Method of manufacturing a composite article

Patent metadata

Field	Value
Publication number	US-10369756-B2
Application number	US-201514834925-A
Country	US
Kind code	B2
Filing date	Aug 25, 2015
Priority date	Aug 25, 2015
Publication date	Aug 6, 2019
Grant date	Aug 6, 2019

Abstract

A system for manufacturing a composite article may include a resin-wetting control layer configured to be placed in contact with a composite ply of a composite preform. The resin-wetting control layer may be configured complementary to a ply surface of the composite ply.

First claim

What is claimed is:

1. A method of manufacturing a composite article, comprising the steps of:
complementarily mating a resin-wetting control layer with a side of a composite preform having a ply surface including a plurality of divots, the resin-wetting control layer including a surface texture comprising a plurality of nubs spaced apart from each other and configured complementary to the plurality of divots in the ply surface; and
preventing resin and gases from entering a space in at least some of the divots respectively occupied by the plurality of nubs of the resin-wetting control layer during curing of the composite preform.

2. The method of claim 1 , further including:
at least partially filling at least some of the divots with the resin-wetting control layer.

3. The method of claim 1 , wherein the step of complementarily mating the resin-wetting control layer with a side of a composite preform comprises:
complementarily mating the resin-wetting control layer with an outermost ply of at least one of a tool side and a caul side of the composite preform having a plurality of divots; and
the resin-wetting control layer being associated with at least one of a tool surface and a caul surface of a respective forming tool and caul plate.

4. The method of claim 1 , wherein the step of complementarily mating the resin-wetting control layer with a side of a composite preform comprises:
complementarily mating the resin-wetting control layer with an inner ply on a core side of the composite preform having a core; and
the resin-wetting control layer being associated with at least one of opposing core surfaces.

5. The method of claim 1 , further including:
distributing resin throughout at least one of a tool side, a caul side, and a core side of the composite preform after at least partially filling the divots with the resin-wetting control layer.

6. The method of claim 1 , wherein:
the plurality of nubs are complementary to the ply surface of a woven fabric of the composite preform.

7. The method of claim 6 , wherein the step of complementarily mating the resin-wetting control layer with a side of a composite preform comprises:
positioning the nubs in alignment with the divots of the ply surface.

8. The method of claim 6 , wherein:
at least one of the nubs is sized and configured to fill at least 50 percent of a divot in the woven fabric.

9. The method of claim 1 , wherein the resin-wetting control layer is a compliant layer being compliant along a through-the-thickness direction, the method further including:
compressing the compliant layer against the ply surface; and
at least partially filling at least some of the divots with localized portions of the compliant layer in response to compressing the compliant layer against the ply surface.

10. The method of claim 9 , further including:
infusing the composite preform with resin after compressing the compliant layer against the ply surface.

11. The method of claim 1 , wherein:
the composite preform is comprised of prepreg composite plies.

12. The method of claim 1 , wherein:
the resin-wetting control layer is integral with at least one of a tool surface of a forming tool, a caul surface of a caul plate, and a core surface of a core.

13. The method of claim 1 , further including:
forming an aircraft component.

14. The method of claim 9 , wherein:
the compliant layer comprises an elastomeric material.

15. The method of claim 14 , wherein:
the elastomeric material is chemically non-reactive with the resin.

16. The method of claim 14 , wherein:
the elastomeric material comprises a sheet of rubber, silicone, urethane, thermoplastic material, or thermosetting material.

17. The method of claim 9 , wherein:
the compliant layer has a layer thickness in a range of from 0.002 to 0.12 inch.

18. The method of claim 1 , wherein:
one or more of the nubs has a nub shape that is symmetrical about a central vertical axis along at least one direction of the nub.

19. The method of claim 1 , wherein:
one or more of the nubs has a nub shape that is non-symmetrical about a central vertical axis.

20. The method of claim 1 , wherein:
the nubs are formed at a nub spacing that is substantially equivalent to a divot spacing of the divots.

Assignees

• Boeing Co

Inventors

• Bernetich Karl R
• Kohlbrenner James W
• Wilenski Mark S

Classifications

• B29C70/546

  Measures for feeding or distributing the matrix material in the reinforcing structure · CPC title

• B29C70/44 Primary

  using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding · CPC title

• B29D7/01 Primary

  Films or sheets · CPC title

• B29C70/547

  using channels or porous distribution layers incorporated in or associated with the product · CPC title

• Y02T50/43

  Cross-Sectional Technologies · mapped topic