Elastic flapping hinge for connecting a rotor blade to a rotor hub of a rotary wing aircraft

Patent metadata

Field	Value
Publication number	US-10967965-B2
Application number	US-201816106288-A
Country	US
Kind code	B2
Filing date	Aug 21, 2018
Priority date	Aug 28, 2017
Publication date	Apr 6, 2021
Grant date	Apr 6, 2021

Abstract

An elastic flapping hinge for connecting a rotor blade to a rotor hub of a rotary wing aircraft, comprising an elastic flapping hinge member arrangement that includes a hub attachment area for attachment to the rotor hub, a connection area for attachment to the rotor blade, and an elastic flapping hinge area that is arranged between the hub attachment area and the connection area and adapted to allow flapping movements, the elastic flapping hinge member arrangement comprising at least two elastic flapping hinge members having a first bending stiffness for flapping movements and a second bending stiffness for lead-lag movements, the first bending stiffness being smaller than the second bending stiffness, wherein the at least two elastic flapping hinge members diverge from each other in the elastic flapping hinge area by a predetermined divergence angle.

First claim

What is claimed is:

1. An elastic flapping hinge for connecting a rotor blade to a rotor hub of a rotary wing aircraft, comprising an elastic flapping hinge member arrangement that includes a hub attachment area for attachment to the rotor hub, a connection area for attachment to the rotor blade, and an elastic flapping hinge area that is arranged between the hub attachment area and the connection area and adapted to allow flapping movements, the elastic flapping hinge member arrangement comprising at least two elastic flapping hinge members having a first bending stiffness for flapping movements and a second bending stiffness for lead-lag movements, the first bending stiffness being smaller than the second bending stiffness, wherein the at least two elastic flapping hinge members are stacked on top of each other at the rotor hub, and the at least two elastic flapping hinge members diverge from each other in the elastic flapping hinge area by a predetermined divergence angle;
wherein the at least two elastic flapping hinge members diverge from each other in the elastic flapping hinge area by the predetermined divergence angle such that a V-shaped gap is formed in the elastic flapping hinge area between the at least two elastic flapping hinge members;
wherein the at least two flapping hinge members comprise a first elastically deformable plate having first and second indentation regions in the connection area and a second elastically deformable plate having first and second indentation regions in the connection area.

2. The elastic flapping hinge of claim 1 ,
wherein the predetermined divergence angle is from 3° to 40°.

3. The elastic flapping hinge of claim 2 ,
wherein the elastically deformable plates are directly joined to each other in the hub attachment area, and wherein the elastically deformable plates are directly or indirectly joined to each other in the connection area.

4. The elastic flapping hinge of claim 3 ,
wherein at least one web is arranged in the connection area between the elastically deformable plates, wherein the at least one web spaces the elastically deformable plates from each other, and wherein the at least one web is adapted to transfer shear forces between the elastically deformable plates.

5. The elastic flapping hinge of claim 4 ,
wherein the at least one web is embodied as an I-beam.

6. The elastic flapping hinge of claim 3 ,
wherein at least one of the elastically deformable plates comprises at least one cut-out.

7. The elastic flapping hinge of claim 3 ,
wherein at least one of the elastically deformable plates is provided in the hub attachment area with at least two separate arms for attachment to the rotor hub.

8. The elastic flapping hinge of claim 3 ,
wherein the elastically deformable plates are at least partly integrated into at least one of:
associated rotor hub plates,
an associated elastic lead-lag hinge and/or torsion area that defines the connection area, and
the rotor blade.

9. The elastic flapping hinge of claim 1 ,
wherein the elastically deformable plates are attached to each other.

10. The elastic flapping hinge of claim 1 , wherein the elastically deformable plates exhibit a W-shaped cross section.

11. The elastic flapping hinge of claim 10 ,
wherein the first and second indentation regions of the first elastically deformable plate are attached to the first and second indentation regions of the second elastically deformable plate.

12. The elastic flapping hinge of claim 11 ,
wherein a spacer is arranged between the first elastically deformable plate and the second elastically deformable plate, at least between the first and second indentation regions of the first elastically deformable plate and the first and second indentation regions of the second elastically deformable plate.

13. A rotary wing aircraft with at least one rotor that comprises at least two rotor blades, and with a rotor hub, each one of the at least two rotor blades being connected to the rotor hub via an associated elastic hinge unit that comprises at least an elastic flapping hinge that is embodied according to claim 1 .

14. An elastic flapping hinge for connecting a rotor blade to a rotor hub of a rotary wing aircraft, the elastic flapping hinge comprising an elastic flapping hinge member arrangement that includes a hub attachment area for attachment to the rotor hub, a connection area for attachment to the rotor blade, and an elastic flapping hinge area arranged between the hub attachment area and the connection area and adapted to allow flapping movements, the elastic flapping hinge member arrangement comprising at least two elastic flapping hinge members having a first bending stiffness for flapping movements and a second bending stiffness for lead-lag movements, the first bending stiffness being smaller than the second bending stiffness, wherein the at least two elastic flapping hinge members are stacked on top of each other at the rotor hub, and the at least two elastic flapping hinge members diverge from each other in the elastic flapping hinge area by a predetermined divergence angle; wherein the at least two flapping hinge members comprise a first elastically deformable plate having first and second indentation regions in the connection area and a second elastically deformable plate having first and second indentation regions in the connection area, the first and second indentation regions of the first elastically deformable plate are attached to the first and second indentation regions of the second elastically deformable plate.

15. The elastic flapping hinge of claim 14 , wherein the first and second elastically deformable plates diverge from each other in the elastic flapping hinge area by the predetermined divergence angle such that a V-shaped gap is formed in the elastic flapping hinge area between the first and second elastically deformable plates.

16. The elastic flapping hinge of claim 14 , wherein a spacer is arranged between the first and second elastically deformable plates between the first and second indentation regions of the first elastically deformable plate and the first and second indentation regions of the second elastically deformable plate.

17. The elastic flapping hinge of claim 14 , wherein at least one beam is arranged in the connection area between the elastically deformable plates, wherein the at least one beam spaces the elastically deformable plates from each other, and wherein the at least one beam is adapted to transfer shear forces between the elastically deformable plates.

18. The elastic flapping hinge of claim 17 , wherein the first and second elastically deformable plates exhibit a W-shaped cross section.

19. An elastic flapping hinge for connecting a rotor blade to a rotor hub of a rotary wing aircraft, comprising an elastic flapping hinge member arrangement that includes a hub attachment area for attachment to the rotor hub, a connection area for attachment to the rotor blade, and an elastic flapping hinge area that is arranged between the hub attachment area and the connection area and adapted to allow flapping movements, the elastic flapping hinge member arrangement comprising at least two elastic flapping hinge members having a first bending stiffness for flapping movements and a second bending stiffness for lead-lag movements, the first bending stiffness being smaller than the second bending stiffness, wherein the at least two elastic flapping hinge members are stacked on top of each other at the rotor hub, and the at least two elastic flapping hinge members d

Assignees

• Airbus Helicopters Deutschland GmbH

Inventors

• Buesing Moritz
• Pfaller Rupert
• Ortner Martin

Classifications

• B64C27/33 Primary

  having flexing arms · CPC title

• B64C27/635

  specially for controlling lag-lead movements of blades · CPC title

• B64C27/48

  Root attachment to rotor head · CPC title