Method and device for producing contoured composite laminate stiffeners with reduced wrinkling

Patent metadata

Field	Value
Publication number	US-10399283-B2
Application number	US-201514876475-A
Country	US
Kind code	B2
Filing date	Oct 6, 2015
Priority date	Oct 6, 2015
Publication date	Sep 3, 2019
Grant date	Sep 3, 2019

Abstract

A contoured composite laminate stiffener is fabricated by assembling a substantially flat composite laminate charge and forming the charge into a substantially straight stiffener having a desired cross sectional shape. A contour is formed in the stiffener which has an inside radius and an outside radius. Ply wrinkling is substantially eliminated by reducing compression strain on the inside radius as the stiffener as being contoured.

First claim

What is claimed is:

1. A method of fabricating a contoured composite laminate stiffener, the method comprising:
assembling a composite laminate charge comprising a substantially flat shape;
forming the composite laminate charge into a stiffener comprising a flange connected to a web connected to a cap comprising a substantially straight shape comprising a desired cross sectional shape;
subsequently using a compactor and forming a contour comprising an inside radius and an outside radius into the stiffener;
spacing slits along a length of an outside edge of the compactor, each slit in the slits cut, substantially perpendicular to the length, through the flange and into an outside edge of the web of the compactor;
inhibiting a compression strain, resulting from forming the contour in the stiffener, on the inside radius of the stiffener during the forming of the contour, via spreading apart the slits during the forming the contour; and
subsequently, curing the stiffener comprising the contour.

2. The method of claim 1 , wherein assembling the composite laminate charge includes laying up prepreg ply segments each having a 0° fiber orientation.

3. The method of claim 2 , wherein laying up the prepreg ply segments includes overlapping the prepreg ply segments.

4. The method of claim 1 , wherein forming the contour in the stiffener includes:
placing the stiffener comprising the substantially straight shape on a curved tool surface,
placing the compactor on the stiffener comprising the substantially straight shape, and
using the compactor to compact the stiffener comprising the substantially straight shape against the curved tool surface.

5. The method of claim 4 , wherein inhibiting the compression strain on the inside radius includes increasing tension strain on the outside radius of the compactor.

6. The method of claim 5 , wherein spreading of the slits enhances elongation and tension strain on the outside radius of the compactor.

7. The method of claim 4 , wherein inhibiting the compression strain on the inside radius of the stiffener is performed by using the compactor to apply tension to outer extremities of the stiffener.

8. A method of fabricating a contoured composite laminate hat stiffener, the method comprising:
forming a substantially flat composite laminate charge into a stiffener comprising a hat-shaped cross section comprising a flange connected to a web connected to a substantially straight cap portion;
forming, using a compactor, a contour comprising an outside radius, in the stiffener;
spacing slits along a length of an outside edge of the compactor, each slit in the slits cut, substantially perpendicular to the length, through the flange and into an outside edge of the web of the compactor;
increasing, as the compactor is forming the contour in the stiffener, a tension strain at the outside radius of the compactor via spreading apart the slits; and
subsequently, curing the stiffener comprising the contour.

9. The method of claim 8 , further comprising:
the contour comprising an inside radius and the outside radius, and
using the compactor to form the contour includes compacting the stiffener against a tool comprising a curved tool surface substantially matching the inside radius.

10. The method of claim 9 , further comprising inhibiting, by producing the tension strain at the outside radius reducing compression strain, due to forming the contour, in an area of the inside radius of the stiffener, out-of-plane buckling of the stiffener in the area of the inside radius of the stiffener.

11. The method of claim 10 , further comprising producing the tension strain comprising the slits in the compactor allowing the outside radius of the compactor to extend as the compactor forms the stiffener against the curved tool surface.

12. The method of claim 10 , further comprising:
curing the stiffener, and
wherein producing the tension strain is continued throughout curing of the stiffener.

13. The method of claim 10 , wherein producing the tension strain comprises elongating the outside radius of the stiffener.

14. A method of fabricating a contoured composite laminate hat stiffener, the method comprising:
forming a substantially flat composite laminate charge into a stiffener comprising a cross section comprising a flange connected to a web connected to a substantially straight cap portion;
forming, using a compactor, a contour, comprising an outside radius, in the stiffener, such that the compactor comprises a contour comprising a curvature greater than a curvature of a tool surface receiving the compactor;
spacing slits along a length of an inner radius of the compactor, each slit in the slits cut substantially perpendicular into an edge of the inner radius of the compactor;
applying a tension strain to the outside radius of the stiffener via increasing a tension strain in an inner radius of the compactor, as the compactor forms the contour in the stiffener, via spreading apart the slits spaced along edge of the inner radius of the compactor; and
subsequently, curing the stiffener comprising the contour.

Assignees

• Boeing Co

Inventors

• Offensend Christopher David
• Kajita Kirk Ben
• Davis Kieran P
• Soja Matthew R

Classifications

• B64F5/10

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title

• B64C2001/0072

  from composite materials · CPC title

• B64C3/18

  Spars; Ribs; Stringers · CPC title

• B29L2031/3082

  Fuselages · CPC title

• B29L2031/001

  Profiled members, e.g. beams, sections · CPC title