Apparatus and method for an aircraft conductor sandwich assembly embedded to an aircraft structure
View Patent ↗An aircraft conductor sandwich assembly configured to be embedded in a composite aircraft structure. The conductor sandwich assembly comprises a plurality of carbon conductors disposed between two sheets of insulating layers and an adhesive resin bonding the plurality of carbon conductors and the two sheets of insulating layers into a carbon sandwich assembly such that (i) the conductors are electrically isolated and (ii) structural loads can be passed through said conductor sandwich assembly.
1. An aircraft conductor sandwich assembly configured to be embedded in a composite aircraft structure without substantial detrimental effect on the electrical and structural properties of the aircraft, comprising:
a plurality of substantially longitudinally-shaped, substantially parallel carbon conductors disposed between two sheets of insulating layers; and
an adhesive resin bonding the plurality of carbon conductors and the two sheets of insulating layers into a carbon sandwich assembly such that (i) the plurality of conductors are electrically isolated from each other and the carbon sandwich assembly and (ii) structural loads can be passed through said conductor sandwich assembly.
2. The aircraft conductor sandwich assembly of claim 1 , wherein each carbon conductor comprises carbon nano-filaments.
3. The aircraft conductor sandwich assembly of claim 1 , wherein each carbon conductor comprises carbon nano-tubes.
4. The aircraft conductor sandwich assembly of claim 1 , wherein each sheet of insulating layer comprises Poly Ether Ketone Ketone (PEKK).
5. The aircraft conductor sandwich assembly of claim 1 , wherein each sheet of insulating layer comprises etched, bondable polytetrafluoroethylene.
6. The aircraft conductor sandwich assembly of claim 1 , wherein the adhesive resin comprises an aircraft film adhesive.
7. The aircraft conductor sandwich assembly of claim 1 , wherein the adhesive resin comprises a liquid epoxy.
8. The aircraft conductor sandwich assembly of claim 1 , wherein the ends of each carbon conductor are plated with a metal or conductive adhesive.
9. The aircraft conductor sandwich assembly of claim 1 , wherein the carbon sandwich assembly is co-cured with the composite aircraft structure.
10. The aircraft conductor sandwich assembly of claim 1 , wherein the carbon sandwich assembly is co-bonded with the composite aircraft structure.
11. The aircraft conductor sandwich assembly of claim 10 , wherein the composite aircraft structure comprises a prefabricated composite structure.
12. An aircraft conductor sandwich assembly configured to (i) be embedded to an aircraft structural member and (ii) be operative without substantial negative impact on the electrical and structural properties of the aircraft, comprising:
a plurality of substantially longitudinally-shaped, substantially parallel carbon conductors bonded between two sheets of insulating layers; and
an adhesive resin bonding the plurality of carbon conductors and the two sheets of insulating layers into a carbon sandwich assembly such that (i) the conductors are electrically isolated from each other and from any aircraft structural member, and (ii) structural loads can be passed through said conductor sandwich assembly.
13. The aircraft conductor sandwich assembly of claim 12 , wherein each carbon conductor comprises carbon nano-filaments.
14. The aircraft conductor sandwich assembly of claim 12 , wherein each carbon conductor comprises carbon nano-tubes.
15. The aircraft conductor sandwich assembly of claim 12 , wherein each sheet of insulating layer comprises Poly Ether Ketone Ketone (PEKK).
16. The aircraft conductor sandwich assembly of claim 12 , wherein each sheet of insulating layer comprises etched, bondable polytetrafluoroethylene.
17. The aircraft conductor sandwich assembly of claim 12 , wherein the adhesive resin comprises an aircraft film adhesive.
18. The aircraft conductor sandwich assembly of claim 12 , wherein the adhesive resin comprises a liquid epoxy.
19. An aircraft conductor sandwich assembly embedded to an aircraft structural member, comprising:
a plurality of sheet-shaped carbon conductors bonded between two sheets of insulating layers, the plurality of conductors being disposed in parallel and extending longitudinally; and
an adhesive resin bonding the plurality of carbon conductors and the two sheets of insulating layers into a sheet-shaped carbon sandwich assembly such that (i) the conductors are electrically isolated from each other and from any aircraft structural member, and (ii) structural loads can be passed through said conductor sandwich assembly.
20. The aircraft conductor sandwich assembly of claim 19 , wherein the conductor sandwich assembly is embedded to the surface of the aircraft structural member.
21. The aircraft conductor sandwich assembly of claim 19 , wherein the conductor sandwich assembly is embedded underneath the surface of the aircraft structural member.
22. The aircraft conductor sandwich assembly of claim 19 , wherein the aircraft structural member comprises a composite material.
23. The aircraft conductor sandwich assembly of claim 22 , wherein the aircraft structural member composite material is co-cured with the conductor sandwich assembly.
24. The aircraft conductor sandwich assembly of claim 19 , wherein each of the of sheet-shaped carbon conductors is folded to make a change of direction.
25. A method for embedding an aircraft conductor sandwich assembly to an aircraft load-bearing structure, comprising the steps of:
forming an aircraft conductor sandwich assembly including (i) a plurality of sheet-shaped carbon conductors bonded between two sheets of insulating layers, the plurality of conductors being disposed in parallel and extending longitudinally, and (ii) an adhesive resin bonding the plurality of carbon conductors and the two sheets of insulating layers into a sheet-shaped carbon sandwich assembly such that the conductors are electrically isolated from each other and from any aircraft structural member, and such that structural loads can be passed through said conductor sandwich assembly; and
bonding the aircraft conductor sandwich assembly to the aircraft load-bearing structure.
26. The method of claim 25 , wherein the bonding step includes the step of co-curing the aircraft conductor sandwich assembly with an aircraft composite load-bearing structure.
27. The method of claim 25 , wherein the bonding step includes the step of co-bonding the aircraft conductor sandwich assembly with an aircraft composite load-bearing structure.