Assembly for an aircraft, comprising an engine attachment body partially produced in one piece with an internal stiffening rib of an attachment pylon box section

Patent metadata

Field	Value
Publication number	US-9862497-B2
Application number	US-201414571772-A
Country	US
Kind code	B2
Filing date	Dec 16, 2014
Priority date	Dec 17, 2013
Publication date	Jan 9, 2018
Grant date	Jan 9, 2018

Abstract

In order to decrease the overall mass of an assembly for an aircraft, including an engine attachment pylon and an engine attachment, the pylon according to the disclosure herein has a primary structure forming a box section equipped with internal transverse stiffening ribs, one of which is produced in one piece with at least a part of the body of the engine attachment.

First claim

The invention claimed is:

1. An assembly for an aircraft, the assembly comprising:
an attachment pylon for an aircraft engine;
an engine attachment mounted on the attachment pylon to provide a joining between the engine and the attachment pylon,
wherein the attachment pylon comprises a primary structure, which comprises an upper spar, a lower spar, and two lateral panels together in a form of a box section, the primary structure being equipped with internal transverse stiffening ribs, and
wherein the engine attachment comprises a body located outside the primary structure; and

shackles that are articulated on the body and can be articulated on the engine,
wherein at least a part of the body of the engine attachment is formed in a single piece with one of the internal transverse stiffening ribs of the primary structure.

2. The assembly according to claim 1 , wherein the part of the body of the engine attachment comprises a central beam located outside the primary structure,
the body further comprising, at each end of the central beam in a transverse direction of the assembly, a one-piece fitting comprising a first joining portion on which one of the shackles can be articulated and a second joining portion that is fixed to the primary structure and passes into the primary structure.

3. The assembly according to claim 2 , wherein the second joining portion is arranged between one of the two lateral panels of the primary structure and a corresponding one of the internal transverse stiffening ribs of the primary structure.

4. The assembly according to claim 2 , wherein the first joining portion is in a form of a clevis and the second joining portion is substantially flat.

5. The assembly according to claim 2 , wherein the two one-piece fittings are fixed to the central beam, on which one or more of the shackles can be articulated.

6. The assembly according to claim 2 , further comprising a device for taking up thrust forces, the device comprising:
a support element fixed to an outside of the primary structure;
two lateral link rods configured to take up thrust forces; and
a spreader articulated on the support element,
wherein the two lateral link rods are articulated on two opposite ends of the spreader, respectively, and
wherein the two ends of the spreader are flexibly mounted on connecting members that are an integral part of the central beam.

7. The assembly according to claim 6 , wherein the support element is arranged in a recess of the central beam.

8. The assembly according to claim 1 , wherein the part of the body of the engine attachment is in a form of two extensions of a base of the internal transverse stiffening rib and is located outside the primary structure, the two extensions being spaced apart from one another in a transverse direction of the assembly, and the body of the engine attachment further comprises a main beam fixed to the two extensions, the shackles being articulated on the central beam.

9. The assembly according to claim 8 , further comprising a device for taking up thrust forces, the device comprising:
a support element fixed to an outside of the primary structure;
two lateral link rods configured to take up thrust forces; and
a spreader articulated on the support element,
wherein the two lateral link rods are articulated on two opposite ends of the spreader, respectively, and
wherein two ends of the spreader are flexibly mounted on connecting members that are an integral part of the main beam.

10. The assembly according to claim 9 , wherein the support element is arranged between the two extensions of the base of the internal transverse stiffening rib.

11. The assembly according to claim 1 , further comprising a device for taking up thrust forces, the device comprising:
a support element fixed to an outside of the primary structure;
two lateral link rods configured to take up thrust forces; and
a spreader articulated on the support element,
wherein the two lateral link rods are articulated on two opposite ends of the spreader, respectively.

12. The assembly according to claim 1 , wherein the engine attachment is a rear engine attachment and the assembly further comprises a front engine attachment.

13. The assembly according to claim 12 , further comprising a device for taking up thrust forces, the device comprising:
a support element fixed to an outside of the primary structure;
two lateral link rods configured to take up thrust forces; and
a spreader articulated on the support element,
wherein the two lateral link rods are articulated on two opposite ends of the spreader, respectively, and
wherein the rear engine attachment, the front engine attachment, and the device for taking up thrust forces comprise a structure for attaching an engine that comprises an isostatic system for taking up forces.

14. The assembly according to claim 1 , wherein the engine attachment comprises first and second lateral half-attachments, wherein the first half-attachment is designed to only take up thrust forces oriented in a vertical direction of the assembly and the second half-attachment is designed to only take up thrust forces oriented in the vertical direction of the assembly and in a transverse direction of the assembly.

15. An aircraft part comprising an assembly according to claim 1 , a wing element from which the attachment pylon is suspended, and an engine fixed to the engine attachment.

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

17. A method for removing an engine fixed by an engine attachment assembly, the method comprising:
providing an engine attachment assembly comprising:
an attachment pylon for an aircraft engine,
an engine attachment mounted on the attachment pylon to provide a joining between the engine and the attachment pylon,
wherein the attachment pylon comprises a primary structure, which comprises an upper spar, a lower spar, and two lateral panels together in a form of a box section, the primary structure being equipped with internal transverse stiffening ribs, and
wherein the engine attachment comprises a body located outside the primary structure, and

shackles that are articulated on the body and are configured to be articulated on the engine,
wherein at least a part of the body of the engine attachment is formed in a single piece with one of the internal transverse stiffening ribs of the primary structure, and
wherein the shackles have at least two ends; and

removing each of the shackles at at least one of the two ends thereof.

Assignees

• Airbus Operations Sas

Inventors

• Ewens David
• Blanc Jonathan

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 Primary

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

• B64D2027/266

  Operations & Transport · mapped topic

• B64D2027/262

  Operations & Transport · mapped topic