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1. 发明授权

US10399663B2 Integrated ribs for central wing box 有权
公开(公告)号：US10399663B2
公开(公告)日：2019-09-03
申请号：US15255639
申请日：2016-09-02
申请人： AIRBUS OPERATIONS (S.A.S.)
发明人： Denis Soula , Matthieu Plet , Javier Maqueda Lahoz
IPC分类号： B64C3/18 , B64C1/06 , B64C1/26 , B64C3/22
摘要： A central wing box for an aircraft, including a top panel, a bottom panel, a front spar, a rear spar, and at least one secondary rib. A secondary rib includes two stiffeners, a first stiffener extending adjacent to the top panel and to one of the front spar and the rear spar, and a second stiffener extending adjacent to the bottom panel and to the other of the front spar and the rear spar. A reduced number of components can be employed, thereby simplifying the construction of the central wing box of an aircraft, particularly the installation of the secondary ribs.

2. 发明授权

US09796142B2 Method for manufacturing a part made of composite material for an aircraft structure by pultrusion and cocuring 有权
公开(公告)号：US09796142B2
公开(公告)日：2017-10-24
申请号：US14706660
申请日：2015-05-07
申请人： Airbus Operations (S.A.S.)
发明人： Denis Soula , Jérome Colmagro , Matthieu Plet
IPC分类号： B29C70/52 , B29C35/02 , B29D99/00 , B29C70/44 , B29C70/46 , B29C70/54 , B29C70/68 , B29C70/86 , B29C65/00 , F16C7/02 , B29L31/06
CPC分类号： B29C70/523 , B29C35/0277 , B29C66/5324 , B29C66/5344 , B29C66/71 , B29C66/721 , B29C66/7212 , B29C66/72141 , B29C66/73754 , B29C66/73941 , B29C70/446 , B29C70/462 , B29C70/52 , B29C70/545 , B29C70/68 , B29C70/865 , B29D99/0003 , B29D99/0046 , B29L2031/06 , B29L2031/3076 , F16C7/026 , Y02T50/43 , B29K2063/00 , B29K2307/04
摘要： The manufacture of structural elements for aircraft requires the use of complex and costly methods, particularly in the case of parts of elongate overall shape and variable thickness or cross section made of composite material. The disclosure herein proposes to overcome this problem by a method that allows the manufacture of a structural part from a preform made of composite material of simple shape obtained by pultrusion and of one or more reinforcing elements made of composite material and secured by cocuring with the preform to a region of this preform which region is to be reinforced.

3. 发明授权

US11872769B2 Method for manufacturing connecting members for connecting an aircraft wing to a center wing box, using preforms 有权
公开(公告)号：US11872769B2
公开(公告)日：2024-01-16
申请号：US16779883
申请日：2020-02-03
申请人： AIRBUS OPERATIONS S.A.S.
发明人： Denis Soula , Tanguy Vercamer , Jago Pridie
IPC分类号： B29C65/70 , B29C65/02 , B29C65/00 , B29C70/48 , B64C1/26 , B29L31/30 , B29K307/04 , B29K309/08
CPC分类号： B29C65/70 , B29C65/02 , B29C66/721 , B29C70/48 , B64C1/26 , B29K2307/04 , B29K2309/08 , B29L2031/3085
摘要： A method is disclosed for manufacturing connecting members for connecting an aircraft wing to a center wing box, using preforms. The method involves a step of manufacturing at least one preform made of composite material forming the connecting member, and a step of assembling the preform or preforms by heat treatment to form the connecting member. The manufacturing method makes it possible, simply and quickly, to manufacture a connecting member that contributes to the connection between a center wing box of an aircraft and a wing of the aircraft.

4. 发明授权

US09199719B2 Keel beam of an aircraft 有权
标题翻译：一架飞机的龙骨梁
公开(公告)号：US09199719B2
公开(公告)日：2015-12-01
申请号：US13888952
申请日：2013-05-07
申请人： AIRBUS OPERATIONS (S.A.S)
发明人： Yves Durand , Denis Soula , Jérôme Colmagro
IPC分类号： B64C3/00 , B64C3/18 , B64C1/06 , B64C1/26
CPC分类号： B64C3/185 , B64C1/065 , B64C1/26
摘要： A keel beam connected to a central wing box of an aircraft and ensuring the connection between a front structure and a rear structure of an aircraft is characterized in that it includes, on the one hand, a U-shaped body with a horizontal base and two solid lateral walls, and on the other hand, a cover which has a U shape oriented in the same manner as the body, with a base in the lower portion and curved edges, the ends of which are oriented upward so that each curved edge includes an outer surface flattened against and fixed to the inner surface of the lateral walls in order to define, with the body, a closed section, the cover including openings for accessing the inside of the keel beam.
摘要翻译：连接到飞行器的中央翼盒并且确保飞机的前部结构和后部结构之间的连接的龙骨梁的特征在于，其一方面包括具有水平基部和两个的U形主体另一方面，具有与主体相同的U形取向的盖，底部位于下部，弯曲的边缘的端部朝向上方，使得每个弯曲的边缘包括外表面被平坦化并固定到侧壁的内表面，以便在主体上限定封闭部分，盖包括用于进入龙骨梁内部的开口。

5. 发明申请

US20150321429A1 METHOD FOR MANUFACTURING A PART MADE OF COMPOSITE MATERIAL FOR AN AIRCRAFT STRUCTURE BY PULTRUSION AND COCURING 有权
标题翻译：制造用于飞机结构和复合材料的复合材料零件制造方法
公开(公告)号：US20150321429A1
公开(公告)日：2015-11-12
申请号：US14706660
申请日：2015-05-07
申请人： Airbus Operations (S.A.S.)
发明人： Denis Soula , Jérome Colmagro , Matthieu Plet
IPC分类号： B29C70/52
CPC分类号： B29C70/523 , B29C35/0277 , B29C66/5324 , B29C66/5344 , B29C66/71 , B29C66/721 , B29C66/7212 , B29C66/72141 , B29C66/73754 , B29C66/73941 , B29C70/446 , B29C70/462 , B29C70/52 , B29C70/545 , B29C70/68 , B29C70/865 , B29D99/0003 , B29D99/0046 , B29L2031/06 , B29L2031/3076 , F16C7/026 , Y02T50/43 , B29K2063/00 , B29K2307/04
摘要： The manufacture of structural elements for aircraft requires the use of complex and costly methods, particularly in the case of parts of elongate overall shape and variable thickness or cross section made of composite material. The disclosure herein proposes to overcome this problem by a method that allows the manufacture of a structural part from a preform made of composite material of simple shape obtained by pultrusion and of one or more reinforcing elements made of composite material and secured by cocuring with the preform to a region of this preform which region is to be reinforced.
摘要翻译：用于飞机的结构元件的制造需要使用复杂和昂贵的方法，特别是在细长整体形状和可变厚度或由复合材料制成的横截面的部分的情况下。本文的公开内容旨在通过一种方法来克服这个问题，该方法允许从由拉挤成型获得的简单形状的复合材料制成的预成型件和由复合材料制成的一个或多个增强元件制成的结构部件，并通过与预成型件共同固化而固定到该预制件的该区域要被加强的区域。

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