Tail rotor actuation system

Patent metadata

Field	Value
Publication number	US-10023304-B2
Application number	US-201414286197-A
Country	US
Kind code	B2
Filing date	May 23, 2014
Priority date	May 23, 2014
Publication date	Jul 17, 2018
Grant date	Jul 17, 2018

Abstract

In some embodiments, an actuation system includes a an actuator assembly, a yoke, and a control rod. The actuator assembly comprises a first actuator. The first actuator is configured to extend in a first direction and retract in a second direction opposite of the first direction. The yoke is coupled to the first actuator at a first actuator end proximate to the first direction. The control rod is coupled to the yoke at a first control rod end and extends in the second direction past the actuator assembly to a second end in mechanical communication with an output device.

First claim

What is claimed is:

1. A rotorcraft, comprising:
a body including an empennage;
a power train coupled to the body and comprising an engine and a drive shaft coupled to the engine;
a rotor system coupled to the power train, the rotor system comprising at least one tail rotor blade and a tail rotor gearbox in mechanical communication with the at least one tail rotor blade and coupled to the empennage; and
an actuation system in mechanical communication with the rotor system, the actuation system comprising:
an actuator assembly comprising a first actuator, the first actuator having a first end, a second end, and a body portion disposed between the first end and the second end, the first actuator configured to extend in a first direction and retract in a second direction opposite of the first direction;
a yoke coupled to the first end of the first actuator such that the body portion of the first actuator is oriented away from the yoke, and such that the yoke translates as the first actuator extends in the first direction and retracts in the second direction;
a control rod having a first end, a second end, and a body portion disposed between the first end and the second end, the first end of the control rod coupled to the yoke such that the body portion of the control rod is oriented away from the yoke in the same direction as the body portion of the first actuator,
wherein the control rod extends through an opening in the tail rotor gearbox such that the first and second control rod ends extend through opposite sides of the empennage, and
wherein when the first actuator extends in the first direction and retracts in the second direction, a pitch angle of the at least one rotor blade is changed.

2. The rotorcraft of claim 1 , wherein the actuator assembly and the at least one tail rotor blade are located on opposite sides of the empennage.

3. The rotorcraft of claim 1 , the rotor system further comprising:
a cross-head coupled to the second end of the control rod; and
a pitch link coupled to the cross-head and in mechanical communication with the at least one tail rotor blade.

4. The rotorcraft of claim 3 , the cross-head and pitch link operable to change the pitch angle of the at least one tail rotor blade in response to movement of the control rod in the first direction or in the second direction.

5. The rotorcraft of claim 1 , the rotor system further comprising a tail rotor mast, the tail rotor mast comprising:
a first portion configured to transfer rotational energy from the tail rotor gearbox to the at least one tail rotor blade; and
a second portion configured to rotate in response to rotation of the cross-head and translate in response to translations of the control rod.

6. The rotorcraft of claim 1 , further comprising a tail rotor control system operable to change a position of the first actuator in response to a request to change the pitch angle of the at least one tail rotor blade.

7. The rotorcraft of claim 1 , wherein the actuator assembly comprises a second actuator and a third actuator, the second actuator and the third actuator coupled to the yoke and configured to extend in the first direction and retract in the second direction opposite of the first direction.

8. A method of actuating a rotor system of a rotorcraft, comprising:
receiving an input; and
changing an actuator output position of an actuator assembly in response to the received input, wherein:
the rotor system comprises at least one tail rotor blade and a tail rotor gearbox coupled to an empennage and in mechanical communication with the at least one tail rotor blade;
the actuator assembly comprises a first actuator, the first actuator having a first end, a second end, and a body portion disposed between the first end and the second end, the first actuator configured to extend in a first direction and retract in a second direction opposite of the first direction;
a yoke is coupled to the first end of the first actuator such that the body portion of the first actuator is oriented away from the yoke;
a control rod has a first end, a second end, and a body portion disposed between the first end and the second end, the first end of the control rod is coupled to the yoke such that the body portion of the control rod is oriented away from the yoke in the same direction as the body portion of the first actuator; and
the second end of the control rod is in mechanical communication with the rotor system such that when the first actuator extends in the first direction and retracts in the second direction, a pitch angle of the at least one rotor blade is changed,
wherein the control rod extends through an opening in the tail rotor gearbox such that the first and second control rod ends extend through opposite sides of the empennage.

9. The method of claim 8 , wherein the actuator assembly and the at least one tail rotor blade are located on opposite sides of the empennage.

10. The method of claim 8 , wherein the actuator assembly comprises a second actuator and a third actuator, the second actuator and the third actuator coupled to the yoke and configured to extend in the first direction and retract in the second direction opposite of the first direction.

11. The rotorcraft of claim 1 , wherein the body portion of the first actuator is substantially adjacent to and substantially parallel to the body portion of the control rod.

12. The method of claim 8 , wherein the body portion of the first actuator is substantially adjacent to and substantially parallel to the body portion of the control rod.

13. The rotorcraft of claim 1 , wherein the control rod translates as the first actuator extends in the first direction and retracts in the second direction.

14. The method of claim 8 , wherein the control rod translates as the first actuator extends in the first direction and retracts in the second direction.

15. The rotorcraft of claim 1 , wherein the body portion of the control rod is disposed at least partially within the actuator assembly.

16. The method of claim 8 , wherein the body portion of the control rod is disposed at least partially within the actuator assembly.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Dickman Corey
• Fenny Carlos A
• Schultz David

Classifications

• B64C13/505

  having duplication or stand-by provisions · CPC title

• B64C27/82

  characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft · CPC title

• B64C13/504 Primary

  using electro-hydrostatic actuators [EHA's] · CPC title

• B64C27/14

  Direct drive between power plant and rotor hub · CPC title

• B64C13/503 Primary

  Fly-by-Wire · CPC title