Composite sandwich panels with over-crushed edge regions

Patent metadata

Field	Value
Publication number	US-11440283-B2
Application number	US-201815887839-A
Country	US
Kind code	B2
Filing date	Feb 2, 2018
Priority date	Feb 2, 2018
Publication date	Sep 13, 2022
Grant date	Sep 13, 2022

Abstract

A composite sandwich panel comprises a first composite skin, a second composite skin, a hollow cell core between the first composite skin and the second composite skin, and a first over-crush edge region with a first edge. The first edge has a first thickness at least 40% less than a nominal thickness of the composite sandwich panel. The first over-crush edge region has a length of at least 0.25 inches over which a thickness of the composite sandwich panel decreases.

First claim

What is claimed is:

1. A method comprising:
loading a first composite skin, a second composite skin, and a hollow cell core into a tool comprising opposing dies;
closing the tool to form an interior shape of the tool between the opposing dies, the interior shape comprising a periphery region; and
compressing the first composite skin, the second composite skin, and the hollow cell core using the opposing dies to form and consolidate a composite sandwich panel having a nominal thickness while applying an over-crush pressure to portions of the composite sandwich panel to form a first over-crush edge region comprising an edge and a transition region, the edge having a first thickness at least 40% less than the nominal thickness of the composite sandwich panel, the nominal thickness being the thickness of the composite sandwich panel away from the first over- crush edge region after consolidating the first composite skin, the second composite skin, and the hollow cell core, wherein the periphery region surrounds the first over-crush edge region when the composite sandwich panel is in the tool and provides a path for volatiles, released from the composite sandwich panel during compression, to escape the tool between the opposing dies.

2. The method of claim 1 , wherein the periphery region has a thickness greater than the nominal thickness.

3. The method of claim 1 further comprising:
reducing a thickness of the composite sandwich panel from the nominal thickness to the first thickness in the transition region using an over-crush forming feature of one of the opposing dies, wherein a length of the transition region is at least 0.25 inches.

4. The method of claim 3 , wherein the over-crush forming feature comprises a protrusion.

5. The method of claim 1 further comprising:
cutting the first over-crush edge region using numerically controlled machinery to create a cut edge having a flat appearance without visible core cells.

6. The method of claim 5 , wherein cutting the first over-crush edge region removes a portion of composite sandwich panel comprising the first thickness.

7. The method of claim 1 , wherein the periphery region is substantially perpendicular to a direction the opposing dies are moveable relative to each other as the periphery region extends away from the first over-crush edge region towards an outside of the tool.

8. The method of claim 1 further comprising:
forming a second over-crush edge region and a third over-crush edge region during compressing of the first composite skin, the second composite skin, and the hollow cell core; and
allowing volatiles to escape through a fourth edge of the composite sandwich panel while forming the second over-crush edge region and the third over-crush edge region of the composite sandwich panel.

9. The method of claim 8 , wherein the periphery region surrounds the second over-crush region, the third over-crush edge region, and the fourth edge when the composite sandwich panel is in the tool.

10. The method of claim 1 , wherein the edge has a flat appearance with no visible core cells.

11. The method of claim 1 , wherein the edge is a rolled edge.

12. The method of claim 1 , further comprising paint covering the edge.

13. The method of claim 1 , wherein the composite sandwich panel forms a light valence of an aircraft, and wherein the edge is visible to passengers on the aircraft.

14. The method of claim 1 , wherein the composite sandwich panel further comprises an open edge having visible core cells, wherein the open edge is the nominal thickness of the composite sandwich panel.

15. The method of claim 14 , wherein the composite sandwich panel further comprises an edge treatment applied to the open edge.

16. The method of claim 1 , wherein the periphery region has a thickness at least twice the nominal thickness.

17. The method of claim 1 , wherein the first thickness is in a range of 0.050 inches to 0.10 inches.

Assignees

• Boeing Co

Inventors

• Turner Jason
• Kotlik Mitchell Zachary
• Schwartz Christopher Robert
• Black Michael B

Classifications

• B32B3/12 Primary

  characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure · CPC title

• B29C70/545

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

• B29C70/46

  using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs · CPC title

• B29C70/865

  completely encapsulated · CPC title

• B29C70/086

  and with one or more layers of pure plastics material, e.g. foam layers (applying a non-preformed coating, e.g. a gel-coat, B29C37/0025; with foam blocks B29C70/86) · CPC title