ROTOR HUB FOR A ROTORCRAFT

• US 20150125300A1
• Filed: 11/05/2013
• Published: 05/07/2015
• Est. Priority Date: 11/05/2013
• Status: Abandoned Application

• Current Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: Stamps, Frank B., Rauber, Richard, Davis, Hunter Jay
• Application Number:
  US14/072,511
• Publication Number:
  US 20150125300A1
• Time in Patent Office: Days
• US Class Current: 416/134.A
• CPC Class Codes: B64C 27/35 having elastomeric joints
• CPC Class Codes: B64C 27/41 with flapping hinge or universal joint, common to the blades

Abstract

A drive mechanism for a rotary aircraft includes an outer drive member having a plurality of drive trunnions extending therefrom; a middle drive member resiliently coupled to the outer drive member; and an inner drive member resiliently coupled to the middle drive member.

Claims

1. A drive mechanism for a rotary aircraft, the drive mechanism comprising:

an outer drive member having a plurality of drive trunnions extending therefrom;

a middle drive member resiliently coupled to the outer drive member;

an inner drive member resiliently coupled to the middle drive member.

2. The drive mechanism according to claim 1, further comprising:

a rotor mast coupled to the inner drive member.

3. The drive mechanism according to claim 1, further comprising:

a rotor mast splined to the inner drive member.

4. The drive mechanism according to claim 1, further comprising:

a plurality of drive links, each drive link being coupled to a rotor yoke and one of the plurality of drive trunnions.

5. The drive mechanism according to claim 1, wherein the inner drive member includes a first member and a second member each extending from a body portion along a first axis.

6. The drive mechanism according to claim 5, wherein the first member and the second member have a square cross sectional shape.

7. The drive mechanism according to claim 5, wherein the first member and the second member are resiliently coupled to a first opening and a second opening, respectively, of the middle drive member with a first elastomeric member and a second elastomeric member.

8. The drive mechanism according to claim 7, wherein the first elastomeric member and the second elastomeric member are configured to deflect and allow relative motion between the inner drive member and the middle drive member in a direction along the first axis.

9. The drive mechanism according to claim 1, wherein the middle drive member includes a third member and a fourth member each extending from a main portion along a second axis.

10. The drive mechanism according to claim 9, wherein the third member and the fourth member have a square cross sectional shape.

11. The drive mechanism according to claim 9, wherein the third member and the fourth member are resiliently coupled to a third opening and a fourth opening, respectively, of the outer drive member with a third elastomeric member and a fourth elastomeric member.

12. The drive mechanism according to claim 11, wherein the third elastomeric member and the fourth elastomeric member are configured to deflect and allow relative motion between the middle drive member and the outer drive member in a direction along the second axis.

13. The drive mechanism according to claim 1, further comprising:

a top plate; and

a lower plate.

14. The drive mechanism according to claim 1, wherein outer drive member, the middle drive member, and the inner drive member are located in a single plane.

15. The drive mechanism according to claim 14, wherein the single plane is normal to a rotational axis of a rotor mast.

16. The drive mechanism according to claim 1, wherein torque from the rotor mast is carried to a rotor yoke through the inner drive member, the middle drive member, and the outer drive member.

17. A rotor hub for an aircraft, the rotor hub comprising:

a yoke being configured for coupling a plurality of rotor blades thereto;

a rotor mast;

a drive mechanism for transferring torque between the rotor mast and the yoke;

the drive mechanism comprising;

an outer drive member having a plurality of drive trunnions extending therefrom;

a middle drive member resiliently coupled to the outer drive member; and

an inner drive member resiliently coupled to the middle drive member;

a plurality of drive links coupled to the yoke and to trunnions of the outer drive member.

18. The rotor hub according to claim 17, wherein the aircraft is a tilt rotor aircraft.

19. The rotor hub according to claim 17, wherein the aircraft is a helicopter.

20. The rotor hub according to claim 17, wherein outer drive member is configured to translate relative to the middle member along a first axis, and wherein the outer drive member and the middle drive member are configured to collectively translate relative to the inner drive member about a second axis.