Rotorcraft elastomeric bearing assembly

Patent metadata

Field	Value
Publication number	US-9873507-B2
Application number	US-201514630382-A
Country	US
Kind code	B2
Filing date	Feb 24, 2015
Priority date	Feb 26, 2014
Publication date	Jan 23, 2018
Grant date	Jan 23, 2018

Abstract

In some embodiments, a rotorcraft may include a yoke, a blade, a spindle associated with the yoke, and an elastomeric bearing assembly. The center length of the spindle may define a center axis that passes through a center of the elastomeric bearing assembly. The elastomeric bearing assembly may contain a housing coupled to the blade and disposed around the center axis that is configured to rotate in relation to the center axis. The elastomeric bearing assembly may contain an elastomeric shear bearing that has an interior portion coupled to the spindle and an exterior portion coupled to the housing. The elastomeric bearing assembly may contain an elastomeric centrifugal force bearing pressed against the housing. The shear bearing may be configured to counteract a torsional force, and the centrifugal force bearing may be configured to counteract a compression force.

First claim

The invention claimed is:

1. A rotor system for a rotorcraft, the rotor system comprising:
a yoke;
a blade; and
a spindle associated with the yoke, wherein the center length of the spindle defines a center axis that passes through a center of an elastomeric bearing assembly, wherein the elastomeric bearing assembly comprises:
a housing disposed around the center axis, the housing configured to rotate about the center axis, the housing coupled to the blade;
an elastomeric shear bearing, wherein an interior portion of the shear bearing is coupled to the spindle, an exterior portion of the shear bearing is coupled to the housing, an outer perimeter of the shear bearing comprises a race that has a first radial aperture and the housing has a second radial aperture, the first and second radial aperture configured to allow a fastener to be disposed within both the first and second radial aperture, and wherein the shear bearing is configured to counteract a torsional force; and
an elastomeric centrifugal force bearing pressed against the housing, the centrifugal force bearing configured to counteract a compression force.

2. The rotor system of claim 1 , wherein the housing comprises a first bolt hole and a second bolt hole, each comprising an opening that is on a plane that is outboard of the shear bearing and inboard of the centrifugal force bearing.

3. The rotor system of claim 1 , wherein the shear bearing has a plurality of cylindrical alternating elastomeric layers and rigid layers.

4. The rotor system of claim 1 , wherein the centrifugal force bearing has a plurality of alternating elastomeric layers and rigid layers.

5. The rotor system of claim 1 , wherein the elastomeric bearing assembly comprises a cap pressed against the centrifugal force bearing, the cap being coupled to the spindle.

6. The rotor system of claim 5 , wherein the centrifugal force bearing is located between the housing and the cap.

7. The rotor system of claim 1 , wherein the elastomeric bearing assembly has an axial aperture configured to allow a pin to be disposed within to prevent a rotation of the shear bearing.

8. The rotor system of claim 1 , wherein the housing comprises an aperture that extends through the housing.

9. An elastomeric bearing assembly for a rotorcraft, the elastomeric bearing assembly comprising:
a housing disposed around a center axis, the housing configured to rotate about the center axis and configured to be coupled to a rotorcraft blade;
an elastomeric shear bearing, wherein an exterior portion of the shear bearing is coupled to the housing, an outer perimeter of the shear bearing comprises a race that has a first radial aperture and the housing has a second radial aperture, the first and second radial aperture configured to allow a fastener to be disposed within both the first and second radial aperture, and wherein the shear bearing is configured to counteract a torsional force created by the rotation of the housing; and
an elastomeric centrifugal force bearing pressed against the housing, the centrifugal force bearing configured to counteract a compression force along the center axis.

10. The elastomeric bearing of claim 9 , wherein the housing comprises a first bolt hole and a second bolt hole, each bolt hole comprising an opening that is on a plane that is located between the shear bearing and the centrifugal force bearing.

11. The elastomeric bearing of claim 9 , wherein the shear bearing has a plurality of alternating elastomeric layers and rigid layers.

12. The elastomeric bearing of claim 11 , wherein the plurality of alternating elastomeric layers and rigid layers are cylindrical.

13. The elastomeric bearing of claim 9 , wherein the centrifugal force bearing has a plurality of alternating elastomeric layers and rigid layers.

14. The elastomeric bearing of claim 11 , wherein the plurality of alternating elastomeric layers and rigid layers are planar.

15. The elastomeric bearing of claim 9 , wherein the elastomeric bearing assembly has an aperture configured to allow a pin to be disposed within to prevent a rotation of the shear bearing.

16. The elastomeric bearing of claim 9 , wherein the housing comprises an aperture that extends through the housing.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Foskey Christopher E
• Southerland Michael J

Classifications

• B64C11/04

  Blade mountings · CPC title

• B64C27/35 Primary

  having elastomeric joints · CPC title

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title

• B64C27/001

  Vibration damping devices · CPC title

• F16F1/38

  with a sleeve of elastic material between a rigid outer sleeve and a rigid inner sleeve or pin {, i.e. bushing-type (hydraulically-damped bushes F16F13/14; suppression of vibrations in rotating systems by making use of elastomeric spring members between rotating elements, driveline torque being transmitted therebetween F16F15/126, by making use of a dynamic damping mass attached to a rotating element by means of elastomeric springs F16F15/14; pivots per se F16C11/00; elastic or yielding bearings or bearing supports F16C27/00; parts of sliding-contact bearings, e.g. bushes F16C33/04)} · CPC title