초록 ▼

An aircraft panel assembly 10 is provided, including a panel core 28, a plurality of pre-preg layers 30 surrounding the panel core 28 forming an internal layer of plies 34, at least one metal foil layer 38 positioned on an outer layer 40 of the internal layer of plies 34. The at least one metal foi

An aircraft panel assembly 10 is provided, including a panel core 28, a plurality of pre-preg layers 30 surrounding the panel core 28 forming an internal layer of plies 34, at least one metal foil layer 38 positioned on an outer layer 40 of the internal layer of plies 34. The at least one metal foil layer 38 providing an electrical conduit between the outer surface 24 of the aircraft panel assembly 10 and a sub-structure 26 for grounding.

대표청구항 ▼

What is claimed is: 1. An aircraft panel assembly comprising: a panel core; a plurality of pre-preg plies applied to said panel core forming an internal layer of plies, said plurality of pre-preg plies including an outer ply layer; at least one metal foil layer permanently applied to said outer p

What is claimed is: 1. An aircraft panel assembly comprising: a panel core; a plurality of pre-preg plies applied to said panel core forming an internal layer of plies, said plurality of pre-preg plies including an outer ply layer; at least one metal foil layer permanently applied to said outer ply layer of said internal layer of plies, said at least one metal foil layer providing an electrical conduit between an outer surface and a sub-structure contact surface of the aircraft panel assembly; and an outer surface skin applied to said at least one metal foil layer, said at least one metal foil layer positioned between said outer surface skin and said outer ply layer, said outer surface skin allowing current to pass through to said at least one metal foil. 2. An aircraft panel assembly as described in claim 1, wherein said outer surface skin comprises a composite surfacing film. 3. An aircraft panel assembly as described in claim 1, wherein said outer surface skin comprises adhesive. 4. An aircraft panel assembly as described in claim 1, further comprising: a periphery pre-preg layer applied between said outer surface skin and said at least one metal foil layer. 5. An aircraft panel assembly as described in claim 1, wherein said panel core comprises a honeycomb core. 6. An aircraft panel assembly as described in claim 1, further comprising: a plurality of filler ply layers positioned between said panel core and said at least one metal foil layer. 7. An aircraft panel assembly as described in claim 1, further comprising: an intermediate adhesive layer positioned between said internal layer of plies and said at least one metal foil layer. 8. An aircraft panel assembly as describe in claim 1, wherein said at least one metal foil layer comprises an aluminum foil. 9. An aircraft structure assembly comprising: a sub-structure; at least one aircraft panel assembly having an outer surface and a sub-structure contact surface, said at least one aircraft panel assembly comprising: a panel core; a plurality of pre-preg plies applied to said panel core forming an internal layer of plies, said plurality of pre-preg plies including an outer ply layer; at least one metal foil layer permanently applied to said outer ply layer of said internal layer of plies, said at least one metal foil layer providing an electrical conduit between said outer surface and said sub-structure contact surface such that current received during a lightning strike is transferred from said outer surface to said substructure; and an outer surface skin applied to said at least one metal foil layer, said at least one metal foil layer positioned between said outer surface skin and said outer ply layer, said outer surface skin allowing current to pass through to said at least one metal foil. 10. An aircraft structure assembly as described in claim 9, wherein said outer surface skin comprises a composite surfacing film. 11. An aircraft structure assembly as described in claim 9, wherein said outer surface skin comprises adhesive. 12. An aircraft structure assembly as described in claim 9, further comprising: a periphery pre-preg layer applied to said at least one metal foil layer. 13. An aircraft structure assembly as described in claim 9, wherein said panel core comprises a honeycomb core. 14. An aircraft structure assembly as described in claim 9, further comprising: a plurality of filler ply layers positioned between said panel core and said at least one metal foil layer. 15. An aircraft structure assembly as described in claim 9, further comprising: an intermediate adhesive layer positioned between said internal layer of plies and said at least one metal foil layer. 16. An aircraft structure assembly as described in claim 9, wherein said at least one aircraft panel assembly comprises a forward box panel. 17. An aircraft structure assembly as described in claim 9, wherein said at least one aircraft panel assembly comprises a trailing edge panel. 18. A method of preventing damage from current generated by a lightning strike on an aircraft structure assembly including a sub-structure and an aircraft panel assembly comprising: transferring the current from the lightning strike from an outer surface to the sub-structure including: transferring the current through an outer surface skin of the aircraft panel assembly to at least one metal foil layer, said at least one metal foil layer permanently positioned over a plurality of pre-preg plies covering a honeycomb core; and transferring the current from said at least one metal foil layer to the sub-structure. 19. An aircraft panel assembly comprising: a panel core; a plurality of pre-preg plies permanently applied to said panel core forming an internal layer of plies, said plurality of pre-preg plies including an outer ply layer; at least one metal foil layer applied to said outer ply layer of said internal layer of plies, said at least one metal foil layer providing an electrical conduit between an outer surface and a sub-structure contact surface of the aircraft panel assembly; an outer surface skin applied to said at least one metal foil layer, said at least one metal foil layer positioned between said outer surface skin and said outer ply layer, said outer surface skin allowing current to pass through to said at least one metal foil; and a periphery pre-peg layer applied between said outer surface skin and said at least one metal foil layer.