Composite panels

Patent metadata

Field	Value
Publication number	US-12325178-B2
Application number	US-202217689088-A
Country	US
Kind code	B2
Filing date	Mar 8, 2022
Priority date	Feb 19, 2020
Publication date	Jun 10, 2025
Grant date	Jun 10, 2025

Abstract

A method of forming a composite panel includes providing an initial composite material, heating the initial composite material, molding the initial composite material to form a preliminary composite panel having a main body connected to an outer edge and a laminate layer secured to the outer edge, and folding an exterior edge portion of the outer edge over an interior edge portion to provide an external folded edge having the laminate layer on at least a portion of an outer surface.

First claim

What is claimed is:

1. A composite panel, comprising:
a main body connected to an outer edge, wherein the outer edge comprises a groove between an interior edge portion and an exterior edge portion; and
a laminate layer secured to the outer edge,
wherein the exterior edge portion of the outer edge is folded over the interior edge portion to provide an external folded edge having the laminate layer on at least a portion of an outer surface.

2. The composite panel of claim 1 , wherein the main body and the outer edge are formed of a thermoplastic matrix and carbon fibers.

3. The composite panel of claim 2 , wherein the carbon fibers are recycled.

4. The composite panel of claim 1 , wherein the main body has a first thickness, and the outer edge has a second thickness.

5. The composite panel of claim 4 , wherein the first thickness is greater than the second thickness.

6. The composite panel of claim 4 , wherein the first thickness is twice the second thickness.

7. The composite panel of claim 1 , wherein the groove is proximate to the laminate layer.

8. The composite panel of claim 1 , wherein the exterior edge portion is folded along the groove.

9. The composite panel of claim 1 , wherein the external folded edge has a same thickness as the main body.

10. A composite panel, comprising:
a main body connected to an outer edge, wherein the main body has a first thickness; and
a laminate layer secured to the outer edge, wherein the outer edge comprises a groove between the interior edge portion and the exterior edge portion, and wherein the outer edge has a second thickness,
wherein the main body and the outer edge are formed of a thermoplastic matrix and carbon fibers, and
wherein an exterior edge portion of the outer edge is folded over an interior edge portion to provide an external folded edge having the laminate layer on at least a portion of an outer surface.

11. The composite panel of claim 10 , wherein the carbon fibers are recycled.

12. The composite panel of claim 10 , wherein the first thickness is greater than the second thickness.

13. The composite panel of claim 10 , wherein the first thickness is twice the second thickness.

14. The composite panel of claim 10 , wherein the groove is proximate to the laminate layer.

15. The composite panel of claim 10 , wherein the exterior edge portion is folded along the groove.

16. The composite panel of claim 10 , wherein the external folded edge has a same thickness as the main body.

17. A composite panel, comprising:
a main body connected to an outer edge, wherein the outer edge comprises a groove between an interior edge portion and an exterior edge portion; and
a laminate layer secured to the outer edge,
wherein the laminate layer is on at least a portion of an outer surface.

18. The composite panel of claim 17 , wherein the main body and the outer edge are formed of a thermoplastic matrix and carbon fibers.

19. The composite panel of claim 17 , wherein the main body has a first thickness, and the outer edge has a second thickness, and wherein the first thickness is greater than the second thickness.

20. The composite panel of claim 17 wherein the groove is proximate to the laminate layer, and wherein the exterior edge portion is folded along the groove.

Assignees

• Boeing Co

Inventors

• Hills Karen L
• Switzer Lon E

Classifications

• B32B3/04

  characterised by {at least one} layer folded at the edge, e.g. over another layer {; characterised by at least one layer enveloping or enclosing a material} · CPC title

• B32B2605/18

  Aircraft · CPC title

• B32B2262/106

  Carbon fibres, e.g. graphite fibres · CPC title

• B32B5/145

  Variation across the thickness of the layer · CPC title

• B32B2398/20

  Thermoplastics · CPC title