Rotor hub with enforced collective coning

Patent metadata

Field	Value
Publication number	US-10654558-B2
Application number	US-201815938979-A
Country	US
Kind code	B2
Filing date	Mar 28, 2018
Priority date	Mar 28, 2018
Publication date	May 19, 2020
Grant date	May 19, 2020

Abstract

One example of a rotor assembly comprises: a rotor hub operable to rotate based on rotation of a mast; a first rotor blade pivotally attached to the rotor hub; a bracing member pivotally attached to the rotor hub at a first end and pivotally attached to the first rotor blade at a second end; and a linkage mechanism coupling the first rotor blade to a second rotor blade. The bracing member is operable to transfer a coning movement of the first rotor blade to a movement of the linkage mechanism and a corresponding coning movement of the second rotor blade.

First claim

What is claimed is:

1. A rotor assembly comprising:
a rotor hub operable to rotate based on rotation of a mast;
a first rotor blade pivotally attached to the rotor hub;
a bracing member pivotally attached to the rotor hub at a first end and pivotally attached to the first rotor blade at a second end; and
a linkage mechanism coupling the first rotor blade to a second rotor blade;
wherein the bracing member is operable to transfer a coning movement of the first rotor blade to a movement of the linkage mechanism and a corresponding coning movement of the second rotor blade.

2. The rotor assembly of claim 1 , further comprising:
an outboard bearing support operable to couple the second end of the bracing member to a root of the first rotor blade, the outboard bearing support comprising a sleeve operable to support the root of the first rotor blade.

3. The rotor assembly of claim 2 , wherein the sleeve of the outboard bearing support comprises:
a ball bearing operable to facilitate movement between the sleeve and the root of the first rotor blade.

4. The rotor assembly of claim 2 , wherein the sleeve of the outboard bearing support comprises:
an elastomeric shear bearing operable to generate a shear resistance based on the coning movement of the first rotor blade.

5. The rotor assembly of claim 1 , further comprising:
an inboard bearing support operable to pivotally attach the first rotor blade to the rotor hub, the inboard bearing support comprising an elastomeric bearing operable to support a load generated between the first rotor blade and the rotor hub.

6. The rotor assembly of claim 1 , further comprising:
a shell configured to enclose at least a portion of the rotor assembly, wherein the shell comprises an opening configured to limit the coning movement of the first rotor blade.

7. The rotor assembly of claim 6 , further comprising:
structural members operable to reinforce the shell, wherein the shell is operable to transfer a load imposed by the first rotor blade to the structural members.

8. The rotor assembly of claim 1 , wherein the linkage mechanism comprises:
a plate operable to translate along the mast; and
a plurality of linkage members comprising:
a first linkage member operable to couple the plate to the first rotor blade, and
a second linkage member operable to couple the plate to the second rotor blade.

9. The rotor assembly of claim 8 , wherein the plurality of linkage members comprises a plurality of pitch horns, and wherein:
the first linkage member comprises a first pitch horn, and
the second linkage member comprises a second pitch horn.

10. The rotor assembly of claim 8 , further comprising:
a gimbaled swashplate assembly coupling the mast to the rotor hub, wherein the gimbaled swashplate assembly is operable to transfer rotational movement of the mast to the rotor hub and the gimbaled swashplate assembly comprises the plate.

11. A tiltrotor aircraft comprising:
a mast operable to rotate based on torque applied by an engine;
a rotor hub operable to rotate based on rotation of the mast;
a first rotor blade and a second rotor blade pivotally attached to the rotor hub;
a bracing member pivotally attached to the rotor hub at a first end and pivotally attached to the first rotor blade at a second end;
a linkage mechanism coupling the first rotor blade to the second rotor blade; and
wherein the bracing member is operable to transfer a coning movement of the first rotor blade to a movement of the linkage mechanism and a corresponding coning movement of the second rotor blade.

12. The tiltrotor aircraft of claim 11 , further comprising:
an outboard bearing support operable to couple the second end of the bracing member to a root of the first rotor blade, the outboard bearing support comprising a sleeve operable to support the root of the first rotor blade.

13. The tiltrotor aircraft of claim 11 , further comprising:
an inboard bearing support operable to pivotally attach the first rotor blade to the rotor hub, the inboard bearing support comprising an elastomeric bearing operable to support a load generated between the first rotor blade and the rotor hub.

14. The tiltrotor aircraft of claim 11 , wherein the linkage mechanism comprises:
a plate operable to translate along the mast; and
a plurality of linkage members comprising:
a first linkage member operable to couple the plate to the first rotor blade, and
a second linkage member operable to couple the plate to the second rotor blade.

15. The tiltrotor aircraft of claim 14 , wherein the plurality of linkage members comprises a plurality of pitch horns, and wherein:
the first linkage member comprises a first pitch horn, and
the second linkage member comprises a second pitch horn.

16. The tiltrotor aircraft of claim 14 , further comprising:
a gimbaled swashplate assembly coupling the mast to the rotor hub, wherein the gimbaled swashplate assembly is operable to transfer rotational movement of the mast to the rotor hub and the gimbaled swashplate assembly comprises the plate.

17. An tiltrotor aircraft comprising:
a plurality of engines; and
a plurality of rotor assemblies, wherein each of the plurality of rotor assemblies comprises:
a rotor hub operable to rotate based on torque applied by one of the plurality of engines,
a plurality of rotor blades pivotally attached to the rotor hub,
a plurality of bracing members pivotally attached to the rotor hub at a first end and to pivotally attach to one of the plurality of rotor blades at a second end, and
a linkage mechanism coupling the plurality of rotor blades to one another,

wherein one of the plurality of bracing members is operable to transfer a coning movement of one of the plurality of rotor blades to a movement of the linkage mechanism and a corresponding coning movement of others of the plurality of bracing members.

18. The tiltrotor aircraft of claim 17 , wherein the linkage mechanism comprises:
a plate operable to translate along a mast; and
a plurality of linkage members operable to couple the plate to the plurality of rotor blades.

19. The tiltrotor aircraft of claim 18 , wherein the plurality of linkage members comprises a plurality of pitch horns.

20. The tiltrotor aircraft of claim 19 , further comprising:
a gimbaled swashplate assembly coupling the mast to the rotor hub, wherein the gimbaled swashplate assembly is operable to transfer rotational movement of the mast to the rotor hub and the gimbaled swashplate assembly comprises the plate.

Assignees

• Textron Innovations Inc

Inventors

• Choi Jouyoung Jason
• Stamps Frank B

Classifications

• B64C11/06 Primary

  for variable-pitch blades · CPC title

• B64C27/322 Primary

  Blade travel limiting devices, e.g. droop stops · CPC title

• B64C11/14

  Spinners · CPC title

• B64C27/39

  with individually articulated blades, i.e. with flapping or drag hinges · CPC title

• B64C11/008

  characterised by vibration absorbing or balancing means · CPC title