Flow body for an aircraft having a solid trailing-edge component

Patent metadata

Field	Value
Publication number	US-11975832-B2
Application number	US-202017425266-A
Country	US
Kind code	B2
Filing date	May 25, 2020
Priority date	May 27, 2019
Publication date	May 7, 2024
Grant date	May 7, 2024

Abstract

A flow body for an aircraft, in particular for a wing leading edge device, is proposed, the flow body having a curved front skin having a leading edge and at least one trailing-edge component coupled with at least one spanwise edge of the front skin, wherein the trailing-edge component comprises a constant cross-sectional profile that tapers in a chordwise direction to form two spanwise flow surfaces that end in a trailing edge, and wherein the trailing-edge component is designed for providing a flush transition between the front skin and at least one of the two spanwise flow surfaces.

First claim

The invention claimed is:

1. A flow body for a wing leading edge device of an aircraft, the flow body comprising:
a curved front skin having a leading edge, and
at least one trailing-edge component coupled with at least one spanwise edge region of the front skin,
wherein the trailing-edge component comprises a single-piece construction having a continuous perimeter cross-sectional profile that tapers in a chordwise direction to form two spanwise flow surfaces that end in a trailing edge, wherein the cross-sectional profile is taken transverse to a longitudinal extension of the trailing-edge component,
wherein the flow body has a rear air chamber,
wherein the trailing-edge component comprises two spaced apart legs forming an intermediate space therebetween, the two spaced apart legs extending into the rear air chamber such that the trailing-edge component encloses the rear air chamber,
wherein the rear air chamber is delimited by the trailing-edge component, and
wherein the trailing-edge component is configured to provide a flush transition between the front skin and at least one of the two spanwise flow surfaces.

2. A flow body for a wing leading edge device of an aircraft, the flow body comprising:
a curved front skin having a leading edge, and
at least one trailing-edge component coupled with at least one spanwise edge region of the front skin,
wherein the trailing-edge component comprises a single-piece construction having a continuous perimeter cross-sectional profile that tapers in a chordwise direction to form two spanwise flow surfaces that end in a trailing edge, wherein the cross-sectional profile is taken transverse to a longitudinal extension of the trailing-edge component,
wherein the flow body has a rear air chamber,
wherein the trailing-edge component comprises two spaced apart legs forming an intermediate space therebetween, the two spaced apart legs extending into the rear air chamber such that the trailing-edge component encloses the rear air chamber,
wherein the rear air chamber is delimited by the trailing-edge component, and
wherein the trailing-edge component is configured to provide a flush transition between the front skin and at least one of the two spanwise flow surfaces, wherein the trailing-edge component comprises at least one recessed spanwise receiving surface for receiving a spanwise edge of the at least one spanwise edge region of the front skin,
wherein the at least one recessed spanwise receiving surface is delimited by a step facing the trailing edge, and
wherein the step is configured to provide the flush transition between the front skin and the trailing-edge component.

3. The flow body according to claim 2 , wherein the front skin is attached to the at least one recessed spanwise receiving surface.

4. The flow body according to claim 1 ,
wherein the flow body comprises the hollow space, in which at least one spar extends along a spanwise direction,
wherein a rear air chamber is created rearward of the at least one spar, in which the rear air chamber extends from the at least one spar to a junction of the two legs.

5. The flow body according to claim 4 ,
wherein a forward air chamber is created forward of the at least one spar, and
wherein the rear air chamber and the forward air chamber are in a fluid communication.

6. The flow body according to claim 1 ,
further comprising a back skin arranged at a distance to the front skin,
wherein a spanwise edge of the back skin is arranged on the trailing-edge component.

7. The flow body according to claim 4 ,
further comprising a back skin arranged at a distance to the front skin,
wherein a spanwise edge of the back skin is arranged on the trailing-edge component,
wherein the back skin is attached to the at least one spar, and
wherein the rear air chamber is additionally delimited by the back skin.

8. The flow body according to claim 1 ,
wherein the flow body is a leading-edge slat and
wherein the trailing-edge component provides a trailing edge of the slat.

9. The flow body according to claim 1 , wherein the trailing-edge component is an extruded part.

10. A wing having a fixed wing body and a wing leading edge device having a flow body according to claim 1 .

11. The wing according to claim 10 , further comprising an anti- or de-icing device providing air at an elevated temperature, which is in fluid communication with a hollow space of the flow body.

12. An aircraft having wings according to claim 10 .

13. An aircraft having at least one flow body according to claim 1 .

14. The aircraft of claim 13 , wherein the flow body is a part of a wing leading edge device arranged on a fixed wing body of a wing.

Assignees

• Airbus Operations Gmbh

Inventors

• Erban Marcus

Classifications

• 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

• B64D15/04

  Hot gas application · CPC title

• B64C2003/146

  comprising leading edges of particular shape · CPC title

• Y02T50/40

  Weight reduction · CPC title