Composite panels assembly, furniture comprising such assembly and aircraft comprising such assembly

Patent metadata

Field	Value
Publication number	US-11480206-B2
Application number	US-201816217630-A
Country	US
Kind code	B2
Filing date	Dec 12, 2018
Priority date	Dec 19, 2017
Publication date	Oct 25, 2022
Grant date	Oct 25, 2022

Abstract

A composite panel assembly including a first panel with a first skin, a second skin, a core, and an assembly flange. A second panel includes a first skin, a second skin, a core, and an assembly flange. A fastening device is adapted to fasten the assembly flange of the first panel to the assembly flange of the second panel, wherein the core of one of the first panel or the second panel includes reinforcing pins and a high-density portion placed along the assembly flange.

First claim

The invention claimed is:

1. A composite panel assembly comprising:
a first panel comprising:
a first layer forming a first skin;
a second layer forming a second skin;
a third layer forming a core, the core being between the first skin and the second skin; and
wherein the first layer, the second layer, and the third layer are arranged to form a panel portion in which the first skin and the second skin are substantially parallel to each other with the core in between, an assembly flange in which the first skin and the second skin are directly against each other, and a bevel portion formed in a transition between the panel portion and the assembly flange;
wherein an outer face of the first skin in the assembly flange forms an angle of between 145 degrees and 168 degrees with the outer face of the first skin in the bevel portion; and
wherein the outer face of the first skin in the assembly flange forms an angle of between 120 degrees and 150 degrees with the outer face of the first skin in the panel portion;

a second panel comprising:
a first layer forming a first skin;
a second layer forming a second skin;
a third layer forming a core, the core being between the first skin and the second skin; and
wherein the first layer, the second layer, and the third layer are arranged to form a panel portion in which the first skin and the second skin are substantially parallel to each other with the core in between, an assembly flange in which the first skin and the second skin are directly against each other, and a bevel portion formed in a transition between the panel portion and the assembly flange;
wherein an outer face of the first skin in the assembly flange forms an angle of between 145 degrees and 168 degrees with the outer face of the first skin in the bevel portion; and
wherein the outer face of the first skin in the assembly flange forms an angle of between 120 degrees and 150 degrees with the outer face of the first skin in the panel portion;

at least a fastening device configured to fasten the assembly flange of the first panel to the assembly flange of the second panel;
the core of at least one of the first panel or the second panel at least partly comprising reinforcing pins;
the core comprising:
a low-density portion with a first density; and
a high-density portion with a second density, the second density being higher than the first density; and
the high-density portion of the core forming a reinforcing edge of the core, the reinforcing edge being along the assembly flange.

2. The assembly according to claim 1 , wherein at least some reinforcing pins are arranged to cross the core from the first skin to the second skin.

3. The assembly according to claim 1 , wherein at least some pins are arranged at least partially in the first skin and/or in the second skin.

4. The assembly according to claim 1 , wherein the high-density portion of the core is at least partially in the bevel portion formed by the first skin and the second skin.

5. The assembly according to claim 1 , wherein the first skin and/or the second skin is reinforced in the bevel portion.

6. The assembly according to claim 1 , wherein a density of the reinforcing pins varies.

7. The assembly according to claim 1 , wherein a density of the reinforcing pins is higher in proximity to a reinforcing edge of the core.

8. The assembly according to claim 1 , wherein the high-density portion of the core comprises reinforcing pins.

9. The assembly according to claim 1 , wherein a density of the reinforcing pins varies within the low-density portion of the core.

10. The assembly according to claim 1 , wherein a density of the reinforcing pins varies within the high-density portion of the core.

11. The assembly according to claim 1 , comprising a cover element, configured to be mounted at least partially on at least part of the assembly flange of the first panel and/or at least part of the assembly flange of the second panel.

12. The assembly according to claim 11 , wherein the cover element comprises an elastomer.

13. The assembly according to claim 1 , wherein the fastening device comprises:
an assembly piece configured to be fastened to the assembly flange of the first panel and to the assembly flange of the second panel; and
at least one fastener adapted to fasten the assembly flange of the first panel and the assembly flange of the second panel to the assembly piece.

Assignees

• Airbus Defence & Space Gmbh

Inventors

• Weber Markus
• Zimmermann Kristian
• Endres Gregor Christian
• Schumacher Christian

Classifications

• B29C65/56

  using mechanical means {or mechanical connections, e.g. form-fits} · CPC title

• B64C2001/0072

  from composite materials · CPC title

• B29D99/0021

  provided with plain or filled structures, e.g. cores, placed between two or more plates or sheets, e.g. in a matrix · CPC title

• B32B7/08

  by mechanical means · CPC title

• B32B2479/00

  Furniture · CPC title