Linkage assemblies for aircraft wing hinged panels

Patent metadata

Field	Value
Publication number	US-11447232-B2
Application number	US-201816178089-A
Country	US
Kind code	B2
Filing date	Nov 1, 2018
Priority date	Nov 1, 2018
Publication date	Sep 20, 2022
Grant date	Sep 20, 2022

Abstract

Linkage assemblies for aircraft wing hinged panels are described herein. An example linkage assembly includes a flap follower arm coupled between a spoiler support beam and a flap, a rocker, a panel link coupled between the hinged panel and the rocker, and a cross-bar link coupled between the flap follower arm and the rocker. The flap follower arm, the rocker, the panel link, and the cross-bar link are configured to coordinate adjustment of positions of the hinged panel and the flap relative to each other.

First claim

What is claimed is:

1. A linkage assembly for coupling a hinged panel of an aircraft wing and a flap of the aircraft wing, the linkage assembly comprising:
a flap follower arm coupled between a spoiler support beam and the flap;
a rocker rotatable about an axis, the rocker including a first arm and a second arm, the first arm extending in a first direction and the second arm extending in a second direction;
a panel link coupled between the hinged panel and the rocker; and
a cross-bar link having a first end and a second, the first end of the cross-bar link coupled to the flap follower arm, the second end of the cross-bar link coupled to the rocker, and wherein the flap follower arm, the cross-bar link, the rocker, and the panel link are configured to coordinate adjustment of positions of the hinged panel and the flap relative to each other as the flap is moved and such that movement of the flap causes movement of the hinged panel.

2. The linkage assembly of claim 1 , wherein the rocker is rotatably coupled to the spoiler support beam.

3. The linkage assembly of claim 2 , wherein the rocker is rotatably coupled to the spoiler support beam inboard or outboard of the flap follower arm.

4. The linkage assembly of claim 3 , wherein the cross-bar link extends in a longitudinal direction adjacent the spoiler support beam.

5. The linkage assembly of claim 2 , wherein the second end of the cross-bar link is coupled to the first arm and the panel link is coupled to the second arm.

6. The linkage assembly of claim 5 , wherein the rocker is rotatably coupled to the spoiler support beam at an intersection of the first and second arms.

7. The linkage assembly of claim 1 , wherein the hinged panel is rotatably coupled to the spoiler support beam via a first bracket, the flap follower arm is rotatably coupled to the spoiler support beam via a second bracket, and the rocker is rotatably coupled to the spoiler support beam via a third bracket.

8. The linkage assembly of claim 1 , wherein the flap follower arm includes a link and a swivel tie rod, wherein the link has a first end and a second end opposite the first end, wherein the first end of the link is rotatably coupled to the spoiler support beam, and wherein the swivel tie rod is coupled between the second end of the link and the flap.

9. The linkage assembly of claim 8 , wherein the swivel tie rod has a first end and a second end opposite the first end, the first end of the swivel tie rod is coupled to the second end of the link via a first universal joint (U-joint), and the second end of the swivel tie rod is coupled to the flap via a second U-joint.

10. A linkage assembly for coupling a hinged panel of an aircraft wing and a flap of the aircraft wing, the linkage assembly comprising:
a flap follower arm coupled between a spoiler support beam and the flap, the flap follower arm including a link and a swivel tie rod, the link having a first end and a second end opposite the first end, the first end of the link rotatably coupled to the spoiler support beam, the first end of the swivel tie rod coupled to the second end of the link via a first universal joint (U-joint), the second end of the swivel tie rod coupled to the flap via a second U-joint, wherein the swivel tie rod includes a swivel joint between the yoke forming the first U-joint and a shaft of the swivel tie rod to enable a second yoke forming the second U-joint to rotate about a longitudinal axis of the shaft;
a rocker rotatable about an axis, the rocker including a first arm and a second arm, the first arm extending in a first direction and the second arm extending in a second direction;
a panel link coupled between the hinged panel and the rocker; and
a cross-bar link coupled between the flap follower arm and the rocker, the flap follower arm, the cross-bar link, the rocker, and the panel link being configured to coordinate adjustment of positions of the hinged panel and the flap relative to each other as the flap is moved.

11. The linkage assembly of claim 1 , wherein the flap follower arm includes a spring pack between the flap follower arm and the cross-bar link.

12. The linkage assembly of claim 1 , wherein the first arm of the rocker is perpendicular to the second arm of the rocker.

Assignees

• Boeing Co

Inventors

• Mortland Michael T

Classifications

• B64C9/34

  collapsing or retracting against or within other surfaces or other members · CPC title

• B64C3/18

  Spars; Ribs; Stringers · CPC title

• B64C9/16 Primary

  at the rear of the wing · CPC title

• B64C9/20 Primary

  by multiple flaps · CPC title

• B64C9/12

  surfaces of different type or function being simultaneously adjusted · CPC title