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    SEGMENTED SPANWISE BEAM FOR ENHANCED CENTER WING BOX ACCESS
    45.
    发明公开
    SEGMENTED SPANWISE BEAM FOR ENHANCED CENTER WING BOX ACCESS 审中-公开

    公开(公告)号：EP4368499A1

    公开(公告)日：2024-05-15

    申请号：EP23199325.4

    申请日：2023-09-25

    Applicant: The Boeing Company

    Inventor： WHITFIELD, IAN FORREST ,  PHILLIPS, ERIK ALAN

    IPC: B64C1/26 ,  B64C1/06 ,  B64C1/00

    CPC classification number: B64C1/26 ,  B64C2001/007220130101 ,  B64C1/065

    Abstract: An aircraft (100), a center wing box assembly (150) for an aircraft (100), and a spanwise beam section (155) for a center wing box assembly (150) that includes a segmented structural configuration with an optimized access hole (155e) to accommodate user access into an interior space of the center wing box for purposes of assembly and maintenance. The center wing box assembly (150) includes a first spanwise beam section (155a), a second spanwise beam section (155b), spaced from the first spanwise beam section (155a), and a plurality of chord members (155c, 155d) serving as load-bearing structural reinforcement members for the first spanwise beam section (155a) and the second spanwise beam section (155b). The chord members (155c, 155d) extend across the space between the first spanwise beam section (155a) and the second spanwise beam section (155b) to connect the first spanwise beam section (155a) and the second spanwise beam section (155b) in a manner which defines an access hole (155e) at the interior space.

    Aircraft with a trimmable horizontal stabilizer having the pivot elements in its forward side
    46.
    发明授权
    Aircraft with a trimmable horizontal stabilizer having the pivot elements in its forward side 有权

    公开(公告)号：EP2889216B1

    公开(公告)日：2018-09-19

    申请号：EP13382578.6

    申请日：2013-12-31

    Applicant: Airbus Operations S.L.

    Inventor： Llamas Sandin, Raúl ,  Luque Buzo, Miguel ,  Martinez Munõz, José Luis

    IPC: B64C5/02 ,  B64C1/26 ,  B64C13/28

    CPC classification number: B64C9/08 ,  B64C1/26 ,  B64C5/02 ,  B64C9/02 ,  B64C13/28

    Abstract: The invention provides an aircraft with a trimmable horizontal stabilizer (13) that not requires a cut-out in resistant areas of the rear fuselage and that occupies less space that in conventional horizontal stabilizers. The rear fuselage (5) comprises at least a first section (9) having a resistant fuselage and a second section (11), aft of the first section, having a non-resistant fuselage (i.e. a fairing). The load-bearing structure (30) of the horizontal stabilizer and the trimming actuator (50) are disposed inside said second section (11). The pivot element (41) is mounted on its forward side and coupled to the first section (9) of the rear fuselage. The connection fitting (21) is mounted on its rearward side and the trimming actuator (50) is disposed so that it exerts a force in the direction of the Z-axis of the aircraft on the connection fitting (21) during a trimming operation.

    METAL FITTINGS FOR ENGAGING THE VERTICAL TAILPLANE OF AN AIRCRAFT
    49.
    发明授权
    METAL FITTINGS FOR ENGAGING THE VERTICAL TAILPLANE OF AN AIRCRAFT 有权
    用于接合飞机垂直尾翼的金属配件

    公开(公告)号：EP2444315B1

    公开(公告)日：2018-01-10

    申请号：EP10719020.9

    申请日：2010-04-21

    Applicant: Airbus Operations, S.L.

    Inventor： FOLCH CORTÉS, Diego ,  ARÉVALO RODRÍGUEZ, Elena ,  VERA VILLARES, Enrique ,  CABEZA HUERTA, Javier ,  PINA LÓPEZ, José María

    IPC: B64C1/26

    CPC classification number: B64C1/26 ,  Y10T29/49826

    Abstract: The invention relates to fittings (41, 71) for fixing the vertical tail stabilizer of an aircraft in an area of its rear fuselage integrally manufactured with a composite material comprising: a) a first piece (43, 73) comprising lugs (45, 45'; 75, 75') for fixing the vertical tail stabilizer and vertical walls (47, 47'; 77, 77') for fixing the fitting (41, 71) to the frames (7); b) at least one pair of additional pieces (49, 49'; 79, 79') comprising horizontal walls (51, 51'; 81, 81') for fixing the fitting (41, 71) to the skin (5). The fitting (71) for fixing with an inclined load also comprises a second pair of pieces (90, 90') having an angular shape comprising vertical walls (93, 93') for the fixing with the lugs (75, 75'). The invention also relates to processes for assembling these fittings (41, 71).

    ADVANCED AUTOMATED PROCESS FOR THE WING-TO-BODY JOIN OF AN AIRCRAFT WITH PREDICTIVE SURFACE SCANNING
    50.
    发明公开
    ADVANCED AUTOMATED PROCESS FOR THE WING-TO-BODY JOIN OF AN AIRCRAFT WITH PREDICTIVE SURFACE SCANNING 有权
    用于自动翼飞机改进的进程与预测表面采样船体连接

    公开(公告)号：EP3168162A1

    公开(公告)日：2017-05-17

    申请号：EP16195724.6

    申请日：2016-10-26

    Applicant: The Boeing Company

    Inventor： VASQUEZ, Christina Michelle ,  VALENZUELA, Dario I ,  COLLINS, Ronald J ,  BODE, Aksel

    IPC: B64F5/10

    CPC classification number: G06F17/5095 ,  B64C1/26 ,  B64F5/10

    Abstract: Disclosed aircraft wing-to-body join methods include (a) applying targets to a wing and a body assembly at the respective wing root and wing stub, (b) determining the 3D locations of the targets by photogrammetry, (c) generating 3D surface profiles for the interface surfaces of the wing root and wing stub by combining scans of the interface surfaces, (d) calculating a virtual fit between the wing and the body assembly that defines one or more gaps between the generated 3D surface profiles of the wing root and wing stub, (e) positioning at least three position sensors within the wing root and/or the wing stub, and (f) aligning the wing to the body assembly to achieve a real fit consistent with the calculated virtual fit using feedback from the position sensors. Methods of determining the target locations and/or the 3D surface profiles may utilize a mobile scanning platform.

    Abstract translation: 公开的飞机机翼 - 机身连接的方法包括（a）将目标以一个翼，并在respectivement翼根和翼存根一主体组件，（b）中确定的采矿通过摄影目标的三维位置，（c）生成三维表面 型材翼根和翼短截线的接口面通过组合扫描接口表面，（d）计算所述翼和主体组件之间的虚拟配合确实定义了一个或翼根的所生成的3D表面轮廓之间多个间隙 和翼存根，翼根和/或机翼存根，和（f）的翼对准至主体组件内（e）中定位至少三个位置传感器以实现与使用从反馈计算出的虚拟配合一致的真实的配合 位置传感器。 确定性采矿方法的目标的位置和/或3D表面轮廓可利用移动扫描台。

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