Assembly for an aircraft, the assembly comprising a mast and a wing

Patent metadata

Field	Value
Publication number	US-11753177-B2
Application number	US-202017621467-A
Country	US
Kind code	B2
Filing date	Jun 9, 2020
Priority date	Jun 26, 2019
Publication date	Sep 12, 2023
Grant date	Sep 12, 2023

Abstract

An assembly having a pylon with an upper spar and two lateral scoops, a wing with a skin and a front spar, port-side/starboard-side front/rear brackets, each with a recess for a nut. The front spar has front/intermediate/rear pleats. Each front bracket is positioned against the front pleat and the intermediate pleat. Each rear bracket is positioned against the intermediate pleat and the skin. For each recess, the associated bracket has an open bore passing through it that opens into the recess. For each recess, the assembly has a fastening bolt having the nut and a screw of which the threaded shank passes through coaxial bores in the front pleat, in the skin, in the upper spar and in the associated lateral scoop, and the open bore, and is screwed into the nut, and of which the head bears against the lateral scoop.

First claim

The invention claimed is:

1. An assembly for an aircraft, said assembly comprising:
a pylon comprising
an upper spar,
a starboard-side lateral panel and a port-side lateral panel that extend vertically on either side of the upper spar, and
two lateral scoops, each scoop being fastened on an outside against a lateral panel and having a surface for contact with the upper spar,

a wing comprising
a skin,
a front spar extending on an inside of the skin,
a starboard-side front bracket,
a port-side front bracket,
wherein each front bracket has a front recess,
wherein, for each front recess, an associated front bracket has an open bore passing through the front bracket that opens into said recess,
wherein the front spar has a front pleat, an intermediate pleat and a rear pleat,
wherein the front pleat has a proximal end as one with a lower edge of the intermediate pleat and a distal end that extends forwards relative to the proximal end, and
wherein the rear pleat has a proximal end as one with an upper edge of the intermediate pleat and a distal end that extends rearwards relative to the proximal end,
wherein each front bracket is positioned in front of the intermediate pleat against the front pleat and the intermediate pleat, and
wherein each front bracket is fastened to said intermediate pleat,
wherein, for each front recess, each one of the front pleat, the skin, the upper spar and an associated lateral scoop has a bore passing therethrough that is coaxial with the open bore corresponding to the front recess,

wherein the wing also comprises a starboard-side rear bracket and a port-side rear bracket,
wherein each rear bracket has a rear recess, and
wherein each rear bracket is positioned behind the intermediate pleat against the intermediate pleat and the skin, and
wherein each rear bracket is fastened to said intermediate pleat,
wherein, for each rear recess, an associated rear bracket has an open bore passing therethrough that opens into said recess,
wherein, for each rear recess, each one of the skin, the upper spar and an associated lateral scoop has a bore passing therethrough that is coaxial with the open bore corresponding to the rear recess, and
wherein, for each of the front and rear recesses, the assembly also has a fastening bolt having a nut housed in said recess, and a screw, of which a threaded shank passes through the coaxial bores and the open bore, and is screwed into the nut, and of which the head bears against the associated lateral scoop.

2. The assembly according to claim 1 ,
wherein the wing has an interposed part that is positioned between the skin and the upper spar, and
wherein the interposed part is fastened to the skin, to the front pleat and to each front bracket by putting in place clamping bolts.

3. The assembly according to claim 2 , wherein, at each front bracket, the assembly is equipped with a shear pin that is formed as a cylinder in which is fitted the threaded shank of the fastening bolt corresponding to said front bracket and that extends through a bore in the lateral scoop and a bore in the interposed part, by passing through a bore in the upper spar.

4. The assembly according to claim 1 ,
wherein, for each open bore in a starboard-side bracket, the starboard-side lateral panel has a stiffener and, for each open bore in a port-side bracket, the port-side lateral panel has a stiffener,
wherein each lateral panel has a mid-plane,
wherein each stiffener has a mid-plane,
wherein an intersection between the mid-plane of each lateral panel and the mid-plane of each associated stiffener is a straight line,
wherein the surface for contact between the upper spar and the lateral scoop intersects an axis of each open bore at a point of intersection, and
wherein each point of intersection belongs to the straight line corresponding to said open bore.

5. An aircraft having at least one assembly according to claim 1 .

Assignees

• Airbus Operations Sas

Inventors

• Pautis Olivier
• Berjot Michael

Classifications

• B64D27/402

  comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant · CPC title

• B64C3/185 Primary

  Spars · CPC title

• B64D27/18

  within, or attached to, wings · CPC title

• B64C3/32

  specially adapted for mounting power plant · CPC title

• B64D27/40 Primary

  Arrangements for mounting power plants in aircraft · CPC title