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公开(公告)号：US09248905B2
公开(公告)日：2016-02-02
申请号：US13894944
申请日：2013-05-15
Applicant: AIRBUS OPERATIONS S.L. , AIRBUS SAS
Inventor： Ludovic Gerard , Alejandro Gutiérrez García , Julián Maldonado
CPC classification number: B64C23/005 , B64C25/16 , B64C2025/003 , B64D41/007 , B64D2201/00
Abstract: 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.
Abstract translation: 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。
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152.发明授权公开(公告)号：US09242438B2
公开(公告)日：2016-01-26
申请号：US14039122
申请日：2013-09-27
Applicant: AIRBUS OPERATIONS S.L.
Inventor： José David Cano Cediel , Ruth Chinarro Vera , Francisco Escobar Benavides , Pedro Nogueroles Viñes
CPC classification number: B32B37/02 , B29C70/32 , Y10T156/1043
Abstract: 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.
Abstract translation: 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。
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153.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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154.发明申请公开(公告)号：US20150329210A1
公开(公告)日：2015-11-19
申请号：US14715846
申请日：2015-05-19
Applicant: Airbus Operations GmbH , Airbus Operations S.L.
Inventor： Holger Bammann , Frank Klimpel , Dariusz Krakowski , Anton Mendez-Diaz
CPC classification number: B64D13/06 , B60H1/00435 , B60H1/3211 , B64D2013/0611 , B64D2013/0618 , B64D2013/0688 , Y02T50/56
Abstract: An aircraft air conditioning system comprises a process air line configured to supply compressed process air provided by a process air source to an air conditioning unit of the aircraft air conditioning system and a trim air line branching off from the process air line upstream of the air conditioning unit and being configured such that trim air flows through the trim air line, the trim air having been branched off from the compressed process air flowing through the process air line. A compressor is arranged in the trim air line and is configured to compress the trim air flowing through the trim air line. A turbine of the aircraft air conditioning system is configured to drive the compressor. A cabin exhaust air line is configured to supply cabin exhaust air discharged from an aircraft cabin to the turbine for driving the turbine.
Abstract translation: 飞机空调系统包括处理空气管线，其被配置为将由处理空气源提供的压缩过程空气供应到飞行器空调系统的空调单元和从空调的上游的处理空气管线分支的调整空气管线 单元并且被配置为使得修剪空气流过修剪空气管线，修剪空气已经从流过处理空气管线的压缩过程空气分支。 压缩机布置在装饰空气管线中并且构造成压缩流过修剪空气管线的修剪空气。 飞机空调系统的涡轮机构造成驱动压缩机。 客舱排气管线被配置为将从飞机机舱排出的客舱排气供应到用于驱动涡轮机的涡轮机。
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公开(公告)号：US20150314539A1
公开(公告)日：2015-11-05
申请号：US14700634
申请日：2015-04-30
Applicant: Airbus Operations S.L.
Inventor： Jose Sanchez Gomez , Rafael Avila Dominguez , Hector Alonso Pintado
CPC classification number: B29C70/54 , B29C35/0261 , B29C70/30 , B29C70/388 , B29C70/543 , B29K2105/0881 , Y10T156/12
Abstract: A method for obtaining a composite piece of n plies, at least one ply having a fiber volume greater than 58% in weight, the method comprising the steps of laying uncured prepreg plies and performing ultrasound compaction over each laid uncured laminate ply, wherein at least one of the uncured laminate plies has a fiber volume greater than 58% in weight. Finally, the composite laminate is cured. The step of performing ultrasound compaction comprises applying an ultrasonic compactor over each laid laminate ply.
Abstract translation: 一种获得n层复合片材的方法，至少一层纤维体积大于58％重量的方法，该方法包括以下步骤：铺设未固化的预浸料层，并在每个铺设的未固化层压板层上进行超声压实，其中至少 未固化的层压板之一具有大于58重量％的纤维体积。 最后，复合层压板固化。 执行超声压缩的步骤包括在每个铺设的层压板层上施加超声压实机。
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Patent Agency Ranking
公开(公告)号：US20150183524A1
公开(公告)日：2015-07-02
申请号：US14583832
申请日：2014-12-29
Applicant: Airbus Operations, S.L.
CPC classification number: B64D45/00 , B64D41/00 , B64D2041/002 , B64D2045/009 , F02C6/00 , F02C7/20 , F05D2220/50 , F05D2240/90 , F05D2260/83 , F16H57/02 , G01K1/14 , G01K13/00 , Y02T50/44 , Y10T74/2186
Abstract: An Auxiliary Power Unit (“APU”) for an aircraft with reduced weight, but which at the same time meets all fire-related airworthiness standards. The APU comprises a metallic housing having mounts for attaching the housing to an external structure. The APU further comprises at least one temperature sensor suitable for detecting temperature under fire conditions. The temperature sensor is coupled with the mounts for sensing temperature at the housing.
Abstract translation: 用于重量轻，但同时符合所有防火相关适航标准的飞机的辅助动力单元（“APU”）。 APU包括具有用于将壳体附接到外部结构的安装件的金属壳体。 APU还包括至少一个温度传感器，适于在火灾条件下检测温度。 温度传感器与安装座耦合，用于感测壳体的温度。
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公开(公告)号：US20150183503A1
公开(公告)日：2015-07-02
申请号：US14584857
申请日：2014-12-29
Applicant: Airbus Operations, S.L.
CPC classification number: B64C1/064 , B29C70/34 , B29C70/44 , B29C70/446 , B29D99/0014 , B29L2031/3076 , B64C3/182 , B64C2001/0072 , Y02T50/43 , Y10T156/1002
Abstract: A manufacturing method is disclosed for manufacturing of a composite stiffening element, including: arranging composite laminates partially between caul plates and mold halves, and partially between a movable upper sandwich plate and a movable lower sandwich plate, moving the upper and lower sandwich plates together and moving the assembly formed by the first caul plate and the first mold half and the assembly formed by the second caul plate and the second mold half, and joining and co-curing the composite laminates to make up the composite stiffening element. A composite stiffening element is also disclosed.
Abstract translation: 公开了一种用于制造复合加强元件的制造方法，包括：将复合层压板部分地放置在挡板和半模之间，并且部分地在可移动的上夹层板和可动下夹层板之间移动，将上夹层板和下夹层板一起移动， 移动由第一挡板和第一半模形成的组件以及由第二挡板和第二半模形成的组件，以及接合和共固化复合层压板以组成复合加强元件。 还公开了复合加强元件。
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158.发明申请T-SHAPED STRINGER WITH A ROUNDED WEB END AND METHOD OF MANUFACTURING IT 审中-公开具有圆形网页末端的T形形状字符串及其制造方法公开(公告)号：US20150174831A1
公开(公告)日：2015-06-25
申请号：US14575569
申请日：2014-12-18
Applicant: AIRBUS OPERATIONS S.L.
Inventor： Yolanda MÍGUEZ CHARINES , Gabriel CERDEÑO CABELLO , Juan Pedro BARRADO RUIZ , Augusto PÉREZ PASTOR
CPC classification number: B29C70/30 , B29C53/04 , B29C70/42 , B29D99/0003 , B29L2031/3076 , B32B3/04 , B32B37/18 , B32B38/0012 , B32B2038/0076 , B32B2250/00 , B32B2309/68 , B32B2605/18 , B64C1/064 , B64C3/182 , B64C2001/0072 , Y02T50/43 , Y10T156/1002 , Y10T428/2419
Abstract: A method of manufacturing T-shaped stringers made of composite material, including a second shaping step for shaping laminates into L-shaped preforms, which includes providing a set of tools formed by a fixed tool comprising a lower portion and an upper portion, and a moveable tool comprising a lower element and an upper element. It also includes the segment of the laminate intended for the foot of the preform being located between the lower portion and the upper portion of the fixed tool, and the segment of the laminate intended for the web of the preform being located between the lower element and the upper element of the moveable tool. It further includes vertically moving the moveable tool to progressively bend the web of the preform supporting it on a vertical wall of the fixed tool. The end of its web adopts a rounded shape.
Abstract translation: 一种制造由复合材料制成的T形桁条的方法，包括用于将层压板成形为L形预成型件的第二成形步骤，其包括提供由包括下部和上部的固定工具形成的一组工具，以及 可移动工具包括下部元件和上部元件。 它还包括用于预成型件的脚部的层压板位于固定工具的下部和上部之间，并且用于预成型件的腹板的层压体部分位于下部元件和 可移动工具的上部元素。 其还包括垂直移动可移动工具以使支撑其的预成型件的腹板逐渐弯曲在固定工具的垂直壁上。 网的末端采用圆形。
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公开(公告)号：US20150053332A1
公开(公告)日：2015-02-26
申请号：US14388555
申请日：2013-03-22
Applicant: AIRBUS OPERATIONS, S.L.
Inventor： David Cano Cediel , Ruth Chinarro Vera , Francisco Escobar Benavides , Pedro Nogueroles Viñes
CPC classification number: B32B37/0046 , B29C33/308 , B29C70/386 , B29D99/0003 , B29L2031/001 , B32B37/16 , B32B38/0012 , B32B2305/076 , B32B2305/72 , B32B2309/06 , B32B2605/18 , Y10T156/1044
Abstract: 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).
Abstract translation: 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）。
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公开(公告)号：US20140352877A1
公开(公告)日：2014-12-04
申请号：US14288931
申请日：2014-05-28
Applicant: Airbus Operations, S.L.
Inventor： Alejandro Fernandez Alonso , Aquilino Garcia Garcia , Jorge Juan Galiana Blanco , Pablo Cebolla Garrofe , Carlos Romon Banogon
IPC: B32B38/00
CPC classification number: 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
Abstract: 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.
Abstract translation: 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。
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