Folding of rotorcraft rotor blades

• US 9,156,545 B1
• Filed: 07/24/2013
• Issued: 10/13/2015
• Est. Priority Date: 05/22/2013
• Status: Active Grant

• Current Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: Fenny, Carlos A., Schank, Troy, Stamps, Frank B.
• Primary Examiner(s): BENEDIK, JUSTIN M
• Application Number:
  US13/949,698
• Publication Number:
  US 20150274290A1
• Time in Patent Office: 811 Days
• Field of Search: 244/17.25
• US Class Current: 1/1
• CPC Class Codes: B64C 11/28 Collapsible or foldable blades
• CPC Class Codes: B64C 27/30 with provision for reducing drag of inoperative rotor
• CPC Class Codes: B64C 27/32 Rotors
• CPC Class Codes: B64C 27/41 with flapping hinge or universal joint, common to the blades
• CPC Class Codes: B64C 27/50 Blades foldable to facilitate stowage of aircraft
• CPC Class Codes: B64C 27/52 Tilting of rotor bodily relative to fuselage of see-saw type construction B64C27/43
• CPC Class Codes: B64C 27/605 including swash plate, spider or cam mechanisms
• CPC Class Codes: B64C 27/615 including flaps mounted on blades
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage

Abstract

According to one embodiment, a rotor blade rotation system includes a hub, a rotor blade in mechanical communication with the hub and pivotable about an axis of rotation, a swashplate, a pitch link, and an actuator. The swashplate includes a rotating portion and a non-rotating portion. The pitch link is coupled to the rotating portion of the swashplate and in mechanical communication with the rotor blade. The actuator is coupled to the non-rotating portion of the swashplate and operable to reposition the swashplate from a first position to a second position such that the pitch links pivot the rotor blade from a deployed position to a folded position.

Claims

1. A rotorcraft, comprising:

a body;

a wing coupled to the body;

a power train coupled to at least one of the body or the wing and comprising a power source and a shaft in mechanical communication with the power source;

a tiltrotor assembly pivotally coupled to the wing and in mechanical communication with the shaft, the tiltrotor assembly comprising;

a hub in mechanical communication with the shaft;

a rotor blade in mechanical communication with the hub and pivotable about an axis of rotation;

a swashplate comprising a rotating portion and a non-rotating portion;

a pitch link coupled to the rotating portion of the swashplate and in mechanical communication with the rotor blade; and

an actuator coupled to the non-rotating portion of the swashplate and operable to reposition the swashplate from a first position to a second position such that the pitch links pivot the rotor blade from a deployed position to a folded position.

2. The rotorcraft of claim 1, wherein the second swashplate position is closer to the hub than the first swashplate position.

3. The rotorcraft of claim 1, wherein the folded position is closer to the swashplate than the deployed position.

4. The rotorcraft of claim 1, the tiltrotor assembly further comprising:

a grip disposed between the hub and the rotor blade; and

a linkage positioned between the pitch link proximate to a first end of the linkage and the rotor blade proximate to a second end of the linkage.

5. The rotorcraft of claim 4, further comprising a lock operable to selectively couple and decouple the linkage and the grip.

6. The rotorcraft of claim 4, further comprising a lock operable to selectively couple and decouple the hub and the grip.

7. The rotorcraft of claim 4, wherein the linkage is positioned between the pitch link and the rotor blade such that repositioning the first end of the linkage towards the hub causes the second end of the linkage to pivot the rotor blade towards the swashplate.

8. The rotorcraft of claim 4, further comprising a fold linkage coupling the second end of the linkage to the rotor blade.

9. The rotorcraft of claim 4, the tiltrotor assembly further comprising a lock operable to selectively lock either the grip to the hub or the grip to the linkage.

10. The rotorcraft of claim 1, the tiltrotor assembly further comprising a fold lock deployable in a locked position 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.

11. The rotorcraft of claim 1, the tiltrotor assembly further comprising a flapping lock deployable in a locked position 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.

12. The rotorcraft of claim 1, the tiltrotor assembly further comprising a lock operable to selectively lock either folding of the rotor blade or flapping movement of the hub.

13. The rotorcraft of claim 12, the lock comprising a translating lock pin and a lock pin actuator, the lock pin actuator operable to reposition the translating lock pin to engage either the hub or the linkage.

14. The rotorcraft of claim 1, the actuator further operable to reposition the swashplate such that the pitch links communicate collective flight control movements to the rotor blade.

15. A rotor blade rotation system, comprising:

a hub;

a rotor blade in mechanical communication with the hub and pivotable about an axis of rotation;

a swashplate comprising a rotating portion and a non-rotating portion;

a pitch link coupled to the rotating portion of the swashplate and in mechanical communication with the rotor blade; and

an actuator coupled to the non-rotating portion of the swashplate and operable to reposition the swashplate from a first position to a second position such that the pitch links pivot the rotor blade from a deployed position to a folded position.

16. The system of claim 15, wherein the second swashplate position is closer to the hub than the first swashplate position.