LAY-UP ARRANGEMENT AND STRUCTURAL ARRANGEMENT AND METHOD FOR PRODUCING A COMPONENT FOR AEROSPACE

• US 20090269596A1
• Filed: 07/10/2007
• Published: 10/29/2009
• Est. Priority Date: 08/01/2006
• Status: Active Grant

• Current Assignee: Airbus Operations GmbH (Airbus SE)
• Original Assignee: Airbus Operations GmbH (Airbus SE)
• Inventors: Jung, Manuel, Bleck, Thorsten, Rocker, Olaf
• Granted Patent: US 8,709,188 B2
• Time in Patent Office: Days
• US Class Current: 428/457
• CPC Class Codes: B29C 70/386 Automated tape laying [ATL]
• CPC Class Codes: B29C 70/545 Perforating, cutting or machining during or after moulding
• CPC Class Codes: B29C 70/885 with incorporated metallic wires, nets, films or plates as lost heating elements B29C35/0272, B29C61/0625
• CPC Class Codes: B32B 27/04 as impregnant, bonding, or embedding substance not used
• CPC Class Codes: B32B 5/28 impregnated with or embedded in a plastic substance not used
• CPC Class Codes: D04H 13/00 Other non-woven fabrics
• CPC Class Codes: D04H 3/004 Glass yarns or filaments
• CPC Class Codes: D04H 3/04 in rectilinear paths, e.g. crossing at right angles
• CPC Class Codes: D04H 3/045 for net manufacturing
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y10T 156/10 Methods of surface bonding and/or assembly therefor
• CPC Class Codes: Y10T 156/1348 Work traversing type
• CPC Class Codes: Y10T 156/1788 Work traversing type and/or means applying work to wall or static structure
• CPC Class Codes: Y10T 156/1795 Implement carried web supply
• CPC Class Codes: Y10T 428/31678 Of metal

Abstract

The invention provides a method for producing a component (37) for aerospace, with the following method steps: supplying a lay-up arrangement (1) to be laid by means of a tape-laying machine (25), with a glass-fibre lay-up (8), which is preimpregnated with a resin matrix (10), and/or supplying a structural arrangement (12) to be laid by means of a tape-laying machine (25), with a structure (16) which is made of metal and is preimpregnated with a resin matrix (18), laying the lay-up and/or structural arrangement (1; 12) on a laminating apparatus (23) by means of a tape-laying machine (25), and curing the lay-up and/or structural arrangement (1; 12) and therefore forming the component (37).

Claims

1. Structural arrangement (12) to be laid by means of a tape-laying machine (28), characterized in that the structural arrangement (12) comprises a structure (16) which is made of metal and is preimpregnated with a resin matrix (18).

2. Structural arrangement according to claim 1, characterized in that the metal contains copper, bronze and/or aluminium.

3. Structural arrangement according to claim 1 or 2, characterized in that the structural arrangement (12) is formed in a sheetlike manner, in particular in the form of web material (35).

4. Structural arrangement according to at least one of the preceding claims, characterized in that the structure (16) is formed as a net, in particular with diamond-shaped and/or rectangular and/or honeycomb-shaped recesses (17), in particular along its thickness.

7. Method for producing a component (37) for aerospace, with the following method steps:

supplying a structural arrangement (12) according to at least one of the preceding claims,

laying the structural arrangement (1;

12) on a laminating apparatus (23) by means of a tape-laying machine (25), and

curing the structural arrangement (1;

12) to form the component (37).

8. Method according to claim 7, characterized in that the tape-laying machine (28) is moved along a plurality of axes (26, 29, 32), in particular by means of computer numerical control.

9. Method according to either of claims 7 and 8, characterized in that the structural arrangement (1;

12) is laid along different directions (26, 29, 32) with respect to the laminating apparatus (23).

10. Method according to one of claims 7 to 9, characterized in that a plurality of lay-up and/or structural arrangements (1;

12) are laid in layers (39;

42) one above another.

11. Method according to one of claims 7 to 10, characterized in that at least one layer (40, 41) of CFRP prepreg material (36) is laid on, between and/or below the lay-up and/or structural arrangement (1;

12), in particular by means of the tape-laying machine (25) and/or a further tape-laying machine.

12. Method according to one of claims 7 to 11, characterized in that the lay-up arrangement (1) is laid on a component, in particular made of aluminium, by means of the tape-layer (25).

13. Method according to one of claims 7 to 12, characterized in that the lay-up and/or structural arrangement (1;

12) and/or the CFRP prepreg material (36) is/are supplied to the tape-laying machine (25) by means of a feeding device (34), as required.

14. Method according to one of claims 7 to 13, characterized in that the lay-up and/or structural arrangement (1;

12) is supplied as a coiled web material (3;

14).

5. Structural arrangement according at least one of the pre-ceding claims, characterized in that, on at least one of its sides, the structure (16) is provided with a backing material (20), in particular a backing paper, in particular detachable from the structure (16), for supporting the structure (16).

6. Structural arrangement according to claim 5, characterized in that, on a further side opposite the one side, the structure (16) is provided with a protective film (21), in particular detachable from the structure (16), for protecting the structure (16).