Flap actuation systems for aircraft

Patent metadata

Field	Value
Publication number	US-11518496-B2
Application number	US-201916552466-A
Country	US
Kind code	B2
Filing date	Aug 27, 2019
Priority date	Aug 27, 2019
Publication date	Dec 6, 2022
Grant date	Dec 6, 2022

Abstract

Flap actuation systems for aircraft are described herein. An example flap actuation system includes a fixed beam coupled to and extending downward from a fixed wing portion of an aircraft wing and a rocking lever plate pivotably coupled to the fixed beam. The rocking lever plate is coupled to a forward end of a flap bracket disposed on a bottom side of a flap of the wing. The flap actuation system also includes a crank arm, a crank rod coupled between the crank arm and the rocking lever plate, and a flap link coupled between the rocking lever plate and an aft end of the flap bracket, such that actuation of the crank arm pivots the rocking lever plate to move the flap between a stowed position and a deployed position relative to the fixed wing portion.

First claim

What is claimed is:

1. A flap actuation system comprising:
a fixed beam coupled to and extending downward from a fixed wing portion of a wing of an aircraft;
a rocking lever plate pivotably coupled to the fixed beam via a first coupling, the first coupling being a one degree-of-freedom (DOF) joint such that the rocking lever plate remains within a plane during movement, the rocking lever plate coupled to a forward end of a flap bracket disposed on a bottom side of a flap of the wing via a second coupling, the second coupling being a two DOF joint to enable the flap bracket to pivot out-of-plane relative to the rocking lever plate;
a crank arm;
a crank rod coupled between the crank arm and the rocking lever plate, the crank rod coupled to the rocking lever plate via a third coupling that is spaced apart from the first coupling; and
a flap link coupled between the rocking lever plate and an aft end of the flap bracket, such that actuation of the crank arm pivots the rocking lever plate to move the flap between a stowed position and a deployed position relative to the fixed wing portion.

2. The flap actuation system of claim 1 , wherein the flap bracket and the flap link are pivotable out-of-plane relative to the rocking lever plate, thereby enabling the flap to undergo a conical motion as the flap is moved between the stowed position and the deployed position.

3. The flap actuation system of claim 2 , wherein the flap link and the rocking lever plate are coupled via a fourth coupling, and the flap link and the flap bracket are coupled via a fifth coupling.

4. The flap actuation system of claim 3 , wherein the fourth and fifth couplings are two degree-of-freedom (DOF) joints.

5. The flap actuation system of claim 4 , wherein the second, fourth, fourth, and fifth couplings are ball joints or spherical bearings.

6. The flap actuation system of claim 1 , wherein an aft end of the flap link moves spanwise when the flap is moved between the stowed position and the deployed position.

7. The flap actuation system of claim 1 , wherein the third coupling is a predetermined distance from the first coupling, and the crank arm has an arm length that is not less than a predetermined fraction of the predetermined distance to provide a mechanical advantage with respect to actuator load relative to linear force applied via the crank rod to move the flap.

8. The flap actuation system of claim 1 , further including a geared rotary actuator (GRA), the crank arm coupled to and driven by the GRA.

9. The flap actuation system of claim 8 , wherein the GRA is coupled to the fixed beam.

10. An aircraft wing comprising:
a fixed wing portion;
a flap;
a first flap actuation system coupled to the fixed wing portion to move the flap relative to the fixed wing portion between a stowed position and a deployed position, the first flap actuation system including:
a first fixed beam coupled to and extending downward from the fixed wing portion;
a first rocking lever plate pivotably coupled to the first fixed beam via a first coupling, the first coupling forming a first hingeline, the first rocking lever plate coupled to a forward end of a flap bracket disposed on a bottom side of the flap, the first rocking lever plate to be rotated relative to the first fixed beam via a rotary actuator; and
a flap link coupled between the first rocking lever plate and an aft end of the flap bracket, the first fixed beam, the first rocking lever plate, the flap bracket, and the flap link oriented generally streamwise; and

a second flap actuation system to move the flap between the stowed position and the deployed position, the second flap actuation system including:
a second fixed beam coupled to an extending downward from the fixed wing portion; and
a second rocking lever plate pivotably coupled to the second fixed beam via a second coupling, the second coupling forming a second hingeline, wherein the second hingeline is offset from and non-parallel to the first hingeline.

11. The aircraft wing of claim 10 , wherein the flap bracket and the flap link are pivotable out-of-plane relative to the first rocking lever plate, thereby enabling the flap to undergo a conical motion when the flap is moved between the stowed position and the deployed position.

12. The aircraft wing of claim 11 , wherein the first rocking lever plate and the flap bracket are coupled via a third coupling, the flap link and the first rocking lever plate are coupled via a fourth coupling, and the flap link and the flap bracket are coupled via a fifth coupling.

13. The aircraft wing of claim 12 , wherein the third, fourth, and fifth couplings are two degree-of-freedom (DOF) joints.

14. The aircraft wing of claim 13 , wherein the first coupling is a one DOF joint such that the first rocking lever plate remains within a plane during movement.

15. The aircraft wing of claim 10 , wherein the flap is moved spanwise when the flap is moved between the stowed position and the deployed position.

16. The aircraft wing of claim 10 , further including a flap actuation fairing coupled to the fixed wing portion and covering at least a portion of the first flap actuation system, the flap actuation fairing oriented streamwise.

17. A flap actuation system comprising:
a fixed beam coupled to and extending downward from a fixed wing portion of a wing of an aircraft;
a rocking lever plate pivotably coupled to the fixed beam via a first coupling, the rocking lever plate coupled to a forward end of a flap bracket disposed on a bottom side of a flap of the wing;
a linear actuator having an output shaft;
a connecting arm coupled between the output shaft and the rocking lever plate, the connecting arm coupled to the rocking lever plate via a second coupling that is spaced apart from the first coupling; and
a flap link coupled between the rocking lever plate and an aft end of the flap bracket, such that actuation of the output shaft pivots the rocking lever plate to move the flap between a stowed position and a deployed position relative to the fixed wing portion, wherein the flap link and the rocking lever plate are coupled via a third coupling, the flap link and the flap bracket are coupled via a fourth coupling, and the third and fourth couplings form rotational axes that are oriented in a direction that is perpendicular to a direction of rotational axes of the first and second couplings.

18. The flap actuation system of claim 17 , wherein the third coupling is a one degree-of-freedom (DOF) joint.

19. The flap actuation system of claim 17 , wherein the connecting arm is coupled to the output shaft via a u-joint.

20. The flap actuation system of claim 17 , wherein the linear actuator is a ball screw actuator.

Assignees

• Boeing Co

Inventors

• Dahl Bruce
• Tsai Kevin

Classifications

• B64D29/02

  associated with wings · CPC title

• B64C9/04 Primary

  with compound dependent movements · CPC title

• B64C9/02 Primary

  Mounting or supporting thereof · CPC title

• Y02T50/40

  Weight reduction · CPC title

• Y02T50/30

  Wing lift efficiency · CPC title