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    Fixed wing of an aircraft
    21.
    发明授权
    Fixed wing of an aircraft 有权
    一架飞机的固定翼

    公开(公告)号：US09555874B2

    公开(公告)日：2017-01-31

    申请号：US14713756

    申请日：2015-05-15

    Applicant: Airbus Operations GmbH ,  Airbus Operations Ltd.

    Inventor： Gerd Heller ,  Alexander Buescher ,  Frank Theurich ,  Tom Gibson ,  Michael Karwin ,  Stephen Powell

    IPC: B64C3/58 ,  B64C23/06

    CPC classification number: B64C3/58 ,  B64C23/069 ,  Y02T50/164

    Abstract: A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box including spars extending along the spanwise direction of the main wing, ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box includes a wing box base section (K10) and a wing box adapter section, that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device. In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib of the wing box base section (K10) up to the outermost rib of the wing box adapter section.

    Abstract translation: 一种飞机的固定翼，具有在半跨上延伸的主翼，翼翼包括沿着主翼的翼展方向延伸的翼梁，沿翼展方向观察的一个在后面布置的肋，以及外翼 皮肤。 机翼箱包括一个翼盒基部（K10）和一个翼盒适配器部分，从机翼根部看，形成了机翼箱的外端区域，并被设计成固定翼尖装置。 在其标称结构状态下，翼箱适配器部分参考相应的局部翼展方向的二面角从翼箱基部（K10）的外肋连续增加至多60度，直到最终肋 翼盒适配器部分。

    GUIDING DEVICE WHICH IS INTENDED TO BE INTERPOSED BETWEEN A DEVICE FOR FIXING COMPONENTS OF AN ASSEMBLY, AND A DEVICE FOR PROTECTING THE FIXING DEVICE
    23.
    发明申请
    GUIDING DEVICE WHICH IS INTENDED TO BE INTERPOSED BETWEEN A DEVICE FOR FIXING COMPONENTS OF AN ASSEMBLY, AND A DEVICE FOR PROTECTING THE FIXING DEVICE 有权
    用于固定装配组件的装置和用于保护固定装置的装置之间的插入装置

    公开(公告)号：US20140321944A1

    公开(公告)日：2014-10-30

    申请号：US14265994

    申请日：2014-04-30

    Applicant: Airbus Operations (SAS) ,  Airbus Operations LTD

    Inventor： Clement Chirol ,  Philip Cresswell ,  Florian Dapot

    IPC: F16B33/00 ,  B64D47/00

    CPC classification number: F16B33/004 ,  B64D45/02 ,  F16B5/025 ,  F16B19/05 ,  F16B33/02 ,  F16B37/14 ,  F16B39/025 ,  Y10T29/49925

    Abstract: An assembly comprising at least two non-metal components which are fixed to each other using at least one fixing system. The fixing system includes a fixing device with a fixing element which is provided with a head and a rod, and a crimping ring which is in contact with one of the components. A protection device is a part of the fixing system which delimits a cavity for confining gas around a portion of the device comprising the crimping ring. In order to improve the repeatability of the operation for positioning the protection device, a guiding device is provided which includes an assembly element on the portion of the fixing device, and an element for guiding the protection device.

    Abstract translation: 一种组件，其包括使用至少一个固定系统彼此固定的至少两个非金属部件。 固定系统包括具有固定元件的固定装置，该固定元件设置有头部和杆，以及与其中一个部件接触的压接环。 保护装置是定影系统的一部分，其限定用于围绕包括压接环的装置的一部分围绕气体的空腔。 为了提高用于定位保护装置的操作的重复性，提供了一种引导装置，其包括在固定装置的部分上的组件元件和用于引导保护装置的元件。

    Trailing edge panel support
    25.
    发明授权
    Trailing edge panel support 有权

    公开(公告)号：US12097953B2

    公开(公告)日：2024-09-24

    申请号：US17703701

    申请日：2022-03-24

    Applicant: Airbus Operations Ltd.

    Inventor： William Tulloch

    IPC: B64C3/28 ,  B64C3/18 ,  B64C7/00 ,  B64C9/00 ,  B64F5/10

    CPC classification number: B64C3/28 ,  B64C7/00 ,  B64C9/00 ,  B64F5/10 ,  B64C3/185

    Abstract: An aircraft wing including a wingbox with an upper cover, a lower cover, a forward spar and a rear spar. A leading edge of a trailing edge panel is attached to the wingbox. A support structure is attached to the wingbox. A kinked link includes a first arm, a second arm, and a corner where the first and second arms meet. The first arm of the kinked link is pivotally attached to the trailing edge panel at a first pivot joint, and the second arm of the kinked link is pivotally attached to the support structure at a second pivot joint.

    Aircraft wing with trailing edge panel
    26.
    发明授权
    Aircraft wing with trailing edge panel 有权

    公开(公告)号：US12071239B2

    公开(公告)日：2024-08-27

    申请号：US17703733

    申请日：2022-03-24

    Applicant: Airbus Operations Ltd.

    Inventor： William Tulloch

    IPC: B64C9/02 ,  B64C7/00 ,  B64C9/16 ,  B64F5/10

    CPC classification number: B64C9/02 ,  B64C7/00 ,  B64C9/16 ,  B64F5/10

    Abstract: An aircraft wing including a wingbox with an upper cover, a lower cover, and a rear spar. A lower trailing edge panel is provided with a leading edge attached to the wingbox. The wing includes a flap, a flap deployment mechanism which is configured to deploy the flap, and a fairing which covers the flap deployment mechanism. A first end of a link is pivotally attached to the lower trailing edge panel at a first pivot joint, and a second end of the link is pivotally attached to the fairing at a second pivot joint. The second pivot joint is lower than the first pivot joint.

    Trailing edge panel support with movable connector
    27.
    发明授权
    Trailing edge panel support with movable connector 有权

    公开(公告)号：US11845549B2

    公开(公告)日：2023-12-19

    申请号：US17703678

    申请日：2022-03-24

    Applicant: Airbus Operations Ltd.

    Inventor： William Tulloch

    IPC: B64C9/16 ,  B64C9/02 ,  B64F5/10

    CPC classification number: B64C9/16 ,  B64C9/02 ,  B64F5/10

    Abstract: An aircraft wing including a wingbox with an upper cover, a lower cover, a forward spar and a rear spar. A leading edge of a trailing edge panel is attached to the wingbox. A support structure is attached to the wingbox and a connector is movably mounted to the trailing edge panel on a bearing. A first end of a link is attached to the connector, and a second end of the link is attached to the support structure. During assembly, the connector is moved on the bearing from a first position to a second position where the connector is aligned with the first end of the link, then the connector at the second position is attached to the first end of the link. The connector may be moved by a rack-and-pinion mechanism.

    TRAILING EDGE PANEL SUPPORT WITH MOVABLE CONNECTOR
    29.
    发明申请
    TRAILING EDGE PANEL SUPPORT WITH MOVABLE CONNECTOR 有权

    公开(公告)号：US20220306283A1

    公开(公告)日：2022-09-29

    申请号：US17703678

    申请日：2022-03-24

    Applicant: Airbus Operations Ltd.

    Inventor： William Tulloch

    IPC: B64C9/16 ,  B64C9/02

    Abstract: An aircraft wing including a wingbox with an upper cover, a lower cover, a forward spar and a rear spar. A leading edge of a trailing edge panel is attached to the wingbox. A support structure is attached to the wingbox and a connector is movably mounted to the trailing edge panel on a bearing. A first end of a link is attached to the connector, and a second end of the link is attached to the support structure. During assembly, the connector is moved on the bearing from a first position to a second position where the connector is aligned with the first end of the link, then the connector at the second position is attached to the first end of the link. The connector may be moved by a rack-and-pinion mechanism.

    AIRCRAFT WING WITH TRAILING EDGE PANEL
    30.
    发明申请
    AIRCRAFT WING WITH TRAILING EDGE PANEL 有权

    公开(公告)号：US20220306274A1

    公开(公告)日：2022-09-29

    申请号：US17703733

    申请日：2022-03-24

    Applicant: Airbus Operations Ltd.

    Inventor： William Tulloch

    IPC: B64C3/18 ,  B64C3/14 ,  B64C3/28

    Abstract: An aircraft wing including a wingbox with an upper cover, a lower cover, and a rear spar. A lower trailing edge panel is provided with a leading edge attached to the wingbox. The wing includes a flap, a flap deployment mechanism which is configured to deploy the flap, and a fairing which covers the flap deployment mechanism. A first end of a link is pivotally attached to the lower trailing edge panel at a first pivot joint, and a second end of the link is pivotally attached to the fairing at a second pivot joint. The second pivot joint is lower than the first pivot joint.

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