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14 条记录 (耗时 0.01 秒)

    WING FOR AN AIRCRAFT
    1.
    发明公开
    WING FOR AN AIRCRAFT 审中-公开

    公开(公告)号：EP4303119A1

    公开(公告)日：2024-01-10

    申请号：EP23179919.8

    申请日：2023-06-19

    申请人： Airbus Operations GmbH

    发明人： BENSMANN, Stefan

    IPC分类号： B64C3/18 ,  B64D15/04 ,  B64D37/00 ,  B64C13/28 ,  B64C13/36 ,  B64D37/04

    摘要： A wing for an aircraft is proposed, comprising a leading edge as a first chordwise edge, a trailing edge as a second chordwise edge, an upper skin extending between the leading edge and the trailing edge, a lower skin extending between the leading edge and the trailing edge, at least one spar extending between the upper skin and the lower skin in a spanwise direction to create wing box with the upper skin and the lower skin, and at least one of a fluid line, an electrical line, and a mechanical power transfer device attached inside or reaching into the wing box at least partially.

    PICCOLO TUBE FOR DE-ICING AN AIRFOIL STRUCTURE OF AN AIRCRAFT, DE-ICING SYSTEM AND AIRFOIL STRUCTURE
    4.
    发明公开
    PICCOLO TUBE FOR DE-ICING AN AIRFOIL STRUCTURE OF AN AIRCRAFT, DE-ICING SYSTEM AND AIRFOIL STRUCTURE 审中-公开

    公开(公告)号：EP4074602A1

    公开(公告)日：2022-10-19

    申请号：EP21168198.6

    申请日：2021-04-13

    申请人： Airbus Operations GmbH

    发明人： BENSMANN, Stefan ,  ERBAN, Marcus ,  FEES, Martin

    IPC分类号： B64D15/04 ,  B64C3/16

    摘要： A piccolo tube (28) for de-icing an airfoil structure of an aircraft, in particular a slat (16), has a shape extending in a longitudinal direction and is configured for installation in an airfoil structure (12,16) of an aircraft (10) in the longitudinal direction of the airfoil structure (12,16). The piccolo tube (28) comprises a connector element (34) for receiving heated air from a supply source, and a longitudinally extending air duct (32) having a plurality of outlet openings arranged along the air duct (32), for supplying and distributing the heated air along the inner side of the airfoil structure (12,16). The piccolo tube (28) is curved and its curvature is adapted to a curvature of the airfoil structure (12,16) in its longitudinal direction. A de-icing system comprises the piccolo tube (28) and a supply source for supplying heated air to the piccolo tube (28). An airfoil structure (12, 16), in particular a slat (16), comprises the piccolo tube (28) and/or the de-icing system.

    WING FOR AN AIRCRAFT
    5.
    发明公开
    WING FOR AN AIRCRAFT 审中-公开

    公开(公告)号：EP4303122A1

    公开(公告)日：2024-01-10

    申请号：EP23180814.8

    申请日：2023-06-22

    申请人： Airbus Operations GmbH

    发明人： BENSMANN, Stefan

    IPC分类号： B64C9/02 ,  B64C3/50 ,  B64C9/22 ,  B64C9/08 ,  B64C13/28 ,  B64C9/24 ,  B64C3/18 ,  B64C3/28 ,  B64C9/14

    摘要： A wing for an aircraft is proposed, comprising a leading edge, a trailing edge, an upper skin extending between the leading edge and the trailing edge, a lower skin extending between the leading edge and the trailing edge, at least one spar extending between the upper skin and the lower skin in a spanwise direction to create a wing box with the upper skin and the lower skin, and at least one droop nose arranged at the leading edge, wherein the at least one droop nose is coupled with a forward end of a hinge arm that extends in a chordwise direction, and wherein a rearward end of the hinge arm is swivably supported directly at or in the wing box.

    WING FOR AN AIRCRAFT
    10.
    发明公开
    WING FOR AN AIRCRAFT 审中-公开

    公开(公告)号：EP4303123A1

    公开(公告)日：2024-01-10

    申请号：EP23181114.2

    申请日：2023-06-23

    申请人： Airbus Operations GmbH

    发明人： BENSMANN, Stefan

    IPC分类号： B64C9/02 ,  B64C3/50 ,  B64C9/22 ,  B64C9/16 ,  B64C9/08 ,  B64C13/28 ,  B64C9/18 ,  B64C9/24 ,  B64C3/18 ,  B64C3/28 ,  F16H19/04 ,  B64C9/14

    摘要： A wing for an aircraft is proposed, comprising a leading edge as a first chordwise edge, a trailing edge as a second chordwise edge, an upper skin extending between the leading edge and the trailing edge, a lower skin extending between the leading edge and the trailing edge, at least one spar extending between the upper skin and the lower skin in a spanwise direction to create wing box with the upper skin and the lower skin, and at least one high lift control surface movably supported at at least one of the chordwise edges by a support device, wherein the support device is attached inside or reaches into the wing box at least partially.