Method for manufacturing at least one portion of a box structure of an aircraft comprising a forming step, and a central wingbox thus obtained

Patent metadata

Field	Value
Publication number	US-12269576-B2
Application number	US-202318164119-A
Country	US
Kind code	B2
Filing date	Feb 3, 2023
Priority date	Feb 22, 2022
Publication date	Apr 8, 2025
Grant date	Apr 8, 2025

Abstract

A method for manufacturing at least a portion of a box structure obtained from an outer skin and a plurality of sections each having a joining face in contact with the outer skin. The method comprises a step of positioning the sections on a mold, a step of obtaining a flat fiber preform having a thickness substantially equal to the outer skin, a step of placing a central portion of the fiber preform on the sections positioned on a first face of the mold and a step of forming a lateral extension of the fiber preform to press the fiber preform against a forming surface. A central wingbox obtained by the method is provided and a forming tool for carrying out the method.

First claim

The invention claimed is:

1. A method for manufacturing at least one portion of a box structure comprising at least one stiffened main wall extended by at least one of at least one flange or at least one stiffened secondary wall, said portion of the box structure being obtained from an outer skin made of a composite material and from a plurality of sections made of a composite material, each of the plurality of sections having a joining face in contact with the outer skin, said method comprising:
a step of obtaining the sections,
a step of positioning said sections on a mold comprising at least a first face on which the sections are positioned,
a step of obtaining a flat fiber preform having a thickness substantially equal to the outer skin,
a step of placing a central portion of the fiber preform on the sections positioned on the first face of the mold, the fiber preform having at least one lateral extension extending the central portion,
a step of forming the lateral extension,
a step of placing at least one polymerization covering, at least one polymerization step, and
at least one demolding step;
wherein during the forming step, the main portion is kept pressed against the joining faces of the sections positioned on the first face of the mold by at least one main jaw, and
wherein the lateral extension of the fiber preform is folded against a forming surface, substantially perpendicular to the first face of the mold, by means of at least one secondary jaw configured to move in translation parallel to the forming surface.

2. The method as claimed in claim 1 , wherein during the forming step, the lateral extension of the fiber preform is held between a pair of secondary jaws configured to move in translation in at least one direction parallel to the forming surface.

3. The method as claimed in claim 1 , wherein the fiber preform includes right- and left-hand lateral extensions positioned on both sides of the main portion.

4. The method as claimed in claim 1 , wherein the forming surface corresponds to joining faces of sections positioned on a side face of the mold.

5. A method for manufacturing a central wingbox comprising a top panel, a bottom panel, a front spar and a rear spar, wherein the central wingbox comprises:
a first portion comprising the top panel, the front and rear spars, and the first and second flanges, the first flange being connected to the front spar, approximately perpendicular to said front spar and extending said front spar in a direction opposite the rear spar, the second flange being connected to the rear spar, approximately perpendicular to said rear spar and extending said rear spar in a direction opposite the front spar, said first portion being obtained using the manufacturing method as claimed in claim 1 ,
a second portion comprising a stiffened panel shaped like the bottom panel and including first and second extensions arranged on both sides of the bottom panel, the first extension being connected to the first flange, the second extension being connected to the second flange.

6. A central wingbox obtained using the manufacturing method as claimed in claim 5 .

7. A forming tool for implementing the manufacturing method as claimed in claim 1 for at least one portion of a box structure comprising at least one stiffened main wall extended by at least one of at least one flange or at least one stiffened secondary wall, wherein the forming tool comprises:
a mold having at least a first face shaped like the stiffened main wall and configured to bear sections,
at least one main jaw comprising a contact face substantially parallel to the first face of the mold, configured to hold a main portion of a fiber preform pressed against sections positioned on the first face of the mold,
at least one secondary jaw configured to fold a lateral extension of the fiber preform against a forming surface and to move in at least one direction parallel to the forming surface.

8. A forming tool as claimed in claim 7 , wherein the forming tool comprises at least one pair of upstream and downstream secondary jaws each configured to hold a lateral extension of the fiber preform and to move in a direction parallel to the forming surface.

9. The forming tool as claimed in claim 8 , wherein each upstream and downstream secondary jaw comprises a first contact face, the first contact faces of the upstream and downstream secondary jaws, being configured to be arranged on both sides of the fiber preform, substantially parallel to each other for each pair and perpendicular to a face of the mold against which the lateral extension held by the upstream and downstream secondary jaws is to be positioned.

10. The tool as claimed in claim 9 , wherein each upstream secondary jaw comprises a second contact face oriented towards the mold, substantially parallel to the face of the mold against which the lateral extension held by the upstream and downstream secondary jaws is to be positioned, in operation the second contact face being spaced apart from the sections positioned on said face of the mold by a distance substantially equal to the thickness of the fiber preform.

11. The forming tool as claimed in claim 10 , wherein each downstream secondary jaw has at least one moving belt on the first contact face thereof.

12. The forming tool as claimed in claim 10 , wherein each upstream secondary jaw has at least one moving belt on at least one of the first or second contact face thereof.

13. The forming tool as claimed in claim 12 , wherein each upstream secondary jaw has a moving belt stretched between at least three pivoting rollers arranged such that the moving belt moves on the first and second contact faces.

14. The forming tool as claimed in claim 8 , wherein the tool comprises a first pair of secondary jaws configured to cooperate with a right-hand lateral extension of the fiber preform and a second pair of secondary jaws configured to cooperate with a left-hand lateral extension of the fiber preform.

Assignees

• Airbus Operations Sas
• Airbus Operations Ltd
• Airbus Operations Sl

Inventors

• Duthille Bertrand
• Price Jonathan
• Pridie Jago
• Menendez Martin Jose Manuel

Classifications

• B29D99/0014 Primary

  provided with ridges or ribs, e.g. joined ribs · CPC title

• B29C70/30

  Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core · CPC title

• Y02T50/40

  Weight reduction · CPC title

• B29C70/541

  Positioning reinforcements in a mould, e.g. using clamping means for the reinforcement (positioning inserts in moulds B29C33/12; lay-up on a mould B29C70/30) · CPC title

• B29C70/461

  Rigid movable compressing mould parts acting independently from opening or closing action of the main mould · CPC title