Central fastening system for an aircraft, fastening a structure of a wing to a structure of a pylon

Patent metadata

Field	Value
Publication number	US-12454364-B2
Application number	US-202418618244-A
Country	US
Kind code	B2
Filing date	Mar 27, 2024
Priority date	Mar 29, 2023
Publication date	Oct 28, 2025
Grant date	Oct 28, 2025

Abstract

A central fastening system having a first central fitting as one with a structure of a wing, a second central fitting as one with a structure of a pylon, a first connection system and a second connection system, wherein each connection system is fastened to the first central fitting and to the second central fitting by clevis type connections and wherein the two connection systems cross between the first central fitting and the second central fitting.

First claim

The invention claimed is:

1. A central fastening system for fastening a structure of a wing of an aircraft to a structure of a pylon of said aircraft, said central fastening system having a longitudinal direction, said central fastening system comprising:
a first central fitting configured to be as one with the structure of the wing and having a first port-side clevis and a first starboard-side clevis, wherein each first clevis has a bore with an axis parallel to the longitudinal direction,
a second central fitting configured to be as one with the structure of the pylon and having a second port-side clevis and a second starboard-side clevis, wherein each second clevis has a bore with an axis parallel to the longitudinal direction,
a first connection system and a second connection system, each connection system having a third clevis and a fourth clevis, wherein each third and fourth clevis has a bore with an axis parallel to the longitudinal direction,
wherein the third clevis of the first connection system is mounted articulated with the first port-side clevis of the first central fitting at a first articulation point on a port side,
wherein the third clevis of the second connection system is mounted articulated with the first starboard-side clevis of the first central fitting at a first articulation point on a starboard side,
wherein the fourth clevis of the first connection system is mounted articulated with the second starboard-side clevis of the second central fitting at a second articulation point on the starboard side, and
wherein the fourth clevis of the second connection system is mounted articulated with the second port-side clevis of the second central fitting at a second articulation point on the port side, and
for each articulation point, a pin mounted in the bores of the corresponding clevises.

2. The central fastening system according to claim 1 , wherein the first connection system comprises two rods disposed on either side of the first port-side clevis and the first starboard-side clevis and on either side of the second port-side clevis and the second starboard-side clevis, and
wherein together the two rods form the third clevis and the fourth clevis of said first connection system.

3. The central fastening system according to claim 1 , wherein one or both of the first connection system and the second connection system comprises a rod having a first end with a female clevis and a second end comprising a male clevis, and
wherein said female clevis forms one of the third clevis and the fourth clevis of the second connection system, and
wherein said male clevis forms the other of the third clevis and the fourth clevis of said second connection system.

4. The central fastening system according to claim 1 , wherein the first connection system comprises a rod wherein each end of the rod comprises a male clevis, and
wherein one of the male clevises of the rod forms one of the third clevis and the fourth clevis of said first connection system, and
wherein the other of the male clevises of the rod forms the other of the third clevis and the fourth clevis of said first connection system.

5. An aircraft comprising:
a wing with a structure,
a pylon with a structure, and
the central fastening system according to claim 1 ,
wherein the first central fitting is as one with the structure of the wing, and
wherein the second central fitting is as one with the structure of the pylon.

Assignees

• Airbus Operations Sas

Inventors

• Berjot Michael
• Bonhomme Philippe
• Taveau Paul-Adrien

Classifications

• F16C11/04

  Pivotal connections (hinges for doors, windows or wings E05D) · CPC title

• B64D27/404 Primary

  Suspension arrangements specially adapted for supporting vertical loads · CPC title

• B64D27/40

  Arrangements for mounting power plants in aircraft · CPC title

• B64D27/18 Primary

  within, or attached to, wings · CPC title

• B64C1/26 Primary

  Attaching the wing or tail units or stabilising surfaces · CPC title