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公开(公告)号：US12097953B2
公开(公告)日：2024-09-24
申请号：US17703701
申请日：2022-03-24
Applicant: Airbus Operations Ltd.
Inventor： William Tulloch
Abstract: An aircraft wing including a wingbox with an upper cover, a lower cover, a forward spar and a rear spar. A leading edge of a trailing edge panel is attached to the wingbox. A support structure is attached to the wingbox. A kinked link includes a first arm, a second arm, and a corner where the first and second arms meet. The first arm of the kinked link is pivotally attached to the trailing edge panel at a first pivot joint, and the second arm of the kinked link is pivotally attached to the support structure at a second pivot joint.
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公开(公告)号：US11975832B2
公开(公告)日：2024-05-07
申请号：US17425266
申请日：2020-05-25
Applicant: Airbus Operations GmbH
Inventor： Marcus Erban
Abstract: A flow body for an aircraft, in particular for a wing leading edge device, is proposed, the flow body having a curved front skin having a leading edge and at least one trailing-edge component coupled with at least one spanwise edge of the front skin, wherein the trailing-edge component comprises a constant cross-sectional profile that tapers in a chordwise direction to form two spanwise flow surfaces that end in a trailing edge, and wherein the trailing-edge component is designed for providing a flush transition between the front skin and at least one of the two spanwise flow surfaces.
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公开(公告)号：US11858616B2
公开(公告)日：2024-01-02
申请号：US17162172
申请日：2021-01-29
Applicant: Goodrich Actuation Systems Limited
Inventor： Jeremy Kracke
Abstract: An actuator system for controlling movement of a plurality of panels. The system includes two lifting mechanisms connected to each panel at two separate locations on the panel, and, for each panel: an actuator in engagement with a first of the lifting mechanisms to drive the lifting mechanism to move the panel, and a torque tube having a first end in engagement with the actuator so as to be rotated by the actuator as the actuator drives the lifting mechanism, the torque tube having a second end in engagement with the other of the two lifting mechanisms to drive the lifting mechanism due to rotation of the torque tube.
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公开(公告)号：US20180072401A1
公开(公告)日：2018-03-15
申请号：US15564520
申请日：2016-04-06
Inventor： Christian ÜCKERT , Tobias BACH , Olaf STEFFEN , Denise DÜRING , Robert KAPS , Markus KLEINEBERG , Christian HÜHNE
Abstract: The invention relates to a wing structure (1) for flying objects, comprising a wing leading edge (4) and a wing box wherein the wing leading edge should be arranged on the wing box in particular in a detachable manner. For this purpose, the wing leading edge is connected to the wing box within a joining segment (9) and to rib extensions (11) of the wing box by means of fastening element (12) near the nose segment (15) such that a fastening-free segment (14) extends on the top side (16) of the wing leading edge in order to compensate thermal deformation during flight.
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公开(公告)号：US20170137123A1
公开(公告)日：2017-05-18
申请号：US15355010
申请日：2016-11-17
Applicant: Charl E. Janeke
Inventor： Charl E. Janeke
Abstract: A system, apparatus and methods for an airspace plane with shockwave piercing leading edge slots has been described. Which mainly combines concepts of thermodynamic sequencing, heat transfer dynamics, boundary layer separation, spatial adaptivity and Carnot conformance. Wherein the leading-edge slots may be thermally conductive and have converging or diverging double decker structures.
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Patent Agency Ranking
公开(公告)号：US20150144742A1
公开(公告)日：2015-05-28
申请号：US14537112
申请日：2014-11-10
Applicant: ROLLS-ROYCE PLC
Inventor： Matthew MOXON
CPC classification number: B64C23/005 , B64C3/00 , B64C3/28 , B64C9/18 , B64C11/00 , B64C39/00 , B64D27/10 , B64D27/12 , B64D27/24 , Y02T50/44 , Y02T50/64
Abstract: 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 centre of thrust (70) of the propulsors (46) on that wing (44).
Abstract translation: 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。
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公开(公告)号：US08925870B1
公开(公告)日：2015-01-06
申请号：US13417201
申请日：2012-03-09
Applicant: Jason Gordon , Carl Borgstrom , Noah Fisher , Cory Fuhrmeister , Nathan Madigan , Carly Parkins
Inventor： Jason Gordon , Carl Borgstrom , Noah Fisher , Cory Fuhrmeister , Nathan Madigan , Carly Parkins
IPC: B64C21/10
CPC classification number: B64C3/28 , B64C2003/445
Abstract: A wing may include a flexible leading edge skin segment having segment ends positioned adjacent to upper and lower leading edge wing skins to form a skin assembly. The upper leading edge wing skin may be positioned between the leading edge skin segment and an upper main wing skin. The lower leading edge wing skin may be positioned between the leading edge skin segment and a lower main wing skin. The wing may include a deployment device configured to flex the upper and lower leading edge wing skins thereby causing the leading edge skin segment to exhibit a rolling motion.
Abstract translation: 机翼可以包括柔性前缘皮肤段，其具有定位成邻近上和前前缘翼皮的段末端以形成皮肤组件。 上前缘翼皮可以位于前缘皮肤段和上主翼皮之间。 下部前缘翼皮可以位于前缘皮肤部分和下部主翼皮肤之间。 机翼可以包括构造成弯曲上和前引导翼翼表面的部署装置，从而使前缘皮肤段呈现滚动运动。
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8.发明申请公开(公告)号：US20140312176A1
公开(公告)日：2014-10-23
申请号：US14323304
申请日：2014-07-03
Applicant: AIRBUS OPERATIONS GMBH , AIRBUS SAS
Inventor： Adrian Eberle , Tobias Nüssle , Jean Bardou
CPC classification number: B64C3/28 , B64C3/14 , B64C3/50 , B64C2003/147 , B64C2003/148 , Y02T50/12
Abstract: A combination comprises an aircraft wing trailing edge section and an adjustment body. The adjustment body comprises a tapered cross section in a local chord axis direction of the wing trailing edge section, a lower adjustment body surface connected to a top surface of the aircraft wing trailing edge section and a back-end surface having a height. The adjustment body is positioned such that the back-end surface is flush with the trailing edge of the aircraft wing trailing edge section. Attaching the adjustment body onto a top surface of the wing trailing edge section leads to compensation of an offset rolling moment due to unavoidable structural shape deviations of the aircraft and eliminates additional structural reinforcement requirements on the trailing edge compared to edge wedges mounted on the bottom surface of trailing edges. The trailing edge section may comprise a flap.
Abstract translation: 组合包括飞机机翼后缘部分和调整体。 所述调整体包括在所述机翼后缘部的局部弦方向的锥形横截面，与所述飞机机翼后缘部的顶面连接的下调整体表面和具有高度的后端面。 调整体被定位成使得后端表面与飞机机翼后缘部分的后缘齐平。 将调节体附接到机翼后缘部分的顶面上导致由于飞机的不可避免的结构形状偏差而导致的偏移滚动力矩的补偿，并且与安装在底面上的边缘楔相比，在后缘处消除了额外的结构加强要求 的后缘。 后缘部分可以包括翼片。
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公开(公告)号：US08746619B2
公开(公告)日：2014-06-10
申请号：US13630654
申请日：2012-09-28
Applicant: Northwestern Polytechnical University
Inventor： Yulong Li , Jun Liu , Tao Suo , Zhongbin Tang , Jun Lv , Liangdao Zhou , Guangrong Zhu , Hao Cong , Zhengli Zhang
Abstract: The present invention relates to a tail for improving anti-bird strike performance of an aircraft. A leading edge reinforcement having a shape of an isosceles triangle is located inside a tail leading edge. The leading edge reinforcement is spanwisely fixed in sections between respective spans formed by the wing rib inside the tail leading edge along the tail of the aircraft. An apex angle of the leading edge reinforcement is the same as an apex angle or arc transition of the tail leading edge skin. The leading edge reinforcement is fixedly connected with the small front beam by a leading edge reinforcement fixed surface. The present invention additionally installs a leading edge reinforcement in the original tail of the aircraft.
Abstract translation: 本发明涉及一种提高飞机防鸟击性能的尾巴。 具有等腰三角形形状的前缘加强件位于尾部前缘内。 前缘加强件沿翼形方向固定在沿着飞机尾部的尾翼前缘内的翼肋形成的相应跨度之间的部分。 前缘加强件的顶角与尾部前缘皮肤的顶角或圆弧过渡相同。 前缘加强件通过前缘加强固定表面与小前梁固定连接。 本发明另外在飞行器的原始尾部安装前缘加强件。
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公开(公告)号：US20130270392A1
公开(公告)日：2013-10-17
申请号：US13829629
申请日：2013-03-14
Applicant: Airbus Operations, S.L.
Inventor： FERNANDO MAESTRE DERQUI , IGNACIO OUTON HERNÁNDEZ
IPC: B64C23/00
Abstract: Interface arrangement for aircraft lifting surface between a first component and a second component made of composite materials and having an aerodynamic contour, wherein the first component comprises a primary joggled area and the second component comprises a secondary joggled area, such that the first component is joined to the second component by means of a supplementary part which accommodates in the primary joggled area and in the secondary joggled area, the secondary part being designed to maintain continuity of aerodynamic contour at the interface arrangement and to fill the gap between the first component and the second component, so the maximum thickness of the supplementary part being the depth of the primary joggled area, the depth of the primary joggled area being lower than the depth needed to accommodate the second component on the first component.
Abstract translation: 用于在由复合材料制成并且具有空气动力学轮廓的第一部件和第二部件之间的飞机提升表面的接口装置，其中所述第一部件包括主要碰撞区域，并且所述第二部件包括辅助碰撞区域，使得所述第一部件被连接 通过一个辅助部件连接到第二部件上，该辅助部件容纳在主要的碰撞区域中，而在辅助碰撞区域中，辅助部件被设计成保持界面布置处的空气动力学轮廓的连续性，并且填充第一部件和 辅助部分的最大厚度是主要碰撞区域的深度，主要碰撞区域的深度低于在第一部件上容纳第二部件所需的深度。
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