[특허]Leading edge element of aircraft, method for manufacturing one, wing and stabilizer

Patria Acostructures Oy

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Leading edge element of aircraft, method for manufacturing one, wing and stabilizer

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-003/18
미국특허분류(USC)	244/123.14; 244/123.1; 244/123.8
출원번호	US-0921037 (2009-03-12)
등록번호	US-8434719 (2013-05-07)
우선권정보	FI-20080208 (2008-03-13)
국제출원번호	PCT/FI2009/050197 (2009-03-12)
§371/§102 date	20101115 (20101115)
국제공개번호	WO2009/112641 (2009-09-17)
발명자 / 주소	Mäkelä, Juha
출원인 / 주소	Patria Acostructures Oy
대리인 / 주소	Ladas & Parry LLP
인용정보	피인용 횟수 : 0 인용 특허 : 2

초록

A leading edge element, a method for manufacturing one, and an aircraft wing and stabilizer furnished with the leading edge element. The leading edge element is an elongate piece that comprises a skin plate and at least one longitudinal stiffener. The shape of the front edge of the skin plate is closed and the tail edge is open. The stiffener is fastened between the inner surfaces of the skin plate. Between the inner surface of the skin plate of the outermost longitudinal stiffener, there is a longitudinal space free of transverse stiffeners.

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1. A leading edge element of an aircraft, which is arrangeable on the leading edge of a wing or stabilizer and which comprises: a skin plate which has a closed front edge and an open tail edge and which comprises an outer surface and an inner surface,at least one stiffener comprising an elongate piece that is fastened to the inner surface of the skin plate with a length of the elongate piece disposed along a length of the leading edge element such that the inner surface of the skin plate and the elongate piece define an elongate space on the front edge of the leading edge element, wherein the elongate piece comprises at least one transverse through-groove that extends a predefined distance along a height of the elongate piece. 2. A leading edge element as claimed in claim 1, wherein the elongate space on the front edge of the leading edge element is hollow. 3. A leading edge element as claimed in claim 1, wherein the elongate space on the front edge of the leading edge element is filled with at least one filling agent. 4. A leading edge element as claimed in claim 1, wherein said elongate piece is plate-like and comprises fastening sections along longitudinal edges thereof that fasten to the inner surface of the skin plate. 5. A leading edge element as claimed in claim 1, wherein, in addition to the at least one stiffener, the leading edge element comprises at least a second stiffener comprising an elongate piece having a length disposed along the length of the leading edge, the elongate piece of the second stiffener being arranged at a distance from the elongate piece of the at least one stiffener and being parallel thereto. 6. A leading edge element as claimed in claim 1, wherein said elongate piece is plate-like and comprises fastening sections along longitudinal edges thereof, wherein each of the fastening sections extends from the longitudinal edges in the same direction, wherein the leading edge element comprises, in addition to said at least one stiffener, a second stiffener that comprises an elongate piece with fastening sections, the elongate piece of the second stiffener having a length disposed along the length of the leading edge element and being parallel to and spaced from the elongate piece of the at least one stiffener, the fastening sections of the elongate piece of the second stiffener extending in the same direction as the fastening sections of the elongate piece of the at least one stiffener. 7. A leading edge element as claimed in claim 1, wherein the elongate piece is plate-like and comprises fastening sections along respective longitudinal edges thereof, wherein each of the fastening sections extends from the longitudinal edges in the same direction, said direction being transverse to the length of the elongate piece, wherein the leading edge element comprises at least a second stiffener comprising an elongate piece having a length that is disposed along a length of the leading edge element, and wherein the elongate piece of the at least one stiffener and the elongate piece of the second stiffener are arranged so that their respective fastening sections extend in opposite directions. 8. A leading edge element as claimed in claim 1, wherein the at least one stiffener is a tubular structure. 9. A leading edge element as claimed in claim 1, wherein the at least one stiffener is a tubular structure, andwherein the at least one stiffener comprises a first fastening surface and a second fastening surface arrangeable against the inner surface of the skin plate and planar side walls connecting the fastening surfaces. 10. A leading edge element as claimed in claim 1, wherein the at least one stiffener is a tubular structure with ends, and the ends of the tubular stiffener comprise transverse flanges, and the tubular stiffener and its end flanges form together a box-type structure. 11. A leading edge element as claimed in claim 1, wherein the at least one stiffener has elongate top and bottom edges, the through-groove extends from the bottom edge of the stiffener toward the top edge, and the through-groove ends before the top edge of the stiffener. 12. A leading edge element as claimed in claim 1, wherein the at least one stiffener comprises at least two stiffener components that are arranged consecutively along a length of the at least one stiffener with a gap of predetermined size between the at least two stiffener components. 13. A leading edge element as claimed in claim 1, wherein the skin plate and the at least one stiffener are separate components that are made in separate steps and fastened to each other when the leading edge element is assembled. 14. A leading edge element as claimed in claim 1, wherein the skin plate and the at least one stiffener of the leading edge element are manufactured at the same time and are integral with each other. 15. A leading edge element as claimed in claim 1, wherein the at least one stiffener comprises at least one transverse flange that is fastenable to the support structure of a wing or stabilizer to transmit forces from the stiffener to the support structure. 16. A leading edge element as claimed in claim 1, wherein the at least one stiffener is made of a composite material. 17. A method for manufacturing a leading edge element of a wing or stabilizer of an aircraft, the method comprising forming an elongated skin plate with a uniform front edge and an open tail edge,fastening at least one stiffener comprising an elongated stiffener piece between respective portions of an inner surface of the skin plate with the elongated stiffener piece is disposed with a length of the elongated stiffener piece along a length of the leading edge element, wherein the elongated stiffener piece comprises at least one transverse through-groove that extends a predefined distance along a height of the elongated stiffener piece,wherein said at least one stiffener is closer to the front edge of the leading edge element than any other stiffener in the leading edge element such that there is an elongated space defined by the inner surface of the skin plate and the at least one stiffener on the front edge of the leading edge element, said elongated space being without stiffeners. 18. A method as claimed in claim 17, comprising: manufacturing the skin plate and the at least one stiffener in separate steps, the at least one stiffener being manufactured of a composite material, andassembling the leading edge element by fastening the at least one stiffener to the inner surface of the skin plate. 19. A method as claimed in claim 17, comprising: manufacturing the skin plate and the at least one stiffener of a composite material, andintegrating during manufacturing the skin plate and the at least one stiffener. 20. A method as claimed in claim 17, comprising: manufacturing the skin plate and the at least one stiffener of a composite material,and integrating during manufacturing the skin plate and the at least one stiffener,forming the skin plate against a mould surface, whereby an outer surface of the skin plate is formed against the mould and the inner surface is formed on an opposite side,arranging a core against the inner surface of the skin plate,forming an outermost stiffener layer on the core, hardening the leading edge element, andremoving the core. 21. An aircraft wing that comprises: at least one front spar on the leading edge side of the wing,at least one rear spar on the trailing edge of the wing, several wing ribs between the front spar and rear spar,a top skin plate and a bottom skin plate,several stringers between the skin plates and wing ribs, andat least one leading edge element arranged on the front side of the front spar, the at least one leading edge element comprising the leading edge element according to claim 1. 22. An aircraft stabilizer having a leading edge side and a trailing edge side that comprises: at least one front spar on the leading edge side of the stabilizer,at least one rear spar on the trailing edge side of the stabilizer,a plurality of stiffener elements between the front spar and rear spar,a plurality of skin plates,at least one leading edge element arranged on a front side of the front spar, the at least one leading edge element comprising the leading edge element of claim 1. 23. A leading edge element as claimed in claim 1, wherein the at least one stiffener has a U-shaped cross-section. 24. A leading edge element of an aircraft, which is arrangeable on the leading edge of a wing or stabilizer and which comprises: a skin plate comprising a closed front edge and an open tail edge and which comprises an outer surface and an inner surface,at least one stiffener comprising an elongate piece that is fastened to the inner surface of the skin plate with a length of the elongate piece disposed along a length of the leading edge element such that the inner surface of the skin plate and the elongate piece define an elongate space on the front edge of the leading edge element, wherein the at least one stiffener comprises at least one transverse through-groove that extends a predefined distance along a height of the stiffener, and the at least one stiffener has elongate top and bottom edges with the through-groove extending from the bottom edge of the stiffener toward the top edge, wherein the through-groove ends before the top edge of the stiffener.

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Leading edge element of aircraft, method for manufacturing one, wing and stabilizer

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Leading edge element of aircraft, method for manufacturing one, wing and stabilizer

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