Gimbaled tail rotor hub with spherical elastomeric centrifugal force bearing for blade retention and pitch change articulation

Patent metadata

Field	Value
Publication number	US-9657582-B2
Application number	US-201313800174-A
Country	US
Kind code	B2
Filing date	Mar 13, 2013
Priority date	Mar 13, 2013
Publication date	May 23, 2017
Grant date	May 23, 2017

Abstract

A rotor hub comprises a gimbal assembly and an elastomeric centrifugal force bearing. The gimbal assembly is configured to transfer rotational movement of a mast to the rotor hub and to enable the rotor hub to flap relative to the mast. The elastomeric centrifugal force bearing is configured to withstand centrifugal force of a rotor blade when the mast is rotated and is configured to accommodate pitch changes of the rotor blade. A method comprises designing a gimbal assembly that enables a tail rotor hub to flap relative to a tail rotor mast. A centrifugal force bearing is selected that enables tail rotor blades to withstand centrifugal force and that allows for tail rotor blade pitch change articulation. Then, instructions are provided to use the gimbal assembly and the centrifugal force bearing in an in-plane tail rotor assembly.

First claim

What is claimed is:

1. A tail rotor assembly for a helicopter comprising a rotor hub and a rotor blade, the rotor hub comprising:
a gimbal assembly that transfers rotational movement of a mast to the rotor hub and comprising two opposing pairs of elastomeric bearings that enable the rotor hub to flap relative to the mast;
a plate attached to the gimbal assembly;
a pitch horn/shear restraint comprising a rotatable connection to the plate; and
an elastomeric centrifugal force bearing attached to the hub plate and configured to withstand centrifugal force of a rotor blade when the mast is rotated and that is configured to accommodate pitch changes of the rotor blade, wherein the rotor blade is positioned between the rotatable connection of the pitch horn/shear restraint and the elastomeric centrifugal force bearing.

2. The tail rotor assembly of claim 1 , further comprising a plurality of pitch horns/shear restraints that are configured in an in-plane configuration.

3. The tail rotor assembly of claim 1 , wherein the elastomeric centrifugal force bearing comprises a spherical elastomeric bearing.

4. The tail rotor assembly of claim 1 , wherein the elastomeric centrifugal force bearing is configured to fit within an aperture of the rotor blade.

5. The tail rotor assembly of claim 1 , wherein the gimbal assembly comprises one or more elastomeric bearings.

6. The tail rotor assembly of claim 1 , the gimbal assembly comprising a first set of elastomeric bearings that fit around opposing protrusions extending from the trunnion, a gimbal body supported by the first set of elastomeric bearings disposed along a first axis, and a second set of elastomeric bearings disposed along a second axis and fit around opposing protrusions on the gimbal body, the two opposite sets of elastomeric bearings comprising the first set of elastomeric bearings and the second set of elastomeric bearings.

7. The tail rotor assembly of claim 6 , further comprising a hub plate attached to the gimbal assembly and the elastomeric centrifugal force hearing; and
wherein the gimbal body is configured to rotate about the first axis on the first set of elastomeric bearings, and the hub plates are configured to rotate about the second axis on the second set of elastomeric bearings.

8. The tail rotor assembly of claim 6 , wherein the first axis is offset from the second axis by 90 degrees relative to a central axis of the tail rotor mast.

9. The tail rotor assembly of claim 1 , wherein the elastomeric centrifugal force bearing and the two sets of opposing elastomeric bearings lie in the same plane of the rotor hub.

10. A tail rotor assembly comprising:
a gimbal assembly that transfers rotational movement a mast to the rotor hub and comprising two opposing sets of elastomeric bearings that enable the rotor hub to flap relative to the mast;
a plate attached to the gimbal assembly;
a pitch horn/shear restraint comprising a rotatable connection to the plate;
a spherical centrifugal force bearing attached to the plate; and
a rotor blade positioned between the rotatable connection of the pitch horn/shear restraint and the spherical centrifugal force bearing; and
wherein the gimbal assembly is configured to transfer rotational movement of the rotor mast to the plate and enable the plate to flap relative to the mast via the two opposing sets of elastomeric bearings.

11. The tail rotor assembly of claim 10 , further comprising additional rotor blades, and wherein the rotor blade and the additional rotor blades are configured in an in-plane configuration.

12. The tail rotor assembly of claim 11 , wherein the rotor blade and the additional rotor blades comprise a scissor configuration.

13. The tail rotor assembly of claim 10 , wherein the gimbal assembly comprises a trunnion and one or more elastomeric bearings.

14. The tail rotor assembly of claim 13 , wherein the one or more elastomeric bearings comprises two sets of opposing elastomeric bearings.

15. The tail rotor assembly of claim 10 , wherein the pitch horn/shear restraint is rotatably connected to the plate through an elastomeric bearing and an elastomeric or metallic shear bearing.

16. The tail rotor assembly of claim 10 , wherein the rotor blade comprises an aperture, and wherein the centrifugal force bearing is positioned within the rotor blade aperture.

17. The tail rotor assembly of claim 10 , wherein the spherical elastomeric bearing is attached to the plate through a CF bearing clevis fitting.

18. The tail rotor assembly of claim 10 , wherein the pitch horn/shear restraint is configured to control a pitch of the rotor blade using a pitch linkage and accommodate in-plane shear loads.

19. The tail rotor assembly of claim 10 , wherein the gimbal assembly, the plate, the pitch born/shear restraint, the spherical centrifugal force bearing, and the rotor blade arc components of a tail rotor assembly, wherein the apparatus further comprises an engine, a transmission, a drive shaft, a mast, and a fuselage, wherein power from the engine is transferred to the tail rotor assembly through the transmission, the drive shaft, and the mast, and wherein the fuselage houses and supports at least a portion of the engine, the drive shaft, and the transmission.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Haldeman Andrew
• Stamps Frank Bradley
• Sutton Drew
• Hethcock James Donn

Classifications

• B64C27/41

  with flapping hinge or universal joint, common to the blades · CPC title

• B64C27/32

  Rotors · CPC title

• B64C27/78

  in association with pitch adjustment of blades of anti-torque rotor · CPC title

• B64C27/35 Primary

  having elastomeric joints · CPC title

• B64C27/48

  Root attachment to rotor head · CPC title