Wing panel for aircraft

Patent metadata

Field	Value
Publication number	US-9415855-B2
Application number	US-201414197945-A
Country	US
Kind code	B2
Filing date	Mar 5, 2014
Priority date	Mar 18, 2013
Publication date	Aug 16, 2016
Grant date	Aug 16, 2016

Abstract

A panel for an aircraft wing, having a sandwich structure in which there is arranged a reinforcing part. When the panel is attached to a bracket so as to be articulated to another element, the reinforcing part is provided in order to distribute, over its entire surface, a force transmitted by the bracket to the panel.

First claim

The invention claimed is:

1. An aircraft wing panel comprising:
a first skin and a second skin having external faces defining outer surfaces of the wing panel and attached to one another such that the first skin and the second skin converge at the rear portion of the wing panel,
a first core arranged in a volume delimited by an assembly of the first and the second skin, sandwiched between an internal face of the first skin and an internal face of the second skin,
a reinforcing part arranged within a cut-out made in the first core, the reinforcing part comprising a flank having one face parallel to and in contact with the internal face of either the first or the second skin and a stiffener extending from the flank toward the internal face of the other of the first or the second skin, wherein the flank, the stiffener, and the internal face of the other of the first or the second skin define a second volume therein,
a second core separated from the first core by the reinforcing part, wherein the second core occupies the second volume, and
at least one cylindrical tube secured to the flank arranged perpendicular to the face of the flank,
the at least one cylindrical tube surrounding a corresponding assembly means passing through the wing panel from the first to the second skin and having one end in contact with the external face of either of the first skin and second skin.

2. The wing panel as claimed in claim 1 , wherein the reinforcing part comprises a rim associated with the stiffener, the rim being positioned substantially parallel to and in contact with the other of the first and second skins, the stiffener connecting the rim to the flank.

3. The wing panel as claimed in claim 2 , wherein the stiffener is transverse to the flank and transverse to the rim.

4. The wing panel as claimed in claim 2 , wherein the stiffener has, in a plane parallel to the face of the flank, a substantially polyhedral shape comprising at least one side around the at least one cylindrical tube.

5. The wing panel as claimed in claim 4 , wherein the stiffener has, in a plane parallel to the face of the flank, a substantially circular shape around the at least one cylindrical tube.

6. The wing panel as claimed in claim 3 , wherein the stiffener has, in a plane parallel to the face of the flank, a closed shape following an entire periphery of the flank around the at least one cylindrical tube.

7. The wing panel as claimed in claim 1 , wherein the reinforcing part comprises a rim associated with the stiffener, the rim being positioned substantially parallel to and in contact with the other of the first and second skins, the stiffener connecting the rim to the flank, wherein a portion of the rim further simultaneously engages the first and the second skin.

8. The wing panel as claimed in claim 1 , wherein the reinforcing part comprises a rim associated with the stiffener, the rim being positioned substantially parallel to and in contact with the other of the first and second skins, the stiffener connecting the rim to the flank, such that the reinforcing part forms a pan-shaped form, wherein the second core is positioned within the pan-shaped form.

9. The wing panel as claimed in claim 8 , wherein a portion of the rim further simultaneously engages the first and the second skin.

10. The wing panel as claimed in claim 1 , wherein the first and second cores are made of a cellular material.

11. An aircraft wing panel assembly comprising:
at least one bracket having a wing panel fastened thereto wherein the at least bracket provides an articulation to the wing panel,
the wing panel comprising:
a first skin and a second skin having external faces defining outer surfaces of the wing panel and attached to one another such that the first skin and the second skin converge at the rear portion of the wing panel,
a first core arranged in a volume delimited by an assembly of the first and the second skin, sandwiched between an internal face of the first skin and an internal face of the second skin,
a reinforcing part arranged within a cut-out made in the first core, the reinforcing part comprising a flank having one face parallel to and in contact with the internal face of either the first or the second skin and a stiffener extending from the flank toward the internal face of the other of the first or the second skin, wherein the flank, the stiffener, and the internal face of the other of the first or the second skin define a second volume therein,
a second core separated from the first core by the reinforcing part, wherein the second core occupies the second volume, and
at least one cylindrical tube secured to the flank arranged perpendicular to the face of the flank,
the at least one cylindrical tube surrounding a corresponding assembly means passing through the wing panel from the first to the second skin and having one end in contact with the external face of either of the first skin and second skin,
the at least one assembly means being secured to the bracket and passing through the wing panel, and being received in the at least one cylindrical tube.

12. The wing panel assembly as claimed in claim 11 , wherein the reinforcing part comprises a rim associated with the stiffener, the rim being positioned substantially parallel to and in contact with the other of the first and second skins, the stiffener connecting the rim to the flank, wherein a portion of the rim further simultaneously engages the first and the second skin.

13. The wing panel assembly as claimed in claim 11 , wherein the reinforcing part comprises a rim associated with the stiffener, the rim being positioned substantially parallel to and in contact with the other of the first and second skins, the stiffener connecting the rim to the flank, such that the reinforcing part forms a pan-shaped form, wherein the second core is positioned within the pan-shaped form.

14. The wing panel as claimed in claim 13 , wherein a portion of the rim further simultaneously engages the first and the second skin.

15. The wing panel as claimed in claim 11 , wherein the first and second cores are made of a cellular material.

Assignees

• Airbus Operations Sas

Inventors

• Normand Mathieu
• Frot Olivier
• Cresto Erik
• Azam Sebastien

Classifications

• B32B3/266

  characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12 · CPC title

• B64C1/12

  Construction or attachment of skin panels · CPC title

• B64C3/26 Primary

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

• B32B3/12

  characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure · CPC title

• B32B27/20

  using fillers, pigments, thixotroping agents · CPC title