Method for achieving low porosity in composite laminates

Patent metadata

Field	Value
Publication number	US-2016257102-A1
Application number	US-201514636012-A
Country	US
Kind code	A1
Filing date	Mar 2, 2015
Priority date	Mar 2, 2015
Publication date	Sep 8, 2016
Grant date	—

Abstract

A method of manufacturing a composite laminate may include laying up bands of composite material in layers to form a composite layup. At least one layer may have at least one gap between an adjacent pair of bands. The gap may extend continuously along a lengthwise direction of the band. The gap in two or more of the layers may be fluidly interconnected and may form at least one breather path that opens to an exterior of the composite layup.

First claim

What is claimed is:

1 . A method of manufacturing a composite laminate, comprising:
laying up bands of composite material in layers to form a composite layup, at least one layer having at least one gap between an adjacent pair of bands and extending continuously along a lengthwise direction of the bands; and the gap in two or more of the layers being fluidly interconnected and forming at least one breather path that opens to an exterior of the composite layup.

2 . The method of claim 1 , wherein the step of laying up the composite material comprises:
forming gaps that are fluidly interconnected and that allow in-plane gas permeability and through-thickness gas permeability of the composite laminate.

3 . The method of claim 1 , wherein the step of laying up the composite material comprises:
laying up bands of composite material in a manner such that at least one of the layers includes at least one gap having a gap width of no greater than approximately 3 percent of a band width.

4 . The method of claim 1 , wherein the step of laying up the bands of composite material comprises:
laying up bands of composite material in a manner such that a gap width of each gap is no greater than approximately 0.030 inch.

5 . The method of claim 1 , wherein the step of laying up the bands of composite material comprises:
laying up bands of composite material using at least one of automated tape layup, automated fiber placement, filament winding, and manual layup.

6 . The method of claim 1 , wherein the step of laying up the bands of composite material comprises laying up tows of composite material using an automated fiber placement machine having at least one of the following configurations:
programmed to provide a gap between one or more pairs of courses, each course containing one or more tows of composite material; configured to lay up under-slit tape in a manner forming gaps between the under-slit tape; and having a fiber placement head modified to lay up a plurality of nominal width tows with a gap between the tows.

7 . The method of claim 1 , wherein the step of laying up the bands of composite material comprises:
laying up at least some of the bands as courses, each course including one or more tows arranged side-by-side.

8 . The method of claim 1 , further including:
applying compaction pressure to the composite layup; consolidating the composite layup in response to application of compaction pressure; and venting gasses through the breather path and out of the composite layup during consolidation of the composite layup.

9 . The method of claim 8 , wherein:
the step of applying compaction pressure is performed in an out-of-autoclave process.

10 . The method of claim 8 , wherein the step of applying compaction pressure comprises:
vacuum bagging the composite layup; and applying no more than 1 atmosphere of compaction pressure to the composite layup.

11 . The method of claim 8 , further including:
controlling compaction pressure on the composite layup in a manner that prevents closing off of the breather path prior to curing the composite layup.

12 . The method of claim 1 , further including:
applying heat to the composite layup; curing the composite layup in response to application of heat to form a cured composite laminate; and venting gasses through the breather path and out of the composite layup during curing of the composite layup.

13 . The method of claim 12 , further including:
controlling a temperature of the composite layup in such a manner as to prevent closing off of the breather path prior to completion of cure of the composite layup.

14 . The method of claim 13 , wherein:
a porosity of the cured composite laminate is less than approximately 2 percent.

15 . The method of claim 13 , wherein:
the cured composite laminate is one of the following: a solid laminate, a face sheet of a sandwich panel.

16 . The method of claim 1 , further including:
laying up bands of composite material in layers to form a composite layup, each layer having gaps between adjacent pairs of bands and extending continuously along a lengthwise direction of the band, the gaps being fluidly coupled and forming breather paths that open to an exterior of the composite laminate; applying heat and compaction pressure to the composite laminate; consolidating the composite laminate in response to application of compaction pressure; curing the composite laminate in response to application of heat; and controlling a temperature and compaction pressure of the composite layup in such a manner as to prevent closing off of the gaps and/or the breather paths during consolidation and prior to completion of cure of the composite layup.

17 . The method of claim 16 , further including:
allowing, after evacuation of gasses through the breather paths, resin and fibers to flow and fill the gaps during the curing of the composite layup to form a cured composite laminate; and the cured composite laminate having a porosity of less than approximately 2 percent.

18 . A method of manufacturing a composite laminate, comprising:
laying up tows of composite material using an automated fiber placement machine providing gaps with a gap width of between 0.005-0.030 inch between the tows of a composite layup, the gaps being fluidly connected to one another and forming an interconnected network of breather paths that each open to an exterior of the composite layup; and applying no more than 1 atmosphere of compaction pressure to the composite layup via a vacuum bag in an out-of-autoclave process.

19 . The method of claim 18 , wherein:
the composite material is a thermosetting composite material containing an epoxy-based resin.

20 . The method of claim 19 , further including:
maintaining a temperature of the epoxy-based resin below approximately 115 F; and preventing closing off of the breather paths prior to curing the composite layup.

Assignees

• Boeing Co

Inventors

• Butler Geoffrey A

Classifications

• B32B37/06

  characterised by the heating method · CPC title

• B32B2309/02

  Temperature · CPC title

• B32B37/1009 Primary

  using vacuum and fluid pressure · CPC title

• B32B2305/72

  Cured, e.g. vulcanised, cross-linked · CPC title

• B32B37/14 Primary

  characterised by the properties of the layers · CPC title