PANEL MEMBER FOR AN AIRFRAME

• US 20150004348A1
• Filed: 06/13/2014
• Published: 01/01/2015
• Est. Priority Date: 06/27/2013
• Status: Active Grant

• Current Assignee: Airbus Operations GmbH (Airbus SE)
• Original Assignee: Airbus Operations GmbH (Airbus SE)
• Inventors: ZUARDY, Ichwan, BULLINGER, Oliver, VULTAGGIO, Claudio
• Granted Patent: US 10,814,957 B2
• Time in Patent Office: Days
• US Class Current: 428/76
• CPC Class Codes: B32B 2305/08 Reinforcements
• CPC Class Codes: B32B 2307/202 Conductive
• CPC Class Codes: B32B 2398/00 Unspecified macromolecular compounds
• CPC Class Codes: B32B 2605/18 Aircraft blades, propellers B32B2603/00
• CPC Class Codes: B32B 38/08 Impregnating
• CPC Class Codes: B32B 38/1808 characterised by the laying up of the layers
• CPC Class Codes: B64C 1/00 Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
• CPC Class Codes: B64C 1/12 Construction or attachment of skin panels
• CPC Class Codes: B64C 2001/0072 from composite materials
• CPC Class Codes: B64C 3/20 Integral or sandwich constructions
• CPC Class Codes: B64D 45/02 Lightning protectors; Static dischargers in general H01T
• CPC Class Codes: B64G 1/22 Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y10T 428/239 Complete cover or casing

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.

Claims

1. A composite panel member for an airframe of an aircraft or spacecraft, the composite panel member having a laminated or sandwich structure comprising:

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 in the core layer between the first and second outer layers;

wherein the at least one support element extends within the core layer substantially parallel to the first and second outer layers.

2. The panel member according to claim 1, wherein the at least one support element is elongate and extends substantially continuously within the core in the direction substantially parallel to the first and second outer 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 a full width of the core layer from the first outer layer to the second outer layer to form a barrier through the core layer.

4. The panel member according to claim 1, wherein the at least one support element is adapted for electrical conduction between the first side and the second side of the panel member, and/or wherein the at least one support element is comprised of a metallic mesh or includes 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 outer layers is comprised of a composite material, and wherein the core layer is a relatively low density material.

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

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

wherein the at least one support element projects through the second outer 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 its longitudinal axis that is I-shaped, T-shaped, L-shaped or Z-shaped.

10. The panel member according to claim 1, wherein either or both of the first and second outer layers includes an electrically conductive sheet or foil which is substantially coextensive therewith.

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

11. A vehicle body structure, the body structure comprising:

a composite panel member having a laminated or sandwich structure comprising;

a first layer over a first side of the panel member, a second layer over a second side of the panel member, a core between the first and second layers, and at least one support element within the core, the at least one support element extending generally parallel to the first and second layers; and

an elongate structural member which is attached to the panel member at the second side thereof, the elongate structural member being substantially aligned and/or connected with the at least one support element;

wherein the at least one support element forms an electrical conductor between the first side of the panel member and the elongate structural element at the second side of the panel member.

12. The vehicle body structure according to claim 11, wherein the elongate structural member is connected with the at least one support element at the second side of the panel member, the elongate structural member having a cross-section or profile transverse to its longitudinal axis that is I-shaped, T-shaped, L-shaped or Z-shaped.

13. The vehicle body structure according to claim 11, wherein the elongate structural member is connected with the at least one support element at an interface that is substantially perpendicular to the second outer layer.

14. The vehicle body structure according to claim 11, wherein the at least one support element is elongate and extends substantially continuously within the core in a direction substantially parallel to the first and second outer layers, wherein the at least one support element spans a full width of the core layer from the first outer layer to the second outer layer such that it forms a barrier in the core layer.

15. The vehicle body structure according to claim 11, wherein each of the first and second outer layers is comprised of a composite material, and wherein the core is a relatively low density material.

16. The vehicle body structure according to claim 15, wherein the composite material of the first and second outer layers comprises a fibre-reinforced polymer composite, and wherein the relatively low density material of the core layer is a hard foam having an open-cell or closed-cell structure.

18. An aircraft or spacecraft having a vehicle body structure according to claim 11.

19. A method of producing a composite panel member for a vehicle body structure, the method comprising:

providing a core layer for a composite sandwich structure;

providing at least one elongate support element in the core layer, the at least one support element being configured as an electrical conductor;

arranging the core layer between first and second fibre reinforcement sheet layers in a sandwich arrangement, such that the at least one support element extends within the core layer substantially parallel to the first and second sheet layers; and

impregnating the sandwich arrangement with a polymer resin.