Systems and methods for forming composite materials

Patent metadata

Field	Value
Publication number	US-10099445-B2
Application number	US-201514711836-A
Country	US
Kind code	B2
Filing date	May 14, 2015
Priority date	May 14, 2015
Publication date	Oct 16, 2018
Grant date	Oct 16, 2018

Abstract

A composite membrane assembly may include a plurality of stacked composite plies. Each composite ply may include a main body of reinforced fibers connected together with a resin. The main body may include a base connected to an opposed boundary surface through opposed ends and opposed sides. At least one non-orthogonal cut is formed through a thickness of the main body from the base to the boundary surface. The non-orthogonal cut(s) is staggered with respect to at least one other non-orthogonal cut of an adjacent composite ply so that the non-orthogonal cut(s) does not form a contiguous linear cut with the other non-orthogonal cut(s) of the adjacent composite ply.

First claim

What is claimed is:

1. A composite ply configured to form a composite membrane assembly along with a plurality of other composite plies, the composite ply comprising:
a main body of reinforced fibers connected together with a resin, wherein the main body includes a base connected to an opposed boundary surface through opposed ends and opposed sides,
wherein at least one non-orthogonal cut relative to a length of the main body is formed through a thickness of the main body between the opposed ends from the base to the boundary surface, wherein the at least one non-orthogonal cut formed through the thickness of the main body is opposite from at least one other non-orthogonal cut formed through a thickness of an adjacent composite ply.

2. The composite ply of claim 1 , wherein the at least one non-orthogonal cut is staggered with respect to the at least one other non-orthogonal cut of the adjacent composite ply so that the at least one non-orthogonal cut does not form a contiguous linear cut with the at least one other non-orthogonal cut of the adjacent composite ply.

3. The composite ply of claim 1 , wherein the non-orthogonal cut forms a non-orthogonal angle with respect to a longitudinal plane of the composite ply, wherein the longitudinal plane extends between the opposed ends and is parallel with one or both of the base and the opposed boundary surface.

4. The composite ply of claim 3 , wherein the non-orthogonal angle is at least 5° and no more than 80°.

5. The composite ply of claim 3 , wherein the non-orthogonal angle is at least 10° and no more than 20°.

6. The composite ply of claim 1 , wherein the at least one non-orthogonal cut forms ply segments that are spliced together.

7. The composite ply of claim 1 , wherein the at least one non-orthogonal cut comprises a plurality of non-orthogonal cuts.

8. The composite ply of claim 7 , wherein the plurality of non-orthogonal cuts are formed at a same angle.

9. The composite ply of claim 7 , wherein at least two of the plurality of non-orthogonal cuts are formed at different angles.

10. The composite ply of claim 7 , wherein at least two of the plurality of non-orthogonal cuts are oriented in different directions.

11. A composite membrane assembly comprising:
a plurality of stacked composite plies, wherein each of the plurality of stacked composite plies comprises:
a main body of reinforced fibers connected together with a resin, wherein the main body includes a base connected to an opposed boundary surface through opposed ends and opposed sides,
wherein at least one non-orthogonal cut relative to a length of the main body is formed through a thickness of the main body between the opposed ends from the base to the boundary surface, and
wherein the at least one non-orthogonal cut is opposite from and staggered with respect to at least one other non-orthogonal cut formed through a thickness of an adjacent composite ply so that the at least one non-orthogonal cut does not form a contiguous linear cut with the at least one other non-orthogonal cut of the adjacent composite ply.

12. The composite ply of claim 11 , wherein the non-orthogonal cut forms a non-orthogonal angle with respect to a longitudinal plane of the composite ply, wherein the longitudinal plane extends between the opposed ends and is parallel with one or both of the base and the opposed boundary surface, and wherein the non-orthogonal angle is at least 10° and no more than 20°.

13. The composite ply of claim 11 , wherein the at least one non-orthogonal cut forms ply segments that are spliced together.

14. The composite ply of claim 11 , wherein the at least one non-orthogonal cut comprises a plurality of non-orthogonal cuts.

15. The composite ply of claim 14 , wherein the plurality of non-orthogonal cuts are formed at a same angle.

16. The composite ply of claim 14 , wherein at least two of the plurality of non-orthogonal cuts are formed at different angles.

17. The composite ply of claim 14 , wherein at least two of the plurality of non-orthogonal cuts are oriented in different directions.

18. A method of forming a composite membrane assembly, the method comprising:
forming a plurality of composite plies, wherein the plurality of composite plies is ten or more composite plies, wherein each of the plurality of composite plies includes a main body of reinforced fibers connected together with a resin, wherein the main body includes a base connected to an opposed boundary surface through opposed ends and opposed sides;
forming at least one non-orthogonal cut relative to a length of the main body in at least one of the plurality of composite plies, wherein the forming at least one non-orthogonal cut operation comprises (a) forming the at least one non-orthogonal cut through a thickness of the main body between the opposed ends from the base to the boundary surface, and (b) forming the at least one non-orthogonal cut through the thickness of the main body opposite from at least one other non-orthogonal cut formed through a thickness of an adjacent composite ply; and
stacking the composite plies together so that the non-orthogonal cuts of adjacent composite plies are staggered with respect to one another.

19. The method of claim 18 , wherein the forming the at least one non-orthogonal cut operation comprises forming the at least one non-orthogonal cut that is at least 10° and no more than 20° with respect to longitudinal axes of the plurality of composite plies.

20. The method of claim 18 , wherein the forming the at least one non-orthogonal cut operation comprises forming a plurality of non-orthogonal cuts in the plurality of composite plies.

Assignees

• Boeing Co

Inventors

• Kismarton Max

Classifications

• B32B2605/18

  Aircraft · CPC title

• B29C70/545

  Perforating, cutting or machining during or after moulding · CPC title

• B29C70/04

  comprising reinforcements only, e.g. self-reinforcing plastics · CPC title

• B32B37/18

  involving the assembly of discrete sheets or panels only · CPC title

• B32B2313/04

  Carbon · CPC title