Flow body with a load introduction element integrated therein, method for manufacturing a flow body, and aircraft with such a flow body

Patent metadata

Field	Value
Publication number	US-10131418-B2
Application number	US-201514709652-A
Country	US
Kind code	B2
Filing date	May 12, 2015
Priority date	May 13, 2014
Publication date	Nov 20, 2018
Grant date	Nov 20, 2018

Abstract

A flow body for an aircraft with a leading edge and a trailing edge includes a first spar, a second spar, and an external skin that spans from the leading edge to the trailing edge and on both sides rests on the spars. At least one of the first spar and the second spar includes a web and two spaced-apart flanges that enclose the web, on which flanges the skin that spans the respective spar is arranged. At least one of the first spar and the second spar includes at least one load introduction fin that forms an integral component with the web and extends outwards by way of one of the flanges and the skin that rests on the spars.

First claim

The invention claimed is:

1. A flow body for an aircraft, the flow body with a leading edge and a trailing edge, comprising:
a first spar;
a second spar parallel to the first spar and spaced part from the first spar in a chordwise direction; and
an external skin spanning from the leading edge to the trailing edge and on both sides resting on the spars;
wherein each of the first spar and the second spar comprises a double T-profile contour in the form of a web and first and second spaced-apart flanges enclosing the web, on which flanges the skin spanning the respective spar is arranged, wherein the webs of the first and the second spars are arranged parallel to each other,
wherein the first spar and the second spar are arranged inside the flow body,
wherein the first flange is arranged at an underside of the flow body and the second flange is arranged at a side of the flow body opposite to the underside, and
wherein at least one of the first spar and the second spar comprises at least one load introduction fin forming an integral component with the web of the respective spar and extending outwards through the underside of the flow body by way of the skin and one of the flanges of the respective spar parallel to the web,
wherein the load introduction fin and the web are made of a fiber composite material comprising a fiber fabric embedded in a matrix material, and
wherein the load introduction fin and the web comprise a cohesive fiber fabric fully extending over the load introduction fin and the web.

2. The flow body of claim 1 , wherein both the first spar and the second spar comprise a load introduction fin, each extending to the same side of the flow body.

3. The flow body of claim 1 , further comprising a fiber fabric extending parallel to the web, starting from a flange through which the load introduction fin extends, towards the opposite flange comprises stepped lengths.

4. The flow body of claim 3 , wherein the stepped lengths have been selected in such a manner that from the flange through which the load introduction fin extends, the web tapers off towards the opposite flange.

5. The flow body of claim 1 , wherein the load introduction fin and the web are manufactured from a metallic material.

6. The flow body of claim 5 , wherein the load introduction fin and the web form a cohesive fabric that is not joined.

7. The flow body of claim 1 , wherein the flange through which the load introduction fin extends from the web towards the outside comprises an aperture.

8. The flow body of claim 7 , wherein when the load introduction fin has been fed through the aperture, surface transitions in the region of the aperture of the flange are lined between an internal surface or external surface of the skin, the web and the load introduction fin, with lines of material comprising a fiber composite material.

9. The flow body of claim 1 , further comprising a load introduction fitting couplable to an actuator and comprises at least one accommodation means for accommodating a load introduction fin.

10. The flow body of claim 9 , wherein the at least one accommodation means is a recess that matches the shape of the load introduction fin.

11. An aircraft, comprising a fuselage and a wing and at least one flow body, movably arranged on the wing, the flow body having a leading edge and a trailing edge and comprising:
a first spar;
a second spar parallel to the first spar and spaced apart from the first spar in a chordwise direction; and
an external skin spanning from the leading edge to the trailing edge and on both sides resting on the spars;
wherein each of the first spar and the second spar comprises a double T-profile contour in the form of a web and first and second spaced-apart flanges enclosing the web, on which flanges the skin spanning the respective spar is arranged, wherein the webs of the first and second spar are arranged parallel to each other,
wherein the first spar and the second spar are arranged inside the flow body,
wherein the first flanges are arranged at an underside of the flow body and the second flanges are arranged at a side of the flow body opposite to the underside, and
wherein at least one of the first spar and the second spar comprises at least one load introduction fin forming an integral component with the web of the respective spar and extending outwards through the underside of the flow body by way of the skin and one of the flanges of the respective spar parallel to the web,
wherein the load introduction fin and the web are made of a fiber composite material comprising a fiber fabric embedded in a matrix material, and
wherein the load introduction fin and the web comprise a cohesive fiber fabric fully extending over the load introduction fin and the web.

Assignees

• Airbus Operations Gmbh

Inventors

• Seack Oliver
• Havar Tamas
• Missbach Mirko
• Franke Thomas

Classifications

• Y02T50/44

  Cross-Sectional Technologies · mapped topic

• B64C3/26 Primary

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

• B32B37/12

  characterised by using adhesives · CPC title

• Y10T156/10

  Methods of surface bonding and/or assembly therefor · CPC title

• B64C9/02

  Mounting or supporting thereof · CPC title