Integrated current return network in composite structures

Patent metadata

Field	Value
Publication number	US-10343791-B2
Application number	US-201615238597-A
Country	US
Kind code	B2
Filing date	Aug 16, 2016
Priority date	Aug 16, 2016
Publication date	Jul 9, 2019
Grant date	Jul 9, 2019

Abstract

An aircraft component incorporated in a current return network (CRN) employs a composite structural element having a web. At least one flange is connected to the web. At least one metallic conductive layer is integrated with and extends the length of the web. The at least one metallic layer is configured to electrically bond to an aircraft system and provide a ground path.

First claim

What is claimed is:

1. A current return network (CRN) comprising:
a composite structural element having a web;
at least one flange connected to the web;
at least one metallic conductive layer integrated with and extending the length of the web;
wherein the at least one metallic layer is configured to electrically bond to an aircraft system and provide a ground path.

2. The CRN as defined in claim 1 wherein the at least one metallic conductive layer is co-cured in the composite structural element.

3. The CRN as defined in claim 2 wherein the at least one metallic conductive layer is an expanded metal foil.

4. The as defined in claim 3 wherein the expanded metal foil is configured to minimize induced stress from thermal expansion of the composite.

5. The aircraft component incorporated in a CRN as defined in claim 2 wherein the at least one metallic conductive layer comprises a conductor on flex.

6. The aircraft component incorporated in a CRN as defined in claim 1 wherein the at least one metallic conductive layer is applied to a surface of the composite structural element.

7. The aircraft component incorporated in a CRN as defined in claim 6 wherein the at least one metallic conductive layer comprises expanded metal foil or conductor on flex bonded to the composite structural element with high temperature adhesive to withstand heating caused by a short circuit or lightning.

8. The aircraft component incorporated in a CRN as defined in claim 6 wherein the at least one metallic conductive layer comprises a thermal spray layer, a direct write metal printed layer or a conductive ink printed layer.

9. A method for implementing a current return network (CRN) comprising:
establishing a desired current return path;
fabricating a structural member providing routing approximating the current return path with at least one integrated conductive layer;
modifying the integrated conductive layer with pad ups for current localization at connection points; and,
electrically connecting the integrated conductive layer and CRN components.

10. The method as defined in claim 9 wherein the step of electrically connecting is accomplished with interference fit sleeved fasteners, electrical fay surface bonds, interference fit fasteners, or rivet bonds.

11. The method as defined in claim 9 wherein the step of fabricating a structural member comprises co-curing the at least one integrated conductive layer as a layer in the layup of the structural member.

12. The method as defined in claim 9 wherein the step of fabricating a structural member comprises applying the at least one integrated conductive layer as a surface layer.

13. The method as defined in claim 12 wherein the step of applying the at least one integrated conductive layer comprises spraying a conductive thermal spray layer.

14. The method as defined in claim 12 wherein the step of applying the at least one integrated conductive layer comprises printing a direct write metal printed layer.

15. The method as defined in claim 12 wherein the step of applying the at least one integrated conductive layer comprises printing a conductive ink printed layer.

16. The method as defined in claim 10 further comprising adapting the integrated conductive layer for matching coefficient of thermal expansion within a carbon fiber reinforced plastic (CFRP) laminate.

17. The method as defined in claim 10 further comprising modifying resin properties of the CFRP laminate to accommodate coefficient of thermal expansion mismatch.

18. The method as defined in claim 10 further comprising minimizing stress build up by adding nano-silica to the epoxy interface between the integrated conductive layer and the CFRP laminate.

19. A method of grounding systems in an aircraft comprising:
receiving current from lightning strike or system faults in an integrated conductive layer in a structural member wherein the structural member comprises a composite structural element having a web with at least one flange connected to the web and the integrated conductive layer is a metallic conductive layer integrated with and extending the length of the web;
transmitting the current along the integrated conductive layer in the structural member; and,
transferring the current to current return network (CRN) components electrically bonded to the integrated conductive layer.

20. The method of claim 19 wherein electrical connections between the integrated conductive layer and CRN components comprise interference fit sleeved fasteners, electrical fay surface bonds, interference fit fasteners, or rivet bonds.

Assignees

• Boeing Co

Inventors

• Le Quynhgiao
• Greegor Robert B
• Whiting Brent A
• Anway Carol E
• Larson Kim M

Classifications

• H02G13/00

  Installations of lightning conductors; Fastening thereof to supporting structure · CPC title

• H05F3/02

  by means of earthing connections · CPC title

• H05F3/00

  Carrying-off electrostatic charges ({from shoes A43B7/36}; from living beings A61N1/14; {from tyres B60C19/08; from vehicles B60R16/06; from aircraft B64D45/02; from large containers B65D90/46}) · CPC title

• B32B2605/18

  Aircraft · CPC title

• B64D45/02 Primary

  Lightning protectors; Static dischargers · CPC title