Aircraft comprising at least one engine attachment system that has reduced vertical bulk

Patent metadata

Field	Value
Publication number	US-12404032-B2
Application number	US-202418905523-A
Country	US
Kind code	B2
Filing date	Oct 3, 2024
Priority date	Oct 6, 2023
Publication date	Sep 2, 2025
Grant date	Sep 2, 2025

Abstract

An aircraft comprising at least one engine attachment system connecting a primary structure of a pylon and a motor, having a right-hand interface connected to the right-hand lateral face of the primary structure, a left-hand interface connected to the left-hand lateral face of the primary structure, first and second shackles connecting the right-hand and left-hand interfaces to the motor by virtue of engine connection pins and interface connection pins, a right-hand emergency connection pin cooperating with the right-hand interface and the motor, and a left-hand emergency connection pin cooperating with the left-hand interface and the motor.

First claim

The invention claimed is:

1. An aircraft comprising:
a motor,
a primary structure of a pylon and an engine attachment system connecting the primary structure and the motor, said primary structure having a lower face and right-hand and left-hand lateral faces positioned on either side of a vertical median plane (PMV),
the engine attachment system comprising:
an L-shaped shackle, positioned in a transverse plane, which has first and second ends and an intermediate zone,
a first engine connection pin connecting the first end of the first shackle and the motor,
a second shackle, positioned in a transverse plane, which has first and second ends,
a second engine connection pin connecting the first end of the second shackle and the motor,
a right-hand interface connected to the right-hand lateral face of the primary structure,
a left-hand interface connected to the left-hand lateral face of the primary structure,
a first interface connection pin connecting the second end of the first shackle and a first interface among the right-hand and left-hand interfaces,
a second interface connection pin connecting the intermediate zone of the first shackle and the first interface,
a third interface connection pin connecting the second end of the second shackle and a second interface, which is different from the first interface, among the right-hand and left-hand interfaces,
a right-hand emergency connection pin cooperating with the right-hand interface and the motor,

a left-hand emergency connection pin cooperating with the left-hand interface and the motor,

wherein each right-hand or left-hand interface comprises front and rear arms positioned in transverse planes, parallel to each other and slightly spaced apart, and a right-hand or left-hand base connecting the front and rear arms, said right-hand or left-hand base being connected to the primary structure by a connection element.

2. The aircraft as claimed in claim 1 , wherein the first, second and third interface connection pins are situated at a lower plane passing through the lower face of the primary structure or offset upward with respect to this lower plane.

3. The aircraft as claimed in claim 1 ,
wherein the first interface among the right-hand and left-hand interfaces comprises, for each of the first and second interface connection pins, a through-orifice, which houses the first or second interface connection pin, dimensioned such that the first or second interface connection pin is immobile in translation, in a transverse plane, with respect to the first interface, and
wherein the second interface among the right-hand and left-hand interfaces comprises a through-orifice, which houses the third interface connection pin, dimensioned such that the third interface connection pin is immobile in translation, in a transverse plane, with respect to the second interface.

4. The aircraft as claimed in claim 1 , wherein the engine attachment system comprises a reinforcing bracket having a first wall pressed against one of the front and rear arms of the right-hand and left-hand interfaces and a second wall pressed against the right-hand or left-hand lateral face of the primary structure and connected to the primary structure by a connection element; the first wall having, for each of the first, second and third interface connection pins that passes through it, a through-orifice dimensioned such that the first, second or third interface connection pin is immobile in translation, in a transverse plane, with respect to the first wall.

5. The aircraft as claimed in claim 4 , wherein, for each right-hand and left-hand interface, the engine attachment system comprises:
a front reinforcing bracket, positioned at the front of the right-hand or left-hand interface, having a first wall pressed against the front arm of the right-hand or left-hand interface and a second wall pressed against the right-hand or left-hand lateral face of the primary structure, and
a rear reinforcing bracket, positioned at the rear of the right-hand or left-hand interface, having a first wall pressed against the rear arm of the right-hand or left-hand interface and a second wall pressed against the right-hand or left-hand lateral face of the primary structure.

6. The aircraft as claimed in claim 1 , wherein each front and rear arm of each right-hand and left-hand interface comprises a side oriented toward the motor and an extension positioned at said side and offset toward the motor with respect to a remainder of said side, said extension having a through-orifice that houses the right-hand or left-hand emergency connection pin.

7. The aircraft as claimed in claim 1 , wherein the motor comprises, for each right-hand or left-hand emergency connection pin, a transverse flange positioned at least partially between the front and rear arms of the corresponding right-hand or left-hand interface, said transverse flange having a through-orifice that houses the right-hand or left-hand emergency connection pin.

8. The aircraft as claimed in claim 1 , wherein the motor comprises, for the first engine connection pin, a first clevis that has two arms between which the first shackle is positioned and, for the second engine connection pin, a second clevis that has two arms between which the second shackle is positioned.

9. The aircraft as claimed in claim 1 , wherein the engine attachment system comprises, for each right-hand or left-hand emergency connection pin, a clearance between the right-hand or left-hand emergency connection pin and one element among the motor and the right-hand or left-hand interface.

10. The aircraft as claimed in claim 1 , wherein the motor comprises, for each of the first and second engine connection pins, a through-orifice, which houses the first or second engine connection pin, dimensioned such that each of the first and second engine connection pins is immobile in translation, in a transverse plane, with respect to the motor.

Assignees

• Airbus Operations Sas

Inventors

• Berjot Michael
• Lansiaux Rémi
• Vignes Jean-Baptiste

Classifications

• B64D27/404 Primary

  Suspension arrangements specially adapted for supporting vertical loads · CPC title