Assembly for aircraft, comprising a primary attachment-pylon structure fixed to a wing box by fasteners partially embedded in the primary structure

Patent metadata

Field	Value
Publication number	US-11084597-B2
Application number	US-201816197726-A
Country	US
Kind code	B2
Filing date	Nov 21, 2018
Priority date	Nov 23, 2017
Publication date	Aug 10, 2021
Grant date	Aug 10, 2021

Abstract

To bring a pylon box of an aircraft engine attachment pylon as close as possible to a wing box, two lateral front fasteners are provided. Each of the fasteners comprises a clevis secured to the wing box, the clevis comprising two webs, at least one of which passes through an upper spar of the box, the upper part of one of the two opposite lateral flanges of a lower transverse rib of the box reinforcement, the upper part of an associated lateral panel, and a pin system passing through the clevis and the two upper parts.

First claim

The invention claimed is:

1. An assembly for aircraft comprising:
an aircraft wing comprising a wing box;
an engine attachment pylon arranged under the wing, the pylon comprising a primary structure formed as a pylon box having a top spar extending at least partly under the wing box, and also having a bottom spar, two opposing lateral panels, and at least one reinforcing inner transverse rib comprising two opposing lateral flanges fixed respectively onto the two opposing lateral panels, each lateral flange being fixed onto an inner surface of its associated lateral panel which extends on either side of this flange in a longitudinal direction of the assembly; and
fixing means for fixing the primary structure of the attachment pylon onto the wing box,
wherein the fixing means comprise two front lateral attachments, each of these attachments comprising:
a clevis secured to the wing box, the clevis comprising two webs of which at least one crosses the top spar of the pylon box to be situated at least partly inside this pylon box;
an upper part of the associated lateral panel;
an upper part of one of the two opposing lateral flanges of the reinforcing inner transverse rib; and
a pin system passing through the two webs of said clevis, the upper part of the associated lateral panel, and the upper part of the lateral flange.

2. The assembly as claimed in claim 1 , wherein said reinforcing inner transverse rib is inclined so as to extend downward in a forward direction.

3. The assembly as claimed in claim 1 , wherein said reinforcing inner transverse rib is configured to be fixed in its bottom part to an engine attachment.

4. The assembly as claimed in claim 1 , wherein said top spar of the pylon box has a substantially planar form all along the pylon box.

5. The assembly as claimed in claim 1 , wherein said pylon box has a transverse section of continuous form all along the pylon box.

6. The assembly as claimed in claim 1 , wherein said wing box comprises a front spar onto which are fixed two reinforcing fittings respectively supporting the two clevises of the front lateral attachments.

7. The assembly as claimed in claim 1 , wherein each of the front lateral attachments is designed so as to allow absorption of the forces that are exerted in the longitudinal direction and in a vertical direction of the assembly, and wherein one of the two front lateral attachments is also designed so as to allow the absorption of the forces that are exerted in a transverse direction of the assembly.

8. The assembly as claimed in claim 1 , wherein said fixing means also comprise a rear attachment fixed onto a rear closing rib of the pylon box, and wherein the rear attachment is designed so as to allow only absorption of the forces that are exerted in a vertical direction of the assembly.

9. The assembly as claimed in claim 1 , wherein said fixing means form an isostatic force absorption system.

10. The assembly as claimed in claim 1 , wherein the web crosses the top spar at a lateral cutout thereof, said cutout being open laterally outward.

11. The assembly as claimed in claim 1 , wherein the upper part of each lateral flange comprises an ear.

12. The assembly as claimed in claim 1 , wherein said upper part of the associated lateral panel, and said upper part of one of the two opposing lateral flanges of the transverse rib, are arranged between the two webs of the clevis.

13. The assembly as claimed in claim 1 , wherein the two clevises, belonging respectively to the two front lateral attachments, are incorporated in one and the same part produced in a single piece.

14. An aircraft comprising at least one assembly as claimed in claim 1 .

Assignees

• Airbus Operations Sas

Inventors

• Pautis Olivier
• Bouchet Eric
• Barbara Olivier

Classifications

• B64D27/406

  Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links · CPC title

• B64D27/404

  Suspension arrangements specially adapted for supporting vertical loads · CPC title

• B64D27/402

  comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant · CPC title

• B64D27/12 Primary

  within, or attached to, wings · CPC title

• B64D27/18

  within, or attached to, wings · CPC title