[특허]Ice protection system for a multi-segment aircraft component

Rohr, Inc.; Goodrich Corporation

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Ice protection system for a multi-segment aircraft component

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-015/12
미국특허분류(USC)	244/134.D
출원번호	UP-0963014 (2007-12-21)
등록번호	US-7837150 (2011-01-22)
발명자 / 주소	Zecca, Joseph Christopher Botura, Galdemir Cezar Burkett, Brian Bobby Hubert, Claude Marc Layland, Michael John Olson, Timothy Robert Roman, James Michael
출원인 / 주소	Rohr, Inc. Goodrich Corporation
대리인 / 주소	Womble Carlyle Sandridge & Rice, PLLC
인용정보	피인용 횟수 : 6 인용 특허 : 50

초록
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An aircraft component includes a first segment having a first leading edge surface that extends to a first end of the first segment. The aircraft component also includes a second segment having a second leading edge surface that extends to a second end of the second segment. The second end is substantially adjacent to the first end of the first segment, and is connected to the first end. The first leading edge surface includes electrical resistance heating that extends to the first end of the first segment. In addition, the second leading edge surface includes electrical resistance heating that extends to the second end of the second segment. The electrical resistance heating is capable of providing ice protection heating immediately on either side of a juncture between the connected first and second ends.

대표
청구항
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What is claimed is: 1. An aircraft component comprising: (a) a first segment having a first leading edge surface extending to a first end of the first segment; (b) a second segment having a second leading edge surface extending to a second end of the second segment, wherein the second end is substantially adjacent to the first end of the first segment; (c) wherein the first leading edge surface includes at least one first electrical heating element that extends at least to the first end of the first segment, and the second leading edge surface includes at least one second electrical heating element that extends at least to the second end of the second segment; and (d) wherein at least a portion of each of the first and second electrical heating elements is disposed between the first and second ends of the first and second segments. 2. An aircraft component according to claim 1 wherein the first leading edge surface further includes acoustic treatment extending to the first end of the first segment, and the second leading edge surface further includes acoustic treatment extending to the second end of the second segment. 3. An aircraft component according to claim 1 wherein the first electrical heating element includes a first perforated portion that substantially extends at least to the first end of the first segment, and wherein the second electrical heating element includes a second perforated portion that substantially extends at least to the second end of the second segment. 4. A method of joining first and second aircraft components to form a leading edge of an aircraft surface, the method comprising: (a) providing a first component having a first exterior surface, a first end, and a first electric ice protection heater element immediately adjacent the first end; (b) providing a second component having a second exterior surface, a second end, and a second electric ice protection heater element immediately adjacent the second end; and (c) joining the first end of the first component to the second end of the second component such that the first and second exterior surfaces combine to form a substantially continuous and selectively heatable leading edge surface along a juncture between the first and second ends; wherein at least a portion of each of the first and second electric ice protection heater elements is disposed between the first and second ends of the first and second components. 5. A method according to claim 4 comprising joining the first end to the second end with at least one mechanical fastener. 6. A method according to claim 4 wherein the first and second components comprise portions of an aircraft nacelle. 7. A method according to claim 4 wherein at least the first component is formed from a plurality of bonded composite layers, and wherein the first electric ice protection heater element is disposed between at least two of the bonded composite layers. 8. An aircraft component comprising: (a) a first segment comprising a first exterior surface, a first end, and a first electric heater element having a first edge proximate to the first end; (b) a second segment comprising a second exterior surface, a second end, and a second electric heater element having a second edge proximate to the second end, wherein the second end is joined to the first end such that the first external surface and the second external surface combine to form at least a portion of a substantially continuous leading edge surface; (c) a first bus bar connected to the first edge of the first heater element; and (d) a second bus bar connected to the second edge of the second heater element; (e) wherein the first and second bus bars are disposed between the first end and the second end when the first end is joined to the second end. 9. An aircraft component according to claim 8 wherein the first and second segments combine to form at least a portion of an aircraft nacelle. 10. An aircraft component according to claim 8 wherein: (a) the first segment comprises a first plurality of layers including a first outermost layer, and wherein the first electric heater element is disposed beneath at least the first outermost layer; and (b) the second segment comprises a second plurality of layers including a second outermost layer, and wherein the second electric heater element is disposed beneath at least the second outermost layer. 11. An aircraft component according to claim 10 wherein the first and second pluralities of layers comprise bonded composite layers, and wherein the first and second electric heater elements each comprise a graphite layer disposed within the bonded composite layers. 12. An aircraft component according to claim 10 wherein a first open cell core is disposed beneath the first plurality layers, and a second open cell core is disposed beneath the second plurality of layers, and wherein a plurality of perforations extend through the first and second pluralities of layers and the first and second electric heater elements to the first and second open cell cores. 13. An aircraft component according to claim 10 and further comprising a first flange portion on the first end of the first segment, a second flange portion on the second end of the second segment, and at least one fastener at least partially connecting the first flange portion to the second flange portion. 14. An aircraft component according to claim 8 wherein the first and second electric heater elements are configured to selectively heat portions of the substantially continuous leading edge surface that border a joint between the first and second ends. 15. An aircraft component according to claim 8 wherein the first and second electric heater elements are configured to selectively heat a gap between the first and second ends. 16. An aircraft engine nacelle having a circumferentially extending inlet lip, the inlet lip comprising: (a) a first circumferentially extending inlet lip section having a first circumferentially extending lip surface and an axially extending first edge surface, and a second circumferentially extending inlet lip section having a second circumferentially extending lip surface and an axially extending second edge surface, the first and second inlet lip sections being arranged such that the first and second edge surfaces are adjacent to each other and define a gap therebetween; (b) a first heater element embedded in the first inlet lip section and extending along the first lip surface and the first edge surface, and a second heater element embedded in the second inlet lip section and extending along the second lip surface and the second edge surface; and (c) a splice plate extending across the gap between the first and second edge surfaces, and securing the first and second inlet lip sections together. 17. An aircraft engine nacelle according to claim 16 wherein the first and second inlet lip sections each comprise a honeycomb core. 18. An aircraft engine nacelle according to claim 17 wherein the first and second heater elements each include a plurality of perforations that provide acoustic communication with cells of one of the honeycomb cores. 19. An aircraft engine nacelle according to claim 16 and further including at least one bus strip that extends into the gap between the first and second edge surfaces. 20. An aircraft engine nacelle according to claim 16 wherein the first and second heater elements comprise graphite. 21. An aircraft component comprising: (a) a first segment having a first leading edge surface extending to a first end of the first segment; (b) a second segment having a second leading edge surface extending to a second end of the second segment, wherein the second end is substantially adjacent to the first end of the first segment; (c) wherein the first leading edge surface includes at least one first electrical heating element that extends at least to the first end of the first segment, and the second leading edge surface includes at least one second electrical heating element that extends at least to the second end of the second segment; and (d) wherein the first end of the first segment and the second end of the second segment are at least partially connected by at least one splice member that extends across a gap between the first end and the second end.

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Ice protection system for a multi-segment aircraft component

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Ice protection system for a multi-segment aircraft component

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