Aircraft pylon fairing, fairing assembly, aircraft pylon and aircraft

Patent metadata

Field	Value
Publication number	US-12337977-B2
Application number	US-202318457148-A
Country	US
Kind code	B2
Filing date	Aug 28, 2023
Priority date	Aug 30, 2022
Publication date	Jun 24, 2025
Grant date	Jun 24, 2025

Abstract

An aircraft pylon comprising an aircraft pylon fairing extending along a longitudinal axis, a primary structure having a peg that is inserted in a through opening of an inner rib of the fairing and four yokes as well as four removable fixing elements that can be inserted from the outside of the fairing. The fixing elements are inserted in a direction perpendicular to said longitudinal axis of the fairing in order to hold in place a fitting of the primary structure that has an oblong through opening and is inserted into one of said yokes of the fairing. Also a method of assembling an aircraft pylon and an aircraft with such a pylon.

First claim

The invention claimed is:

1. An aircraft pylon fairing assembly comprising:
an aircraft pylon fairing extending along a longitudinal axis, the aircraft pylon fairing comprising:
a wall having at least two opposite flanks oriented respectively one on each side of said longitudinal axis,
a central interior cavity, the at least two opposite flanks meeting in a lower or an upper part of said fairing,
a front transverse rib securely fixed to said wall and extending perpendicularly on each side of said longitudinal axis, said front transverse rib comprising a through opening configured to accept a peg of an exterior structure by push-fitting in a direction parallel to said longitudinal axis, and comprising two yokes each having bores along an axis oriented perpendicular to said longitudinal axis of the fairing and arranged facing a through opening in one of said opposing flanks, and
a rear transverse rib securely fixed to said wall and extending perpendicularly on each side of said longitudinal axis and comprising two yokes each having bores along an axis oriented perpendicular to said longitudinal axis of the fairing and arranged facing another through opening in one of said opposing flanks,

the aircraft pylon fairing assembly further comprising four fixing elements which are configured to each be inserted into and held in position in the bore of one of said yokes of the front transverse rib and the rear transverse rib,
wherein the aircraft pylon fairing is a secondary structure which contributes to an aerodynamic performance of a flight, and
wherein the exterior structure is an aircraft primary structure indispensable for the flight,
wherein the peg of said aircraft primary structure is oriented along an axis parallel to the longitudinal axis of the fairing and configured to be inserted into said through opening of said front transverse rib, and wherein said aircraft primary structure comprises four fittings which are respectively arranged in such a way as to each be inserted into one of said yokes of said front transverse rib and said rear transverse rib, and each having a through opening configured to be arranged facing said bore of said yoke and configured to receive a portion of one of said four fixing elements which is inserted into said bore of said yoke, said openings in the fittings which are configured to be inserted into the yokes of the front transverse rib of said fairing having an oblong shape extending in a direction perpendicular to the longitudinal axis of the fairing, and said openings in the fittings that are configured to be inserted into the yokes of the rear transverse rib of said fairing having an oblong shape extending along an axis parallel to said longitudinal axis of said fairing, or vice versa.

2. The aircraft pylon fairing assembly according to claim 1 , wherein said openings in the fittings configured to be inserted into the yokes of the front transverse rib of said fairing have the oblong shape extending in the direction perpendicular to the longitudinal axis of the fairing, and
wherein said openings of the fittings configured to be inserted into the yokes of the rear transverse rib of said fairing have the oblong shape extending along the axis parallel to said longitudinal axis of said fairing.

3. The aircraft pylon fairing assembly according to claim 1 , wherein said openings in the fittings configured to be inserted into the yokes of the front transverse rib of said fairing have an oblong shape extending in a direction parallel to the longitudinal axis of the fairing, and
wherein said openings of the fittings configured to be inserted into the yokes of the rear transverse rib of said fairing have an oblong shape extending along an axis perpendicular to said longitudinal axis of said fairing.

4. The aircraft pylon fairing assembly according to claim 1 , wherein the peg has a conical or frustoconical shape.

5. The aircraft pylon fairing assembly according to claim 1 , wherein the fixing elements are countersunk screws, and
wherein all or part of each of said bores comprises an internal screw thread of a shape that complements a screw thread of said screws.

6. An aircraft comprising the aircraft pylon fairing assembly according to claim 1 .

7. A method for assembling the aircraft pylon fairing assembly according to claim 1 , the method comprising:
push-fitting the fairing onto the peg of the aircraft primary structure, then
positioning said yokes of the fairing around the four fittings of the aircraft primary structure in such a way as to align said bores of said yokes with said oblong openings of said fittings, said fittings each being inserted into one of said yokes, and then
inserting each of the four fixing elements into the bore of said yoke into which said fitting has been inserted and into the oblong opening in said fitting so as to hold the fairing in position on said aircraft primary structure in a statically determinate manner.

Assignees

• Airbus Operations Sas

Inventors

• Messina Paolo
• Robiglio Thomas
• Firmignac Thomas

Classifications

• B64D27/406

  Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links · CPC title

• B64F5/10

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

• B64C7/02

  Nacelles · CPC title

• B64D33/04

  of exhaust outlets or jet pipes · CPC title

• B64D29/06

  Attaching of nacelles, fairings or cowlings · CPC title