IP Library Granted Patent US 12,522,366
Granted Patent B2
US 12,522,366 · App. 18/755,122 · Granted Jan 13, 2026

Front engine attachment system intended for an aircraft engine and having a compact structure

Inventors: Michael Berjot (Toulouse, FR); Rémi Lansiaux (Toulouse, FR); Jean-Baptiste Vignes (Toulouse, FR)
Assignee: Airbus Operations SAS
B64D27/404B64D27/406
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Quick Facts
Patent No.
US 12,522,366
App. No.
18/755,122
Granted
Jan 13, 2026
Kind
B2
Abstract

A front engine attachment system for an engine having an engine pylon with a nose having a male clevis and a cylindrical stud, two links that are fastened to the engine by a second ball-joint connection about a second axis, a first shaft establishing a first ball-joint connection of the links to the male clevis about a first axis, wherein the first axis and the second axis are in the same vertical plane, and wherein the cylindrical stud is mounted so as to be able to move, via an annular linear connection, with respect to the front casing.

Claims (15)

1 . A front engine attachment system for an engine of an aircraft, the front engine attachment system having a vertical median plane and comprising:

an engine pylon having, at a front part, a nose having a male clevis and a cylindrical stud that is cylindrical about a vertical axis and configured to be mounted so as to move, via an annular linear connection, about the vertical axis with respect to a front casing of the engine,

two links, which are configured to be fastened to the front casing by a second ball-joint connection about a second axis perpendicular to the vertical median plane, the two links being arranged on either side of the male clevis, and

a first shaft, which is perpendicular to the vertical median plane and forms a first ball-joint connection of the two links to the male clevis about a first axis,

wherein the first axis and the second axis are in the same vertical plane perpendicular to the vertical median plane.

2 . The front engine attachment system according to claim 1 , wherein the first axis is arranged towards a rear of the vertical axis.

3 . The front engine attachment system according to claim 1 , wherein each link comprises two adjoining links.

4 . The front engine attachment system according to claim 1 , wherein the nose comprises two fittings that are fastened to one another, and

wherein the cylindrical stud comprises two half-cylinders adjoining the vertical median plane, wherein each half-cylinder belongs to one of the fittings of the nose.

5 . The front engine attachment system according to claim 1 , wherein the first shaft comprises a first peripheral shaft, which is hollow, and a first inner shaft, fitted within the first peripheral shaft.

6 . An aircraft comprising:

an engine with a front casing and

the front engine attachment system according to claim 1 ,

wherein the links are fastened to the front casing by the second ball-joint connection, and

wherein the cylindrical stud is mounted to move, via the annular linear connection, about the vertical axis with respect to the front casing.

Assignments (1)
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Jul 24, 2024
From: BERJOT, MICHAEL; LANSIAUX, RÉMI; VIGNES, JEAN-BAPTISTE
To: AIRBUS OPERATIONS SAS
Reel/Frame 068066/0916 →
Priority Claims (1)
FR 2306782 · Jun 28, 2023 · national
Continuity (1)
Related Publication 20250002166A1 · Jan 2, 2025
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