Inboard bearing assemblies for proprotor systems

Patent metadata

Field	Value
Publication number	US-10472059-B2
Application number	US-201715648650-A
Country	US
Kind code	B2
Filing date	Jul 13, 2017
Priority date	Jul 13, 2017
Publication date	Nov 12, 2019
Grant date	Nov 12, 2019

Abstract

A proprotor system for a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode. The proprotor system includes a yoke having a plurality of blade arms with inboard pockets. A centrifugal force and shear bearing assembly is disposed in each of the inboard pockets of the yoke. Each of a plurality of proprotor blades is coupled to the yoke by one of the bearing assemblies such that each proprotor blade has a pitch change degree of freedom about a pitch change axis and a tilting degree of freedom about a focal point. Each bearing assembly includes a centrifugal force bearing coupled to the yoke, a shear bearing coupled to the yoke and an inboard beam coupled between the centrifugal force bearing and the shear bearing. Each inboard beam is coupled to a respective proprotor blade.

First claim

What is claimed is:

1. A proprotor system for a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode, the proprotor system comprising:
a yoke having a plurality of blade arms including a first blade arm having an inboard pocket and an outboard end;
an outboard shear bearing coupled to the outboard end of the first blade arm;
a bearing assembly disposed at least partially within the inboard pocket, the bearing assembly including an inboard shear bearing coupled to the yoke and a centrifugal force bearing coupled to the yoke;
an inboard beam disposed at least partially between the centrifugal force bearing and the inboard shear bearing; and
a proprotor blade coupled to the inboard beam such that the proprotor blade has a pitch change degree of freedom about a pitch change axis and a tilting degree of freedom about a focal point.

2. The proprotor system as recited in claim 1 wherein, the centrifugal force bearing is positioned outboard of the inboard shear bearing.

3. The proprotor system as recited in claim 1 wherein, the inboard beam is operable to rotate relative to the yoke about the pitch change axis.

4. The proprotor system as recited in claim 1 wherein, the centrifugal force bearing further comprises:
an outboard member coupled to the yoke and having a concave spherical surface;
an inboard member coupled to the inboard beam and having a convex spherical surface; and
a series of spherical elastomeric layers separated by inelastic shims between the outboard member and the inboard member.

5. The proprotor system as recited in claim 4 wherein, the inboard member of the centrifugal force bearing is operable to rotate relative to the outboard member of the centrifugal force bearing responsive to rotation of the inboard beam about the pitch change axis.

6. The proprotor system as recited in claim 1 wherein, the inboard shear bearing further comprises:
a radially inwardly disposed journal bearing coupled to the inboard beam; and
a radially outwardly disposed spherical bearing providing the tilting degree of freedom for the inboard beam relative to the yoke.

7. The proprotor system as recited in claim 6 wherein, the radially inwardly disposed journal bearing of the inboard shear bearing is operable to rotate relative to the radially outwardly disposed spherical bearing of the inboard shear bearing responsive to rotation of the inboard beam about the pitch change axis.

8. The proprotor system as recited in claim 1 wherein, the centrifugal force bearing is coupled to the inboard shear bearing.

9. The proprotor system as recited in claim 1 wherein a first in-plane frequency of the proprotor system is greater than 1.0/rev.

10. The proprotor system as recited in claim 1 wherein a first in-plane frequency of the proprotor system is between about 1.2/rev and about 1.8/rev.

11. The proprotor system as recited in claim 1 wherein a first in-plane frequency of the proprotor system is between about 1.4/rev and about 1.6/rev.

12. A tiltrotor aircraft having a helicopter flight mode and an airplane flight mode, the tiltrotor aircraft comprising:
a fuselage;
a wing extending from the fuselage having first and second outboard ends;
first and second pylon assemblies respectively coupled to the wing proximate the first and second outboard ends; and
first and second proprotor systems operably associated respectively with the first and second pylon assemblies, each proprotor system including:
a yoke having a plurality of blade arms including a first blade arm having an inboard pocket and an outboard end;
an outboard shear bearing coupled to the outboard end of the first blade arm;
a bearing assembly disposed at least partially within the inboard pocket, the bearing assembly including an inboard shear bearing coupled to the yoke and a centrifugal force bearing coupled to the yoke;
an inboard beam disposed at least partially between the centrifugal force bearing and the inboard shear bearing; and
a proprotor blade coupled to the inboard beam such that the proprotor blade has a pitch change degree of freedom about a pitch change axis and a tilting degree of freedom about a focal point.

13. The tiltrotor aircraft as recited in claim 12 wherein, the centrifugal force bearing is positioned outboard of the inboard shear bearing.

14. The tiltrotor aircraft as recited in claim 12 wherein the centrifugal force bearing further comprises:
an outboard member coupled to the yoke and having a concave spherical surface;
an inboard member coupled to the inboard beam and having a convex spherical surface; and
a series of spherical elastomeric layers separated by inelastic shims between the outboard member and the inboard member; and
wherein the inboard member is operable to rotate relative to the outboard member responsive to rotation of the inboard beam about the pitch change axis.

15. The tiltrotor aircraft as recited in claim 12 wherein, the inboard shear bearing further comprises:
a radially inwardly disposed journal bearing coupled to the inboard beam; and
a radially outwardly disposed spherical bearing providing the tilting degree of freedom for the inboard beam relative to the yoke.

16. The tiltrotor aircraft as recited in claim 12 wherein, the centrifugal force bearing is coupled to the inboard shear bearing.

17. The tiltrotor aircraft as recited in claim 12 wherein a first in-plane frequency of each proprotor system is greater than 1.0/rev.

18. The tiltrotor aircraft as recited in claim 12 wherein a first in-plane frequency of each proprotor system is between about 1.2/rev and about 1.8/rev.

19. The tiltrotor aircraft as recited in claim 12 wherein a first in-plane frequency of each proprotor system is between about 1.4/rev and about 1.6/rev.

Assignees

• Bell Helicopter Textron Inc
• Bell Textron Inc

Inventors

• Cravener Kyle Thomas
• Kizhakkepat Amarjit
• Shundo Ken
• Paulson Jared Mark
• Baldwin Tyler Wayne

Classifications

• F16C33/22

  Sliding surface consisting mainly of rubber or synthetic rubber (F16C33/24 - F16C33/28 take precedence) · CPC title

• F16C27/063

  Sliding contact bearings · CPC title

• B64C27/54

  Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement · CPC title

• B64C27/35

  having elastomeric joints · CPC title

• F16C23/045

  for radial load mainly, e.g. radial spherical plain bearings · CPC title