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    Method of coupling aerofoil surface structures and an aerofoil assembly
    82.
    发明公开
    Method of coupling aerofoil surface structures and an aerofoil assembly 审中-公开
    程序机翼结构的耦合和机翼组件

    公开(公告)号：EP2669187A3

    公开(公告)日：2017-04-19

    申请号：EP13169031.5

    申请日：2013-05-23

    申请人： Airbus Operations Limited

    发明人： Parker, Simon John

    IPC分类号： B64C3/00 ,  B64C5/08 ,  B64C23/06

    CPC分类号： B64C3/00 ,  B64C5/08 ,  B64C23/065 ,  B64C23/072 ,  Y02T50/164 ,  Y10T29/49337

    摘要： A method of attaching first 200 and second 300 aerofoil sections to each other is disclosed. The method comprises the steps of: positioning one aerofoil section in an initial assembly orientation with respect to the other aerofoil section so that hinge elements 225, 325 on each aerofoil section are in alignment with each other, inserting a hinge shaft 450 through said aligned hinge elements to initially couple the aerofoil sections together whilst the aerofoil sections are in their initial assembly orientation; and rotating one aerofoil section relative to the other aerofoil section about a compound angle defined by the hinge shaft into a second orientation in which the aerofoil sections are in their final, assembled orientation relative to each other. An aerofoil assembly 100 is also disclosed.

    PRODUITS FILÉS POUR PLANCHERS D'AVION EN ALLIAGE ALUMINIUM CUIVRE LITHIUM
    83.
    发明公开
    PRODUITS FILÉS POUR PLANCHERS D'AVION EN ALLIAGE ALUMINIUM CUIVRE LITHIUM 审中-公开
    STRANGPRESSPRODUKTEFÜRFLUGZEUGBÖDENAUS EINER铝合金 - 锂离子

    公开(公告)号：EP3080319A2

    公开(公告)日：2016-10-19

    申请号：EP14825362.8

    申请日：2014-12-10

    申请人： Constellium Issoire

    发明人： PIGNATEL, Jérome ,  POUGET, Gaëlle

    IPC分类号： C22C21/16 ,  C22C21/18 ,  B21C23/00 ,  C22F1/057

    CPC分类号： B64C1/18 ,  B21C23/142 ,  B64C1/061 ,  B64C3/00 ,  B64C2001/0081 ,  C22C21/14 ,  C22C21/16 ,  C22C21/18 ,  C22F1/057

    摘要： The invention relates in particular to an unprocessed extruded product for manufacturing a machined extruded product for the aeronautical industry, made of an Al-Cu-Li alloy with the following composition, as weight percentages: Cu: 2.0 - 6.0; Li: 0.5 - 2.0; Mg: 0 - 1.0; Ag: 0 - 0.7; Zn 0 - 1.0; and at least one element selected among Zr, Mn, Cr, Se, Hf and Ti, the amount of said element, if chosen, being 0.05 to 0.20 wt % for Zr, 0.05 to 0.8 wt % for Mn, 0.05 to 0.3 wt % for Cr and for Se, 0.05 to 0.5 wt % for Hf and 0.01 to 0.15 wt % for Ti, Si ≤ 0.1; Fe ≤ 0.1; others ≤ 0.05 each and ≤ 0.15 in total, the balance being aluminium, having an unprocessed core (21) with an aspect ratio of at least 5 and at least one unprocessed flank (22) with an aspect ratio of less than 4 and in which the length direction is substantially perpendicular to the lengthwise direction of the core, characterised in that a portion of the unprocessed flank (22) connecting the unprocessed flank to the unprocessed core has decreasing thickness and in that the ratio of the thickness of said unprocessed flank (22) at the end of said unprocessed flank connected to the web (E221) to that at the end thereof opposite the core (E222) — i.e. E221/E222 — is less than 0.8, thus defining two substantially symmetrical concave areas. The invention also relates to the method for manufacturing a machined extruded product and to the corresponding machined extruded product. The products according to the invention are useful in particular for manufacturing floor beams and girders.

    摘要翻译： 本发明具体涉及用于制造由Al-Cu-Li合金制成的用于航空工业的加工挤出产品的未加工的挤出产品。 本发明还涉及用于制造加工的挤出产品的方法和相应的加工的挤出产品。 根据本发明的产品特别用于制造地板梁和桁架。

    PROCEDE DE FABRICATION D'UN ELEMENT DE STRUCTURE D'EPAISSEUR VARIABLE POUR CONSTRUCTION AERONAUTIQUE
    85.
    发明公开
    PROCEDE DE FABRICATION D'UN ELEMENT DE STRUCTURE D'EPAISSEUR VARIABLE POUR CONSTRUCTION AERONAUTIQUE 有权
    一种用于生产结构元件具有可变厚度的飞机生产

    公开(公告)号：EP2917380A2

    公开(公告)日：2015-09-16

    申请号：EP13801604.3

    申请日：2013-11-07

    申请人： Constellium France

    发明人： EHRSTROM, Jean-Christophe ,  DANIELOU, Armelle ,  WARNER, Timothy

    IPC分类号： C22C21/00 ,  C22F1/04

    CPC分类号： C22F1/057 ,  B64C3/00 ,  C22C21/00 ,  C22C21/12 ,  C22C21/14 ,  C22C21/16 ,  C22C21/18 ,  C22F1/002 ,  C22F1/04

    摘要： The invention relates to a method for manufacturing a laminated product having a variable thickness and consisting of a heat-treated aluminum alloy, in which a variation in thickness of at least 10% lengthwise, between the thickest portion and the thinnest portion, is achieved by heat-rolling, the resulting laminated product having a variable thickness is solution heat-treated and soaked, and the laminated product, which has a variable thickness and which is thus solution heat-treated and soaked, is stress-relieved by controlled traction with a permanent deformation of at least 1 % in the thickest portion prior to natural or artificial aging. The products obtained according to the invention have a mechanical resistance that is improved by at least 5% in the thinnest portion and an improvement in stiffness of at least 15% in the thickest portion. The products according to the invention are useful in particular for producing lower or upper wing skins for an aircraft because the "buy to fly" ratio and the properties are simultaneously improved.

    摘要翻译： 本发明涉及的制造方法制成在其中热轧的可热处理铝合金的可变厚度的轧制产品被执行以实现在最厚的部分和最薄部分之间的纵向的至少10％的厚度变化; 下获得的可变厚度的轧制产品进入固溶热处理，并与天然或人工时效之前最厚的部分的永久变形至少1％猝灭。 获得gemäß发明表现出改进的产品的在最薄的部分至少5％的机械强度和至少15％的最厚的部分改进的断裂韧性。 产品雅丁到本发明的是在飞机上或下机翼蒙皮“购买飞”比率的制造特别有用和性能同时提高。

    Upper joints between outboard wing boxes and wing center sections of aircraft wing assemblies
    86.
    发明公开
    Upper joints between outboard wing boxes and wing center sections of aircraft wing assemblies 有权
    外侧机翼盒和飞机的中央翼部之间上连杆

    公开(公告)号：EP2848519A1

    公开(公告)日：2015-03-18

    申请号：EP14172648.9

    申请日：2014-06-17

    申请人： The Boeing Company

    发明人： Charles, Jordan Daniel ,  Hamada, Jason

    IPC分类号： B64C1/26

    CPC分类号： B64C1/26 ,  B64C3/00 ,  B64C3/182 ,  B64C3/187 ,  B64C2001/0072 ,  B64C2001/0081

    摘要： An upper joint of a wing assembly of an aircraft includes an outboard upper wing panel, a center upper wing panel, a rib, and an upper joint assembly operatively interconnecting the outboard upper wing panel, the center upper wing panel, and the rib. In some embodiments, outboard upper stringers may be configured differently than center upper stringers. In some embodiments, a subset of the center upper stringers may not directly oppose the outboard upper stringers. In other embodiments, for at least a substantial fore/aft span of the upper joint, each of the center upper stringers may directly oppose an outboard upper stringer. In particular the present invention relates to An upper joint for a wing assembly of an aircraft, the upper joint comprising: an outboard upper wing panel (24) of an outboard wing box (20, 22); a center upper wing panel (28) of a wing center section (18); a rib (32) that is located between the outboard wing box and the wing center section; and an upper joint assembly (38) operatively interconnecting the outboard upper wing panel, the center upper wing panel, and the rib; wherein the upper joint assembly defines a mating plane (48) between the outboard wing box and the wing center section; wherein when the upper joint is in compression, the outboard upper wing panel expresses a compressive inward pressure toward the upper joint assembly; wherein when the upper joint is in compression, the center upper wing panel expresses a compressive outward pressure toward the upper joint assembly; and wherein a centroid (54) of the compressive inward pressure (50) across an acreage of the outboard upper wing panel when extended across the mating plane intersects the mating plane below or above where a centroid (56) of the compressive outward pressure (52) across an acreage of the center upper wing panel when extended across the mating plane intersects the mating plane.

    摘要翻译： 飞行器的机翼组件的上接头包括在外侧上翼板，中央上翼板，肋，并且在上接头组件可操作地相互连接的外侧机翼上面板，该上翼中央面板，和肋。 在一些实施方案中，外侧上部桁可以不同于中央上桁条构成。 在一些实施例中，中心的一个子集上桁条可能不会直接相对外侧上桁。 在其它实施方案中，对于至少一个实质性的前/后上部关节的跨度，每个所述中心上部桁条可以直接在外侧上部纵梁反对。 特别是在本发明涉及一种用于飞行器的机翼组件上关节，上接头包括：一个外侧翼盒（20，22）的外侧上翼面板（24）; 一个机翼中心部分的一个中心翼上面板（28）（18）; 的肋（32）做了位于外侧机翼盒和机翼中心部分之间; 并在上接头组件（38），可操作地连接所述外侧机翼上面板，该上翼中央面板，和肋; worin上部接头组件定义外侧机翼盒和机翼中心部分之间的配合面（48）; worin当上关节处于压缩状态，上外侧翼面板表达向内培养压缩压力朝向上接头组件; worin当上关节处于压缩状态，上翼中心面板表达向外训练压缩压力朝向上接头组件; 和worin横跨外侧上翼板的面积的平面的压缩向内压力（50）的质心（54）当跨越配合延伸的配合平面相交的下方或上方，其中压缩的向外压力的质心（56）（52 ）横跨在中心上翼板的面积当跨越配合平面相交延伸的配合平面。

    METHOD AND APPARATUS FOR INHIBITING FORMATION OF AND/OR REMOVING ICE FROM AIRCRAFT COMPONENTS
    87.
    发明公开
    METHOD AND APPARATUS FOR INHIBITING FORMATION OF AND/OR REMOVING ICE FROM AIRCRAFT COMPONENTS 审中-公开
    方法和装置来抑制形成和/或删除EIS飞机部件

    公开(公告)号：EP2740210A2

    公开(公告)日：2014-06-11

    申请号：EP12822015.9

    申请日：2012-08-03

    申请人： General Atomics

    发明人： GILES, Alan, M. ,  MACHIN, James, T. ,  GERIGUIS, John, A.

    IPC分类号： H02N2/06 ,  H01L41/02

    CPC分类号： B64D15/20 ,  B64C3/00 ,  B64C9/00 ,  B64C11/16 ,  B64D15/16 ,  B64D15/163 ,  B64D15/22

    摘要： Methods and systems are generally described that inhibit debris (such as ice) accretions and/or remove debris (such as ice) accretions from the exterior surface of an aircraft. In some embodiments, the invention is a system for an aircraft comprising: a component of the aircraft having a surface; a plurality of piezo-kinetic actuators each positioned proximate to a portion of the surface; and a control unit coupled to the plurality of actuators, the control unit configured to actuate one or more of the actuators at one or more frequencies between about 1 Hz and about 1 kHz; wherein the actuators are each configured to introduce a displacement of the surface in three dimensions to inhibit a formation of ice on at least the portion of the surface and to break up existing ice formations on at least the portion of the surface.

    SUPPORT STRUCTURE FOR A WING
    88.
    发明授权
    SUPPORT STRUCTURE FOR A WING 有权
    支护结构翼

    公开(公告)号：EP1915291B1

    公开(公告)日：2011-11-16

    申请号：EP06776883.8

    申请日：2006-08-16

    申请人： Airbus Operations GmbH

    发明人： MÄNZ, Christian

    IPC分类号： B64C3/26 ,  B64C3/00 ,  E04B1/19 ,  F16B7/18

    CPC分类号： B64C1/26 ,  B64C3/00 ,  B64C3/26 ,  B64C5/06 ,  E04B2001/193 ,  Y10T403/4381

    摘要： The present invention relates to a support structure for an aircraft, which support structure comprises one or several bar elements (36) and one or several junction elements (37), wherein at least one bar element (36) comprises a transition region (9) which can be made to engage at least one junction element (37). When the transition region (9) of the bar element (36) engages the junction element (37), of which there is at least one, centric force transmission takes place between the bar element (36) and the junction element (37).