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31. 发明授权

US09387922B2 Main supporting structure of an aircraft lifting surface 有权
标题翻译：飞机提升面的主要支撑结构
公开(公告)号：US09387922B2
公开(公告)日：2016-07-12
申请号：US14083531
申请日：2013-11-19
申请人： Airbus Operations S.L.
发明人： Enrique Guinaldo Fernandez , Francisco Cruz Dominguez , Francisco Javier Honorato Ruiz , Paula Mas Mas , Iker Velez de Mendizabal Alonso , Carlos Garcia Nieto
IPC分类号： B64C3/18 , B64C5/02
CPC分类号： B64C3/187 , B64C3/185 , B64C5/02 , Y10T29/49622
摘要： An aircraft lifting surface with a main supporting structure comprising upper and lower faces defining its aerodynamic profile, front and rear faces oriented towards, respectively, the leading and trailing edges, a first set of transverse ribs extended from the front face to the rear face and a second set of transverse ribs crossing the front face and/or the rear face. The integration of leading and trailing edge ribs in the main supporting structure allows a weight and cost reduction of aircraft lifting surfaces. A manufacturing method of said main supporting structure is also disclosed.
摘要翻译：具有主支撑结构的飞行器提升表面包括限定其空气动力学轮廓的上表面和下表面，前表面和后表面分别面向前缘和后缘，第一组横向肋从前表面延伸到后表面，并且横过前表面和/或后表面的第二组横向肋。主支撑结构中的前缘和后缘肋骨的集成允许飞机提升表面的重量和成本降低。还公开了所述主支撑结构的制造方法。

32. 发明授权

US09381991B2 Highly integrated structure including leading and trailing edge ribs for an aircraft lifting surface 有权
标题翻译：高度一体化的结构，包括用于飞机提升表面的前缘和后缘肋骨
公开(公告)号：US09381991B2
公开(公告)日：2016-07-05
申请号：US14086424
申请日：2013-11-21
申请人： AIRBUS OPERATIONS S.L.
发明人： Enrique Guinaldo Fernandez , Francisco Cruz Dominguez , Francisco Javier Honorato Ruiz , Paula Más Más , Iker Vélez De Mendizábal Alonso , Carlos Garcia Nieto
IPC分类号： B64C1/00 , B64C3/00 , B64C5/00 , B64C3/18 , B29C70/30 , B64C3/20 , B64C5/02 , B29C35/02 , B29D99/00 , B29L31/30
CPC分类号： B64C3/182 , B29C35/0238 , B29C70/30 , B29D99/0014 , B29L2031/3085 , B64C3/185 , B64C3/187 , B64C3/20 , B64C5/02 , Y02T50/43
摘要： An aircraft lifting surface with a monolithic main supporting structure of a composite material including an upper skin having at least a part of the upper aerodynamic profile of the leading edge and/or of the trailing edge, a lower skin, a front spar, a rear spar, and leading edge ribs and/or a trailing edge ribs. The main supporting structure allows a weight and cost reduction of aircraft lifting surfaces.
摘要翻译：一种具有复合材料的整体主支撑结构的飞行器提升表面，其包括具有前缘和/或后缘的上空气动力学轮廓的至少一部分的上皮，下皮，前翼梁，后翼梁和前缘肋骨和/或后缘肋骨。主要的支撑结构允许飞机提升表面的重量和成本降低。

33. 发明授权

US09248905B2 Aircraft landing gear 有权
标题翻译：飞机起落架
公开(公告)号：US09248905B2
公开(公告)日：2016-02-02
申请号：US13894944
申请日：2013-05-15
申请人： AIRBUS OPERATIONS S.L. , AIRBUS SAS
发明人： Ludovic Gerard , Alejandro Gutiérrez García , Julián Maldonado
IPC分类号： B64C23/00 , B64C25/16 , B64D41/00 , B64C25/00
CPC分类号： B64C23/005 , B64C25/16 , B64C2025/003 , B64D41/007 , B64D2201/00
摘要： An aircraft (11) with at least an inflatable device (41) installed in a cavity (21) in its external surface which is equipped with a door (25) for opening/closing said cavity (21) is provided. The inflatable device (41), comprising a cushion (45) and a gas generator is configured for filling the cavity (21) with the cushion (45) when it is inflated with the gas supplied by said gas generator, without protruding from the cavity (21) for reducing the downstream air flow disturbances generated by said cavity (21) when the door (25) is open. The inflatable device (41) includes control means for inflating the cushion (45) in predetermined circumstances, being the door (25) open. The invention is particularly applicable to the cavities of the Main Landing Gear (31) for avoiding power losses to a Ram Air Turbine (51) placed behind it.
摘要翻译：提供一种具有安装在其外表面中的空腔（21）中的至少一个可充气装置（41）的飞行器（11），其配备有用于打开/关闭所述空腔（21）的门（25）。包括衬垫（45）和气体发生器的充气装置（41）构造成当用气体发生器供应的气体充气时，利用衬垫（45）填充空腔（21），而不会从空腔（21），用于当门（25）打开时减小由所述空腔（21）产生的下游空气流动干扰。充气装置（41）包括控制装置，用于在门（25）打开的情况下在预定情况下使垫子（45）充气。本发明特别适用于主起落架（31）的空腔，用于避免向放置在其后面的拉姆空气涡轮机（51）的功率损失。

34. 发明授权

US09242438B2 Tape laying tool and method used in manufacturing composite material parts 有权
标题翻译：复合材料零件制造中使用的铺带工具和方法
公开(公告)号：US09242438B2
公开(公告)日：2016-01-26
申请号：US14039122
申请日：2013-09-27
申请人： AIRBUS OPERATIONS S.L.
发明人： José David Cano Cediel , Ruth Chinarro Vera , Francisco Escobar Benavides , Pedro Nogueroles Viñes
IPC分类号： B29C70/32 , B32B37/02
CPC分类号： B32B37/02 , B29C70/32 , Y10T156/1043
摘要： A method of manufacturing composite material parts is provided. The method includes tape laying by means of fiber placement on the outer surface of a tape laying tool, such that at least one laminate with a geometry different from the end geometry of the part is obtained and forming the at least one laminate obtained in tape laying by means of a forming tool, such that the laminate acquires the end geometry of the part. The method also includes curing the at least one part.
摘要翻译：提供了制造复合材料部件的方法。该方法包括通过将光纤放置在带状铺设工具的外表面上进行铺带，使得至少一个几何形状与部件的端部几何形状不同的叠层，并形成至少一个层压板通过成形工具，使得层压板获得部件的端部几何形状。该方法还包括固化至少一个部分。

35. 发明授权

US09216810B2 Highly loaded frame of an aircraft fuselage with a lattice structured web 有权
标题翻译：具有格子网格的飞机机身的高度装载的框架
公开(公告)号：US09216810B2
公开(公告)日：2015-12-22
申请号：US13688738
申请日：2012-11-29
申请人： AIRBUS OPERATIONS S.L.
发明人： Francisco Jose Cruz Dominguez , Elena Arevalo Rodriguez
IPC分类号： B64C1/00 , B64C1/26 , B64C1/06
CPC分类号： B64C1/26 , B64C1/061
摘要： 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.
摘要翻译：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。

36. 发明申请

US20150053332A1 METHOD AND DEVICE FOR MANUFACTURING COMPOSITE MATERIAL PARTS 有权
标题翻译：用于制造复合材料部件的方法和装置
公开(公告)号：US20150053332A1
公开(公告)日：2015-02-26
申请号：US14388555
申请日：2013-03-22
申请人： AIRBUS OPERATIONS, S.L.
发明人： David Cano Cediel , Ruth Chinarro Vera , Francisco Escobar Benavides , Pedro Nogueroles Viñes
IPC分类号： B32B37/00 , B32B38/00 , B32B37/16
CPC分类号： B32B37/0046 , B29C33/308 , B29C70/386 , B29D99/0003 , B29L2031/001 , B32B37/16 , B32B38/0012 , B32B2305/076 , B32B2305/72 , B32B2309/06 , B32B2605/18 , Y10T156/1044
摘要： The manufacturing method object of the invention comprises the following stages: A) stacking strips of prepreg material on a laminating tool (14), so that an angled laminated part (2) is obtained comprising a central section (2a) contained in a first plane (12), at least one side section (2b) contained in a second plane (13), and at least one bending axis (5) between the central section (2a) and the at least one side section (2b), so that, the first plane and the second plane form an angle α; B) forming of the angled laminated part (2) comprising bending along the bending axis (5) the, at least, one side section with respect to the central section (2a), obtaining a formed part (6); C) curing, of the formed part (6).
摘要翻译：本发明的制造方法目的包括以下步骤：A）在层压工具（14）上堆叠预浸材料的条带，从而获得成角度的层叠部分（2），其包括包含在第一平面中的中心部分（2a）（12），包含在第二平面（13）中的至少一个侧部（2b）和在所述中心部分（2a）和所述至少一个侧部（2b）之间的至少一个弯曲轴线（5），使得，第一平面和第二平面形成角度α; B）形成所述倾斜的层叠部分（2），包括沿所述弯曲轴线（5）相对于所述中心部分（2a）至少一个侧部弯曲，获得成形部分（6）; C）固化所形成的部分（6）。

37. 发明授权

US08943666B2 Method for assembling fuselage sections of an aircraft 有权
标题翻译：组装飞机机身部分的方法
公开(公告)号：US08943666B2
公开(公告)日：2015-02-03
申请号：US13357238
申请日：2012-01-24
申请人： Enrique Vera Villares , Maria Aranzazu Garcia Patino
发明人： Enrique Vera Villares , Maria Aranzazu Garcia Patino
IPC分类号： B23P21/00 , B64C1/06 , B64C1/00
CPC分类号： B64C1/069 , B64C2001/0072 , B64C2001/0081 , Y02T50/43 , Y10T29/49826 , Y10T29/49904
摘要： The method comprises the manufacture of a front section (2) and an rear section (3) with an assembly structure integrated into the rear section and the subsequent assembly of the two sections.The manufacture of the front section (2) comprises the manufacture of a main portion (9) of the front section separated from a coupling portion (10) of the front section.The assembly of the two sections comprises the assembly of the main portion (9) with the group comprising of the rear section assembly (3) and the coupling portion (10) of front section.
摘要翻译：该方法包括制造前部（2）和后部（3），其具有集成在后部中的组装结构和随后的两个部分的组装。前部（2）的制造包括与前部的联接部分（10）分离的前部的主要部分（9）的制造。两部分的组件包括主部分（9）与前部组件（3）和前部联接部分（10）组成的组件。

38. 发明授权

US08943664B2 Manufacturing method for “T” shaped stringers with an angle different from 90° between the web and the foot 有权
标题翻译： “网”和“脚”角度不同于90°的“T”形桁条的制造方法
公开(公告)号：US08943664B2
公开(公告)日：2015-02-03
申请号：US13483782
申请日：2012-05-30
申请人： Yolanda Miguez Charines , Antonio Jose Fuentes Espejo , Oscar Miguel Macias Jareno , Julian Sanchez Fernandez
发明人： Yolanda Miguez Charines , Antonio Jose Fuentes Espejo , Oscar Miguel Macias Jareno , Julian Sanchez Fernandez
IPC分类号： B23P25/00 , B29C70/42 , B29D99/00 , B29C70/34
CPC分类号： B29C70/42 , B29C70/342 , B29D99/0003 , Y02T50/43 , Y10T29/49826 , Y10T29/49885
摘要： Method of manufacturing “T” shaped stringers (1) with an angle different from 90° between the web (2) and the foot (3) whereby the “T” shaped stringers have a stringer web and a stringer foot. The method comprises, after placing together two hot-formed “L” shaped semi-stringers to form a “T” shaped stringer, placing the “T” shaped stringer inside an invar alloy angle leaving a gap between the stringer web and the invar alloy angle. Afterwards, a heating device (7) is moved over the stringer feet (3) surface and a roller (8) slides over said stringer feet (3) surface to adapt the geometry of the stringer feet to the geometry of the invar alloy angle. The resulting “T” shaped stringer is co-bonded on a cured skin with an adhesive line between the stringer and the cured skin, and finally the obtained “T” shaped stringer is cured.
摘要翻译：在腹板（2）和脚部（3）之间制造“T”形桁条（1）的角度不同于90°的方法，由此“T”形桁条具有桁条和桁条脚。该方法包括在将两个热成形的“L”形半桁条放置在一起以形成“T”形桁条之后，将“T”形桁条放置在冕状合金角度内，在桁条腹板和玄武岩合金之间留下间隙角度。之后，加热装置（7）在桁条支脚（3）表面上移动，并且一个滚轮（8）在所述桁条支脚（3）表面上滑动，以使桁条脚的几何形状适应于玄武岩合金角度的几何形状。所得到的“T”形桁条在绷带和固化皮之间用粘合剂线共同粘合在固化的皮肤上，最后固化所得到的“T”形桁条。

39. 发明申请

US20140352877A1 HYBRID TOOL FOR CURING PIECES OF COMPOSITE MATERIAL 审中-公开
标题翻译：复合材料固化剂混合工具
公开(公告)号：US20140352877A1
公开(公告)日：2014-12-04
申请号：US14288931
申请日：2014-05-28
申请人： Airbus Operations, S.L.
发明人： Alejandro Fernandez Alonso , Aquilino Garcia Garcia , Jorge Juan Galiana Blanco , Pablo Cebolla Garrofe , Carlos Romon Banogon
IPC分类号： B32B38/00
CPC分类号： B32B38/00 , B29C33/38 , B29C33/405 , B29C70/44 , B29K2995/0046 , B29K2995/007 , B29L2031/001 , B29L2031/003 , B29L2031/3076 , B29L2031/3082 , B29L2031/3085 , B32B2038/0076 , B32B2305/77 , Y10T156/1002
摘要： A hybrid tool for curing composite structures for aircrafts, such as stringers, torsion boxes, skin panels, wing surfaces, horizontal tail or vertical stabilizers, etc. The hybrid tool comprises a metallic portion and an elastic portion arranged on a surface of the metallic portion. The elastic portion and the metallic portion are permanently joined to each other so that the metallic portion and the elastic portion together define a surface having a shape which copies at least part of a surface of a piece of composite material to be cured. The tool is capable of satisfactorily curing pieces of composite material which have a minimum thickness and/or a very aggressive change of thickness.
摘要翻译：一种用于固化飞机的复合结构的混合工具，例如桁条，扭转箱，皮肤板，翼面，水平尾部或垂直稳定器等。混合工具包括金属部分和布置在金属部分的表面上的弹性部分。弹性部分和金属部分彼此永久地接合，使得金属部分和弹性部分一起限定具有复制待固化的复合材料片的表面的至少一部分的形状的表面。该工具能够令人满意地固化具有最小厚度和/或非常积极的厚度变化的复合材料片。

40. 发明授权

US08844874B2 Interchangeable joint concept for an aircraft rear fuselage cone 有权
标题翻译：飞机后机身锥形可互换联合概念
公开(公告)号：US08844874B2
公开(公告)日：2014-09-30
申请号：US13253520
申请日：2011-10-05
申请人： José Maria Pina López , Pablo Timoteo Sanz Martinez
发明人： José Maria Pina López , Pablo Timoteo Sanz Martinez
IPC分类号： B64C1/06 , B64C1/10 , B64D41/00
CPC分类号： B64C1/068 , B64C1/061 , B64C1/10 , B64D2041/002 , Y10T29/49826
摘要： Rear fuselage of an aircraft comprising a tail cone end and a rest of the real fuselage whereby the tail cone end is attached to the rest of the rear fuselage by means of an attachment system comprising a balancer fitting, three lugs and a waiting link. When there is a failure in one of the lugs, the balancer fitting acts supporting loads in the transversal direction of the aircraft. The waiting link only acts if a failure in other link occurs. This waiting link is able to support loads in the longitudinal direction of the aircraft.
摘要翻译：飞机的后部机身包括尾锥端和实际机身的其余部分，由此尾锥端部通过包括平衡器配件，三个凸耳和等待连接件的附接系统附接到后机身的其余部分。当其中一个接线片发生故障时，平衡器配件可在飞行器的横向上支撑负载。只有当其他链路发生故障时，等待链路才会起作用。这个等待的链接能够支持飞机纵向的负载。

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