Sealing strip, control surface arrangement, aircraft wing and aircraft

Patent metadata

Field	Value
Publication number	US-12486018-B2
Application number	US-202418602477-A
Country	US
Kind code	B2
Filing date	Mar 12, 2024
Priority date	Mar 27, 2023
Publication date	Dec 2, 2025
Grant date	Dec 2, 2025

Abstract

A sealing strip for sealing a gap between convexly curved aerodynamic surface elements of an aircraft. The sealing strip has a convexly curved outer side, welting sections at both longitudinal edges of the sealing strip for fixing the sealing strip at the aerodynamic surface elements, and a mid-seal section between the welting sections. The welting sections protrude on an inner side from the mid-seal section. The sealing strip has a first, second, and third length regions, the second length region being located longitudinally between the first and third length region. The welting sections are omitted in the second length region or the welting sections in the second length region are less rigid than the welting sections in the first and third length regions. Further, a control surface arrangement, a wing and an aircraft with such a sealing strip.

First claim

The invention claimed is:

1 . A control surface arrangement for an aircraft, comprising:
a first and a second control surface element each having convexly curved outer surfaces and being arranged side by side in a spanwise direction with a gap therebetween, wherein the gap is covered by a sealing strip comprising: a convexly curved outer side, welting sections at both longitudinal edges of the sealing strip for fixing the sealing strip at the first and the second control surface elements, and a mid-seal section between the welting sections, wherein the welting sections protrude on an inner side from the mid-seal section, wherein the sealing strip has a first length region, a second length region, and a third length region, the second length region being located longitudinally of the sealing strip between the first and third length regions, wherein the welting sections are omitted in the second length region or the welting sections in the second length region are less rigid than the welting sections in the first and third length regions, wherein the second length region is arranged in an area of the control surface arrangement with a strongest curvature or a smallest curvature radius.

2 . The control surface arrangement according to claim 1 , wherein the sealing strip has, in the first and third length regions, a profile with the welting sections and the mid-seal section therebetween and with at least one stringer-type stiffening structure arranged on the inner side of the mid-seal section.

3 . The control surface arrangement according to claim 2 , wherein the stringer-type stiffening structure is omitted in the second length region or has a stiffness reduced compared to the stiffness of the stringer-type stiffening structure of the first and third length regions.

4 . The control surface arrangement according to claim 2 , wherein the stiffening structure comprises a flange protruding on the inner side of the mid-seal section, or a neck portion and a head portion, or is configured to align a local neutral fiber location of the mid-seal section of a bent sealing strip with a local neutral fiber location of the welting sections, or a combination thereof.

5 . The control surface arrangement according to claim 1 , wherein one of the welting sections is fixed to the first control surface element, the other welting section is fixed to the second control surface element and an outer side of the mid-seal section is convexly curved.

6 . The control surface arrangement according to claim 1 ,
wherein the welting sections of the second length region comprise a thickness or diameter which is smaller than the thickness or diameter, respectively, of the welting sections of the first and third length regions, or cut-outs, or castellations, or any combination thereof, wherein a number, distance or size of the cut-outs or the castellations is based on a local curvature radius.

7 . The control surface arrangement according to claim 1 , wherein the first and second control surface elements are configured to move between a fully extended position and a fully retracted position.

8 . The control surface arrangement according to claim 1 , wherein the first and second control surface elements are leading edge slats for an aircraft wing.

9 . An aircraft comprising:
the control surface arrangement according to claim 1 .

Assignees

• Airbus Operations Gmbh

Inventors

• Schlipf Bernhard
• Fees Martin

Classifications

• B64C9/18

  by single flaps · CPC title

• B64C2009/005

  Ailerons · CPC title

• F16J15/50

  between relatively-movable members, by means of a sealing without relatively-moving surfaces, e.g. fluid-tight sealings for transmitting motion through a wall · CPC title

• B64C9/34

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

• B64C9/22

  at the front of the wing · CPC title