Method for manufacturing a fiber reinforced synthetic composite structural element using fiber textile preforms

• US 7,175,795 B2
• Filed: 03/10/2003
• Issued: 02/13/2007
• Est. Priority Date: 03/08/2002
• Status: Expired due to Fees

• Current Assignee: Airbus Operations GmbH (Airbus SE), Fraunhofer Gesellschaft Zur Foerderung Der Angewandten Forsching E.V.
• Original Assignee: Airbus Deutschland GmbH (Airbus SE), Fraunhofer Gesellschaft Zur Foerderung Der Angewandten Forsching E.V.
• Inventors: Joern, Paul, Eberth, Ulrich
• Primary Examiner(s): Lee; Edmund H.
• Application Number:
  US10/385,289
• Publication Number:
  US 20030168775A1
• Time in Patent Office: 1,436 Days
• Field of Search: None
• US Class Current: 264/250
• CPC Class Codes: B29C 70/222 the structure being shaped to form a three dimensional configuration
• CPC Class Codes: B29C 70/30 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 Class Codes: B29C 70/34 and shaping or impregnating by compression , i.e. combined with compressing after the lay-up operation
• CPC Class Codes: B29C 70/386 Automated tape laying [ATL]
• CPC Class Codes: B29L 2031/005 for making window frames windows B29L2031/778
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

A fiber textile semi-finished material is fed directly and reformed onto a carrier and reforming tool, where it is fixed with a binder. The carrier has a contour matching the negative or positive shape of the final required geometry of a preform that is to be fabricated. The reformed semi-finished article fixed with the binder is removed from the carrier to provide the preform. Several preforms of different cross-sectional shapes are joined together, compacted to form a dense component having nearly the required finished contour, impregnated with a matrix system including a curable adhesive resin, and then cured under an elevated temperature and/or pressure. The result is a finished fiber reinforced composite structural element such as an aircraft window frame. This method is carried out on an apparatus including the rotating carrier and reforming tool, which may have a cylindrical and/or annular surface for receiving and reforming the material.

Claims

1. A method of manufacturing a structural element of fiber reinforced synthetic composite material, comprising the steps:

a) arranging respective fiber textile semi-finished materials respectively on plural carriers, which respectively have carrier contours that correspond to a positive or a negative of at least a portion of respective preform contours of respective preforms that are to be produced;

b) applying a binder respectively to said semi-finished materials, and fixing said semi-finished materials respectively with said binder to form thereof respective semi-finished articles;

c) removing said carriers from said semi-finished articles to form thereof said respective preforms having said respective preform contours, which respectively correspond to a positive or a negative of respective portions of a structural element contour of said structural element that is to be manufactured;

d) arranging said preforms together with one another, and compacting said preforms;

e) before, during or after said step d), impregnating said preforms with a matrix material comprising a curable resin; and

f) after said steps d) and e), curing said matrix material comprising said curable resin, to bond together, stiffen and harden said preforms, and thereby to form thereof said structural element having said structural element contour;

wherein each one of said preforms respectively has a plan shape surrounding an opening and has a cross-sectional shape including plural flanges that extend at an angle relative to each other, wherein said step d) comprises arranging said preforms so that respective adjacent ones of said flanges of neighboring ones of said preforms run parallel along one another so as to form thereof said structural element including a main frame body and a frame web protruding from said main frame body relative to a major plane of said structural element.

2. The method according to claim 1, wherein said curing is carried out under an elevated temperature and/or an elevated pressure.

3. The method according to claim 1, wherein said step e) is performed after said step d).

5. The method according to claim 1, further comprising a preliminary step of making said textile semi-finished materials by carrying out a textile production process, and wherein said step a) of arranging said semi-finished materials on said carriers is carried out directly following said textile production process, without intermediately arranging said semi-finished materials on temporary storage carriers.

6. The method according to claim 1, wherein said step a) further comprises positioning and holding said semi-finished materials on said carriers using fixing pins, clamp elements, grippers, or transport and clamping bands.

7. The method according to claim 1, wherein said step a) further comprises pressing said semi-finished materials against said carriers using counter-pressing elements.

8. The method according to claim 1, wherein said step a) further comprises reforming and draping said semi-finished materials onto said carriers so as to reorient as-yet unfixed fibers of said semi-finished materials into a desired orientation.

9. The method according to claim 1, wherein, in said step b), said binder is applied as a liquid, a paste, a powder, threads, a web or a sheet.

10. The method according to claim 9, wherein said step b) further comprises activating said binder using hot air heating, flame heating, infrared heating, induction heating, laser heating, contact heating, or microwave heating.

11. The method according to claim 1, wherein each one of said preforms is made up of a single textile layer of one of said textile semi-finished materials, and has a continuous complete oval shape or a shape of a segment of an oval.

12. The method according to claim 1, wherein each one of said preforms is made up of plural textile layers of at least one of said textile semi-finished materials, and has a continuous complete oval shape or a shape of a segment of an oval.

13. The method according to claim 1, wherein said structural element is a window frame for an aircraft window.

14. The method according to claim 1, wherein said preforms include first, second and third preforms, said first preform has two said flanges with a first said angle therebetween, said second preform has two said flanges with a second said angle therebetween, said third preform has two said flanges with a third said angle therebetween, said third angle is less than or equal to 180°

, said first, second and third angles together sum to 360°

, said two flanges of said third preform together with first ones of said flanges of said first and second preforms form said main frame body, and second ones of said flanges of said first and second preforms together form said frame web protruding from said main frame body.

15. The method according to claim 1, further comprising inserting a core member between adjacent ones of said flanges of said preforms.

16. The method according to claim 1, wherein:

said step a) of arranging the respective fiber textile semi-finished materials respectively on plural carriers comprises using a supply head to supply the respective fiber textile semi-finished materials,

said plural carriers comprises a carrier and reforming tool having said carrier contours comprising at least a cylindrical receiving surface or an annular receiving surface that receives the respective semi-finished material thereon, and

said step a) further comprises rotating at least one of said supply head and said carrier and reforming tool relative to the other so as to lay the respective semi-finished material from said supply head onto said respective receiving surface of said carrier and reforming tool.

17. The method according to claim 16, wherein said carrier and reforming tool comprises a drum having said cylindrical receiving surface and a bounding flange disc secured on a side of said drum, and wherein said step a) includes rotating said drum.

18. The method according to claim 17, wherein said bounding flange disc has a larger diameter than said drum, protrudes radially outwardly beyond said cylindrical receiving surface, and has said annular receiving surface on a side face thereof, and wherein said step a) includes laying at least one of said textile semi-finished materials on said annular receiving surface on said side face of said bounding flange disc.

19. The method according to claim 18, wherein said annular receiving surface is arranged at a disc angle relative to said cylindrical receiving surface, wherein said disc angle corresponds to a respective said angle formed between two of said flanges of the respective preform that is produced in said step c).

20. The method according to claim 16, wherein said step c) of arranging the respective fiber textile semi-finished materials further comprises using a counter-pressing element that cooperates with said cylindrical receiving surface and/or said annular receiving surface to position and press the respective semi-finished material thereagainst.

21. The method according to claim 20, wherein said counter-pressing element is equipped with a heating or cooling device, and further comprising heating or cooling the respective semi-finished material using said heating or cooling device.

22. The method according to claim 16, wherein said carrier and reforming tool comprises a disc having said annular receiving surface on a side face thereof, and wherein said step a) includes rotating said disc.

23. The method according to claim 22, wherein said annular receiving surface has two annular surface portions that extend at a surface angle relative to each other, wherein said surface angle corresponds to a respective said angle formed between two of said flanges of the respective preform that is produced in said step c).

24. The method according to claim 16, further comprising positioning said supply head relative to said carrier and reforming tool so as to achieve a defined positioning of the respective semi-finished material on said respective receiving surface.

25. The method according to claim 16, wherein said carrier and reforming tool comprises a circular ring-shaped first die part including said annular receiving surface on a face surface thereof and said cylindrical receiving surface on an inner circumferential surface thereof, a second die part, and a draping tool, and further comprising moving said second die part selectively adjacent to and away from said first die part, and moving said draping tool along said first die part after moving away said second die part so as to drape and reform a portion of the semi-finished material along said cylindrical receiving surface.

26. The method according to claim 1, wherein said plan shape is a curvilinear plan shape, and said opening is a curvilinear opening, and said step a) includes rotating said carriers while arranging said semi-finished materials thereon.

27. The method according to claim 1, wherein said plan shape is an oval plan shape, and said opening is an oval opening, and said step a) includes rotating said carriers while arranging said semi-finished materials thereon.

28. The method according to claim 1, wherein said frame web protrudes from said main frame body substantially perpendicularly relative to said major plane of said structural element.

29. The method according to claim 1, wherein said arranging and said compacting of said preforms in said step d) forms said preforms into an intermediate component that is highly densified and has a contour nearly corresponding to said structural element contour in a finished condition of said structural element, and wherein said step e) of impregnating said preforms is performed after said step d) of arranging and compacting said preforms.

4. The method according to clam 1, wherein said arranging and said compacting of said preforms forms said preforms into an intermediate component that is highly densified and has a contour nearly corresponding to said structural element contour in a finished condition of said structural element.