Rotorcraft rotor including primary pitch horns and secondary horns

Patent metadata

Field	Value
Publication number	US-9457889-B2
Application number	US-201314035934-A
Country	US
Kind code	B2
Filing date	Sep 24, 2013
Priority date	Sep 24, 2013
Publication date	Oct 4, 2016
Grant date	Oct 4, 2016

Abstract

A rotorcraft rotor comprises a blade having a pitch axis, a primary pitch horn for the blade, and a secondary horn opposite the primary pitch horn with respect to the pitch axis.

First claim

The invention claimed is:

1. A rotorcraft rotor comprising:
a hub to rotate about a z-axis via a rotor mast;
a blade coupled to the hub, the blade having a pitch axis;
a primary horn and a secondary horn coupled to the blade, the secondary horn being positioned opposite the primary horn with respect to the pitch axis;
a control mechanism to vary a first angle of the primary horn relative to a second angle of the secondary horn, the control mechanism to maintain the second angle of the secondary horn with respect to the first angle of the primary horn when the blade moves through collective or pitch cycle changes, the control mechanism including:
a rotating portion including a rocker arm and a rocker carrier, the rocker arm pivotally coupled to the rocker carrier about a pivot axis normal to the z-axis, the primary and secondary horns linked to the rocker arm on opposite sides of the pivot axis, the rocker carrier to slide along the z-axis, the rotating portion of the control mechanism to rotate with the hub and change the first angle of the primary horn and the second angle of the secondary horn; and
a non-rotating portion to provide mechanical control inputs to the rotating portion, the non-rotating portion of the control mechanism including a slide cylinder to cause the rocker carrier to slide along the z-axis.

2. The rotor of claim 1 , wherein the blade has a mechanism to change blade flight mechanics, and wherein the secondary horn is mechanically coupled to the mechanism.

3. The rotor of claim 1 , further comprising a torque tube within the blade, wherein the primary horn is connected to the blade and the secondary horn is connected to the torque tube.

4. The rotor of claim 1 , further comprising a swashplate linked to the primary horn, the slide cylinder to extend through a central opening in the swashplate.

5. The rotor of claim 1 , further comprising a swashplate linked to the secondary horn.

6. The rotor of claim 1 , wherein the rocker arm and the rocker carrier are located below the blade.

7. A rotorcraft rotor comprising:
a hub to rotate about a z-axis via a rotor mast;
a blade coupled to the hub, the blade having a pitch axis;
a primary horn and a secondary horn coupled to the blade, the secondary horn being positioned opposite the primary horn with respect to the pitch axis;
a control mechanism to vary a first angle of the primary horn relative to a second angle of the secondary horn, the control mechanism to maintain the second angle of the secondary horn with respect to the first angle of the primary horn when the blade pitch changes at least one of collectively or cyclically, the control mechanism including:
a rotating portion including a rocker arm and a rocker carrier located above the blade, the rocker arm pivotally coupled to the rocker carrier about a pivot axis normal to the z-axis, the primary and secondary horns linked to the rocker arm on opposite sides of the pivot axis, the rocker carrier to slide along the z-axis, the rotating portion of the control mechanism to rotate with the hub and change the first angle of the primary horn and the second angle of the secondary horn; and
a non-rotating portion to provide mechanical control inputs to the rotating portion.

8. A method comprising:
using first horns to vary blade pitch of rotorcraft blades at least one of collectively or cyclically;
using second horns to vary flight mechanics of the rotorcraft blades, wherein an angle of the second horns is unchanged with respect to an angle of the first horns when varying the blade pitch via the first horn; and
varying the angle of the second horns by translating collectively rocker arms coupled between the first and second horns of each of the rotorcraft blades.

9. The method of claim 8 , further including varying a position of outboard flaps of the rotorcraft blades by varying the angle the second horns.

10. The method of claim 8 , wherein each rotorcraft blade includes an inboard segment and an outboard segment, the method including controlling a pitch of the inboard segment via the first horns and controlling a pitch of the outboard segment controlled via the second horns.

11. The method of claim 8 , further including varying blade twist of the rotorcraft blades by varying the angle of the second horns.

12. The method of claim 8 , further including coupling each of the first horns to a swashplate.

13. The rotor of claim 1 , further comprising a torque tube within the blade, wherein the secondary horn is connected to the blade and the primary horn is connected to the torque tube.

14. A method comprising:
using first horns to vary blade pitch of rotorcraft blades at least one of collectively or cyclically; and
using second horns to vary flight mechanics of the rotorcraft blades, wherein an angle of the second horns is unchanged with respect to an angle of the first horns when varying the blade pitch via the first horn, wherein a rocker arm is linked between the primary and secondary horns of each blade, and wherein each second horn is linked to a swashplate.

15. A rotorcraft comprising:
a rotor mast having a z-axis;
a rotor hub coupled to the rotor mast;
a blade assembly coupled to the rotor hub, the blade assembly including a blade, a first horn, and a second horn;
a first control assembly to vary a first angle of the first horn; and
a second control assembly to vary a second angle of the second horn, the second control assembly including:
a rocker carrier configured to rotate about the z-axis and slide long the z-axis; and
a rocker arm pivotally coupled to the rocker carrier about a pivot axis, the rocker arm having a first end fixed relative to the first horn and a second end coupled to the second horn, the rocker arm to pivot about the pivot axis to vary the second angle of the second horn without changing the first angle of the first horn when the rocker carrier slides along the z-axis.

16. The rotorcraft of claim 15 , wherein the blade assembly defines a pitch axis, the first horn positioned on a first side of the pitch axis and the second horn positioned on a second side of the pitch axis opposite the first side.

17. The rotorcraft of claim 16 , wherein the pivot axis of the rocker arm is positioned below the pitch axis or above the pitch axis.

18. The rotorcraft of claim 15 , wherein the pivot axis of the rocker arm is non-parallel relative to the z-axis.

19. The rotorcraft of claim 15 , wherein the first control assembly includes a swashplate coupled to the first horn via a first link, and wherein the swashplate is to move relative to the z-axis to vary the first angle of the first horn.

20. The rotorcraft of claim 15 , further including a slide cylinder coupled to the rocker carrier, the slide cylinder to slide along the z-axis to move the rocker carrier in a direction along the z-axis.

21. The rotorcraft of claim 20 , wherein movement of the rocker carrier along the z-axis is to cause the rocker arm to rotate about the pivot axis.

22. The rotorcraft of claim 20 , wherein the slide cylinder extends through a central opening of a swashplate and surrounds the rotor mast.

23. The rotorcraft of claim 15 , further including a first link to couple the first end of the rocker arm to the first horn and a second link to couple the second end of the rocker arm to the second horn.

24. The rotorcraft of claim 15 , wherein the rocker arm includes a longitudinal axis that is non-parallel relative to

Assignees

• Boeing Co

Inventors

• Filter Evan J

Classifications

• B64C27/615

  including flaps mounted on blades · CPC title

• B64C2027/7205

  on each blade individually, e.g. individual blade control [IBC] · CPC title

• B64C27/32

  Rotors · CPC title

• B64C11/30 Primary

  Blade pitch-changing mechanisms · CPC title

• B64C27/46 Primary

  Blades · CPC title