COMPOSITE ARTICLE HAVING REINFORCING FIBERS ORIENTED TO SUPPRESS OR DELAY PLY SPLITTING

• US 20090104398A1
• Filed: 12/19/2008
• Published: 04/23/2009
• Est. Priority Date: 03/31/2005
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Kismarton, Max U.
• Granted Patent: US 7,807,249 B2
• Time in Patent Office: Days
• US Class Current: 428/113
• CPC Class Codes: B29C 70/202 arranged in parallel planes or structures of fibres crossing at substantial angles, e.g. cross-moulding compound [XMC] B29C70/207 takes precedence
• CPC Class Codes: B29C 70/545 Perforating, cutting or machining during or after moulding
• CPC Class Codes: G01N 2203/0069 Fatigue, creep, strain-stress relations or elastic constants
• CPC Class Codes: Y10T 428/24124 Fibers
• CPC Class Codes: Y10T 428/249927 Fiber embedded in a metal matrix

Abstract

A composite article comprises a plurality of reinforcing fibers embedded in a matrix. The fibers have a fiber orientation of ±α with respect to an axis of loading, where α=2 to 8 degrees to suppress or delay ply splitting.

Claims

1. A composite article comprising a plurality of reinforcing fibers embedded in a matrix, the fibers having a fiber orientation of ±

α

with respect to an axis of loading, where α

=2 to 8 degrees for suppression or delay of ply splitting.

2. The article of claim 1, wherein the article is designed to be uni-axially loaded along the axis.

3. The article of claim 1, wherein α

=3 to 5 degrees.

4. The article of claim 1, wherein α

=3 degrees.

5. The article of claim 1, wherein at least some of the reinforcing fibers at ±

α

are machined.

6. The article of claim 1, further comprising drilled holes through at least some of the fibers.

7. The article of claim 6, further comprising fasteners extending through the drilled holes.

8. The article of claim 1, wherein the article includes a laminate of multiple plies of the fibers.

9. The article of claim 8, wherein the fibers provide strength in compression and tension, and wherein the article further comprises means for providing additional strength in at least one shear, transverse and bearing.

10. The article of claim 9, wherein the means includes at least one ply having fibers oriented at ±

β

, where β

is between 50 and 85 degrees.

11. The article of claim 10, wherein of the total fibers oriented at ±

α and

±

β

, only 20-30% of the total fibers are oriented at ±

β

.

12. A method of manufacturing a composite article comprising laying up plies of reinforcing fibers on a tool, wherein the fibers in at least some of the plies have an orientation of ±

α

with respect to a uni-axial load bearing direction of the article, where α

=2 to 8 degrees.

13. The method of claim 12, wherein each ply includes unidirectional fibers having a 0 degree orientation, wherein the plies are rotated to their correct angles of ±

α

while being dispensed on the tool, and wherein overhang is afterward cut off.

14. The method of claim 12, wherein cassettes having fibers oriented at ±

α

are dispensed on the tool.

15. The method of claim 14, wherein each cassette includes a first ply having fibers oriented at +α

and a second ply having fibers oriented at −

α

, the first and second plies bound together.

16. The method of claim 12, wherein the fibers in at least some of the plies have an orientation to boost shear, transverse and bearing strength.

17. The method of claim 16, wherein the fibers for boosting shear, transverse and bearing strength are oriented at ±

β

, where β

is between 50 and 85 degrees.

18. A method of manufacturing a composite article, comprising creating a laminate of reinforcing fibers embedded in a matrix, the fibers having an orientation of ±

α

with respect to a uni-axial load bearing direction of the article; and

machining at least some of the fibers, the fiber orientation suppressing or delaying ply splitting in the composite article when the article is loaded in tension or compression.

19. The method of claim 18, wherein at least some of the fibers are cut by drilling a hole into the laminate.

20. The method of claim 19, wherein α

=3 to 5 degrees.