Method for assembling an aircraft pylon and aircraft pylon obtained by this method

Patent metadata

Field	Value
Publication number	US-12054271-B2
Application number	US-202117391825-A
Country	US
Kind code	B2
Filing date	Aug 2, 2021
Priority date	Aug 4, 2020
Publication date	Aug 6, 2024
Grant date	Aug 6, 2024

Abstract

A method for assembling an aircraft pylon including a primary structure and at least one internal system positioned at least partially within the primary structure, wherein the assembly method includes a first step of assembling a part of the primary structure so that the interior of the primary structure remains accessible, a step of mounting an internal systems module including at least one support and at least one internal system connected to the support, a second step of assembling the internal systems module and the partially assembled primary structure, a third step of assembling any element of the primary structure not assembled in the first assembly step, and an aircraft pylon assembled by such a method.

First claim

The invention claimed is:

1. A method for assembling an aircraft pylon comprising:
a primary structure comprising upper and lower spars and first and second lateral panels,
a secondary structure capping the primary structure,
at least one internal system positioned at least partially inside the primary structure, and
at least one external system positioned between the primary structure and the secondary structure, wherein the assembly method comprises:
a first step of assembling a subassembly comprising at least one of the upper and lower spars and at least one of the first and second lateral panels,
a step of mounting an internal systems module comprising the at least one internal system and at least one support to which the at least one internal system is connected, the at least one support being distinct from the primary structure, the at least one support comprising at least one through-hole through which the at least one internal system passes, and the at least one support comprising a first part and a second part which meet and are joined at a junction plane, the junction plane being parallel to and equidistant from the first and second lateral panels, each of the first and second parts of the support comprising a plate and a comb positioned at a side of the plate and having a first flange connected to the plate and a second flange extending outwardly transversely from each plate, each second flange delimiting a portion of the at least one through-hole through which the at least one internal system passes,
a second step of assembling the internal systems module and the subassembly assembled in the first assembly step, and during the second assembly step, said at least one support for the internal systems module is connected to at least one of at least one upper or lower spar, or at least one first or second lateral panel of the subassembly assembled in the first assembly step,
a third step of assembling any element of the primary structure not assembled in the first assembly step, and
a step of installing and securing the external systems and the secondary structure.

2. The method for assembling an aircraft pylon as claimed in claim 1 ,
wherein the upper and lower spars, the first and second lateral panels and the supports are pre-drilled before being assembled, and
wherein during the first, second and third assembly steps, the upper and lower spars, the first and second lateral panels and the at least one support are positioned relative to one another in such a way that holes line up in order to be able to receive fasteners, and then the fasteners are installed.

3. The method for assembling an aircraft pylon as claimed in claim 1 , wherein the internal systems module comprises multiple mutually independent supports.

4. The method for assembling an aircraft pylon as claimed in claim 1 , wherein the internal systems module comprises multiple supports that are connected to one another by longitudinal stiffeners.

5. The method for assembling an aircraft pylon as claimed in claim 4 , wherein each support is formed as a frame, the at least one internal system of the internal systems module comprises multiple internal systems, and the multiple internal systems are connected to the at least one support or the longitudinal stiffeners by connectors, so as to keep the internal systems from moving relative to the at least one support and relative to the longitudinal stiffeners.

6. The method for assembling an aircraft pylon as claimed claim 1 , wherein the at least one through-hole intersects the junction plane where the first and second parts meet, the first and second parts comprising first and second semi-cylindrical shapes delimiting the at least one through-hole when the first and second parts meet.

7. The method for assembling an aircraft pylon as claimed in claim 6 , wherein the at least one internal system passing through the at least one through-hole is cylindrical at least in line with the at least one through-hole, and the at least one through-hole is cylindrical and has a diameter substantially equal to that of the at least one internal system.

8. The method for assembling an aircraft pylon as claimed in claim 6 , wherein each of the comb of the first and second parts of the at least one support is made of elastomeric material, having a semi-cylindrical shape for each through-hole.

9. An aircraft pylon obtained by the assembly method as claimed in claim 1 , wherein the aircraft pylon comprises:
a primary structure, and
an internal systems module comprising:
at least one internal system, and
at least one support to which the at least one internal system is connected,
said internal systems module being positioned inside the primary structure, and
the at least one support of the internal systems module being connected to the primary structure.

10. The aircraft pylon as claimed in claim 9 ,
wherein the at least one support comprises at least one through-hole through which there passes an internal system and first and second parts that meet at a junction plane, and
wherein the first and second parts comprise, for the at least one through-hole, first and second semi-cylindrical shapes delimiting the at least one through-hole when the first and second parts meet.

11. The aircraft pylon as claimed in claim 10 ,
wherein the internal system passing through the at least one through-hole is cylindrical at least in line with the at least one through-hole, and
wherein the at least one through-hole is cylindrical and has a diameter substantially equal to that of the internal system.

12. The aircraft pylon as claimed in claim 10 , wherein each of the first and second parts of the at least one support comprises a comb made of elastomeric material, having a semi-cylindrical shape for the at least one through-hole.

Assignees

• Airbus Sas
• Airbus Operations Sas

Inventors

• Alby Sebastien
• Geliot Jean
• Deforet Thomas
• Dubois Olivier
• Dedieu Joël
• Bardey Xavier

Classifications

• B64F5/10 Primary

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

• B64D27/40 Primary

  Arrangements for mounting power plants in aircraft · CPC title