Mechanical droop for spoiler operation

Patent metadata

Field	Value
Publication number	US-10766602-B2
Application number	US-201715800710-A
Country	US
Kind code	B2
Filing date	Nov 1, 2017
Priority date	Nov 1, 2017
Publication date	Sep 8, 2020
Grant date	Sep 8, 2020

Abstract

A system for mechanical operation of an aircraft wing includes a torque tube rotatable at a first rate of rotation to cause a downward rotation of a control surface relative to the aircraft wing. A gearing assembly including an output shaft is coupled to the torque tube. The torque tube is configured to rotate the output shaft, via the gearing assembly, at a second rate of rotation less than the first rate of rotation. A rotational member is coupled to the output shaft, and the output shaft is configured to drive a rotation of the rotational member. A first end of a linear actuator is coupled to the rotational member at a forward attach point, which is eccentric to a rotational center of the rotational member. The rotational member is rotatable to cause a translation of the forward attach point relative to the aircraft wing.

First claim

What is claimed is:

1. A system for mechanical operation of an aircraft wing, comprising:
a torque tube coupled to a control surface of the aircraft wing, wherein the torque tube is rotatable at a first rate of rotation to cause a downward rotation of the control surface relative to the aircraft wing;
a gearing assembly coupled to the torque tube, wherein the gearing assembly comprises an output shaft, and wherein the torque tube is configured to rotate the output shaft, via the gearing assembly, at a second rate of rotation that is less than the first rate of rotation of the torque tube;
a rotational member coupled to the output shaft of the gearing assembly, wherein the output shaft is configured to drive a rotation of the rotational member, and wherein a rotational center of the output shaft and a rotational center of the rotational member are concentric; and
a linear actuator comprising a first end and a second end, wherein the first end of the linear actuator is coupled to the rotational member at a forward attach point, wherein the forward attach point is eccentric to the rotational center of the rotational member, and wherein the rotational member is rotatable to cause a translation of the forward attach point relative to the aircraft wing,
wherein the rotational member comprises a first leg and a second leg coupled by a curved portion, wherein the first leg and the second leg of the rotational member straddle the first end of the linear actuator, and wherein a pin joint extends from the first leg, through the first end of the linear actuator, to the second leg.

2. The system of claim 1 , wherein a rotational center of the torque tube and the rotational center of the rotational member are not concentric.

3. The system of claim 1 , wherein the gearing assembly comprises a strain wave reduction gear.

4. The system of claim 1 , wherein the control surface is a first control surface, wherein the second end of the linear actuator is coupled to a second control surface of the aircraft wing, and wherein the rotation of the rotational member is configured to cause a downward rotation of the second control surface relative to the aircraft wing.

5. The system of claim 4 , wherein the downward rotation of the first control surface is between about 30 and about 40 degrees relative to the aircraft wing, and wherein the downward rotation of the second control surface is between about 10 and about 15 degrees relative to the aircraft wing.

6. The system of claim 1 , wherein the control surface is a first control surface, wherein the torque tube is rotatable in a first direction to cause the downward rotation of the first control surface, wherein the torque tube is rotatable in a second direction opposite the first direction to cause an upward rotation of the first control surface relative to the aircraft wing, and to further cause, via the gearing assembly and the rotational member, an upward rotation of a second control surface relative to the aircraft wing.

7. The system of claim 1 , wherein the first end of the linear actuator is coupled to the rotational member at the forward attach point via the pin joint, and wherein the linear actuator is rotatable relative to the rotational member via the pin joint.

8. The system of claim 1 , wherein the control surface is a first control surface, wherein the second end of the linear actuator is coupled to a second control surface of the aircraft wing, wherein the system comprises a breakaway joint between the gearing assembly and the second control surface, and wherein the breakaway joint is configured to decouple the gearing assembly from the second control surface in response to a force that is greater than a breakaway force acting on the breakaway joint.

9. The system of claim 8 , wherein the breakaway joint is located on the rotational member between the forward attach point and the output shaft of the gearing assembly, and wherein the breakaway joint is configured to decouple the rotational member from the output shaft.

10. A method for mechanically operating an aircraft wing, comprising:
rotating a torque tube at a first rate of rotation, wherein the rotation of the torque tube causes a downward rotation of a control surface, wherein the torque tube is coupled to a gearing assembly comprising an output shaft;
reducing, via the gearing assembly, the first rate of rotation of the torque tube to a second rate of rotation that is less than the first rate of rotation;
rotating the output shaft at the second rate of rotation, wherein the output shaft is coupled to a rotational member, and wherein a rotational center of the output shaft and a rotational center of the rotational member are concentric;
rotating the rotational member, wherein the rotational member is coupled to a first end of a linear actuator at a forward attach point, wherein the linear actuator comprises the first end and a second end, and wherein the forward attach point is eccentric to the rotational center of the rotational member, wherein the rotational member comprises a first leg and a second leg coupled by a curved portion, wherein the first leg and the second leg of the rotational member straddle the first end of the linear actuator, and wherein a pin joint extends from the first leg, through the first end of the linear actuator, to the second leg; and
translating the forward attach point relative to the aircraft wing based on the rotation of the rotational member.

11. The method of claim 10 , wherein the gearing assembly comprises a strain wave reduction gear, and wherein reducing the first rate of rotation of the torque tube comprises rotating the strain wave reduction gear.

12. The method of claim 10 , wherein the control surface is a first control surface, wherein the second end of the linear actuator is coupled to a second control surface of the aircraft wing, further comprising:
rotating the second control surface downward relative to the aircraft wing based on the translation of the forward attach point.

13. The method of claim 12 , wherein the downward rotation of the first control surface is between about 30 and about 40 degrees, and wherein rotating the second control surface downward relative to the aircraft wing comprises rotating the second control surface between about 10 and about 15 degrees.

14. The method of claim 12 , wherein the torque tube is rotatable in a first direction to cause the downward rotation of the first control surface, further comprising:
rotating the torque tube in a second direction opposite the first direction to cause an upward rotation of the first control surface relative to the aircraft wing; and
rotating, via the gearing assembly and the rotational member, the second control surface upward relative to the aircraft wing.

15. The method of claim 10 , wherein the first end of the linear actuator is coupled to the rotational member at the forward attach point via a pin joint, and wherein rotating the rotational member comprises rotating the linear actuator about the pin joint relative to the rotational member.

16. The method of claim 10 , wherein the control surface is a first control surface, wherein the second end of the linear actuator is coupled to a second control surface of the aircraft wing, and wherein the aircraft wing comprises a breakaway joint between the gearing assembly and the second control surface, further comprising:
decoupling the gearing assembly from the second control surface, at the breakaway joint, in response to a force that is greater than a breakaway force acting on the breakaway joint.

17. The method of

Assignees

• Boeing Co

Inventors

• Sakurai Seiya
• Good Mark S
• Schleuter Lisa
• Jones Kelly T
• Santini Gregory M

Classifications

• B64C9/18

  by single flaps · CPC title

• Y02T50/30

  Wing lift efficiency · CPC title

• B64C9/323 Primary

  associated with wings · CPC title

• B64C9/02

  Mounting or supporting thereof · CPC title

• B64C9/06 Primary

  with two or more independent movements · CPC title