Lightning and corrosion protection arrangement in an aircraft structural component
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64D-045/02
F16B-005/04
출원번호
US-0033410
(2011-02-23)
등록번호
US-9016615
(2015-04-28)
우선권정보
ES-201031838 (2010-12-14)
발명자
/ 주소
Granado Macarrilla, José Orencio
Martínez Valdegrama, Vincente
Lozano Sevilla, Alberto
Casares Rodríguez, Daniel
출원인 / 주소
Airbus Operations S.L.
대리인 / 주소
Michael Best & Friedrich LLP
인용정보
피인용 횟수 :
0인용 특허 :
2
초록▼
A lightning and corrosion protection arrangement for a joint between an outer metallic part (11) and an aircraft structural component (13) completely or partially made of CFRP by means of a row of metallic rivets (15), that comprise inner and outer metallic layers (21, 25) and an intermediate dielec
A lightning and corrosion protection arrangement for a joint between an outer metallic part (11) and an aircraft structural component (13) completely or partially made of CFRP by means of a row of metallic rivets (15), that comprise inner and outer metallic layers (21, 25) and an intermediate dielectric layer (23), the inner metallic layer (21) in contact with said structural component (13) being thinner and bigger than the outer metallic layer (21) in contact with the metallic part (11), the intermediate dielectric layer (23) extending in an area bigger than the area of the foot (12) of the metallic part (11) by a predetermined minimum linear distance D1 between its edges, the outer metallic layer (25) extending in an area bigger than the area of the intermediate dielectric layer (23) by a predetermined minimum linear distance D2 between its edges.
대표청구항▼
1. A lightning and corrosion protection system for an aircraft, the system comprising: an aircraft structural component comprised of carbon fiber reinforced plastic, wherein the aircraft structural component defines an outer surface of the aircraft, and wherein the aircraft structural component incl
1. A lightning and corrosion protection system for an aircraft, the system comprising: an aircraft structural component comprised of carbon fiber reinforced plastic, wherein the aircraft structural component defines an outer surface of the aircraft, and wherein the aircraft structural component includes an opening therethrough;a metallic part extending substantially parallel to the aircraft structural component;a metallic rivet coupling the metallic part to the aircraft structural component, wherein the metallic rivet is inserted through the opening;an inner metallic layer coupled to the outer surface of the aircraft structural component;an outer metallic layer having one side coupled to a surface of the metallic part and having an opposite side sealed directly to the inner metallic layer; anda dielectric layer interposed between the inner and outer metallic layers, wherein the inner metallic layer extends in an area greater than the outer metallic layer, the dielectric layer extends in an area greater than the metallic part and wherein the outer metallic layer extends in an area greater than the dielectric layer. 2. A system as set forth in claim 1, wherein the inner metallic layer is thinner than the outer metallic layer. 3. A system as set forth in claim 1, wherein the metallic part defines a metallic part edge, the dielectric layer defines a dielectric layer edge, and the dielectric layer edge is offset relative to the metallic part edge by a predetermined distance D1. 4. A system as set forth in claim 3, wherein the predetermined distance D1 is about 25 mm. 5. A system as set forth in claim 1, wherein the outer metallic layer defines an outer metallic layer edge, the dielectric layer defines a dielectric layer edge, and the outer metallic layer edge is offset relative to the dielectric layer edge by a predetermined distance D2. 6. A system as set forth in claim 5, wherein the predetermined distance D2 is about 50 mm. 7. A system as set forth in claim 1, wherein the inner and outer metallic layers each include expanded copper foil grids. 8. A system as set forth in claim 1, wherein the inner metallic layer is associated with a density of 50 gr/m2 to 100 gr/m2 and the outer metallic layer is associated with a density of 700 gr/m2 to 900 gr/m2. 9. A system as set forth in claim 1, wherein the dielectric layer includes fiberglass. 10. A system as set forth in claim 1, wherein the aircraft structural component includes an aircraft wing skin. 11. A system as set forth in claim 1, wherein the metallic part includes a drip fence. 12. A lightning and corrosion protection arrangement for applying between an aircraft wing skin and a metallic drip fence, the arrangement comprising: an inner metallic layer coupled to an outer surface of the aircraft wing skin;an outer metallic layer coupled to a surface of the metallic drip fence, wherein the outer metallic layer is sealed directly to the inner metallic layer; anda dielectric layer embedded between the inner and outer metallic layers, wherein the inner and outer metallic layers and the dielectric layers each include an opening therethrough, and wherein the openings accommodate a rivet connecting the aircraft wing skin and the metallic drip fence. 13. An arrangement as set forth in claim 12, wherein the inner metallic layer is thinner than the outer metallic layer. 14. An arrangement as set forth in claim 12, wherein the inner metallic layer defines an inner surface area, the outer metallic layer defines an outer surface area, and the inner surface area is greater than the outer surface area. 15. An arrangement as set forth in claim 12, wherein the outer metallic layer defines an outer metallic layer edge, the dielectric layer defines a dielectric layer edge, and the outer metallic layer edge is offset relative to the dielectric layer edge by a predetermined distance D2. 16. An arrangement as set forth in claim 15, wherein the predetermined distance D2 is about 50 mm. 17. An arrangement as set forth in claim 12, wherein the inner and outer metallic layers each include expanded copper foil grids. 18. An arrangement as set forth in claim 12, wherein the inner metallic layer is associated with a density of 50 gr/m2 to 100 gr/m2 and the outer metallic layer is associated with a density of 700 gr/m2 to 900 gr/m2. 19. An arrangement as set forth in claim 12, wherein the dielectric layer includes fiberglass.
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이 특허에 인용된 특허 (2)
Olson Glenn O. (Seattle WA), Composite aircraft structure having lightning protection.
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