Wing leading edge device and a wing having such a wing leading edge device

Patent metadata

Field	Value
Publication number	US-11453477-B2
Application number	US-202016796025-A
Country	US
Kind code	B2
Filing date	Feb 20, 2020
Priority date	Feb 28, 2019
Publication date	Sep 27, 2022
Grant date	Sep 27, 2022

Abstract

A wing leading edge device includes a flow body having a front side, which is delimited by a first spanwise edge and a second spanwise edge, a back side, which is delimited by the first spanwise edge and the second spanwise edge, a front skin arranged on the front side, a back skin arranged on the back side, and at least one stiffening arrangement between the front skin and the back skin in the region of the first spanwise edge, wherein the front skin extends continuously and free from interruptions between the first spanwise edge and the second spanwise edge and covers the at least one stiffening arrangement.

First claim

The invention claimed is:

1. A flow body for an aircraft, the flow body comprising:
a front side delimited by a first spanwise edge and a second spanwise edge;
a back side delimited by the first spanwise edge and the second spanwise edge;
a front skin arranged on the front side;
a back skin arranged on the back side; and
at least one stiffening arrangement from the front skin to the back skin in the region of the first spanwise edge, the at least one stiffening arrangement comprising a corrugated sheet material extending from the front skin to the back skin,
wherein the front skin extends continuously and free from interruptions between the first spanwise edge and the second spanwise edge and covers the at least one stiffening arrangement.

2. The flow body according to claim 1 , wherein the at least one stiffening arrangement extends from the front skin to the back skin in the region of the first spanwise edge.

3. The flow body according to claim 1 , wherein the at least one stiffening arrangement further comprises a tip profile body attached to the front skin neighboring the first spanwise edge at side of the front skin that faces the back skin for stiffening the flow body in the region of the first spanwise edge.

4. The flow body according to claim 1 , wherein the back skin is joggled in a spanwise section adjacent to the first spanwise edge.

5. The flow body according to claim 1 ,
wherein the flow body is a leading-edge slat, and
wherein the first spanwise edge is a trailing edge of the slat.

6. A wing comprising a fixed wing body and a wing leading edge device comprising a flow body according to claim 1 .

7. An aircraft comprising at least one flow body according to claim 1 .

8. The aircraft of claim 7 , wherein the at least one flow body is a part of a wing leading edge device arranged on a fixed wing body of a wing.

9. A flow body for an aircraft, the flow body comprising:
a front side delimited by a first spanwise edge and a second spanwise edge;
a back side delimited by the first spanwise edge and the second spanwise edge;
a front skin arranged on the front side;
a back skin arranged on the back side; and
at least one stiffening arrangement from the front skin to the back skin in the region of the first spanwise edge,
wherein the front skin extends continuously and free from interruptions between the first spanwise edge and the second spanwise edge and covers the at least one stiffening arrangement, and
wherein the at least one stiffening arrangement comprises a honeycomb core extending from the front skin to the back skin.

Assignees

• Airbus Operations Gmbh

Inventors

• Bensmann Stefan
• Erban Marcus
• Fees Martin

Classifications

• B64C9/22 Primary

  at the front of the wing · CPC title

• B64F5/10

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title

• B64C9/24

  by single flap · CPC title

• B64C3/26 Primary

  Construction, shape, or attachment of separate skins, e.g. panels · CPC title

• B64C3/185

  Spars · CPC title