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14 条记录 (耗时 0.012 秒)

    AIRCRAFT STRUCTURAL, ANTI-BALLISTIC FLOOR PANEL
    1.
    发明申请
    AIRCRAFT STRUCTURAL, ANTI-BALLISTIC FLOOR PANEL 有权

    公开(公告)号：US20230036032A1

    公开(公告)日：2023-02-02

    申请号：US17790514

    申请日：2021-01-14

    申请人： Fokker Aerostructures B.V.

    发明人： Erik Dekker

    IPC分类号： B64D7/00 ,  B64C27/04 ,  B64C1/18 ,  F41H5/02 ,  F41H5/04

    摘要： There is provided an anti-ballistic aerospace structure, said structure comprising a strike layer defining an outwardly facing surface and an opposing capture layer defining an inwardly facing surface and an intermediate structural layer arranged between the strike layer and capture layer, wherein the intermediate structural layer is spaced relative to the strike layer to define a space between the intermediate structural layer and the strike layer, said space comprising one or more reinforcement elements, and wherein the strike layer is formed of a fiber reinforced plastic laminate comprising at least one metallic layer.

    AIRFOIL-SHAPED BODY WITH A VARIABLE OUTER SHAPE
    6.
    发明申请
    AIRFOIL-SHAPED BODY WITH A VARIABLE OUTER SHAPE 有权

    公开(公告)号：US20210139128A1

    公开(公告)日：2021-05-13

    申请号：US16492905

    申请日：2018-03-16

    申请人： FOKKER AEROSTRUCTURES B.V.

    发明人： Adrianus Marinus Franciscus BASTIAANSEN

    IPC分类号： B64C3/48 ,  B64C3/26

    摘要： An airfoil-shaped body having a variable outer shape, comprising: a first skin, defining a suction surface, a second skin, defining a pressure surface and connected to the first skin at least at a leading edge and/or a trailing edge of the airfoil-shaped body, at least one elongate stiffening beam, arranged inside a cavity of the airfoil-shaped body and secured to at least one of said first and second skins, the stiffening beam including at least a first and a second beam section arranged one after the other and a joining member, arranged between end portions of the beam sections and connected thereto, said joining member being adapted to allow relative movement between the beam sections by an elastic deformation; and an actuator that is operationally associated with said elongate stiffening beam, wherein, upon operating the actuator, the first beam section is moved with respect to the second beam section, or vice versa, changing the orientation of the beam sections with respect to each other, which causes a change in the variable outer shape of the airfoil-shaped body.

    Airplane wing, an airplane and a flap system
    8.
    发明授权
    Airplane wing, an airplane and a flap system 有权

    公开(公告)号：US09868512B2

    公开(公告)日：2018-01-16

    申请号：US14440272

    申请日：2013-10-29

    申请人： FOKKER AEROSTRUCTURES B.V.

    发明人： Adrianus Marinus Franciscus Bastiaansen ,  Michel Schoonhoven

    IPC分类号： B64C9/38 ,  B64C9/16 ,  B64C9/18 ,  B64C13/00

    CPC分类号： B64C9/38 ,  B64C9/16 ,  B64C9/18 ,  B64C13/00 ,  Y02T50/32

    摘要： An airplane wing comprises a main wing and a flap system that has a flap at the trailing edge of the main wing. An elongate flap track member is connected to the main wing in such a manner that it can be moved substantially in its longitudinal direction and is guided by supporting bearing elements relative to the main wing between a forward retracted position and a rearward extended position. The flap is rotatably connected to the rear end of the flap track member in such a manner that it can rotate about a rotation axis that extends substantially parallel to the trailing edge of the main wing, so that the flap moves together with the flap track member when the flap track member is moved and so that the flap can be rotated about the rotation axis mechanically independently of the movement of the flap track member. The flap system comprises an actuator system having two actuators. The first actuator is connected to the main wing and has an engagement member that engages the flap or the flap track member for moving the flap together with the flap track member so that the flap track member is move able between its retracted position and its extended position. The second actuator is connected to the flap track member so that the second actuator moves together with the flap track member when the flap track member is moved by means of the first actuator. The second actuator has an engagement member that engages the flap for rotating the flap about the rotation axis.

    Apparatus and a method for ultrasonic inspection of multi-layered structures
    9.
    发明授权
    Apparatus and a method for ultrasonic inspection of multi-layered structures 有权

    公开(公告)号：US11333632B2

    公开(公告)日：2022-05-17

    申请号：US16606527

    申请日：2018-04-20

    申请人： FOKKER AEROSTRUCTURES B.V.

    发明人： Jaap Louis Speijer ,  Jeroen Jozef Gerardus Ignatius Rutten

    IPC分类号： G01N29/22 ,  G01N29/24 ,  G01N29/28 ,  G01N29/04

    摘要： Disclosed is an apparatus for ultrasonic inspection of a multi-layered, ML, plate with a stiffener attached on a first surface of the ML plate. The apparatus includes a transmitter directing a first ultrasonic beam along a first guiding medium to the ML plate, along a first axis at an angle to the first surface, the first axis being within a transmission angle with respect to a first normal perpendicular to the first surface, and a receiver for receiving a transmitted ultrasonic beam originating from the first beam after passing through the ML plate along a second axis of a second guiding medium for directing the transmitted beam. The apparatus is configured for setting the transmission angle of the first axis of the first beam to let the second axis pass through a location beneath the stiffener beneath the first surface to which the stiffener is attached.

    Airfoil-shaped body with a variable outer shape
    10.
    发明授权
    Airfoil-shaped body with a variable outer shape 有权

    公开(公告)号：US11254411B2

    公开(公告)日：2022-02-22

    申请号：US16492905

    申请日：2018-03-16

    申请人： FOKKER AEROSTRUCTURES B.V.

    发明人： Adrianus Marinus Franciscus Bastiaansen

    IPC分类号： B64C3/48 ,  B64C3/26

    摘要： An airfoil-shaped body having a variable outer shape, comprising: a first skin, defining a suction surface, a second skin, defining a pressure surface and connected to the first skin at least at a leading edge and/or a trailing edge of the airfoil-shaped body, at least one elongate stiffening beam, arranged inside a cavity of the airfoil-shaped body and secured to at least one of said first and second skins, the stiffening beam including at least a first and a second beam section arranged one after the other and a joining member, arranged between end portions of the beam sections and connected thereto, said joining member being adapted to allow relative movement between the beam sections by an elastic deformation; and an actuator that is operationally associated with said elongate stiffening beam, wherein, upon operating the actuator, the first beam section is moved with respect to the second beam section, or vice versa, changing the orientation of the beam sections with respect to each other, which causes a change in the variable outer shape of the airfoil-shaped body.