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    FLAP SYSTEM FOR AN AIRCRAFT AND METHOD OF OPERATING A FLAP FAIRING AT AN AIRCRAFT WING
    1.
    发明公开
    FLAP SYSTEM FOR AN AIRCRAFT AND METHOD OF OPERATING A FLAP FAIRING AT AN AIRCRAFT WING 审中-公开

    公开(公告)号：EP4410667A1

    公开(公告)日：2024-08-07

    申请号：EP23154160.8

    申请日：2023-01-31

    申请人： Airbus Operations GmbH

    发明人： Lorenz, Florian ,  Bernhard, Schlipf

    IPC分类号： B64C9/16 ,  B64C13/28 ,  B64C9/32 ,  B64C9/34

    CPC分类号： B64C9/16 ,  B64C13/28 ,  B64C9/32 ,  B64C9/34

    摘要： The invention relates to a flap system (10) for an aircraft (100). The flap system (10) comprises a wing structure (12), a trailing-edge movable (18a, 18b, 18c) and an attachment unit (20) for movably coupling the trailing-edge movable (18a, 18b, 18c) to the wing structure (12). The attachment unit (20) comprises an attachment mechanism (22) and a cover element (24) which at least partly encloses the attachment mechanism (22). The attachment unit (20) comprises a drive element (26) which is configured to move the cover element (24) along an aerodynamic outer surface (16) of a skin section (14) of the wing structure (12) between a first position (51) and a second position (52), wherein the movement of the cover element (24) along the aerodynamic outer surface (16) is defined by a translational movement (53) of the cover element (24) relative to the skin section (14).

    AN AIRCRAFT CONTROL SURFACE DEPLOYMENT SYSTEM
    2.
    发明公开
    AN AIRCRAFT CONTROL SURFACE DEPLOYMENT SYSTEM 审中-公开

    公开(公告)号：EP4375183A1

    公开(公告)日：2024-05-29

    申请号：EP23210640.1

    申请日：2023-11-17

    申请人： Airbus Operations Limited

    发明人： CUSTANCE, Denys ,  LOPEZBOIX, Marc

    IPC分类号： B64C3/58 ,  B64C9/02 ,  B64C9/32

    CPC分类号： B64C3/58 ,  B64C9/02 ,  B64C9/323

    摘要： An aircraft control surface deployment system (100) for an aircraft structure, for example a spoiler deployment system for an aircraft wing, comprises a cam body (300), an actuator (200) and a coupling mechanism (120). The actuator (200) moves the cam body (300) such that it raises and lowers the aircraft control surface (400). The actuator (200) is connected to the cam body (300) via the coupling mechanism (120). The coupling mechanism (120) has a first portion (320) connected to the cam body (300) and a second portion (220) connected to the actuator (200), configured such that the coupling mechanism (120) allows some free relative movement and rotation of the first and second portions (220, 320). Loads transverse to the axis of movement of the actuator (200), resulting from relative movement of the cam body (300), are not transferred to the actuator (200).

    BRAKE SYSTEMS FOR AIRCRAFT AND RELATED METHODS
    6.
    发明公开
    BRAKE SYSTEMS FOR AIRCRAFT AND RELATED METHODS 审中-公开

    公开(公告)号：EP3670351A1

    公开(公告)日：2020-06-24

    申请号：EP19212676.1

    申请日：2019-11-29

    申请人： The Boeing Company

    发明人： JASKLOWSKI, Christopher T ,  MACKIN, Steve G

    IPC分类号： B64D29/08 ,  B64C9/32 ,  F02K1/70

    摘要： Braking systems for aircraft (100) are disclosed. An example braking system (102) includes a fan cowl (208) having a leading edge (212) and a trailing edge (214). The braking system (102) includes a hinge assembly (216) coupled between the leading edge (212) and a fan cage (218) of an aircraft engine (110/112) to enable the fan cowl (208) to move between a stowed position (202) and a deployed position (204). An actuator system (220) is coupled to the leading edge (212) of the fan cowl (208), and the actuator system (220) is to move the fan cowl (208) via the hinge assembly (216) from the stowed position (202) to the deployed position (204) in a direction away from the aircraft engine (110/112) and toward a fore end of the aircraft (100) to provide an air brake during a braking event.

    TRAILING EDGE DEVICE WITH BELL CRANK MECHANISM
    9.
    发明授权
    TRAILING EDGE DEVICE WITH BELL CRANK MECHANISM 有权

    公开(公告)号：EP3034393B1

    公开(公告)日：2018-10-17

    申请号：EP15199859.8

    申请日：2015-12-14

    申请人： The Boeing Company

    发明人： Fevergeon, Matthew D M ,  Kordel, Jan A.

    IPC分类号： B64C9/16 ,  B64C9/02 ,  B64C9/04 ,  B64C9/12 ,  B64C9/10 ,  B64C9/32

    CPC分类号： B64C9/04 ,  B64C9/02 ,  B64C9/10 ,  B64C9/16 ,  B64C9/18 ,  B64C9/323 ,  B64C13/28 ,  B64C2009/005 ,  Y02T50/32

    摘要： A bell crank mechanism 150 is configured to at least indirectly link any movement of an aircraft wing spoiler-like hinge panel to the movement of an aircraft wing 110 trailing edge flight control device 124. The aircraft wing is configured to be fixed to and to extend from an aircraft fuselage, the wing including a leading edge and a trailing edge. The flight control device is attached to the trailing edge, and any movement of the control device is directly subject to an aircraft input controller. The moveable aerodynamic hinge panel is situated proximally to the control device, and the hinge panel is separately attached to the trailing edge. As configured, the bell crank mechanism assures that any hinge panel motion is slaved to the control device in a manner intended to optimize aerodynamic performance and efficiency.