Integral composite bushing system and method

Patent metadata

Field	Value
Publication number	US-9682519-B2
Application number	US-201414341083-A
Country	US
Kind code	B2
Filing date	Jul 25, 2014
Priority date	Jul 26, 2013
Publication date	Jun 20, 2017
Grant date	Jun 20, 2017

Abstract

A composite bearing comprising a densified portion, wherein a hole location is positioned at the approximate center of said densified portion; and a plurality of filament tendrils, wherein the plurality of filament tendrils are configured to wrap around the hole location to create a “U” shape.

First claim

What is claimed is:

1. A composite aircraft structure comprising:
an aircraft body portion having a first density;
a disk-shaped densified portion comprising ceramic, metal, high-strength plastic, or a combination thereof,
wherein the disk-shaped densified portion includes a hole positioned at an approximate center of said disk-shaped densified portion,
wherein the densified portion has a density that is greater than said first density and is configured to resist a load imparted via said hole; and

a plurality of filament tendrils,
wherein the plurality of filament tendrils is configured to wrap around at least a portion of said hole to form a form a “U” shape,
wherein at least one of said plurality of filament tendrils comprises a carbon fiber material, a para-aramid synthetic fiber material, or a fiberglass material,
wherein said plurality of filament tendrils is configured to direct stress away from said hole and into the aircraft body portion.

2. The composite aircraft structure of claim 1 , wherein said densified portion's diameter is approximately 1.5 to 3 times said hole's diameter.

3. A composite bearing for use in a composite structure, the composite bearing comprising:
a densified portion to resist a load imparted upon the composite bearing at a hole positioned at an approximate center of said densified portion; and
a plurality of filament tendrils encircling at least a portion of said hole,
wherein the plurality of filament tendrils are configured to direct stress away from the hole and into the composite structure.

4. The composite bearing of claim 3 , wherein the plurality of filament tendrils form a “U” shape around said at least a portion of said hole.

5. The composite bearing of claim 3 , wherein the composite bearing is disk-shaped.

6. The composite bearing of claim 3 , wherein at least one of said plurality of filament tendrils comprises a carbon fiber material.

7. The composite bearing of claim 3 , wherein at least one of said plurality of filament tendrils comprises a para-aramid synthetic fiber material.

8. The composite bearing of claim 3 , wherein at least one of said plurality of filament tendrils comprises a fiberglass material.

9. The composite bearing of claim 3 , wherein said densified portion's diameter is approximately 1.5 to 3 times said hole's diameter.

10. The composite bearing of claim 3 , wherein said densified portion comprises ceramic, metal, high-strength plastic, or a combination thereof.

11. A composite structure comprising:
a composite material body portion;
a densified portion to resist a load imparted via a hole positioned at an approximate center of said densified portion; and
a plurality of filament tendrils wrapped around at least a portion of said hole to direct stress away from said hole and into the composite material body portion, wherein at least a portion of each of said plurality of filament tendrils is embedded within said composite material body portion.

12. The composite structure of claim 11 , wherein the plurality of filament tendrils form a “U” shape around said at least a portion of said hole.

13. The composite structure of claim 11 , wherein the densified portion is disk-shaped.

14. The composite structure of claim 11 , wherein at least one of said plurality of filament tendrils comprises a carbon fiber material.

15. The composite structure of claim 11 , wherein at least one of said plurality of filament tendrils comprises a para-aramid synthetic fiber material.

16. The composite structure of claim 11 , wherein at least one of said plurality of filament tendrils comprises a fiberglass material.

17. The composite structure of claim 11 , wherein said densified portion's diameter is approximately 1.5 to 3 times said hole's diameter.

18. The composite structure of claim 11 , wherein said densified portion comprises ceramic, metal, high-strength plastic, or a combination thereof.

19. The composite bearing of claim 3 , wherein the densified portion is embedded within the composite structure.

20. The composite structure of claim 11 , wherein the densified portion is embedded within the composite material body portion.

Assignees

• Aurora Flight Sciences Corp

Inventors

• Pollett Brandon

Classifications

• B29C70/30

  Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core · CPC title

• B29C70/887 Primary

  locally reinforced, e.g. by fillers (filler concentrated near the surface B29C70/64) · CPC title

• B64C2001/0072

  from composite materials · CPC title

• B29L2031/737

  Articles provided with holes, e.g. grids, sieves (nets B29L2028/00) · CPC title

• Y10T403/74

  Cross-Sectional Technologies · mapped topic