Radius filler and method of manufacturing same

Patent metadata

Field	Value
Publication number	US-9827710-B2
Application number	US-201414171779-A
Country	US
Kind code	B2
Filing date	Feb 4, 2014
Priority date	Feb 4, 2014
Publication date	Nov 28, 2017
Grant date	Nov 28, 2017

Abstract

A method of manufacturing a radius filler may include providing a plurality of fibers, braiding the plurality of fibers into a braided preform, shaping the braided preform into a braided radius filler, and cutting the braided radius filler to a desired length.

First claim

What is claimed is:

1. A method of manufacturing a consolidated radius filler, the method comprising the steps of:
providing a plurality of fibers including resin;
braiding the plurality of fibers to form a braided preform;
shaping the braided preform into a braided radius filler having opposing radius filler side surfaces, wherein the fibers of the braided radius filler include resin either before or after the braiding;
mounting the braided radius filler in a mandrel die cavity of a mandrel forming system having a mandrel forming base;
injecting a ceramic matrix into the mandrel die cavity containing the braided radius filler;
hardening the injected ceramic matrix; and
heating the hardened ceramic matrix to cause expansion of the hardened matrix against the radius filler side surfaces to form the consolidated radius filler.

2. The method of claim 1 , wherein the step of shaping the braided preform includes:
shaping the braided radius filler into a substantially triangular cross-sectional shape having the opposing radius filler side surfaces and a radius filler base surface, the radius filler side surfaces each being concave, and the radius filler base surface being substantially planar.

3. The method of claim 1 , wherein the plurality of provided fibers comprise prepreg composite tape containing the resin.

4. The method of claim 3 , wherein the step of shaping the braided preform into the braided radius filler includes:
heating the prepreg composite tape of the braided preform;
softening and intermingling the resin in the prepreg composite tape in response to the heating; and
curing the resin after forming the consolidated radius filler.

5. The method of claim 1 , wherein the step of braiding the plurality of fibers comprises:
braiding the plurality of fibers into a braided preform having a triangular cross-sectional shape approximating a final shape of the braided radius filler.

6. The method of claim 1 , wherein the step of braiding the plurality of fibers comprises:
braiding the plurality of fibers around an inner core to form the braided preform comprising the plurality of fibers and the inner core.

7. The method of claim 6 , wherein:
the inner core is formed of a material functioning as a conduit for communication signals or data signals.

8. The method of claim 6 , wherein:
the inner core has one of a generally cylindrical shape and a generally triangular shape.

9. The method of claim 1 , wherein:
the braided preform has a non-hollow cross-section.

10. The method of claim 1 , wherein the step of providing the plurality of fibers comprises:
providing the plurality of fibers as dry fibers; and
wetting the dry fibers in a resin bath of the resin during at least one of:
prior to braiding into the braided preform; and
following braiding into the braided preform.

11. The method of claim 1 , further including:
internally braiding one or more heater wires into the braided preform during the braiding of the plurality of fibers; and
resistively heating the heater wires to soften the resin during at least one of:
prior to consolidation of the braided radius filler; and
during consolidation of the braided radius filler.

12. The method of claim 1 , further comprising the step of:
clamping the mandrel forming system within a press system prior to the expansion of the hardened ceramic matrix.

13. The method of claim 12 , wherein the ceramic matrix is provided as one of a slurry and a semi-liquid composition.

14. The method of claim 12 , wherein the step of clamping the mandrel forming system within the press system comprises:
clamping the mandrel forming system between a movable upper press and a press base of the press system.

15. The method of claim 12 , further comprising:
applying heat to the mandrel forming system for heating the ceramic matrix by placing the press system in an autoclave or an oven.

16. The method of claim 1 , further comprising the steps of:
removing the braided radius filler from the mandrel die cavity;
applying a solvent to the hardened ceramic matrix; and
solubilizing the hardened ceramic matrix to remove the hardened ceramic matrix from the mandrel die cavity.

17. The method of claim 1 , wherein the step of injecting the ceramic matrix into the mandrel die cavity comprises:
injecting the ceramic matrix into one or more ports in the mandrel die until excess ceramic matrix starts flowing out of at least one additional port in the mandrel die.

18. The method of claim 17 , further comprising:
curing the consolidated radius filler.

19. The method of claim 18 , further comprising:
cutting the consolidated radius filler to a desired length after curing.

20. The method of claim 17 , further comprising:
closing off the one or more ports and the at least one additional port with plugs after the ceramic matrix starts flowing out of the at least one additional port.

Assignees

• Boeing Co

Inventors

• Rossi Angelo
• Marcoe Jeffery L
• Matsen Marc R
• Bartel Aaron W

Classifications

• B29B11/16

  comprising fillers or reinforcement {(non-woven fabrics per se D04H1/00, D04H3/00)} · CPC title

• B29C70/504

  using rollers or pressure bands (for corrugating B29C53/22) · CPC title

• B29C33/448

  destructible (B29C33/52 takes precedence; in particular used in injection moulding B29C45/4457) · CPC title

• B29C65/62

  Stitching · CPC title

• B29D99/0007

  having a variable cross-section · CPC title