IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0424811
(2009-04-16)
|
등록번호 |
US-8118260
(2012-02-21)
|
우선권정보 |
ES-200803103 (2008-10-31) |
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
Oblon, Spivak, McClelland, Maier & Neustadt, L.L.P.
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
8 |
초록
▼
A fitting for trimming the horizontal stabilizer of an aircraft, made of composite material, the fitting including side walls of a torsion box as well as joining elements which join the fitting to the frames of the tail fuselage of the aircraft, the side walls being joined together by a central elem
A fitting for trimming the horizontal stabilizer of an aircraft, made of composite material, the fitting including side walls of a torsion box as well as joining elements which join the fitting to the frames of the tail fuselage of the aircraft, the side walls being joined together by a central element which includes a first end part joined to the first side wall of the fitting, a second end part joined to the second side wall of the fitting and a central part which joins together the end parts, the fitting includes end elements which are joined to the side walls on their outer face, the fitting having, owing to its greater rigidity in response to side load and vertical load stresses which tend to close the side walls, its greater integration and the simplicity of the load path, an optimum structural behavior in response to the aircraft stresses.
대표청구항
▼
1. A fitting made of composite material for trimming a horizontal stabilizer of an aircraft with respect to a tail fuselage of the aircraft, wherein the fitting includes side walls of a torsion box as well as joining units which join the fitting to the frames of the tail fuselage of the aircraft, sa
1. A fitting made of composite material for trimming a horizontal stabilizer of an aircraft with respect to a tail fuselage of the aircraft, wherein the fitting includes side walls of a torsion box as well as joining units which join the fitting to the frames of the tail fuselage of the aircraft, said side walls being joined together by a central element which includes a first end part joined to a first side wall of the fitting, a second end part joined to a second side wall of the fitting, and a central part which joins together said end parts, the fitting includes end elements which are joined to said side walls on their outer face, said fitting having, owing to its greater rigidity in response to side load and vertical load stresses which try to close the side walls, its greater integration and the simplicity of the load path, an optimum structural behaviour in response to the aircraft loads. 2. The fitting according to claim 1, wherein the side walls of the fitting are joined together by an upper section constituting a single U-shaped integrated part which allows the side walls to be joined directly, without the need of additional parts, to a skin of the tail fuselage of the aircraft by the upper section, improving moreover the behaviour of the fitting in response to the side load since the U-shaped cross section provides a better support for the side walls of the fitting. 3. The fitting according to claim 1, wherein each side wall has, on each side of the central element, zones intended to prevent buckling of the side walls. 4. The fitting according to claim 1, wherein the end elements have an overall cross section in the form of an omega. 5. The fitting according to claim 1, further comprising an additional laminate which copies the geometrical form of the said end elements is added to the end elements, forming a single piece with the end elements, so that possible problems of separation of the end elements and the side walls are avoided. 6. The fitting according to claim 5, wherein the additional laminate is made of composite material. 7. The fitting according to claim 1, further comprising a primary fastening which includes in turn through-holes which are aligned and respectively located in primary lugs. 8. The fitting according to claim 7, wherein the through-holes are arranged in reinforced zones of the end elements, and the through-holes being arranged in reinforced zones of the side walls. 9. The fitting according to claim 8, wherein the reinforced zones of the end elements and the side walls are zones of greater thickness. 10. The fitting according to claim 8, wherein the reinforced zones of the end elements and the side walls are zones provided with a hybrid titanium-CFRP laminate. 11. The fitting according to claim 1, further comprising a secondary fastening which in turn comprises through-holes situated in the central element. 12. The fitting according to claim 11, wherein the secondary fastening of the fitting is reinforced with a hybrid titanium-CFRP laminate. 13. The fitting according to claim 11, wherein the secondary fastening of the fitting is a zone of greater thickness.
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