Low-drag fairing and rotor assembly

Patent metadata

Field	Value
Publication number	US-11053001-B2
Application number	US-201916447618-A
Country	US
Kind code	B2
Filing date	Jun 20, 2019
Priority date	Jun 20, 2019
Publication date	Jul 6, 2021
Grant date	Jul 6, 2021

Abstract

A rotorcraft includes a main rotor system coupled to a mast and a rotor assembly. The rotor assembly includes a yoke comprising a rotor coupling, a first damper mount attached to the rotor coupling, a rotor extension configured to couple to the rotor coupling and comprising a second damper mount, a damper coupled to the first and second damper mounts, and a fairing enclosing the damper and the yoke.

First claim

What is claimed is:

1. A low-drag rotor assembly comprising:
a yoke comprising a rotor coupling and a first damper mount;
a rotor extension comprising a first connector, a second connector, a second damper mount, and a shaft extending between the first connector and the second connector, wherein the first connector is attached to a rotor blade and the second connector is attached to the rotor coupling;
a damper coupled to the first and second damper mounts;
a fairing enclosing the damper and the yoke, wherein a first portion of the shaft extends through a cut-out in the fairing and a second portion of the shaft is positioned outside of the fairing, the first portion having a circular cross-section and the second portion having an elliptical cross-section.

2. The low-drag rotor assembly of claim 1 , wherein a central axis passing through the damper forms an angle between 15° and 75° relative to a central axis passing through the rotor extension.

3. The low-drag rotor assembly of claim 1 , wherein the shaft is hollow.

4. The low-drag rotor assembly of claim 3 , wherein a central axis passing through the damper forms an angle between 15° and 75° relative to a central axis passing through the rotor extension.

5. The low-drag rotor assembly of claim 1 , wherein the first connector comprises a tongue and the second connector comprises a clevis.

6. The low-drag rotor assembly of claim 1 , wherein the rotor coupling comprises a bearing assembly.

7. The low-drag rotor assembly of claim 6 , wherein the bearing assembly comprises:
an inboard beam that couples to the yoke; and
a CF bearing coupled between the inboard beam and a bearing seat of the yoke.

8. The low-drag rotor assembly of claim 1 , wherein the first connector and the second connector are disposed on the shaft at an angle relative to one another to introduce an amount of blade twist to the rotor blade.

9. The low-drag rotor assembly of claim 1 , wherein a central axis passing through the damper forms an angle of 45° relative to a central axis passing through the rotor extension.

10. A rotorcraft comprising:
a main rotor system coupled to a mast and comprising a rotor assembly having a yoke and a first damper mount;
a rotor extension comprising a first connector attached to a rotor blade, a second connector attached to the yoke, a second damper mount, and a shaft extending between the first connector and the second connector;
a damper coupled to the first and second damper mounts; and
a fairing enclosing the damper and the yoke, wherein a first portion of the shaft is positioned in a cut-out in the fairing and a second portion of the shaft is positioned outside of the fairing, wherein the first portion has a circular cross-section and the second portion has an elliptical cross-section.

11. The rotorcraft of claim 10 , wherein the first connector and the second connector are disposed on the shaft at an angle relative to one another to introduce an amount of blade twist to the rotor blade.

12. The rotorcraft of claim 10 , wherein a central axis passing through the damper forms an angle between 15° and 75° relative to a central axis passing through the rotor extension.

13. The rotorcraft of claim 10 , wherein the shaft is hollow.

14. The rotorcraft of claim 10 , wherein the first connector comprises a tongue and the second connector comprises a clevis.

15. The rotorcraft of claim 14 , wherein the clevis is attached to the yoke via a bearing assembly.

16. The rotorcraft of claim 15 , wherein the bearing assembly comprises:
an inboard beam that couples to the yoke; and
a CF bearing coupled between the inboard beam and a bearing seat of the yoke.

17. The rotorcraft of claim 10 , wherein the first connector and the second connector are disposed on the shaft at an angle relative to one another to introduce an amount of blade twist to the rotor blade; and
the second connector comprises a clevis attached to the yoke via a bearing assembly.

18. The rotorcraft of claim 17 , wherein the shaft is hollow.

19. The rotorcraft of claim 17 , wherein the bearing assembly comprises:
an inboard beam that couples to the yoke; and
a CF bearing coupled between the inboard beam and a bearing seat of the yoke.

20. The rotorcraft of claim 19 , wherein the shaft is hollow.

Assignees

• Bell Textron Inc

Inventors

• Shimek Glenn Alan
• Paulson Jared Mark
• Donovan Tom
• Burnett Michael Christopher

Classifications

• B64C27/32

  Rotors · CPC title

• B64C27/48

  Root attachment to rotor head · CPC title

• B64C27/51 Primary

  Damping of blade movements · CPC title

• B64C27/37

  having articulated joints · CPC title