Apparatus, system, and method for pitching and twisting a blade of a rotorcraft

Patent metadata

Field	Value
Publication number	US-9487291-B2
Application number	US-201213705780-A
Country	US
Kind code	B2
Filing date	Dec 5, 2012
Priority date	Dec 5, 2012
Publication date	Nov 8, 2016
Grant date	Nov 8, 2016

Abstract

A method and apparatus for moving a blade of a rotorcraft. The method comprises operating the rotorcraft and applying a torque to an elongate member connected to a tip portion of the blade during operation of the rotorcraft using a tip actuation mechanism that is external to the blade and associated with the elongate member such that the tip portion of the blade rotates about an axis through the blade.

First claim

What is claimed is:

1. An apparatus comprising:
a blade of a rotorcraft; and
a tip actuation mechanism that is external to the blade and associated with an elongate member that is connected to a tip portion of the blade, wherein the tip actuation mechanism is configured to apply a torque to the elongate member such that the tip portion of the blade twists relative to a root portion of the blade about an axis through the blade defined by the elongate member.

2. The apparatus of claim 1 further comprising:
a root actuation mechanism external to the blade and associated with the root portion of the blade, wherein the root actuation mechanism is configured to apply a torque to the root portion of the blade such that the root portion of the blade rotates about the axis.

3. The apparatus of claim 2 , wherein the tip actuation mechanism and the root actuation mechanism are part of an actuation system configured to at least one of pitch and twist the blade.

4. The apparatus of claim 3 , wherein the actuation system is configured to pitch the blade at a selected pitch frequency greater than once per revolution during operation of the rotorcraft.

5. The apparatus of claim 3 , wherein the actuation system is configured to change an amount of twisting of the blade while the rotorcraft is in a flight regime during operation of the rotorcraft.

6. The apparatus of claim 2 , wherein the torque applied to the root portion of the blade is a first torque applied by transferring a first force generated by the root actuation mechanism to the root portion of the blade and wherein the torque applied to the elongate member is a second torque applied by transferring a second force generated by the tip actuation mechanism to the tip portion of the blade through the elongate member.

7. The apparatus of claim 6 , wherein the blade pitches when the first torque and the second torque are substantially equal and in a same direction.

8. The apparatus of claim 6 , wherein the blade twists when the first torque and the second torque are at least one of not substantially equal and not in a same direction.

9. The apparatus of claim 6 , wherein the root actuation mechanism comprises:
an actuator configured to generate the first force, wherein the actuator is selected from one of a linear actuator and a rotary actuator.

10. The apparatus of claim 6 , wherein the tip actuation mechanism comprises:
an actuator configured to generate the second force, wherein the actuator is selected from one of a linear actuator and a rotary actuator.

11. The apparatus of claim 2 , wherein the root actuation mechanism and the tip actuation mechanism are associated with a swashplate assembly.

12. The apparatus of claim 1 , wherein the elongate member is a torque tube.

13. A rotor system comprising:
A plurality of blades; and
A pitch and twist system comprising a plurality of actuation systems in which each of the plurality of actuation systems is associated with a corresponding one of the plurality of blades and comprises:
A root actuation mechanism that is external to a blade and associated with a root portion of the blade, wherein the root actuation mechanism is configured to apply a first torque to the root portion of the blade such that the root portion of the blade rotates about an axis through the blade; and
A tip actuation mechanism that is external to the blade and associated with an elongate member that is connected to a tip portion of the blade, wherein the tip actuation mechanism is configured to apply a second torque to the elongate member such that the tip portion of the blade twists about an axis through the blade defined by the elongate member, the tip portion twisting relative to the root portion of the blade.

14. The rotor system of claim 13 , wherein the blade pitches when the first torque and the second torque are substantially equal and in a same direction.

15. The rotor system of claim 13 , wherein the blade twists when the first torque and the second torque are at least one of not substantially equal and not in a same direction.

16. A method for moving a blade of a rotorcraft, the method comprising:
Operating the rotorcraft; and
Applying a torque to the elongate member connected to a tip portion of the blade during operation of the rotorcraft using a tip actuation mechanism that is external to the blade and associated with the elongate member such that the tip portion of the blade twists about an axis through the blade defined by the elongate member, the tip portion twisting relative to a root portion of the blade.

17. The method of claim 16 further comprising:
applying a torque to the root portion of the blade using a root actuation mechanism external to the blade and associated with the root portion of the blade such that root portion of the blade rotates about the axis, wherein the torque applied to the root portion is a first torque and wherein the torque applied to the elongate member is a second torque.

18. The method of claim 17 further comprising:
performing at least one of applying the first torque to the root portion of the blade and applying the second torque to the elongate member to pitch the blade at a selected pitch frequency greater than once per revolution during operation of the rotorcraft.

19. The method of claim 17 further comprising:
performing at least one of applying the first torque to the root portion of the blade and applying the second torque to the elongate member to change an amount of twisting of the blade while the rotorcraft is in a flight regime during operation of the rotorcraft.

20. The method of claim 19 , wherein the step of performing the at least one of applying the first torque to the root portion of the blade and applying the second torque to the elongate member comprises:
performing the at least one of applying the first torque to the root portion of the blade and applying the second torque to the elongate member to change the amount of twisting of the blade while the rotorcraft is in the flight regime during operation of the rotorcraft such that at least one of vibrations generated by the blade and noise is reduced and such that aerodynamic performance is improved.

Assignees

• Boeing Co

Inventors

• Zientek Thomas A
• Birchette Terrence S
• Straub Friedrich K

Classifications

• B64C2027/7244

  by using dedicated actuators · CPC title

• B64C2027/7222

  using airfoil deformation · CPC title

• B64C27/605 Primary

  including swash plate, spider or cam mechanisms · CPC title

• B64C27/463

  Blade tips · CPC title

• Y02T50/34

  Cross-Sectional Technologies · mapped topic