Vehicle panel assembly and method of panel assembly

Patent metadata

Field	Value
Publication number	US-12060145-B2
Application number	US-202217653227-A
Country	US
Kind code	B2
Filing date	Mar 2, 2022
Priority date	Mar 2, 2022
Publication date	Aug 13, 2024
Grant date	Aug 13, 2024

Abstract

A panel assembly for use in a vehicle includes a first face sheet, a second face sheet, and a core layer disposed between the first and second face sheets. The core layer is defined by a base material along a first section of the panel assembly, and the core layer is defined by a honeycomb structure along a second section of the panel assembly. The first section and the second section are discrete, and the first section that includes the base material extends along a perimeter of the panel assembly.

First claim

What is claimed is:

1. A panel assembly for use in a vehicle, the panel assembly comprising:
a first face sheet;
a second face sheet;
a core layer disposed between the first and second face sheets, wherein the core layer is defined by a high density foam material along a first section of the panel assembly, and the core layer is defined by a honeycomb structure along a second section of the panel assembly, wherein the first section and the second section are discrete so that the high density foam material and the honeycomb structure are non-overlapping and co-planar, and the first section that includes the high density foam material extends along a perimeter of the panel assembly, wherein the high density foam material has a greater strength and density than the honeycomb structure, wherein the first section defines a hole that continuously extends through the first face sheet, the high density foam material, and the second face sheet, and the second section is void of any holes that continuously extend through the first face sheet, the honeycomb structure, and the second face sheet; and
an insert element extending through the first face sheet, the high density foam material, and the second face sheet within the hole, the insert element defining a channel configured to receive a fastener therethrough for mounting the panel assembly to a structural support in the vehicle.

2. The panel assembly of claim 1 , wherein the first section surrounds the second section.

3. The panel assembly of claim 1 , further comprising the fastener disposed within the channel of the insert element and extending through the first face sheet, the high density foam material, and the second face sheet, wherein the fastener is a quarter-turn fastener.

4. The panel assembly of claim 1 , wherein the first and second face sheets are bonded to the core layer via an adhesive.

5. The panel assembly of claim 1 , wherein the high density foam material includes urethane foam.

6. The panel assembly of claim 1 , further comprising a liner secured to the first face sheet such that the first face sheet is disposed between the liner and the core layer.

7. The panel assembly of claim 1 , wherein each of the first and second face sheets comprises one or more skin layers, each skin layer of the one or more skin layers comprises a fiberglass material or a metal material.

8. The panel assembly of claim 1 , wherein the panel assembly is a bulkhead panel configured to be mounted within a cargo area of the vehicle.

9. The panel assembly of claim 1 , wherein the first section that includes the high density foam material is located along all edges of the panel assembly.

10. The panel assembly of claim 1 , wherein the insert element has flanges that mechanically contact at least one of (i) the high density foam material or (ii) the first and second face sheets to retain the insert element within the hole.

11. The panel assembly of claim 1 , wherein the insert element is composed of a metal material.

12. The panel assembly of claim 1 , wherein the core layer along the first section has approximately a same thickness as the core layer along the second section.

13. A method for assembling a composite panel, the method comprising:
securing a honeycomb structure to an interior surface of a first face sheet;
securing a foam material to the interior surface of the first face sheet, the foam material and the honeycomb structure being secured to different portions of the interior surface, and the foam material extending along a perimeter border area of the first face sheet, wherein the foam material and the honeycomb structure are non-overlapping and co-planar, wherein the foam material has a greater strength and density than the honeycomb structure;
securing a second face sheet to at least one of the honeycomb structure or the foam material such that the honeycomb structure and the foam material are sandwiched between the first and second face sheets;
forming a hole that continuously extends through the first face sheet, the foam material, and the second face sheet, the hole spaced apart from the honeycomb structure, wherein forming the hole comprises not forming any holes that continuously extend through the first face sheet, the honeycomb structure, and the second face sheet; and
installing an insert element within the hole to extend through the first face sheet, the foam material, and the second face sheet, the insert element defining a channel configured to receive a fastener therethrough for mounting the composite panel to a structural support.

14. The method of claim 13 , further comprising:
inserting the fastener through the channel of the insert element for mounting the composite panel to the structural support.

15. The method of claim 13 , wherein securing the honeycomb structure to the interior surface of the first face sheet and securing the foam material to the interior surface comprises bonding the honeycomb structure and the foam material to the interior surface via an adhesive.

16. The method of claim 13 , further comprising securing a liner to an exterior surface of the first face sheet such that the first face sheet is disposed between the liner and each of the honeycomb structure and the foam material.

17. An aircraft comprising:
a fuselage defining an internal volume and including one or more structural supports; and
a panel assembly coupled to the fuselage within the internal volume, the panel assembly comprising:
a first face sheet;
a second face sheet;
a core layer disposed between the first and second face sheets, wherein the core layer is defined by a foam material along a first section of the panel assembly, and the core layer is defined by a honeycomb structure along a second section of the panel assembly, wherein the first section and the second section are discrete so that the foam material and the honeycomb structure are non-overlapping and co-planar, and the first section that includes the foam material follows a contour of a perimeter of the panel assembly, wherein the foam material has a greater strength and density than the honeycomb structure, wherein the panel assembly defines multiple holes along the first section that continuously extend through the first face sheet, the foam material, and the second face sheet, wherein none of the holes is located along the second section so that the holes are spaced apart from the honeycomb structure;
multiple insert elements extending through the first face sheet, the foam material, and the second face sheet within the holes, the insert elements defining respective channels therethrough; and
multiple fasteners extending through the channels of the insert elements and coupled to the one or more structural supports to mount the panel assembly to the fuselage.

18. The aircraft of claim 17 , wherein the internal volume comprises a cargo area configured to contain cargo to be transported on the aircraft, and the panel assembly is a component of a bulkhead wall within the cargo area.

19. The aircraft of claim 17 , wherein the panel assembly defines an opening that continuously extends through a full thickness of the panel assembly, and the aircraft further comprises a vent mounted within the opening, wherein the foam material of the panel assembly extends along an edge of the opening and surrounds the vent.

20. The aircraft of claim 17 , wherein the insert elements have flanges that mechanically contact at least one of (i) the foam material or (ii) the first and second face sheets to retain the inser

Assignees

• Boeing Co

Inventors

• Hurtado Joe L
• Le Chau T

Classifications

• B32B2605/18

  Aircraft · CPC title

• B32B2266/0278

  Polyurethane · CPC title

• B32B2262/101

  Glass fibres · CPC title

• B32B37/12

  characterised by using adhesives · CPC title

• B32B15/046

  of foam · CPC title