Tail Rotor Actuation System

Patent metadata

Field	Value
Publication number	US-2016200430-A1
Application number	US-201414286197-A
Country	US
Kind code	A1
Filing date	May 23, 2014
Priority date	May 23, 2014
Publication date	Jul 14, 2016
Grant date	—

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

1 . A rotorcraft, comprising:
a body; 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 rotor blade; 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 configured to extend in a first direction and retract in a second direction opposite of the first direction; a yoke coupled to the first actuator at a first actuator end proximate to the first direction; a control rod coupled to the yoke at a first control rod end and extending in the second direction past the actuator assembly to a second end in mechanical communication with the rotor system.

2 . The rotorcraft of claim 1 , wherein the rotor system comprises a tail 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 an empennage of the body.

3 . The rotorcraft of claim 2 , wherein the control rod extends through an opening in the tail rotor gearbox such that the first and second control rod ends are located on opposite sides of the empennage.

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

5 . The rotorcraft of claim 2 , the tail 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.

6 . The rotorcraft of claim 5 , the cross-head and pitch link operable to change an angle of attack 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.

7 . The rotorcraft of claim 2 , the tail rotor system further comprising a tail rotor mast, the tail rotor mast comprising:
a first portion configured to transfer rotational energy from the 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.

8 . The rotorcraft of claim 2 , further comprising a tail rotor control system operable to change a position of the first actuator in response to a request to change an angle of attack of the at least one tail rotor blade.

9 . 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.

10 . (canceled)

11 . (canceled)

12 . An actuation system comprising:
an actuator assembly comprising a first actuator, 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 actuator at a first actuator end proximate to the first direction; a control rod coupled to the yoke at a first control rod end and extending in the second direction past the actuator assembly to a second end in mechanical communication with an output device.

13 . The actuation system of claim 12 , 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.

14 . (canceled)

15 . (canceled)

16 . 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 rotor blade; the actuator assembly comprises a first actuator, 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 actuator at a first actuator end proximate to the first direction; a control rod is coupled to the yoke at a first control rod end and extending in the second direction past the actuator assembly to a second control rod end; and the second control rod end is in mechanical communication with the rotor system such that changing the actuator output position causes the control rod to change an angle of attack of the at least one rotor blade.

17 . The method of claim 16 , wherein the rotor system comprises a tail 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 an empennage of the body.

18 . The method of claim 17 , wherein the control rod extends through an opening in the tail rotor gearbox such that the first and second control rod ends are located on opposite sides of the empennage.

19 . The method of claim 17 , wherein the actuator assembly and the at least one tail rotor blade are located on opposite sides of the empennage.

20 . The method of claim 16 , 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.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Dickman Corey
• Fenny Carlos A
• Schultz David

Classifications

• B64C13/504 Primary

  using electro-hydrostatic actuators [EHA's] · 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

• B64C13/505

  having duplication or stand-by provisions · CPC title

• B64C27/14

  Direct drive between power plant and rotor hub · CPC title

• B64C13/503

  Fly-by-Wire · CPC title