Leading-edge component for an aircraft

Patent metadata

Field	Value
Publication number	US-11230365-B2
Application number	US-202016852862-A
Country	US
Kind code	B2
Filing date	Apr 20, 2020
Priority date	Apr 29, 2019
Publication date	Jan 25, 2022
Grant date	Jan 25, 2022

Abstract

A leading-edge component for an aircraft includes at least a part of a flow body having a front skin and at least one rib, wherein the front skin includes a top section, a bottom section and a leading edge arranged therebetween, wherein the rib extends from the bottom section to the top section, wherein the rib includes at least one kink separating the rib into a first section and at least one second section, and wherein main extension planes of the first section and the at least one second section enclose an angle of at least 10°.

First claim

The invention claimed is:

1. A leading-edge component for an aircraft, comprising:
at least a part of a flow body having a front skin, at least one rib, and a flange,
wherein the front skin comprises a top section, a bottom section and a leading edge arranged therebetween,
wherein the rib extends from the bottom section to the top section,
wherein the rib comprises at least one kink separating the rib into a first section and at least one second section,
wherein main extension planes of the first section and the at least one second section enclose an angle of at least 10°, and
wherein the at least one rib is attached to the flange such that the flange encloses an offset to the main extension plane of the at least one second section.

2. The leading-edge component according to claim 1 , wherein the main extension plane of the first section is not perpendicular to the leading edge.

3. The leading-edge component according to claim 2 , wherein a surface normal of the main extension plane of the first section and the leading edge enclose an angle of at least 10°.

4. The leading-edge component according to claim 1 , wherein the main extension plane of the at least one second section is perpendicular to the leading edge.

5. The leading-edge component according to claim 1 , wherein the main extension plane of the at least one second section is parallel to a chord axis of the flow body.

6. The leading-edge component according to claim 1 , wherein the kink between the first section and a directly adjacent second section is configured for at least folding or breaking the first section relative to the second section on an impact of a moving object onto the leading edge.

7. The leading-edge component according to claim 1 , wherein the leading-edge component is configured to be a fixed component rigidly attachable to a structure.

8. The leading-edge component according to claim 1 , wherein the leading-edge component is configured to be a movable component having a substantially closed surface.

9. A wing for an aircraft, having a leading-edge component according to claim 1 .

10. The wing according to claim 9 ,
further comprising a fixed leading edge,
wherein the leading-edge component is movable between a retracted position directly forward the fixed leading-edge and at least one extended position at a further distance to the fixed leading edge.

11. An aircraft having at least one wing of claim 9 or at least one leading-edge component comprising:
at least a part of a flow body having a front skin and at least one rib,
wherein the front skin comprises a top section, a bottom section and a leading edge arranged therebetween,
wherein the rib extends from the bottom section to the top section,
wherein the rib comprises at least one kink separating the rib into a first section and at least one second section, and
wherein main extension planes of the first section and the at least one second section enclose an angle of at least 10°.

12. The aircraft of claim 11 , wherein the first section and the at least one second section are parallel to a vertical axis of the aircraft.

Assignees

• Airbus Operations Gmbh

Inventors

• Bensmann Stefan

Classifications

• B64C9/22 Primary

  at the front of the wing · CPC title

• B64C3/187

  Ribs · CPC title

• Y02T50/30

  Wing lift efficiency · CPC title

• B64C3/28 Primary

  Leading or trailing edges attached to primary structures, e.g. forming fixed slots · CPC title

• B64C9/24

  by single flap · CPC title