Method and device for manufacturing a composite part of an aircraft

Patent metadata

Field	Value
Publication number	US-10071507-B2
Application number	US-201514700677-A
Country	US
Kind code	B2
Filing date	Apr 30, 2015
Priority date	Apr 30, 2014
Publication date	Sep 11, 2018
Grant date	Sep 11, 2018

Abstract

A method for manufacturing a composite part of an aircraft comprising the steps of placing a prepreg preform in a molding die between at least a molding die base part and a molding die upper part, debulking the air trapped in the prepreg, displacing the molding die upper part against the molding die base part in a direction perpendicular to the plane of the prepreg preform such that the molding die upper part presses the laminated perform until it reaches a blocking arrangement defining the position of the upper part relative to the base part for giving the prepreg preform the nominal thickness of the cured part, wherein said displacement is achieved by bolting the different parts of the molding die against each other, providing an elevated temperature to the preform such that it is cured.

First claim

The invention claimed is:

1. A method for manufacturing a composite part of an aircraft comprising the steps of:
placing a prepreg preform in a molding die between at least a molding die base part and a molding die upper part, said molding die having a shape of the composite part to be produced, the prepreg preform comprising at least one web and at least one flange,
debulking air trapped in the prepreg preform,
displacing the molding die upper part downwards against the molding die base part, in a direction perpendicular to a plane of the prepreg preform such that the molding die upper part presses the prepreg preform until it reaches a blocking arrangement defining a position of the upper part relative to the base part for giving the prepreg preform a web nominal thickness of a cured composite part, wherein said displacement is achieved by bolting the upper and lower parts of the molding die against each other,
displacing at least one molding die lateral part against at least one of the molding die base part and the molding die upper part, in a direction perpendicular to the at least one flange of the prepreg preform such that the at least one molding die lateral part presses said at least one flange and until the at least one molding die lateral reaches a blocking arrangement defining the position of the at least one molding die lateral for giving the at least one flange of the prepreg preform a flange nominal thickness of the cured composite part, wherein said displacement is achieved by bolting the at least one molding die lateral part with another part of the molding die,
curing the prepreg preform at an elevated temperature.

2. The method according to claim 1 , further comprising the steps of:
placing an upper tool element in contact with the molding die upper part, and
bolting said upper tool element to a part of the molding die such that the molding die upper part is displaced against the molding die base part.

3. The method according to claim 1 , further comprising the step of:
placing the at least one molding die lateral part such that the flange is located in-between the at least one molding die lateral part and the molding die upper part and the molding die base part.

4. The method according to claim 1 , wherein the molding die comprises a plurality of molding die lateral parts.

5. The method according to claim 4 , wherein the molding die lateral parts each comprise an inner wall having a recess for accommodating a flange of the prepreg preform, the contact between the inner wall and the molding die base part or the molding die upper part acting as a blocking arrangement of the displacement of the molding die lateral parts.

6. The method according to claim 4 , wherein the molding die lateral parts each comprise an upper recess for receiving the upper tool element, said upper recess defining the blocking means of the upper tool element.

7. The method according to claim 4 , wherein an upper tool element is bolted against each of the molding die lateral parts for displacing the molding die lateral parts.

8. The method according to claim 4 , wherein the molding die lateral parts are each bolted against the molding die base part.

9. The method according to claim 2 , wherein the at least one molding die lateral part is bolted against the upper tool element.

10. The method according to claim 1 , wherein at least one of the tooling element and the molding die comprise a heating system.

11. A method for manufacturing a composite part comprising:
placing a prepreg preform comprising a web in a molding die, the molding die having a shape of the composite part to be produced and comprising a plurality of metallic parts,
debulking air from the prepreg preform,
displacing a first part from the plurality of metallic parts in a first direction by bolting the first part against a second part from the plurality of metallic parts such that the first part presses the prepreg preform until the first part reaches a blocking arrangement defining a position of the first part relative to the second part for providing the prepreg preform with a first nominal thickness of a cured composite part, and,
displacing a third part from the plurality of metallic parts in a second direction by bolting the third part against a fourth part from the plurality of metallic parts such that the first part presses the prepreg preform until the third part reaches a blocking arrangement preform with a second nominal thickness of a cured composite part, wherein the second direction is perpendicular to the first direction,
curing the prepreg preform at an elevated temperature to form the cured composite part.

12. The method of claim 11 , wherein the prepreg is cured by a heating system that is integrated with the molding die.

13. The method of claim 11 , wherein the first part from the plurality of parts comprises an upper part, and wherein the second part comprises a base part.

14. The method of claim 13 , wherein the third part from the plurality of parts and the fourth part from the plurality of parts both comprise a lateral part.

Assignees

• Airbus Operations Sl

Inventors

• Garcia Martin Diego
• Cebolla Garrofe Pablo
• Chamorro Alonso Francisco Javier
• Dominguez Escauriaza Felix

Classifications

• B29K2105/0872

  Prepregs · CPC title

• Y10T428/2419

  Fold at edge · CPC title

• Y02T50/43

  Cross-Sectional Technologies · mapped topic

• B29K2063/00

  Use of {EP, i.e.} epoxy resins {or derivatives thereof}, as moulding material · CPC title

• B29L2031/3076

  Aircrafts (blades, propellers B29L2031/08) · CPC title