초록 ▼

Disclosed in this application is a novel method and apparatus for reducing electrical resistance of a carbon-reinforced plastic structure to thereby reduce damage due to lightning strikes or precipitation static. This apparatus includes a galvanically compatible conductive interface layer positioned

Disclosed in this application is a novel method and apparatus for reducing electrical resistance of a carbon-reinforced plastic structure to thereby reduce damage due to lightning strikes or precipitation static. This apparatus includes a galvanically compatible conductive interface layer positioned between a nonconductive substrate and a conductive outer surface. The interface layer is electrically conductive to transmit electrical current from the outer surface to the substrate.

대표청구항 ▼

1. A method for constructing an aircraft structural assembly, the method comprising: providing a composite substrate having a low electrical conductivity;layering an interface layer directly onto said substrate, said interface layer consisting of a boron fiber with resin; andattaching a conductive l

1. A method for constructing an aircraft structural assembly, the method comprising: providing a composite substrate having a low electrical conductivity;layering an interface layer directly onto said substrate, said interface layer consisting of a boron fiber with resin; andattaching a conductive layer directly to an outer surface of said interface layer, said conductive layer having a higher electrical conductivity than said composite substrate;wherein said interface layer is highly galvanically compatible with said conductive layer and is highly galvanically compatible with said composite substrate. 2. The method of claim 1, further comprising applying a surfacer over said conductive layer. 3. The method of claim 1, wherein said interface layer consists of boron fibers and a resin selected from a thermoplastic resin and a thermoset resin. 4. The method of claim 1, wherein said conductive layer comprises expanded aluminum foil. 5. A structural assembly for applying to a portion of an aircraft structure, the structural assembly comprising: a nonmetallic, composite substrate having a relatively low electrical conductivity;an outer layer having an electrical conductivity higher than the electrical conductivity of the nonmetallic substrate, said outer layer being galvanically incompatible with said nonmetallic substrate; andan interface layer consisting of a boron fiber with resin layered directly onto said nonmetallic, composite substrate, and said outer layer being attached directly to an outer surface of said interface layer, said interface layer having a higher electrical conductivity than said nonmetallic substrate and being highly galvanically compatible with said nonmetallic substrate and highly galvanically compatible with said outer layer. 6. The structural assembly of claim 5, wherein the nonmetallic substrate comprises a carbon-reinforced plastic. 7. The structural assembly of claim 5, wherein the outer layer is a nonferrous metal. 8. The structural assembly of claim 7, wherein the outer layer comprises an expanded foil. 9. The structural assembly of claim 8, wherein the nonferrous metal is aluminum. 10. The structural assembly of claim 5, wherein the resin comprises a thermoset resin or a thermoplastic resin. 11. The structural assembly of claim 10, wherein the boron fibers comprise pre-impregnated composite fibers. 12. The structural assembly of claim 11, wherein the boron fibers include a fully borided- tungsten core. 13. The structural assembly of claim 5, further comprising a surfacer permeating said outer layer. 14. The structural assembly of claim 5, wherein said nonmetallic substrate comprises a carbon reinforced plastic, said interface layer comprises a pre-impregnated tape including a thermoset resin and a unidirectional boron fiber, said outer layer comprises an expanded aluminum foil and said pre-impregnated tape is galvanically compatible with said nonmetallic substrate and said outer layer. 15. The structural assembly of claim 14, wherein said aircraft structure is selected from the group consisting of: a wing;a tail structure;a nose portion;a fairing;an engine nacelle; anda fuselage section. 16. A method of increasing the electrical conductivity of an aircraft having a substrate with low electrical conductivity, the method comprising: applying a resin tape consisting of pre-impregnated boron fibers directly to a portion of said substrate;applying an expanded aluminum foil directly to said tape and over said substrate, said expanded aluminum foil having a higher electrical conductivity than said substrate, whereby said resin tape is highly galvanically compatible with said substrate and highly galvanically compatible with said expanded aluminum foil; andapplying a filler to said expanded aluminum foil to create an aerodynamic surface. 17. The method of claim 16, wherein the portion of said substrate is selected from the group consisting of: a wing;a tail structure;a nose portion;a fairing;an engine nacelle; anda fuselage section. 18. The method of claim 17, wherein said expanded aluminum foil is applied to said portion of said substrate in overlapping sheets. 19. The method of claim 18, wherein said resin tape is applied to locations where said sheets overlap. 20. The method of claim 18, wherein said resin tape is applied to the terminal regions of said sheets.