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    CONTROL SYSTEM AND METHOD FOR LANDING GEAR EXTENSION/RETRACTION
    31.
    发明申请
    CONTROL SYSTEM AND METHOD FOR LANDING GEAR EXTENSION/RETRACTION 审中-公开

    公开(公告)号：US20200055592A1

    公开(公告)日：2020-02-20

    申请号：US16556651

    申请日：2019-08-30

    Applicant: Airbus Operations Ltd.

    Inventor： Martin Griffith ROWLANDS ,  Maxwell William JONES ,  Graham KING ,  Trevor Anthony BRIGHTON ,  Matthew GADD

    IPC: B64C25/26 ,  B64C25/16

    Abstract: A control system has first and second processing modules for controlling retraction and extension of an aircraft landing gear assembly. The processing modules operate independently providing redundancy. Each processing module is configured to perform a first sequence of steps for retracting the landing gear assembly and a second sequence of steps for extending the landing gear assembly. A step of switching control from one processing module to the other (e.g. an avionics side changeover step) is performed (a) as part of the first sequence of steps, but only after the landing gear assembly has been retracted, or (b) as part of the second sequence of steps. By ensuring that the step of switching control is performed at such times, and not for example between initiation of the first sequence of steps and the retraction of the landing gear assembly, the landing gear assembly may be retracted sooner after such initiation.

    WING ARRANGEMENT FOR AN AIRCRAFT
    33.
    发明申请
    WING ARRANGEMENT FOR AN AIRCRAFT 审中-公开

    公开(公告)号：US20180334238A1

    公开(公告)日：2018-11-22

    申请号：US15979806

    申请日：2018-05-15

    Applicant: Airbus Operations GmbH ,  Airbus Operations Ltd

    Inventor： Christoph Winkelmann ,  Wilfried Ellmers ,  Stephen BRIANCOURT ,  David BRAKES

    IPC: B64C3/54 ,  B64C3/56 ,  F16B45/02

    CPC classification number: B64C3/56

    Abstract: A wing arrangement for an aircraft, comprising a wing having a base section and a tip section pivotably connected to base section such that the tip section is pivotable about a pivot axis between a deployed position and a stowed position. The wing arrangement also comprises a latching arrangement which includes an engagement portion, a latching actuator selectively movable between a first actuator position and a second actuator position, an elastically deformable structure, and a latching element. When the tip section is pivoted from the stowed or deployed position into an engagement position, the elastically deformable structure is initially deformed, and as the tip section pivots further into the deployed or stowed position, the elastic deformation of the elastically deformable structure decreases.

    Fixed wing of an aircraft
    34.
    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
    36.
    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 with biasing arrangement
    37.
    发明授权
    Trailing edge panel support with biasing arrangement 有权

    公开(公告)号：US11993376B2

    公开(公告)日：2024-05-28

    申请号：US17703653

    申请日：2022-03-24

    Applicant: Airbus Operations Ltd.

    Inventor： William Tulloch

    IPC: B64C9/02 ,  B64C9/20 ,  B64C13/34 ,  B64F5/10

    CPC classification number: B64C9/02 ,  B64C9/20 ,  B64C13/34 ,  B64F5/10

    Abstract: A method of securing a lower trailing edge panel of an aircraft wing. The wing includes a wingbox with an upper cover, a lower cover, and a rear spar. A leading edge of the lower trailing edge panel is attached to the wingbox. A support structure is also attached to the wingbox and a connector is mounted to the trailing edge panel. A link is provided, with a first end and a second end. The second end of the link is pivotally attached to the support structure at a pivot joint. A biasing arrangement biases the link towards an upright orientation in which the first end of the link is higher than the pivot joint. The link is held in its upright orientation with the biasing arrangement; and then the first end of the link is attached to the connector.

    Overheat detection systems for aircraft
    38.
    发明授权
    Overheat detection systems for aircraft 有权

    公开(公告)号：US11506561B2

    公开(公告)日：2022-11-22

    申请号：US16711886

    申请日：2019-12-12

    Applicant: Airbus Operations, S.L.U. ,  Airbus Operations SAS ,  Airbus Operations LTD

    Inventor： Alessio Cipullo ,  Sy-Dat Le ,  Carlos Bueno Vazquez

    IPC: G01M3/04 ,  G01K11/3206 ,  B64D45/00 ,  G01K11/32 ,  G01K13/024 ,  G01M3/00 ,  G01M3/38

    Abstract: An overheat detection system for an aircraft, the system comprising a first bleed monitoring computer, BMC1, configured to identify leakages in a pneumatic system, the BMC1 including a first optical controller, a second bleed monitoring computer, BMC2, the BMC2 including a second optical controller, an optical fiber link connecting the first optical controller of the BMC1 and the second optical controller of the BMC2 for communication between the BMC1 and the BCM2 and between the first optical controller and the second optical controller, wherein the first and the second optical controllers are configured to detect overheat of the optical fiber link based on a wavelength shift of a modulated optical signal transmitted through the optical fiber link, and transmit signals to the first BMC1 and the second BMC2 based at least on the detected overheat.

    TRAILING EDGE PANEL SUPPORT WITH BIASING ARRANGEMENT
    39.
    发明申请
    TRAILING EDGE PANEL SUPPORT WITH BIASING ARRANGEMENT 有权

    公开(公告)号：US20220306282A1

    公开(公告)日：2022-09-29

    申请号：US17703653

    申请日：2022-03-24

    Applicant: Airbus Operations Ltd.

    Inventor： William Tulloch

    IPC: B64C9/02 ,  B64C9/20 ,  B64F5/10 ,  B64C13/34

    Abstract: A method of securing a lower trailing edge panel of an aircraft wing. The wing includes a wingbox with an upper cover, a lower cover, and a rear spar. A leading edge of the lower trailing edge panel is attached to the wingbox. A support structure is also attached to the wingbox and a connector is mounted to the trailing edge panel. A link is provided, with a first end and a second end. The second end of the link is pivotally attached to the support structure at a pivot joint. A biasing arrangement biases the link towards an upright orientation in which the first end of the link is higher than the pivot joint. The link is held in its upright orientation with the biasing arrangement; and then the first end of the link is attached to the connector.

    TRAILING EDGE PANEL SUPPORT
    40.
    发明申请
    TRAILING EDGE PANEL SUPPORT 有权

    公开(公告)号：US20220306279A1

    公开(公告)日：2022-09-29

    申请号：US17703701

    申请日：2022-03-24

    Applicant: Airbus Operations Ltd.

    Inventor： William Tulloch

    IPC: B64C3/28 ,  B64C7/00 ,  B64C9/00 ,  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. 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.

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