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    AIRCRAFT ASSEMBLY WITH MOVEABLE DEVICE
    51.
    发明公开
    AIRCRAFT ASSEMBLY WITH MOVEABLE DEVICE 审中-公开

    公开(公告)号：EP4406830A1

    公开(公告)日：2024-07-31

    申请号：EP24152424.8

    申请日：2024-01-17

    申请人： Airbus Operations Limited

    发明人： CUSTANCE, Denys

    IPC分类号： B64C9/02 ,  B64C9/14 ,  B64C9/32

    CPC分类号： B64C9/146 ,  B64C9/323 ,  B64C9/02

    摘要： An aircraft assembly has: a cover with an outer aerodynamic surface and an aperture with a stop adjacent an edge of the aperture, and a moveable device for extending through the aperture in the cover. The moveable device carries a panel attached to the moveable device by a plurality of leaf springs. The assembly is configured so that when the moveable device is moved towards a retracted position the panel bears against the stop forming a substantially flush surface with the outer aerodynamic surface of the cover surrounding the aperture. The panel is displaced from the moveable device by elastic deformation of at least some of the leaf springs.

    AIRCRAFT WING TRAILING EDGE DEVICE
    54.
    发明公开
    AIRCRAFT WING TRAILING EDGE DEVICE 审中-公开

    公开(公告)号：EP4306408A1

    公开(公告)日：2024-01-17

    申请号：EP23185127.0

    申请日：2023-07-12

    申请人： Airbus Operations Limited

    发明人： FAMILY, Oliver

    IPC分类号： B64C3/50 ,  B64C3/54 ,  B64C9/20 ,  B64C9/32 ,  B64C13/16

    摘要： An aircraft wing (4) comprising a trailing edge system (12), comprising a pivotable spoiler (8) and a moveable flap (6). The flap has a pivotable trailing edge device (e.g. a tab 14), which is for example able to rotate independently of the flap by up to +/-20 degrees. The flap (6) is translatable and rotatable relative to the wing independently of the movement of the spoiler (8). In use, the trailing edge system (12) is configured to adopt one of several different configurations or modes of operation facilitating all of camber and/or wing chord change during cruise, high speed and low speed roll control mode, enhanced high lift, and load alleviation. As such, the wing may not need any separate ailerons or other trailing edge control surfaces, and may also offer improved aerodynamics, reduced drag and other efficiency improving benefits.

    MINI-SPOILERS FOR ENHANCING THE EFFECTIVENESS OF LATERAL-CONTROL SURFACES OF AIRCRAFT WINGS
    59.
    发明公开
    MINI-SPOILERS FOR ENHANCING THE EFFECTIVENESS OF LATERAL-CONTROL SURFACES OF AIRCRAFT WINGS 审中-公开

    公开(公告)号：EP3825227A1

    公开(公告)日：2021-05-26

    申请号：EP20209049.4

    申请日：2020-11-20

    申请人： The Boeing Company

    发明人： VIJGEN, Paul M. ,  MALACHOWSKI, Adam P. ,  KONINGS, Christopher A. ,  GEPPERT, Brian E.

    IPC分类号： B64C9/00 ,  B64C9/04 ,  B64C9/10 ,  B64C9/12 ,  B64C9/32

    摘要： Mini-spoilers for enhancing the effectiveness of lateral-control surfaces of aircraft wings are described. An example aircraft includes a wing (800), a lateral-control surface in the form of an aileron (132), a flaperon or a spoiler, as well as a mini-spoiler (808). The lateral-control surface is movably coupled to the wing. The lateral-control surface is movable between a neutral position, a first upward deflected position, and a second upward deflected position extending beyond the first upward deflected position. The mini-spoiler is located on or forward of the lateral-control surface. The mini-spoiler is movable between a retracted position and a deployed position. The mini-spoiler is configured to be moved from the retracted position to the deployed position based on the lateral-control surface being moved from the neutral position to or toward the first upward deflected position.

    FRICTION STIR WELDED AIRCRAFT STRUCTURE AND METHOD
    60.
    发明公开
    FRICTION STIR WELDED AIRCRAFT STRUCTURE AND METHOD 审中-公开

    公开(公告)号：EP3782903A1

    公开(公告)日：2021-02-24

    申请号：EP20191268.0

    申请日：2020-08-17

    申请人： The Boeing Company

    发明人： GRUNER, Bryan J. ,  SCHLEUTER, Lisa G.

    IPC分类号： B64C9/32 ,  B23K20/12

    摘要： An aircraft control structure (108, 200) includes first (212) and second outer surfaces (214) joined to a side wall (212). Stiffening webs (230, 234, 238) extends between the first (212) and second outer surfaces (214), each stiffening web at least partially surrounding an associated aperture (218, 220, 222) formed in either the first or second outer surface and defining a stiffening recess (248). Skin plates (260, 262, 264) are sized to extend over an associated stiffening recess and are shaped to conform to an associated aperture (218, 220, 222). Each skin plate is joined to an associated stiffening web by a friction stir welded seam (300, 302, 304).