Offset stacked yoke hub for tiltrotor aircraft

• US 9,169,010 B2
• Filed: 02/24/2012
• Issued: 10/27/2015
• Est. Priority Date: 02/24/2012
• Status: Active Grant

• Current Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: Foskey, Christopher, Stamps, Frank B.
• Primary Examiner(s): Kim, Craig
• Assistant Examiner(s): DAVIS, JASON GREGORY
• Application Number:
  US13/405,030
• Publication Number:
  US 20130224025A1
• Time in Patent Office: 1,341 Days
• Field of Search: 416/102, 416/134.A, 416/148
• US Class Current: 1/1
• CPC Class Codes: B64C 27/33 having flexing arms
• CPC Class Codes: B64C 27/35 having elastomeric joints

Abstract

A tiltrotor rotor hub comprises first and second configurations of yokes arranged in two parallel and axially offset planes, each having an equal number of two or more yokes substantially equally spaced about a mast, wherein a portion of each yoke overlaps with a portion of each azimuthally adjacent yoke. Another tiltrotor rotor hub is selectively positionable for operation in helicopter/airplane/transition modes and comprises substantially parallel and axially offset first and second planes, each containing a plurality of blade yokes arranged about a central axis and a portion of each yoke overlaps with a portion of each azimuthally adjacent yoke. Another tiltrotor rotor hub is coupled to a tiltrotor mast and comprises a stacked arrangement of blade yokes wherein a portion of each yoke overlaps with a portion of each azimuthally adjacent yoke, and a plurality of mounting components coupling each yoke to the overlapping azimuthally adjacent yoke.

Claims

1. A rotor hub of a tiltrotor aircraft, comprising:

a first configuration of two or more yokes arranged in a first plane about a mast of the tiltrotor aircraft and having substantially equal angular spacing therebetween;

a second configuration of an equal number of yokes as the first configuration, the equal number of yokes being arranged in a second plane about the mast of the tiltrotor aircraft and having substantially equal angular spacing therebetween;

wherein the second plane is substantially parallel to and axially offset from the first plane; and

wherein a portion of each yoke in the first configuration overlaps with a portion of each azimuthally adjacent yoke in the second configuration; and

a plurality of mounting plates disposed about the rotor hub, wherein each of the plurality of mounting plates includes a plurality of mounting holes,

wherein the number of mounting holes disposed in each of the plurality of mounting plates equals a total quantity of both the configuration yokes and the second configuration yokes.

2. The hub according to claim 1, wherein the second configuration yokes are angularly offset from the first configuration yokes.

3. The hub according to claim 2, wherein the second configuration yokes substantially bisect the angular spaces separating the first configuration yokes, and wherein the angular spaces are equal between each side of each of the second configuration yokes and each side of each of the first configuration yokes.

4. The hub according to claim 1, wherein the second plane is axially offset from the first plane by a predetermined distance sufficient to accommodate flapping without interference.

5. The hub according to claim 1, further comprising a common mounting component coupling each first configuration yoke to at least one azimuthally adjacent second configuration yoke.

6. The hub according to claim 1, wherein the first configuration yokes and the second configuration yokes are arranged at a common radius from the mast.

7. The hub according to claim 1 wherein the first configuration has exactly two yokes and the second configuration has exactly two yokes.

8. The hub according to claim 1 wherein the first configuration has exactly three yokes and the second configuration has exactly three yokes.

9. The hub according to claim 1 wherein the first configuration has four yokes and the second configuration has four yokes.

10. The hub according to claim 1 wherein at least some of the yokes of the first configuration and the second configuration are substantially stiff in-plane.

11. The hub according to claim 1, wherein the second plane is axially offset from the first plane by a predetermined distance substantially equal to about one to two rotor blade chord lengths.

12. The hub according to claim 1, wherein at least some of the yokes of the first configuration and second configuration may undergo flapping motion.

13. A rotor hub of a tiltrotor aircraft, comprising:

a plurality of blade yokes arranged in a first plane about a central axis;

a plurality of blade yokes arranged in a second plane about the central axis;

wherein the second plane is substantially parallel to and axially offset from the first plane;

wherein a portion of each yoke in the first plane overlaps with a portion of each azimuthally adjacent yoke in the second plane; and

wherein the rotor hub is selectively positionable for operation of the tiltrotor aircraft in helicopter mode, airplane mode, and transition modes there between;

a plurality of mounting plates disposed about the rotor hub, wherein each of the plurality of mounting plates includes a plurality of mounting holes; and

a quantity of mounting holes disposed in each of the plurality of mounting plates equal to a total quantity of both the plurality of blade yokes arranged in the first plane and the plurality of blade yokes arranged in the second plane.

14. The hub of claim 13, wherein the plurality of blade yokes in each of the first plane and the second plane are positioned with substantially equal angular spacing therebetween.

15. The hub according to claim 14, wherein the plurality of blade yokes in the first plane are angularly offset from the plurality of blade yokes in the second plane.

16. The hub according to claim 15, wherein the plurality of blade yokes in the second plane substantially bisect the angular spaces separating the plurality of blade yokes in the first plane.

17. The hub according to claim 13, further comprising a common mounting component coupling each yoke in the first plane to the overlapping azimuthally adjacent yoke in the second plane.

18. A rotor hub of a tiltrotor aircraft, comprising:

a plurality of blade yokes configured in a stacked arrangement such that a portion of each yoke in a first axial plane overlaps with a portion of each azimuthally adjacent yoke in a second axial plane;

a plurality of mounting components including a plurality of mounting plates and a plurality of mounting holes, each mounting component coupling each yoke in the first axial plane to the overlapping azimuthally adjacent yoke in the second axial plane;

wherein the rotor hub is coupled to a mast of the tiltrotor aircraft; and

a quantity of mounting holes disposed in each mounting plate equal to a total quantity of the plurality of blade yokes in both the first axial plane and the second axial plane.

19. The hub of claim 18, wherein the plurality of blade yokes in each of the first plane and the second plane are positioned with substantially equal angular spacing therebetween.

20. The hub according to claim 19, wherein the plurality of blade yokes in the second plane substantially bisect the angular spaces separating the plurality of blade yokes in the first plane.