Panel member for an airframe

Patent metadata

Field	Value
Publication number	US-10814957-B2
Application number	US-201414304252-A
Country	US
Kind code	B2
Filing date	Jun 13, 2014
Priority date	Jun 27, 2013
Publication date	Oct 27, 2020
Grant date	Oct 27, 2020

Abstract

The disclosure relates to a composite panel member for an airframe of an aircraft or spacecraft, the composite panel member having a laminated or sandwich structure including: a first outer layer extending over a first side of the panel member; a second outer layer extending over a second side of the panel member; a core layer between the first and second outer layers; and at least one support element configured as an electrical conductor and provided within the core layer between the first and second outer layers. In this regard, the at least one support element extends within the core layer substantially parallel to the first and second outer layers.

First claim

What is claimed is:

1. A composite panel member for forming an outer skin around an internal structure of an airframe of an aircraft or spacecraft, the composite panel member comprising:
a first layer extending over a first side of the panel member, the first side of the panel member being an external surface of the outer skin, wherein the first side faces away from and is separated from the internal structure;
a second layer extending over a second side of the panel member, the second side of the panel member being an internal surface of the outer skin, wherein the second side faces towards and contacts the internal structure;
a core layer between the first and second layers, the core layer being external to the internal structure and separated from the internal structure by at least the second layer; and
at least one support element, which is an electrically conductive material and extends within the core layer to electrically connect the first layer to the second layer through a full width of the core layer;
wherein the at least one support element has a longitudinal axis that extends in a direction substantially parallel to the first and second layers;
wherein the panel member is configured to be attached, at the second side thereof, to an elongate structural member of the internal structure that is external to the panel member and extends away from the second layer of the panel member;
wherein the first layer, the second layer, and the core layer are arranged such that the panel member has a laminated, or sandwich, structure; and
wherein the first layer or the second layer include an electrically conductive sheet or foil, which is substantially coextensive with the first layer or the second layer.

2. The panel member according to claim 1 , wherein the at least one support element is elongate and extends substantially continuously within the core layer in the direction substantially parallel to the first and second layers.

3. The panel member according to claim 1 , wherein, in a plane of a cross-section taken through the laminated or sandwich structure from the first side to the second side of the panel member, the at least one support element spans the full width of the core layer, from the first layer to the second layer, to form a barrier through the core layer.

4. The panel member according to claim 1 , wherein the at least one support element comprises a metallic mesh or a metallic foil.

5. The panel member according to claim 1 , wherein the at least one support element includes a covering or a coating, the covering or coating comprising a prepreg.

6. The panel member according to claim 1 , wherein each of the first and second layers comprises a composite material, and wherein the core layer comprises a material having a lower density than the composite material of the first and second layers.

7. The panel member according to claim 6 , wherein the composite material of the first and second layers comprises a fibre-reinforced polymer composite, and wherein the core layer comprises a hard foam having an open-cell or closed-cell structure.

8. The panel member according to claim 1 , wherein a first portion of the at least one support element is fully embedded within the core layer of the laminated or sandwich structure, the first portion of the at least one support element being in contact with and/or connected to either of the first and second layers, and wherein a second portion of the at least one support element projects through the second layer to the second side of the panel member.

9. The panel member according to claim 1 , wherein the at least one support element has a cross-section or profile transverse to the longitudinal axis thereof that is I-shaped, T-shaped, L-shaped, or Z-shaped.

10. The panel member according to claim 1 , wherein both the first layer and the second layer include the electrically conductive sheet or foil which is substantially coextensive therewith.

11. An aircraft or spacecraft having a panel member according to claim 1 .

12. A vehicle body structure, the body structure comprising:
a composite panel member for forming an outer skin around an internal structure of the vehicle body structure, the panel member comprising:
a first layer over a first side of the panel member, the first side of the panel member being an external surface of the outer skin, wherein the first side faces away from and is separated from the internal structure;
a second layer over a second side of the panel member, the second side of the panel member being an internal surface of the outer skin, wherein the second side faces towards and contacts the internal structure;
a core layer between the first and second layers, the core layer being external to the internal structure and separated from the internal structure by at least the second layer; and
at least one support element, which is an electrically conductive material and extends within the core layer to electrically connect the first layer to the second layer through a full width of the core layer,
wherein the at least one support element has a longitudinal axis that extends in a direction generally parallel to the first and second layers; and
wherein the first layer, the second layer, and the core layer are arranged such that the panel member has a laminated, or sandwich, structure; and
wherein the first layer or the second layer include an electrically conductive sheet or foil, which is substantially coextensive with the first layer or the second layer; and

an elongate structural member attached to the panel member at the second side of the panel member, the elongate structural member being substantially aligned and/or connected with the at least one support element;
wherein the elongate structural member is external to the panel member and extends away from the second layer of the panel member.

13. The vehicle body structure according to claim 12 , wherein the elongate structural member is connected to the at least one support element at the second side of the panel member, and wherein the elongate structural member has a cross-section or profile transverse to the longitudinal axis thereof that is I-shaped, T-shaped, L-shaped, or Z-shaped.

14. The vehicle body structure according to claim 12 , wherein the elongate structural member is connected to the at least one support element at an interface that is substantially perpendicular to the second layer.

15. The vehicle body structure according to claim 12 , wherein the at least one support element is elongate and extends substantially continuously within the core layer in the direction substantially parallel to the first and second layers, and wherein the at least one support element spans the full width of the core layer, from the first layer to the second layer, such that a barrier is formed in the core layer.

16. The vehicle body structure according to claim 12 , wherein each of the first and second layers comprises a composite material, and wherein the core layer comprises a material having a lower density than the composite material of the first and second layers.

17. The vehicle body structure according to claim 16 , wherein the composite material of the first and second layers comprises a fibre-reinforced polymer composite, and wherein the core layer comprises a hard foam having an open-cell or closed-cell structure.

18. An aircraft or spacecraft having a vehicle body structure according to claim 12 .

19. A method of producing a composite panel member for forming an outer skin around an internal structure of

Assignees

• Airbus Operations Gmbh

Inventors

• Zuardy Ichwan
• Bullinger Oliver
• Vultaggio Claudio

Classifications

• B64C1/00

  Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like · CPC title

• B32B2307/202

  Conductive · CPC title

• B32B38/08

  Impregnating · CPC title

• B64D45/02

  Lightning protectors; Static dischargers · CPC title

• B32B38/1808

  characterised by the laying up of the layers · CPC title