Forward folding rotor blades

Patent metadata

Field	Value
Publication number	US-10676183-B2
Application number	US-201715593521-A
Country	US
Kind code	B2
Filing date	May 12, 2017
Priority date	May 13, 2016
Publication date	Jun 9, 2020
Grant date	Jun 9, 2020

Abstract

A rotor blade rotation system includes two or more rotor blades, each rotor blade in mechanical communication with a hub and pivotable about an axis of rotation, a bearing plate comprising a rotating portion and a non-rotating portion, a fold linkage coupled to the rotating portion of the bearing plate and in mechanical communication with the rotor blade, and an actuator coupled to the non-rotating portion of the bearing plate and operable to reposition the bearing plate from a first position to a second position such that the folding links pivot the rotor blades from a deployed position to a forward folded position.

First claim

What is claimed is:

1. An aircraft, comprising:
a fuselage;
a closed wing coupled to the fuselage with one or more spokes, wherein the closed wing provides lift whenever the aircraft is in a forward flight;
one or more engines or motors disposed within or attached to the wing or fuselage, wherein the one or more engines or motors provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight, and provide thrust whenever the aircraft is in forward flight;
wherein the closed wing, the fuselage and the one or more spokes are symmetrically shaped to provide transition between vertical takeoff and landing, stationary flight and forward flight in any direction;
a shaft operably connected to the one or more engines or motors;
a hub in mechanical communication with the shaft;
two or more rotor blades, each rotor blade in mechanical communication with the hub and pivotable about an axis of rotation;
a bearing plate comprising a rotating portion and a non-rotating portion;
a fold linkage coupled to the rotating portion of the bearing plate and in mechanical communication with the rotor blade;
an actuator coupled to the non-rotating portion of the bearing plate and operable to reposition the bearing plate from a first position to a second position, wherein the fold linkage pivots the rotor blades from a deployed position to a forward folded position; and
wherein a tip of all the rotor blades are upstream from the hub and the hub is upstream from the bearing plate when the rotor blades are in the forward folded position.

2. The aircraft of claim 1 , wherein the forward folded position comprises the first position of the bearing plate is closer to the hub than the second position of the bearing plate.

3. The aircraft of claim 1 , further comprising a grip disposed between the hub and the rotor blade.

4. The aircraft of claim 3 , further comprising a lock operable to selectively couple and decouple the fold linkage and the grip.

5. The aircraft of claim 3 , further comprising a lock operable to selectively couple and decouple the hub and the grip.

6. The aircraft of claim 1 , wherein the fold linkage is positioned between the bearing plate and the rotor blade such that repositioning a first end of the fold linkage towards the hub causes a second end of the fold linkage to pivot the rotor blade towards the bearing plate.

7. The aircraft of claim 1 , wherein the fold linkage is positioned between the bearing plate and the rotor blade such that repositioning a first end of the fold linkage away from the hub causes a second end of the linkage to pivot the rotor blade towards the hub.

8. The aircraft of claim 1 , further comprising a fold lock deployable in a locked position or in an unlocked position, the fold lock operable in the locked position to prevent at least some folding of the rotor blade, the fold lock operable in the unlocked position to allow the at least some folding of the rotor blade.

9. The aircraft of claim 1 , further comprising a flapping lock deployable in a locked position or in an unlocked position, the flapping lock operable in the locked position to prevent at least some flapping movement of the hub relative to the shaft, the flapping lock operable in the unlocked position to allow the at least some flapping movement of the hub relative to the shaft.

10. The aircraft of claim 1 , further comprising a lock operable to selectively lock either folding of the rotor blade or flapping movement of the hub.

11. The aircraft of claim 1 , wherein a tip of all the rotor blades are preloaded together in the forward folded position such that a vibration of the rotor blades is reduced compared to the tip of all the rotor blades not being preloaded together.

12. The aircraft of claim 1 , wherein the closed wing, the fuselage and the one or more spokes are not substantially reconfigured for transition between vertical takeoff and landing, stationary flight and forward flight.

13. A rotor blade rotation system comprising:
two or more rotor blades, each rotor blade in mechanical communication with a hub and pivotable about an axis of rotation;
a bearing plate comprising a rotating portion and a non-rotating portion;
a fold linkage coupled to the rotating portion of the bearing plate and in mechanical communication with the rotor blade;
an actuator coupled to the non-rotating portion of the bearing plate and operable to reposition the bearing plate from a first position to a second position, wherein the fold linkage pivots the rotor blades from a deployed position to a forward folded position; and
wherein a tip of all the rotor blades are upstream from the hub and the hub is upstream from the bearing plate when the rotor blades are in the forward folded position.

14. The rotor blade rotation system of claim 13 , wherein the forward folded position comprises the first position of the bearing plate is closer to the hub than the second position of the bearing plate.

15. The rotor blade rotation system of claim 13 , further comprising a grip disposed between the hub and the rotor blade.

16. The rotor blade rotation system of claim 15 , further comprising a lock operable to selectively couple and decouple the fold linkage and the grip.

17. The rotor blade rotation system of claim 15 , further comprising a lock operable to selectively couple and decouple the hub and the grip.

18. The rotor blade rotation system of claim 13 , wherein the fold linkage is positioned between the bearing plate and the rotor blade such that repositioning a first end of the fold linkage towards the hub causes a second end of the fold linkage to pivot the rotor blade towards the bearing plate.

19. The rotor blade rotation system of claim 13 , wherein the fold linkage is positioned between the bearing plate and the rotor blade such that repositioning a first end of the fold linkage away from the hub causes a second end of the linkage to pivot the rotor blade towards the hub.

20. The rotor blade rotation system of claim 13 , further comprising a fold lock deployable in a locked position or in an unlocked position, the fold lock operable in the locked position to prevent at least some folding of the rotor blade, the fold lock operable in the unlocked position to allow the at least some folding of the rotor blade.

21. The rotor blade rotation system of claim 13 , further comprising a flapping lock deployable in a locked position or in an unlocked position, the flapping lock operable in the locked position to prevent at least some flapping movement of the hub relative to the shaft, the flapping lock operable in the unlocked position to allow the at least some flapping movement of the hub relative to the shaft.

22. The rotor blade rotation system of claim 13 , further comprising a lock operable to selectively lock either folding of the rotor blade or flapping movement of the hub.

23. The rotor blade rotation system of claim 13 , wherein a tip of all the rotors are preloaded together in the forward folded position such that a vibration of the rotors is reduced compared to the tip of all the rotor blades not being preloaded together.

24. The rotor blade rotation system of claim 13 , wherein the fold linkage is in mechanical communication with an upper portion of the rotor blade.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Fenny Carlos Alexander
• Olson Rohn Lee
• Zahasky Andrew James

Classifications

• B64C1/068

  Fuselage sections · CPC title

• B64C39/024

  of the remote controlled vehicle type, i.e. RPV · CPC title

• B64D31/00

  Power plant control systems; Arrangement of power plant control systems in aircraft · CPC title

• B64C27/12

  Rotor drives · CPC title

• B64C11/28 Primary

  Collapsible or foldable blades · CPC title