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81. 发明授权

US09238338B2 Method of fabricating composite laminate structures allowing ply slippage during forming 有权
标题翻译：复合层压结构的制造方法，允许在成形期间进行层压滑移
公开(公告)号：US09238338B2
公开(公告)日：2016-01-19
申请号：US13313382
申请日：2011-12-07
申请人： Randall Dow Wilkerson , James R. Fox , Charles R. Prebil
发明人： Randall Dow Wilkerson , James R. Fox , Charles R. Prebil
IPC分类号： B29C70/00 , B29C70/54 , B29C70/40 , B29C53/04
CPC分类号： B29C70/543 , B29C53/04 , B29C70/40 , Y02T50/43 , Y10T29/49826 , Y10T428/24479
摘要： A composite structure having a contoured cross section is fabricated by assembling a flat ply stack and forming the stack. The full plies in the stack are tacked through their entire thickness and the partial plies are tacked to individual ones of the full plies in a manner that enables the plies to slip in relation to each other, preventing wrinkling and distortion of the plies during forming.
摘要翻译：具有轮廓横截面的复合结构通过组装扁平叠层并形成叠层来制造。堆叠中的整层通过它们的整个厚度粘合，并且部分帘布层以使得帘布层相对于彼此滑动的方式固定到单层帘布层中，防止在成型期间帘布层的起皱和变形。

82. 发明申请

US20160009365A1 STRUCTURE 审中-公开
标题翻译：结构体
公开(公告)号：US20160009365A1
公开(公告)日：2016-01-14
申请号：US14793581
申请日：2015-07-07
申请人： Airbus Operations Limited
发明人： Oliver Marks
IPC分类号： B64C3/18 , B64C5/00 , B64C3/26
CPC分类号： B64C3/18 , B64C3/182 , B64C3/187 , B64C3/26 , B64C5/00 , B64C2001/0072 , Y02T50/43
摘要： The invention relates to a structure having a panel, a stringer and a rib. The stringer has a stringer flange that is joined to an inner surface of the panel and a stringer web that extends away from the stringer flange. The rib has a rib web and a rib foot. The rib foot has a rib foot flange that is joined to the stringer web, first and second rib foot base parts that are joined to the inner surface of the panel or to the stringer flange and a rib foot web that is joined to the rib web. The rib foot is formed as a single folded piece such that the rib foot flange is connected to the rib foot web by a first folded corner, the first rib foot base part is connected to the rib foot flange by a second folded corner and the second rib foot base part is connected to the rib foot web by a third folded corner.
摘要翻译：本发明涉及具有面板，纵梁和肋的结构。纵梁具有连接到面板的内表面的纵梁法兰和从纵梁凸缘延伸的纵梁腹板。肋具有肋腹板和肋脚。肋脚具有连接到纵梁腹板的肋脚凸缘，连接到面板的内表面或纵梁凸缘的第一和第二肋脚基部，以及连接到肋腹板的肋脚腹板。肋脚形成为单个折叠片，使得肋脚法兰通过第一折叠角部连接到肋脚腹板，第一肋脚基部通过第二折角连接到肋脚法兰，第二折角肋脚基部通过第三折角连接到肋脚腹板。

83. 发明申请

US20150380811A1 Method for Manufacturing a Radome 有权
标题翻译：制造天线罩的方法
公开(公告)号：US20150380811A1
公开(公告)日：2015-12-31
申请号：US14748892
申请日：2015-06-24
申请人： Airbus Defence and Space GmbH
发明人： Bernhard SCHOENLINNER , Ulrich PRECHTEL , Thomas SCHUSTER , Michael SABIELNY , Herbert ZIPPOLD , Kay W. DITTRICH , Franz STADLER , Markus ROTHENHAEUSLER , Wilhelm WULBRAND , Thomas KOERWIEN
IPC分类号： H01Q1/42 , H01Q15/14
CPC分类号： H01Q1/42 , H01Q1/28 , H01Q1/3275 , H01Q1/38 , H01Q1/40 , H01Q1/422 , H01Q3/08 , H01Q15/141 , Y02T50/43
摘要： A method is provided for manufacturing a radome. The method has the following steps: creation of a contoured fit of at least one section of an inner surface of a wall of the radome; arrangement of a plurality of planar photosensitive semiconductor elements on an outer surface of the contoured fit; placement of the contoured fit with the plurality of planar photosensitive semiconductor elements on the at least one section of the inner surface of the wall; establishing of a connection between the plurality of planar photosensitive semiconductor elements and the wall; and removal of the contoured fit from the radome. This method enables the simple manufacture of a radome with a layer having several semiconductor elements for the electromagnetic shielding of the interior of the radome.
摘要翻译：提供了制造天线罩的方法。该方法具有以下步骤：产生天线罩的壁的内表面的至少一个部分的轮廓拟合; 多个平面光敏半导体元件在轮廓配合的外表面上的布置; 将所述轮廓配合与所述多个平面光敏半导体元件放置在所述壁的内表面的所述至少一个部分上; 建立所述多个平面光敏半导体元件与所述壁之间的连接; 并从天线罩中移除轮廓拟合。该方法能够简单地制造具有用于雷达罩内部的电磁屏蔽的具有若干半导体元件的层的雷达罩。

84. 发明授权

US09221532B2 Multi-role aircraft with interchangeable mission modules 有权
标题翻译：具有可互换任务模块的多角色飞机
公开(公告)号：US09221532B2
公开(公告)日：2015-12-29
申请号：US14205156
申请日：2014-03-11
申请人： Abe Karem
发明人： Abe Karem
IPC分类号： B64C1/00 , B64C3/56 , B64C1/06 , B64C39/10 , B64C39/02 , B64D37/00 , B64C1/26
CPC分类号： B64C39/10 , B64C1/00 , B64C1/0009 , B64C1/061 , B64C1/065 , B64C1/26 , B64C3/56 , B64C25/10 , B64C39/024 , B64C2001/0072 , B64C2039/105 , B64C2201/028 , B64C2201/126 , B64C2211/00 , B64D37/00 , Y02T50/12 , Y02T50/14 , Y02T50/43
摘要： A flight-operable, truly modular aircraft has an aircraft core to which one or more of outer wings members, fuselage, cockpit, leading and trailing edge couplings, and empennage and tail sections can be removably coupled and/or replaced during the operating life span of the aircraft. In preferred embodiments the aircraft core houses the propulsive engines, avionics, at least 80% of the fuel, and all of the landing gear. The aircraft core is preferably constructed with curved forward and aft composite spars, that transfer loads across the center section, while accommodating a mid-wing configuration. The aircraft core preferably has a large central cavity dimensioned to interchangeably carry an ordnance launcher, a surveillance payload, electronic countermeasures, and other types of cargo. Contemplated aircraft can be quite large, for example having a wing span of at least 80 ft.
摘要翻译：飞行可操作的，真正模块化的飞机具有飞行器核心，一个或多个外翼构件，机身，驾驶舱，前后联轴器，尾翼和尾翼部分可在其运行寿命期间可拆卸地联接和/或更换的飞机。在优选实施例中，飞机核心容纳推进发动机，航空电子设备，至少80％的燃料和所有起落架。飞机核心优选地构造有弯曲的前向和后部复合翼梁，其在中心部分处传递载荷，同时容纳中翼构造。飞机核心优选地具有大的中心空间，其大小可互换地携带军械发射器，监视有效载荷，电子对抗措施和其他类型的货物。考虑的飞机可能相当大，例如具有至少80英尺的翼展。

85. 发明授权

US09221236B1 Systems and methods for assembling stiffened composite structures 有权
标题翻译：用于组装加固复合结构的系统和方法
公开(公告)号：US09221236B1
公开(公告)日：2015-12-29
申请号：US14012911
申请日：2013-08-28
申请人： The Boeing Company
发明人： Daniel M. Rotter , Brian G. Robins , Brad Andrew Coxon
IPC分类号： B29C65/00 , B32B37/00 , B32B37/10
CPC分类号： B32B37/10 , B29C65/00 , B29C66/00145 , B29C66/004 , B29C66/0042 , B29C66/005 , B29D99/0014 , B32B37/00 , B64C1/068 , B64C1/12 , B64C2001/0072 , B64F5/10 , Y02T50/43
摘要： Methods of and systems for assembling stiffened composite structures are disclosed. Some methods include loading a stiffener onto an inner mold line layup mandrel and then loading a filler structure within the stiffener cavity of the stiffener. Some methods include loading, with a loading tool, a stiffener charge and a filler structure onto an inner mold line layup mandrel so the respective stiffener charge conforms to a stiffener form of the inner mold line layup mandrel to form a stiffener. Some methods include loading, with a loading tool, a stiffener and a filler structure onto an inner mold line layup mandrel.
摘要翻译：公开了用于组装加强复合结构的方法和系统。一些方法包括将加强件加载到内部模具线铺层心轴上，然后将加强件结构加载到加强件的加强件腔内。一些方法包括用加载工具将加强筋装料和填料结构装载到内模线铺层心轴上，使得相应的加强件装料符合内模线叠层心轴的加强件形式以形成加强件。一些方法包括用加载工具将加强件和填料结构加载到内模线叠层心轴上。

86. 发明申请

US20150344118A1 AIRCRAFT FUSELAGE FRAME MADE OF LAMINATED COMPOSITE MATERIALS AND INCLUDING REINFORCEMENT CURVED ZONES OF VARYING VALUE OF RADIUS OF CURVATURE 有权
标题翻译：层压复合材料的飞机熔融框架，包括弯曲半径变化值的加固弯曲区域
公开(公告)号：US20150344118A1
公开(公告)日：2015-12-03
申请号：US14445448
申请日：2014-07-29
申请人： AIRBUS HELICOPTERS
发明人： Pierre PRUD'HOMME-LACROIX
IPC分类号： B64C1/06
CPC分类号： B64C1/061 , B64C2001/0072 , Y02T50/43
摘要： A structural frame for a fuselage of an aircraft. The frame is formed from a composite material profile comprising curved zones (7) that interconnect together zones to be joined of the frame, having respective orientations. Each of the curved zones (7) of the frame is geometrically defined by at least one radius of curvature. The value of the radius of curvature (R2), geometrically defining a curved zone (7) of the frame varies as a function of the curvilinear abscissa of each points on the inside periphery of the inside flange from any point of the curved zone relative to a given reference point (P1).
摘要翻译：机身机身的结构框架。框架由复合材料型材形成，该复合材料型材包括将具有各自取向的框架连接的区域互连在一起的弯曲区域（7）。框架的每个弯曲区域（7）由至少一个曲率半径几何地限定。在几何上限定框架的弯曲区域（7）的曲率半径（R2）的值根据弯曲区域的任何点相对于内凸缘的内周边上的每个点的曲线横坐标相对于给定的参考点（P1）。

87. 发明申请

US20150328846A1 COMPOSITE STRUCTURES HAVING INTEGRATED STIFFENERS WITH SMOOTH RUNOUTS AND METHOD OF MAKING THE SAME 审中-公开
标题翻译：具有平滑运动的综合加强器的复合结构及其制造方法
公开(公告)号：US20150328846A1
公开(公告)日：2015-11-19
申请号：US14141433
申请日：2013-12-27
申请人： The Boeing Company
发明人： David A. Pook , Peter J. Lockett , Andrew K. Glynn
IPC分类号： B29C70/48 , B29B11/04 , B29C70/06
CPC分类号： B29C70/48 , B29B11/04 , B29C65/4835 , B29C65/5057 , B29C65/564 , B29C66/112 , B29C66/1122 , B29C66/131 , B29C66/472 , B29C66/4722 , B29C66/474 , B29C66/532 , B29C66/61 , B29C66/721 , B29C66/7212 , B29C66/72141 , B29C66/723 , B29C66/7394 , B29C66/81455 , B29C70/06 , B29C70/443 , B29C70/865 , B29D99/0014 , B29D99/0017 , B29K2101/10 , B29K2105/0827 , B29L2009/00 , B29L2031/3076 , B29L2031/3082 , B64C1/12 , B64C1/1446 , B64C3/26 , Y02T50/43 , Y10T156/10 , Y10T428/24488 , Y10T428/24521 , Y10T428/2457 , Y10T428/24612 , B29K2307/04 , B29K2309/08 , B29K2301/00
摘要： A unitized composite structure comprises a composite member having at least one integrally formed composite stiffener. At least one end of the stiffener includes a runout forming a substantially smooth transition between the stiffener and the composite structure.
摘要翻译：组合复合结构包括具有至少一个整体形成的复合加强件的复合构件。加强件的至少一端包括在加强件和复合结构之间形成基本上平滑的过渡的跳动。

88. 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。

89. 发明授权

US09180958B2 Aircraft, airframes and associated methods 有权
标题翻译：飞机，机身及相关方法
公开(公告)号：US09180958B2
公开(公告)日：2015-11-10
申请号：US13480918
申请日：2012-05-25
申请人： Victor A. Munsen , David Neal Berry
发明人： Victor A. Munsen , David Neal Berry
IPC分类号： B64C1/12 , B64C1/00
CPC分类号： B64C1/12 , B64C2001/0072 , B64C2001/0081 , Y02T50/43 , Y10T29/49622
摘要： Aircraft and airframes include a skin operatively coupled to a structural reinforcement member. The structural reinforcement member and the skin collectively define a run-out region that encompasses a terminal edge of the structural reinforcement member. Within the run-out region, the skin is more flexible than in adjacent portions of the skin. Methods include defining a region of increased flexibility of a skin relative to adjacent portions of the skin, and operatively coupling the skin to a structural reinforcement member.
摘要翻译：飞机和机身包括可操作地联接到结构加强构件的皮肤。结构加强构件和皮肤共同地限定包围结构加强构件的终端边缘的越过区域。在外出区域内，皮肤比皮肤的相邻部分更加柔软。方法包括限定皮肤相对于皮肤的相邻部分增加的柔韧性的区域，以及将皮肤可操作地连接到结构加强构件。

90. 发明授权

US09180628B2 Method and device for the production of tubular structural components 有权
标题翻译：用于生产管状结构件的方法和装置
公开(公告)号：US09180628B2
公开(公告)日：2015-11-10
申请号：US14285704
申请日：2014-05-23
申请人： AIRBUS OPERATIONS GMBH
发明人： Hauke Lengsfeld , Volker Reye
IPC分类号： B29C70/34 , B29C70/44 , B29C33/50 , B29D23/00 , B30B5/02 , B29C70/36 , B29C70/54 , B29L23/00 , B29L31/30 , B29K307/04
CPC分类号： B29C70/48 , B29C33/505 , B29C70/345 , B29C70/36 , B29C70/443 , B29C70/446 , B29C70/541 , B29D23/001 , B29K2105/089 , B29K2307/04 , B29L2023/22 , B29L2031/3082 , B30B5/02 , Y02T50/43
摘要： A method for producing a tubular structural component and device for production thereof are disclosed. A tubular molding tool has an inner mold surface shaped corresponding to an outer surface of the structural component. A support surface of an expandable support, formed corresponding to the molding tool shape such that in an unexpanded state the support fills the molding tool while the support surface and the mold surface run parallel leaving an expansion spacing of the support surface to the mold surface, is covered with a tubular non-crimp fiber fabric, such that fibers of a fiber layer of the non-crimp fiber fabric run diagonally around the support. After the support has been arranged in the molding tool, the non-crimp fiber fabric is pressed against the mold surface by expanding the support with radial expansion of the non-crimp fiber fabric. The non-crimp fiber fabric is infiltrated by a curable matrix.
摘要翻译：公开了一种管状结构部件的制造方法及其制造装置。管状模制工具具有对应于结构部件的外表面成形的内模表面。可膨胀支撑件的支撑表面，其对应于模制工具形状形成，使得在未膨胀状态下，支撑件填充模具，同时支撑表面和模具表面平行延伸，留下支撑表面与模具表面的膨胀间隔，被管状非卷曲纤维织物覆盖，使得非卷曲纤维织物的纤维层的纤维在支撑件周围对角地延伸。在支撑件已经被布置在模具中之后，非卷曲纤维织物通过使非卷曲纤维织物的径向膨胀膨胀而压靠在模具表面上。非卷曲纤维织物被可固化基质渗透。

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