Method for promoting electrical conduction between metallic components and composite materials
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B32B-003/00
B32B-007/14
B32B-027/20
C09D-011/52
C09D-005/24
출원번호
US-0268339
(2016-09-16)
등록번호
US-10052847
(2018-08-21)
발명자
/ 주소
Day, Arthur C.
McIver, Carl Roy
Nikic, Dejan
출원인 / 주소
THE BOEING COMPANY
대리인 / 주소
Gates & Cooper LLP
인용정보
피인용 횟수 :
0인용 특허 :
4
초록▼
A method for promoting electrical conduction between metallic components and composite materials. A composite body is coated with an adhering layer comprising a conductive material, and a metallic component is electrically connected to the conductive material of the adhering layer, when the metallic
A method for promoting electrical conduction between metallic components and composite materials. A composite body is coated with an adhering layer comprising a conductive material, and a metallic component is electrically connected to the conductive material of the adhering layer, when the metallic component is coupled to the composite body. The adhering layer is deposited inside a hole in the composite body, and/or along an edge of the hole, and/or on at least a portion of a surface of the composite body. The composite body is a structure of an aircraft or other vehicle comprised of composite materials formed from carbon fiber-reinforced polymers (CFRPs), the metallic component is a fastener or is positioned at an interface between the fastener and the composite body, and the electrical connection is made as part of a lightning protection system, an electromagnetic effects (EME) management system, or grounding system.
대표청구항▼
1. A method for enhancing electrical conduction, comprising: coating a composite body with an adhering layer comprising a conductive material, wherein a metallic component is electrically connected to the conductive material of the adhering layer, when the metallic component is coupled to the compos
1. A method for enhancing electrical conduction, comprising: coating a composite body with an adhering layer comprising a conductive material, wherein a metallic component is electrically connected to the conductive material of the adhering layer, when the metallic component is coupled to the composite body. 2. The method of claim 1, wherein the composite body is a structure of an aircraft or other vehicle comprised of composite materials formed from carbon fiber-reinforced polymers (CFRPs), the metallic component is a fastener, and the metallic component electrically connected to the conductive material of the adhering layer forms part of a lightning protection system, an electromagnetic effects (EME) management system, or grounding system. 3. The method of claim 1, wherein the metallic component comprises a sleeve, washer or other element positioned at an interface between a fastener and the composite body. 4. The method of claim 1, wherein the adhering layer comprises at least one of an electrically conductive ink or an electrically conductive paint. 5. The method of claim 4, wherein the electrically conductive ink or paint is comprised of a plurality of particles including at least one of copper or silver in a formulation including low temperature sintering agents. 6. The method of claim 5, wherein the electrically conductive ink or paint includes titanium, the titanium promotes adhesion to carbon fibers of the composite body by converting a thin surface layer of the carbon fibers to titanium carbide (TiC), and the particles form a thicker adherent layer on top of the TiC. 7. The method of claim 4, wherein the electrically conductive ink or paint is applied on the composite body using at least one of screen-printing, ink-jet printing, intaglio, dry film transfer, metallization, or plating. 8. The method of claim 1, further comprising curing the adhering layer coating the composite body at a temperature that does not adversely affect the composite body. 9. The method of claim 8, wherein the temperature is between about 100° C. and about 200° C. 10. The method of claim 8, wherein coating step further comprises depositing the adhering layer inside a hole in the composite body and the curing step further comprises performing in-situ curing of the adhering layer deposited inside the hole. 11. The method of claim 10, wherein the in-situ curing of the adhering layer is performed by at least one of baking, flash radiant heating, or laser heating. 12. The method of claim 10, wherein the in-situ curing of the adhering layer is performed by electrical inductive heating when the metallic component is inserted into the hole. 13. An apparatus for enhancing electrical conduction, comprising: a composite body coated with an adhering layer comprising a conductive material, wherein a metallic component is electrically connected to the conductive material of the adhering layer, when the metallic component is coupled to the composite body. 14. The apparatus of claim 13, wherein the composite body is a structure of an aircraft or other vehicle comprised of composite materials formed from carbon fiber-reinforced polymers (CFRPs), the metallic component is a fastener, and the metallic component electrically connected to the conductive material of the adhering layer forms part of a lightning protection system, an electromagnetic effects (EME) management system, or grounding system. 15. The apparatus of claim 13, wherein the metallic component is positioned at an interface between a fastener and the composite body. 16. The apparatus of claim 13, wherein the adhering layer comprises an electrically conductive ink or paint. 17. The apparatus of claim 16, wherein the electrically conductive ink or paint is comprised of a plurality of particles including copper or silver in a formulation including low temperature sintering agents. 18. The apparatus of claim 17, wherein the electrically conductive ink or paint includes titanium, the titanium promotes adhesion to carbon fibers of the composite body by converting a thin surface layer of the carbon fibers to titanium carbide (TiC), and the particles form a thicker adherent layer on top of the TiC. 19. An aircraft with enhanced electrical conduction, comprising: a composite body coated with an adhering layer comprising a conductive material; anda metallic component coupled to the composite body, wherein the metallic component is electrically connected to the conductive material of the adhering layer. 20. The aircraft of claim 19, wherein the composite body is a structure of the aircraft comprised of composite materials formed from carbon fiber-reinforced polymers (CFRPs), the metallic component is a fastener or is positioned at an interface between the fastener and the composite body, and the metallic component electrically connected to the conductive material of the layer forms part of a lightning protection system, an electromagnetic effects (EME) management system, or grounding system.
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이 특허에 인용된 특허 (4)
Marshall,Joseph A.; Weems,Douglas B.; Bussom,Richard C.; Anderson,David M., Composite structural member having an integrated electrical circuit.
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