of claim 1 , wherein the blade is pivotable around a folding axis.

10. The rotorcraft of claim 1 , further comprising:
a second proprotor;
wherein the shaft mechanically connects the first proprotor to the second proprotor.

11. The rotorcraft of claim 1 , wherein the sun gear, the ring gear, and the planet carrier are rotatable on the first axis.

12. The rotorcraft of claim 1 , wherein the torque splitter further comprises:
a spiral bevel gear in mechanical communication with the sun gear, wherein the spiral bevel gear is rotatable around a second axis that is perpendicular to the first axis.

13. The rotorcraft of claim 1 , the torque splitter further comprising:
a hole through the ring gear;
an actuator;
a pin;
wherein the actuator is configured to displace the pin into the hole, thereby locking the ring gear.

14. The rotorcraft of claim 1 , wherein the planet carrier is in direct mechanical engagement with the shaft.

15. A method of transferring the power from a proprotor to a pusher propeller in a rotorcraft, the method comprising:
providing a proprotor coupled to a wing of the rotorcraft;
providing a pusher propeller coupled to a body of the rotorcraft;
providing an engine coupled to the body of the rotorcraft;
providing a torque split gearbox comprising:
a sun gear rotating on an axis and in mechanical communication with a plurality of planetary gears;
the plurality of planetary gears rotating around the sun gear and in mechanical communication with a ring gear and a planet carrier, wherein the planet carrier is rotating on the axis; and
a clamp associated with the ring gear, wherein the clamp is engaged on the ring gear and prevents the ring gear from moving;

providing a shaft in mechanical communication with the planet carrier and the proprotor, and rotating on the axis; and
disengaging the clamp and allowing the ring gear to increase a ring gear speed of rotation around the axis.

16. The method of claim 15 , wherein the torque split gearbox further comprises:
a spiral bevel gear in mechanical communication with the sun gear.

17. The method of claim 15 , further comprising:
providing a shaft clamp associated with the shaft, wherein the shaft clamp is engaged on the shaft and prevents the shaft from moving.

18. The method of claim 17 , further comprising:
engaging the shaft clamp and allowing the shaft to decrease a shaft speed of rotation around the axis.

19. The method of claim 15 , wherein the torque splitter further comprises:
a disk coupled to the ring gear;
a hole through the disk;
an actuator; and
a pin;
wherein the actuator is configured to displace the pin into the hole, thereby locking the ring gear.

20. The method of claim 19 , further comprising:
linearly displacing the pin so that the pin is outside the hole.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Robertson Daniel B
• Smith Dudley E

Classifications

• B64C39/04

  having multiple fuselages or tail booms · CPC title

• B64D35/04

  characterised by the transmission driving a plurality of propellers or rotors · CPC title

• B64C29/0033 Primary

  the propellers being tiltable relative to the fuselage · CPC title

• B64C11/28

  Collapsible or foldable blades · CPC title