초록 ▼

A system for protecting a composite-body aircraft from damage caused by lightning strikes includes a Faraday cage defined on the exterior surface of the aircraft body by a continuous, electrically conductive grid that extends to the outermost lateral periphery of the body. In one possible embodiment

A system for protecting a composite-body aircraft from damage caused by lightning strikes includes a Faraday cage defined on the exterior surface of the aircraft body by a continuous, electrically conductive grid that extends to the outermost lateral periphery of the body. In one possible embodiment in which the aircraft's body includes a plurality of composite panels that are joined at their adjacent edges by splice plates, the conductive grid may advantageously be formed by electrically conductive splice plates, e.g., of titanium, that have their respective, adjacent ends electrically connected to each other, e.g., with conductive straps and fasteners. The conductive grid provides preferential attachment points and conductive paths for lightning strikes on the surface of the aircraft, thereby shielding the interior of the grid from lightning damage. The conductive grid can optionally function as a ground return path for the aircraft's electrical system.

대표청구항 ▼

What is claimed is: 1. Apparatus for protecting a composite-body aircraft against damage from lightning strikes, comprising: an aircraft body including a plurality of composite panels; a first plurality of electrically conductive splice plates extending along junctions between adjacent ones of the

What is claimed is: 1. Apparatus for protecting a composite-body aircraft against damage from lightning strikes, comprising: an aircraft body including a plurality of composite panels; a first plurality of electrically conductive splice plates extending along junctions between adjacent ones of the composite panels at respective edges of the adjacent composite panels, the first plurality of electrically conductive splice plates abutting exterior surfaces of the composite panels; a second plurality of electrically conductive splice plates extending along the junctions between adjacent ones of the composite panels at respective edges of the adjacent composite panels, the second plurality of electrically conductive splice plates abutting interior surfaces of the composite panels; a plurality of electrically conductive straps; and a plurality of electrically conductive fasteners; wherein the straps and the fasteners mechanically and electrically couple adjacent ends of the splice plates to one another such that the splice plates form a continuous, electrically conductive grid about the aircraft body. 2. The apparatus of claim 1, wherein the continuous, electrically conductive grid extends to the outermost lateral periphery of the aircraft body. 3. The apparatus of claim 1, wherein the first plurality of electrically conductive splice plates comprise titanium. 4. The apparatus of claim 1, wherein the aircraft body comprises a blended-wing-body ("BWB") aircraft. 5. The apparatus of claim 1, wherein the plurality of composite panels comprise graphite fibers. 6. The apparatus of claim 1, wherein the aircraft body includes an electrical system, and wherein the electrically conductive grid comprises a ground return path of the electrical system. 7. A method for protecting a composite-body aircraft against damage from lightning strikes, comprising: coupling adjacent composite panels on an aircraft body to one another at respective edges of the adjacent composite panels using electrically conductive splice plates, electrically conductive straps and electrically conductive fasteners; wherein the straps and the fasteners mechanically and electrically couple adjacent ends of the splice plates to one another such that the splice plates form a continuous, electrically conductive grid about the aircraft body; and further wherein a first plurality of the electrically conductive splice plates extend along junctions between the adjacent composite panels and abut exterior surfaces of the composite panels, and a second plurality of the electrically conductive splice plates extend along the junctions between the adjacent composite panels and abut interior surfaces of the composite panels. 8. The method of claim 7, wherein the continuous, electrically conductive grid extends to the outermost lateral periphery of the aircraft body. 9. The method of claim 7, wherein the first plurality of the electrically conductive splice plates comprise titanium. 10. The method of claim 7, wherein the aircraft body comprises a blended-wing-body ("BWB") aircraft. 11. The method of claim 7, wherein the composite panel comprise graphite fibers. 12. The method of claim 7, wherein the aircraft body includes an electrical system, and wherein the electrically conductive grid comprises a ground return path of the electrical system. 13. An aircraft body comprising: a plurality of composite panels, adjacent pairs of the composite panels defining a V-shaped groove therebetween; and a plurality of electrically conductive splice plates disposed within the grooves such that an exterior surface of each splice plate is flush with exterior surfaces of the adjacent pair of composite panels; wherein adjacent ends of the splice plates are mechanically and electrically coupled to one another such that the splice plates form a continuous, electrically conductive grid about the aircraft body. 14. The aircraft body of claim 13, further comprising plurality of electrically conductive straps and a plurality of electrically conductive fasteners, wherein the straps and the fasteners in mechanically and electrically couple the adjacent ends of the splice plat is to one another. 15. The aircraft body of claim 13, wherein the electrically conductive splice plates comprise titanium. 16. The aircraft body of claim 13, wherein the aircraft body comprises a blended-wing-body ("BWB") aircraft. 17. The aircraft body of claim 13, wherein the continuous, electrically conductive grid extends to the outermost lateral periphery of the exterior surface of the aircraft body. 18. The aircraft body of claim 13, wherein the composite panels comprise graphite fibers. 19. The aircraft body of claim 13, wherein the aircraft body includes an electrical system, and the electrically conductive grid comprises a ground return path of the electrical system.