Rotor blade folding system

• US 7,530,790 B2
• Filed: 09/20/2006
• Issued: 05/12/2009
• Est. Priority Date: 09/20/2006
• Status: Active Grant

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Schmaling, David N., Cabrera, Pedro L.
• Primary Examiner(s): Look; Edward
• Assistant Examiner(s): White; Dwayne J
• Application Number:
  US11/524,020
• Publication Number:
  US 20090097973A1
• Time in Patent Office: 965 Days
• Field of Search: 416/134.A, 416/142, 416/143, 416/141
• US Class Current: 416/134.00A
• CPC Class Codes: B64C 27/10 arranged coaxially
• CPC Class Codes: B64C 27/50 Blades foldable to facilitate stowage of aircraft

Abstract

A rotor blade folding system includes a bearing housing which supports a bearing and rotor blade spindle which folds relative the rotor hub assembly about a fold axis. The rotor blade folding system essentially collapses the rotor hub to facilitate compatibility with a fairing system. By rotating the entire pitch bearing assembly, pitch lock systems are also minimized as the pitch lock system need only react a blade-feathering moment.

Claims

1. A rotor blade assembly comprising:

a rotor blade bearing housing foldable about a fold axis; and

a rotor blade bearing mounted to said bearing housing which defines a blade pitch axis transverse to said fold axis, said fold axis inboard of said rotor blade bearing.

2. The assembly as recited in claim 1, wherein said bearing housing defines a bearing housing lug which defines said fold axis.

3. The assembly as recited in claim 1, further comprising a rotor blade spindle mounted to said rotor blade bearing, said rotor blade spindle mounted to a rotor blade for rotation about said blade pitch axis.

4. The assembly as recited in claim 3, wherein said bearing housing defines a bearing housing lug opposite said rotor blade spindle.

5. The assembly as recited in claim 3, further comprising a rotor hub mounted horn spindle coupling engageable with a pitch control coupling mounted to said bearing housing for rotation within said rotor blade spindle.

6. The assembly as recited in claim 3, wherein said rotor blade bearing includes an elastomeric bearing contained within said rotor blade bearing housing.

7. The assembly as recited in claim 6, wherein said elastomeric bearing is an elastomeric spherical bearing.

8. A rotor blade assembly comprising:

a rotor blade bearing housing foldable about a fold axis;

a rotor blade bearing mounted to said bearing housing which defines a blade pitch axis transverse to said fold axis; and

a blade pitch control coupling mounted for rotation within a blade retention spindle along said blade pitch axis to operate a servo-flap assembly.

9. The assembly as recited in claim 8, further comprising a joint interspaced within said rotor blade spindle.

10. A rotor hub assembly comprising:

a rotor hub having a rotor hub lug;

a rotor blade bearing housing having a bearing housing lug pivotably engaged with said rotor hub lug about a fold axis, said bearing housing foldable relative said rotor hub about said fold axis between a folded position and a flight position; and

a rotor blade bearing mounted to said bearing housing which defines a blade pitch axis transverse to said fold axis, said fold axis inboard of said bearing.

11. The assembly as recited in claim 10, further comprising a rotor blade spindle mounted to said rotor blade bearing for rotation about said blade pitch axis.

12. The assembly as recited in claim 11, further comprising a second bearing housing lug selectively engageable with a second rotor hub lug.

13. The assembly as recited in claim 12, further comprising a pitch control coupling mounted for rotation with said rotor blade spindle, said pitch control coupling located between said bearing housing lug and said second bearing housing lug.

14. The assembly as recited in claim 10, further comprising a pitch control coupling mounted for rotation with said rotor blade spindle.

15. The assembly as recited in claim 10, further comprising a horn spindle mounted to said rotor hub for rotation about a hub spindle pitch axis, said hub spindle pitch axis in-line with said blade pitch axis when said bearing housing is in said flight position.

16. The assembly as recited in claim 10, further comprising a pitch control rod engaged with said horn spindle to pitch said horn spindle about said hub spindle pitch axis.

17. A method of folding a rotor blade assembly of a rotary wing aircraft rotor hub assembly comprising the steps of:

(A) mounting an elastomeric bearing assembly within a rotor blade bearing housing to support a rotor blade spindle about a blade pitch axis; and

(B) folding the rotor blade bearing assembly inboard of the elastomeric bearing assembly relative a rotor hub about a fold axis transverse to the blade pitch axis.

18. A method as recited in claim 17, wherein said step (A) further comprises:

(a) controlling the pitch of a rotor blade with the rotor blade spindle through a pitch control coupling assembly when the rotor blade bearing assembly is locked in a flight position relative the rotor hub.

19. A method as recited in claim 17, wherein said step (A) further comprises:

(a) controlling the pitch of a servo-flap control system with the rotor blade spindle through a pitch control coupling assembly when the rotor blade bearing assembly is locked in a flight position relative the rotor hub.

20. A rotor blade assembly comprising:

a rotor blade bearing housing foldable about a fold axis an elastomeric bearing assembly within said rotor blade bearing housing, said fold axis inboard of said elastomeric bearing assembly.

21. The assembly as recited in claim 20, wherein said elastomeric bearing assembly supports a rotor blade spindle about a blade pitch axis.

22. The assembly as recited in claim 21, wherein said blade pitch axis is transverse to said fold axis.