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91. 发明申请

US20160176501A1 DEVICE FOR PROTECTING THE FRONT SPAR STRUCTURE OF A CENTRAL CASING OF AN AIRCRAFT WING AND AT LEAST ONE PIECE OF EQUIPMENT LOCATED IN SAID WING 有权
标题翻译：用于保护飞机的中央航空器的前部结构的设备和至少一个设置在设备中的设备
公开(公告)号：US20160176501A1
公开(公告)日：2016-06-23
申请号：US14417406
申请日：2013-06-20
申请人： Airbus Operations (SAS)
发明人： Francis Dazet
IPC分类号： B64C3/28 , B64D45/00
CPC分类号： B64C3/28 , B64D45/00 , B64D2045/0095
摘要： A device for protecting a front spar structure of a central casing of an aircraft wing and at least one item of equipment situated in the wing, comprising:a shielding surface extending in front of the front spar of the central casing, from a surface of an intersection between the wing and the fuselage delimited by the root of the wing, transversely to the surface of intersection, to a first rib of the central casing partially surrounding at least one item of equipment; andmeans—for fixing the shielding surface to the central casing producing an isostatic link.
摘要翻译：一种用于保护飞机机翼的中心壳体的前翼梁结构和位于机翼中的至少一个设备的装置，包括：从中心壳体的前翼梁的前面延伸的屏蔽表面，机翼与机翼根部之间的横向于交叉路口表面的机身与机身之间的交点连接至部分围绕至少一件设备的中央壳体的第一肋; 以及用于将屏蔽表面固定到中心壳体的装置，其产生等静压连杆。

92. 发明授权

US09272495B1 Compaction system for composite stringers 有权
标题翻译：复合桁材压实系统
公开(公告)号：US09272495B1
公开(公告)日：2016-03-01
申请号：US13626452
申请日：2012-09-25
申请人： Brian G. Robins , Kurtis S. Willden , Daniel M. Rotter , Brad A. Coxon
发明人： Brian G. Robins , Kurtis S. Willden , Daniel M. Rotter , Brad A. Coxon
IPC分类号： B29C65/00 , B32B37/00 , B32B37/10 , B64C1/00 , B64C1/06 , B64C3/00 , B64C3/18 , B64C3/24 , B64C3/26 , B64C3/30 , B64C3/28
CPC分类号： B32B37/1018 , B29C65/00 , B29C66/00145 , B29C70/44 , B29D99/0003 , B32B37/00 , B32B37/0046 , B32B37/10 , B32B2605/18 , B64C1/00 , B64C1/06 , B64C1/061 , B64C1/064 , B64C1/068 , B64C1/069 , B64C3/18 , B64C3/182 , B64C3/24 , B64C3/26 , B64C3/28 , B64C3/30 , B64C2001/0072 , B64F5/10 , Y02T50/43
摘要： A method and apparatus for compacting composite stringers. In one illustrative embodiment, an apparatus comprises a compacting structure, a compactor vacuum system, and a carrier vacuum system. The compacting structure has a shape configured to contact layers of uncured composite material for a composite stringer. The compactor vacuum system is associated with the compacting structure. The compactor vacuum system is configured to cause the compacting structure to apply a pressure to the layers of uncured composite material when a compactor vacuum is applied to the compactor vacuum system. The carrier vacuum system is associated with the compacting structure. The carrier vacuum system is configured to hold the layers of uncured composite material against the compacting structure when a carrier vacuum is applied to the carrier vacuum system.
摘要翻译：一种压实复合桁条的方法和装置。在一个说明性实施例中，设备包括压实结构，压实机真空系统和载体真空系统。压实结构具有被配置为接触用于复合纵梁的未固化复合材料层的形状。压实机真空系统与压实结构相关联。压实机真空系统构造成当压实机真空施加到压实机真空系统时，使压实结构向未固化的复合材料层施加压力。载体真空系统与压实结构相关联。载体真空系统构造成当将载体真空施加到载体真空系统时将未固化的复合材料层保持抵靠压实结构。

93. 发明授权

US09248903B2 Aircraft assembly and spar 有权
标题翻译：飞机组件和翼梁
公开(公告)号：US09248903B2
公开(公告)日：2016-02-02
申请号：US13138706
申请日：2010-04-15
申请人： James Eden
发明人： James Eden
IPC分类号： B64C9/00 , B64C9/22 , B64C3/28
CPC分类号： B64C9/22 , B64C3/28 , Y02T50/43 , Y02T50/44
摘要： An aircraft assembly comprising: a pair of covers; a spar web extending between the covers in a thickness direction, the spar web having a length which extends in a span-wise direction; and a container which extends from the spar web and houses at least part of a system component. The container comprises first and second side walls which are spaced apart from each other across the spar web in the thickness direction, and inboard and outboard walls which are spaced apart from each other along the spar web in the span-wise direction. The spar web and at least part of the container are integrally formed as a single piece. Typically the assembly is a wing assembly with a fuel tank; a track; a high-lift device carried by the track; an actuation mechanism for moving the track and high-lift device between an extended high-lift position and a retracted low-lift position; and a track container which extends from the spar web into the fuel tank and houses at least part of the track when it is in its retracted low-lift position. The spar web and at least part of the track container are integrally formed as a single piece, typically from a laminar composite material.
摘要翻译：一种飞机组件，包括：一对盖; 在厚度方向上在盖之间延伸的翼梁腹板，所述翼梁腹板具有沿跨度方向延伸的长度; 以及从翼梁网延伸并容纳系统部件的至少一部分的容器。该容器包括第一侧壁和第二侧壁，该第一侧壁和第二侧壁在厚度方向上跨越翼梁腹板彼此间隔开，以及内侧壁和外侧壁，所述内侧壁和外侧壁沿翼梁腹板沿跨度方向彼此间隔开。翼梁腹板和容器的至少一部分整体形成为单件。通常，组件是具有燃料箱的翼组件; 轨道; 由轨道承载的高升降装置; 致动机构，用于在延伸的高升起位置和缩回的低提升位置之间移动轨道和高升程装置; 以及轨道容器，其从翼梁腹板延伸到燃料箱中并且当其处于其缩回的低提升位置时容纳轨道的至少一部分。翼梁腹板和轨道容器的至少一部分通常由层状复合材料整体形成为单件。

94. 发明授权

US09187170B2 Aircraft airfoil, and an aircraft provided with such an airfoil 有权
标题翻译：飞机机翼和配有这种翼型的飞机
公开(公告)号：US09187170B2
公开(公告)日：2015-11-17
申请号：US13840512
申请日：2013-03-15
申请人： AIRBUS HELICOPTERS
发明人： Luc Lecerf , Vincent Moreau , Xavier Maraninchi , Jean-Charles Sicard
IPC分类号： B64C3/18 , B64C3/28 , B64C5/02 , B64D45/00 , B64C27/04
CPC分类号： B64C3/185 , B64C3/28 , B64C5/02 , B64C27/04 , B64D2045/0095
摘要： An airfoil (10) having a main structure (15) including at least one spar (16) and a front structure (20) forming a leading edge (21), said airfoil (10) having an empty space (25) between said main structure (15) and said front structure (20). The airfoil (10) includes a rigid deflector member (30) in said empty space (25), the deflector member being fastened to the main structure (15), said deflector member (30) having a sharp edge (31) facing towards said front structure (20) in order to deflect an external obstacle impacting against said front structure (20).
摘要翻译：具有主结构（15）的翼型件（10）包括至少一个翼梁（16）和形成前缘（21）的前结构（20），所述翼型件（10）在所述主体结构（15）和所述前部结构（20）。机翼（10）在所述空的空间（25）中包括一个刚性偏转构件（30），该导流构件紧固到该主结构（15）上，该导流构件（30）具有一锋利边缘（31）前部结构（20），以便偏转撞击所述前部结构（20）的外部障碍物。

95. 发明授权

US09102394B2 Flow body with a base body and a leading edge 有权
标题翻译：流体与基体和前缘
公开(公告)号：US09102394B2
公开(公告)日：2015-08-11
申请号：US13559825
申请日：2012-07-27
申请人： Bernhard Schlipf , Xavier Hue
发明人： Bernhard Schlipf , Xavier Hue
IPC分类号： B64C3/28 , B64C3/14
CPC分类号： B64C3/28 , B64C2003/146
摘要： A flow body includes a flow body base body with a first shell element, a leading flow body edge with a second shell element and a clamping body, and a receiving space partially delimited by the clamping body. The flow body base body includes on a front end a projection, having a shape corresponding to that of the receiving space for engaging into the receiving space. The clamping body is internally arranged on the leading flow body edge spaced apart from a rear end of the second shell element. The rear end of the second shell element is flushly positioned on the first shell element when the projection engages into the receiving space. A smooth and harmonious transition that does not influence a laminar flow around the flow body can be achieved between the two components.
摘要翻译：流体包括具有第一壳单元的流体基体，具有第二壳单元的引导流体边缘和夹紧体，以及由夹紧体部分界定的容纳空间。流动体基体在前端具有突起，该突起具有与用于接合到接收空间的接收空间的形状相对应的形状。夹紧体内部布置在与第二壳体元件的后端间隔开的引导流动体边缘上。当突起部接合到接收空间中时，第二壳体元件的后端被平齐地定位在第一壳体元件上。可以在两个部件之间实现不影响流体周围的层流的平滑和谐的转变。

96. 发明授权

US09096312B2 Aircraft 有权
标题翻译：飞机
公开(公告)号：US09096312B2
公开(公告)日：2015-08-04
申请号：US14537112
申请日：2014-11-10
申请人： ROLLS-ROYCE PLC
发明人： Matthew Moxon
IPC分类号： B64C3/28 , B64C23/00 , B64C3/00 , B64C39/00 , B64D27/24 , B64D27/10 , B64C11/00 , B64C9/18
CPC分类号： B64C23/005 , B64C3/00 , B64C3/28 , B64C9/18 , B64C11/00 , B64C39/00 , B64D27/10 , B64D27/12 , B64D27/24 , Y02T50/44 , Y02T50/64
摘要： An aircraft (40). The aircraft (40) comprises a propulsion system comprising a pair of internal combustion engines (10) each driving an electrical power generator (56), each electrical power generator (56) being electrically coupled to a plurality of electrically driven propulsors (46). The propulsors (46) are located forward of a leading edge (45) of the wings (44) such that an airstream generated by the propulsors flows over the wings (44) in use. Each internal combustion engine (10) and electrical generator (56) is mounted on a respective wing (44) outboard of a center of thrust (70) of the propulsors (46) on that wing (44).
摘要翻译：飞机（40）。飞机（40）包括推进系统，其包括一对驱动发电机（56）的内燃机（10），每个发电机（56）电耦合到多个电驱动推进器（46）。推进器（46）位于翼（44）的前缘（45）的前方，使得由推进器产生的气流在使用中在翼（44）上流动。每个内燃机（10）和发电机（56）安装在该翼（44）上的推进器（46）的推力中心（70）外侧的相应翼（44）上。

97. 发明申请

US20150048207A1 LEADING EDGE STRUCTURE 审中-公开
标题翻译：领先的结构
公开(公告)号：US20150048207A1
公开(公告)日：2015-02-19
申请号：US14360512
申请日：2012-11-22
申请人： AIRBUS OPERATIONS LIMITED , AIRBUS OPERATIONS GMBH
发明人： Llifon Williams , Ross Salisbury , Marcus Rafla , Hugh Theobald , Christopher Payne , Robert McCormick , Heinz Hansen , Timothy Evans
IPC分类号： B64C3/28 , B64C3/24 , B64C3/18
CPC分类号： B64C3/28 , B64C3/00 , B64C3/18 , B64C3/187 , B64C3/24 , B64C2003/146
摘要： The invention provides a leading edge structure for providing an aerodynamic surface of an aircraft, the leading edge structure comprising a skin structure, the skin structure providing an outer aerodynamic surface and an inner surface, both surfaces extending in a chordwise and spanwise direction of the structure, and a plurality of structural members, each structural member being connected to the inner surface of the skin structure and extending in the chordwise direction along the inner surface, wherein the structural members are integrally formed with the inner surface of the skin structure. The invention also provides an aircraft wing, aircraft tailplane, wing box structure, wing or wing structure and an aircraft including the leading edge structure.
摘要翻译：本发明提供了一种用于提供飞行器的空气动力学表面的前缘结构，所述前缘结构包括皮肤结构，所述皮肤结构提供外部空气动力学表面和内表面，两个表面在所述结构的弦向和翼展方向上延伸和多个结构构件，每个结构构件连接到表层结构的内表面并且沿着内表面沿着弦方向延伸，其中结构构件与皮肤结构的内表面一体地形成。本发明还提供了一种飞机机翼，飞机尾翼，翼盒结构，机翼或机翼结构以及包括前缘结构的飞机。

98. 发明申请

US20140374536A1 AIRCRAFT WING 有权
标题翻译：飞机票
公开(公告)号：US20140374536A1
公开(公告)日：2014-12-25
申请号：US14154321
申请日：2014-01-14
申请人： William M. OTTO
发明人： William M. OTTO
IPC分类号： B64C3/58 , B64C13/30 , B64C3/28 , B64C3/18 , B64C3/26
CPC分类号： B64C3/58 , B64C1/061 , B64C1/065 , B64C1/16 , B64C1/26 , B64C3/185 , B64C3/26 , B64C3/28 , B64C9/02 , B64C9/20 , B64C13/30 , B64C25/14 , B64C2025/125 , B64D33/04 , B64D33/10 , F16F3/04 , Y02T50/32 , Y02T50/44
摘要： A wing including a spar, a box shaped sleeve in the spar running substantially the entire length of the wing, a skin affixed to spar and to the corners of the sleeve and shaped to from a leading edge and trailing edge of the wing, a spoiler affixed to an upper surface of the trailing edge of the spar, a vent affixed to the lower surface of the trailing edge of the spar below the spoiler.
摘要翻译：机翼包括翼梁，翼梁中的箱形套筒，基本上在机翼的整个长度上运行，固定到翼梁和套筒角部的皮肤，并且从翼的前缘和后缘成形为扰流板固定到翼梁的后缘的上表面，固定在扰流板下方的翼梁后缘的下表面的通风口。

99. 发明授权

US07938360B2 Main wing structure of aircraft 有权
标题翻译：飞机主翼结构
公开(公告)号：US07938360B2
公开(公告)日：2011-05-10
申请号：US11978717
申请日：2007-10-30
申请人： Jun Nakazawa , Kazuhide Hasegawa , Hirohide Azuma
发明人： Jun Nakazawa , Kazuhide Hasegawa , Hirohide Azuma
IPC分类号： B64B1/24 , B64C3/28
CPC分类号： B64D29/02 , B64C3/18 , B64C3/32 , B64D27/18
摘要： Plural regions are defined within a main wing by a plurality of spars and ribs. Of these regions, predetermined regions extending from a main wing connecting portion of the pylon to an internal space of a leading edge skin are used as wiring/piping accommodating chambers for collectively accommodating wiring and piping which provide communication between an engine and a fuselage, a predetermined region adjacent to parts of the wiring/piping accommodating chambers is used as a landing device accommodating chamber for accommodating a landing device and predetermined regions adjacent to other parts of the wiring/piping accommodating chambers are used as fuel tanks. Thus, the maintainability is improved as compared with the case where the wiring and the piping are distributed within the main wing. In addition, because the wiring/piping accommodating chambers are isolated from the landing device accommodating chamber and the fuel tanks, the operational reliability can be improved.
摘要翻译：多个区域通过多个翼梁和肋条限定在主翼内。在这些区域中，将从塔架的主翼连接部分延伸到前缘皮肤的内部空间的预定区域用作用于集体容纳提供发动机和机身之间的连通的布线和管道的布线/管道容纳室，使用与布线/管道容纳室的部分相邻的预定区域作为用于容纳着陆装置的着陆装置容纳室，并且将与布线/管道容纳室的其他部分相邻的预定区域用作燃料箱。因此，与布线和配管分布在主翼内的情况相比，可维护性提高。另外，由于布线/管道容纳室与着陆装置容纳室和燃料箱隔离，因此可以提高操作可靠性。

100. 发明申请

US20090294589A1 METHODS AND APPARATUS FOR AN INTEGRATED AERODYNAMIC PANEL 有权
标题翻译：一种集成气动面板的方法和装置
公开(公告)号：US20090294589A1
公开(公告)日：2009-12-03
申请号：US11954974
申请日：2007-12-12
申请人： Eldon R. Berry , John E. Mundel , Vladislay Andryukov
发明人： Eldon R. Berry , John E. Mundel , Vladislay Andryukov
IPC分类号： B64C1/00 , B64C3/28 , B23P19/04
CPC分类号： B64C1/12 , B64C3/26 , B64C5/02 , B64C5/06 , Y10T29/49838
摘要： An integrated aerodynamic panel—e.g., for a trailing edge or leading edge of an aircraft aerodynamic surface—includes a first panel region defining inner and outer mold lines, and a second panel region contiguous with and extending from the first panel region in a tapering fashion. A splice plate region extends from the second panel region and includes an edge band region configured to accept a fastener. A filler region (e.g., a SYNCORE or fiberglass structure) adjacent the second panel region has an exposed surface substantially flush with the outer mold line.
摘要翻译：集成空气动力学面板 - 例如用于飞行器空气动力学表面的后缘或前缘 - 包括限定内部和外部模具线的第一面板区域和与锥形区域相邻并且从第一面板区域延伸的第二面板区域。接合板区域从第二面板区域延伸并且包括被配置为接纳紧固件的边缘带区域。与第二面板区域相邻的填充区域（例如，SYNCORE或玻璃纤维结构）具有与外部模具线基本上齐平的暴露表面。

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