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公开(公告)号：US09771140B2
公开(公告)日：2017-09-26
申请号：US14140511
申请日：2013-12-25
Applicant: Airbus Operations S.L.
Inventor： Elena Arevalo Rodriguez , Estelle Baligand
CPC classification number: B64C1/061 , B32B2605/18 , B64C1/064 , B64C1/12 , B64C1/1461 , B64C3/18 , B64C3/182 , B64C2001/0072 , Y02T50/43 , Y10T428/24008
Abstract: The invention provides an integrated aircraft structure, such as a fuselage, with reinforcing elements in areas of the structure that need them because they have openings or are subjected to high loads. The structure comprises a skin, a plurality of stringers and a plurality of frames with mouseholes for the passage of stringers at their crossing zones. The reinforcing elements are configured with a suitable shape to be superimposed to the stringers in said areas. A manufacturing processes of said integrated aircraft structure is also provided.
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公开(公告)号：US09637216B2
公开(公告)日：2017-05-02
申请号：US14585877
申请日：2014-12-30
Applicant: Airbus Operations S.L.
Inventor： Elena Arevalo Rodriguez
CPC classification number: B64C1/12 , B32B37/02 , B32B37/16 , B32B38/00 , B32B2038/0076 , B32B2305/34 , B32B2305/74 , B32B2605/18 , B64C1/061 , B64C1/064 , B64C2001/0072 , Y02T50/43
Abstract: An aircraft structure made of composite material, comprising a skin reinforced longitudinally with stringers, and frames perpendicular to the stringers, each stringer comprising a head and two webs, and each frame having recesses in its web for the passage of the longitudinal stringers, such that an internal preform is provided in the gap existing between each stringer and the skin, filling the gap.
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Patent Agency Ranking
3.发明授权公开(公告)号：US09216810B2
公开(公告)日：2015-12-22
申请号：US13688738
申请日：2012-11-29
Applicant: AIRBUS OPERATIONS S.L.
Inventor： Francisco Jose Cruz Dominguez , Elena Arevalo Rodriguez
Abstract: A frame of a fuselage section of an aircraft that receives external loads, such as the rear section that receives the loads of the tail planes, comprising a first sector configured specifically to withstand these external loads and a second sector along the remaining perimeter of the fuselage, said first sector comprising the following structural elements a) a foot piece to be joined to the fuselage skin; b) a head piece; c) a web comprising one or more fitting-pieces for receiving said external loads and a plurality of X-shaped pieces joined by its ends to said foot piece and said head piece; and d) two connecting pieces of the ends of said foot piece and said head piece with the second sector of the frame.
Abstract translation: 接收外部负载的飞机的机身部分的框架，例如接收尾翼的载荷的后部，包括专门承受这些外部载荷的第一部分和沿着机身的剩余周边的第二部分 所述第一部分包括以下结构元件：a）待接合到机身皮肤的脚件; b）头部件; c）一个网，其包括用于接收所述外部载荷的一个或多个配件件和由其端部连接到所述脚件和所述头部件的多个X形件; 以及d）所述脚件和所述头部件的端部的两个连接件与所述框架的第二部分。
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4.发明申请公开(公告)号：US20130140401A1
公开(公告)日：2013-06-06
申请号：US13688738
申请日：2012-11-29
Applicant: AIRBUS OPERATIONS S.L.
Inventor： Francisco Jose Cruz Dominguez , Elena Arevalo Rodriguez
Abstract: Frame of a fuselage section of an aircraft that receives external loads, such as the rear section that receives the loads of the tail planes, comprising a first sector (11) configured specifically to withstand these external loads and a second sector along the remaining perimeter of the fuselage, said first sector (11) comprising the following structural elements: a) a foot piece (21) to be joined to the fuselage skin (13); b) a head piece (23); c) a web (25) comprising one or more fitting-pieces (27, 27′) for receiving said external loads and a plurality of X-shaped pieces (31) joined by its ends to said foot piece (21) and said head piece (23); d) two connecting pieces (39, 39′) of the ends of said foot piece (21) and said head piece (23) with the second sector of the frame.
Abstract translation: 接收外部载荷的机身的机身部分的框架，例如接收尾翼的载荷的后部，包括专门承受这些外部载荷的第一部分（11），以及沿着其余周边的第二部分 所述第一扇区（11）包括以下结构元件：a）要连接到机身皮肤（13）的脚踏（21）; b）头部件（23）; c）包括用于接收所述外部载荷的一个或多个配件件（27,27'）的腹板（25）和由其端部连接到所述脚件（21）和所述头部的多个X形件（31） （23）; d）所述脚件（21）的端部和所述头部件（23）的端部的两个连接件（39,39'）与框架的第二部分。
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公开(公告)号：US11440634B2
公开(公告)日：2022-09-13
申请号：US16521057
申请日：2019-07-24
Applicant: AIRBUS OPERATIONS S.L.
Inventor： Elena Arevalo Rodriguez , Antonio Torres Esteban
Abstract: A frame (1) for fuselage shells of an aircraft, the fuselage comprising a skin (3) and stringers (4), the frame (1) including: a plurality of sections (5), the sections (5) being separated by intermediate gaps corresponding to the position of the stringers (4) in the fuselage, each section (5) having a multi-cell configuration constituted by several modular elements (6) of composite material arranged in longitudinal direction, and a continuous inner cap (7) on top of the sections (5) and the intermediate gaps.
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公开(公告)号：US20160185437A1
公开(公告)日：2016-06-30
申请号：US14979081
申请日：2015-12-22
Applicant: Airbus Operations S.L.
Inventor： Elena Arevalo Rodriguez
CPC classification number: B64C1/068 , B64C1/061 , B64C1/12 , B64C2001/0072 , B64D2041/002 , Y02T50/43
Abstract: A tail cone of an aircraft, more specifically a tail cone made of composite materials comprising an internal skin, an external skin surrounding the internal skin, longitudinal structural members located on the inner face of the internal skin in the longitudinal direction of the tail cone, and transversal structural members located between the external skin and the internal skin in the transverse direction of the tail cone.
Abstract translation: 飞机的尾锥，更具体地，由复合材料制成的尾锥，其包括内部皮肤，围绕内部皮肤的外部皮肤，沿着尾锥的纵向方向位于内部皮肤的内表面上的纵向结构构件， 横向结构构件位于尾锥的横向方向上位于外皮和内皮之间。
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公开(公告)号：US20150183504A1
公开(公告)日：2015-07-02
申请号：US14585877
申请日：2014-12-30
Applicant: Airbus Operations S.L.
Inventor： Elena Arevalo Rodriguez
CPC classification number: B64C1/12 , B32B37/02 , B32B37/16 , B32B38/00 , B32B2038/0076 , B32B2305/34 , B32B2305/74 , B32B2605/18 , B64C1/061 , B64C1/064 , B64C2001/0072 , Y02T50/43
Abstract: An aircraft structure made of composite material, comprising a skin reinforced longitudinally with stringers, and frames perpendicular to the stringers, each stringer comprising a head and two webs, and each frame having recesses in its web for the passage of the longitudinal stringers, such that an internal preform is provided in the gap existing between each stringer and the skin, filling the gap.
Abstract translation: 由复合材料制成的飞行器结构，包括纵向加强的桁条和垂直于纵梁的框架，每个纵梁包括头部和两个腹板，每个框架在其腹板中具有用于纵向纵梁通过的凹槽，使得 在每个桁条和皮肤之间存在的间隙中设置内部预制件，填充间隙。
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