Aircraft assembly comprising a mounting pylon primary structure integrated to the structure of the wing element

Patent metadata

Field	Value
Publication number	US-9889942-B2
Application number	US-201615015841-A
Country	US
Kind code	B2
Filing date	Feb 4, 2016
Priority date	Feb 6, 2015
Publication date	Feb 13, 2018
Grant date	Feb 13, 2018

Abstract

In order to optimize the bulk of a primary structure of an aircraft engine attachment pylon, and to favor the installation of the engine as close as possible to the wing element, the disclosure herein provides an aircraft assembly comprising a wing element, a turbofan engine and an engine attachment pylon, the engine comprising a rear part arranged under the wing element equipped with a wing structure, the pylon comprising a primary structure for transmitting loads from the engine to the wing structure, this primary structure comprising a pylon box, and the assembly also comprising an attachment for attaching the primary structure to the engine. According to the disclosure herein, the wing structure comprises two wing boxes that follow one another in a wingspan direction of the wing element, and the pylon box is arranged between these boxes and fixed to each of the latter.

First claim

The invention claimed is:

1. An aircraft assembly comprising a wing element, a turbofan engine and an engine attachment pylon, the engine comprising a rear part arranged under the wing element, which is equipped with a wing structure, the pylon comprising a primary structure for transmitting loads from the engine to the wing structure, the primary structure comprising a pylon box, and the assembly also comprising an attachment for attaching the primary structure to the engine,
the wing structure comprising two wing boxes that follow one another in a wingspan direction of the wing element, and the pylon box being arranged between the wing boxes and fixed to each of the latter.

2. The assembly according to claim 1 , wherein the two wing boxes form an internal box and an external box, the internal box being delimited by an external lateral panel and the external box being delimited by an internal lateral panel, the pylon box being delimited by an external lateral panel and by an internal lateral panel, and wherein it has a first mechanical connection between the external lateral panel of the internal wing box and the internal lateral panel of the pylon box, and also a second mechanical connection between the internal lateral panel of the external wing box and the external lateral panel of the pylon box.

3. The assembly according to claim 2 , wherein the external lateral panel of the internal wing box is pressed against the internal lateral panel of the pylon box, and in that the internal lateral panel of the external wing box is pressed against the external lateral panel of the pylon box.

4. The assembly according to claim 2 , wherein the first and second mechanical connections are each produced by shear pins and/or bolts, the shear pins and/or bolts preferably having axes substantially parallel to the wingspan direction.

5. The assembly according to claim 2 , wherein the pylon box and the internal and external wing boxes are each delimited by lower spars and upper spars, the lower spars of the pylon box ensuring surface continuity between the lower spars of the internal and external wing boxes, and the upper spars of the pylon box ensuring surface continuity between the upper spars of the internal and external wing boxes.

6. The assembly according to claim 1 , wherein the pylon box has internal transverse box stiffening ribs.

7. The assembly according to claim 1 , wherein the pylon box extends forwards beyond the internal and external wing boxes.

8. The assembly according to claim 2 , wherein the pylon box and the internal and external wing boxes are each delimited by a rear closing rib, the rear closing rib of the pylon box ensuring surface continuity between the rear closing ribs of the internal and external wing boxes.

9. The assembly according to claim 1 , wherein the pylon box has a cross section in the overall shape of a quadrilateral, preferably square or rectangular, the cross section having a changing size along the pylon box.

10. The assembly according to claim 1 , wherein the primary structure also has an intermediate structure interposed between the pylon box and the attachment for attaching the primary structure to the engine, the intermediate structure taking the form of a fitting, preferably having the overall shape of a pyramid.

11. The assembly according to claim 1 , wherein the pylon box bears, at its front end, a part of the attachment for attaching the primary structure to the engine.

12. The assembly according to claim 1 , wherein a front part of the attachment for attaching the primary structure to the engine is connected to an external shroud of an intermediate casing of the engine, this external shroud extending in the rearward axial continuation of a fan casing, or in that this front part of the attachment for attaching the primary structure to the engine is connected to an internal shroud of the intermediate casing of the engine.

13. A method for mounting an assembly according to claim 1 , comprising the following successive steps of:
a) fixing at least one part of the pylon box to an internal wing box; and then
b) fixing an external wing box to the at least one part of the pylon box.

14. The mounting method according to claim 13 , wherein the pylon box is delimited by upper spars mounted on the assembly after step b).

15. An aircraft comprising at least one assembly according to claim 1 .

Assignees

• Airbus Operations Sas

Inventors

• Pautis Olivier
• Brochard Wolfgang

Classifications

• B64D27/12 Primary

  within, or attached to, wings · CPC title

• B64D27/402 Primary

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

• B64C3/187

  Ribs · CPC title

• B64D27/26

  Operations & Transport · mapped topic

• B64F5/10

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