Methods for forming a composite blade stiffener and facilitating application of barely visible impact damage treatments

Patent metadata

Field	Value
Publication number	US-10377091-B2
Application number	US-201615340568-A
Country	US
Kind code	B2
Filing date	Nov 1, 2016
Priority date	Nov 1, 2016
Publication date	Aug 13, 2019
Grant date	Aug 13, 2019

Abstract

An example method for forming a flat composite charge into a composite blade stiffener includes cutting a flat composite charge along a cut line into a first piece and a second piece having an angle, positioning the first piece and the second piece of the flat composite charge on a forming mandrel about a tooling plunger, activating the tooling plunger to drive the first piece and the second piece into a cavity of the forming mandrel resulting in the first piece and the second piece folding at the cut line, withdrawing the tooling plunger from the cavity of the forming mandrel, compressing the forming mandrel to apply a lateral pressure to the first piece and the second piece folded into the cavity, and applying a vertical pressure to a first flange and a second flange of the first piece and the second piece, respectively, to form the composite blade stiffener.

First claim

What is claimed is:

1. A method comprising:
assembling a flat composite charge to a thickness in a predetermined orientation;
forming a cut line on the flat composite charge having opposing 45 degree beveled edges angled outward from the cut line;
positioning the flat composite charge centered about a tooling plunger such that the tooling plunger is aligned with the cut line; and
activating the tooling plunger to move downward and fold the flat composite charge at the cut line into a cavity of a forming mandrel, wherein at completion of movement of the tooling plunger and resulting folding of the flat composite charge, the opposing 45 degree beveled edges form a flat surface perpendicular to the cut line and form a first flange and a second flange connected to the flat surface.

2. The method of claim 1 , further comprising:
separating the forming mandrel as the tooling plunger moves downward.

3. The method of claim 1 , further comprising:
applying a reinforcement ply over the flat composite charge.

4. The method of claim 1 , further comprising:
loading a plate over the first flange and the second flange following withdrawal of the tooling plunger from the cavity of the forming mandrel; and
applying a vertical pressure to the first flange and the second flange using the plate.

5. The method of claim 1 , wherein the flat surface and the first flange and the second flange connected to the flat surface form a composite blade stiffener, and the method further comprises:
applying a barely visible impact damage (BVID) treatment to the composite blade stiffener; and
curing both the composite blade stiffener and the BVID treatment during a single curing process.

6. The method of claim 1 , further comprising:
heating the flat composite charge prior to activating the tooling plunger.

7. A method for forming a flat composite charge into a composite blade stiffener, comprising:
trimming a flat composite charge to a final design dimension;
cutting the flat composite charge along a cut line into a first piece and a second piece separated by edges having an angle;
applying a reinforcement ply over the first piece and the second piece to hold the first piece and the second piece together;
applying a ply of contact material to a forming mandrel;
positioning the first piece and the second piece of the flat composite charge on the ply of contact material on the forming mandrel about a tooling plunger such that the tooling plunger is aligned with the cut line;
activating the tooling plunger to contact the reinforcement ply and drive the first piece and the second piece of the flat composite charge into a cavity of the forming mandrel resulting in the first piece and the second piece folding at the cut line;
withdrawing the tooling plunger from the cavity of the forming mandrel;
compressing the forming mandrel to apply a lateral pressure to the first piece and the second piece folded into the cavity; and
applying a vertical pressure to a first flange and a second flange of the first piece and the second piece, respectively, to form the composite blade stiffener.

8. The method of claim 7 , wherein cutting the flat composite charge along the cut line comprises cutting the flat composite charge along a centerline.

9. The method of claim 7 , wherein cutting the flat composite charge along the cut line into the first piece and the second piece separated by the edges having the angle comprises cutting the edges to have about a 45 degree angle.

10. The method of claim 7 , wherein cutting the flat composite charge along the cut line into the first piece and the second piece separated by the edges having the angle comprises cutting the edges to have opposing 45 degree edges angled outward from the cut line.

11. The method of claim 7 , wherein applying the reinforcement ply over the first piece and the second piece to hold the first piece and the second piece together comprises applying a composite fabric ply.

12. The method of claim 7 , wherein applying the ply of contact material to the forming mandrel comprises applying a polyester peel ply.

13. The method of claim 7 , wherein applying the vertical pressure to the first flange and the second flange of the first piece and the second piece, respectively, to form the composite blade stiffener comprises applying the vertical pressure to form a T-shaped structure with a substantially flat top.

14. The method of claim 7 , further comprising:
loading a plate over the first flange and the second flange following withdrawal of the tooling plunger from the cavity of the forming mandrel; and
applying the vertical pressure to the first flange and the second flange using the plate.

15. The method of claim 7 , further comprising:
applying a barely visible impact damage (BVID) treatment to the composite blade stiffener; and
curing both the composite blade stiffener and the BVID treatment during a single curing process.

16. The method of claim 7 , further comprising:
heating the flat composite charge prior to activating the tooling plunger.

17. A method for forming a flat composite charge into a composite blade stiffener, comprising:
cutting the flat composite charge along a cut line into two pieces separated by edges having opposing 45 degree edges angled outward from the cut line;
positioning the flat composite charge on a forming mandrel about a tooling plunger such that the tooling plunger is aligned with the cut line;
activating the tooling plunger to drive the two pieces of the flat composite charge into a cavity of the forming mandrel resulting in the opposing 45 degree edges forming a flat surface perpendicular to the cut line and a first flange and a second flange connected to the flat surface;
withdrawing the tooling plunger from the cavity of the forming mandrel;
compressing the forming mandrel to apply a lateral pressure to the two pieces folded into the cavity;
applying a vertical pressure to the first flange and the second flange to form the composite blade stiffener;
applying a barely visible impact damage (BVID) treatment to the composite blade stiffener; and
curing both the composite blade stiffener and the BVID treatment during a single curing process.

18. The method of claim 17 , further comprising:
applying a reinforcement ply over the two pieces to hold the two pieces together.

19. The method of claim 17 , further comprising:
applying a ply of contact material to the forming mandrel; and
positioning the flat composite charge on the ply of contact material on the forming mandrel.

20. The method of claim 17 , further comprising:
loading a plate over the first flange and the second flange following withdrawal of the tooling plunger from the cavity of the forming mandrel; and
applying the vertical pressure to the first flange and the second flange using the plate.

Assignees

• Boeing Co

Inventors

• Carlson Lisa
• Pham Kanna M
• Sweetin Joseph
• Hanson Garrett C
• Reeves Jake Adam
• Chan Chilip
• Nguyen Kiet

Classifications

• B64F5/60

  Testing or inspecting aircraft components or systems · CPC title

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• B29C70/22

  oriented in at least two directions forming a two-dimensional [2D] structure · CPC title

• B29K2307/04

  Carbon · CPC title

• Y10T156/1051

  by folding · CPC title