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    METHOD FOR OPERATING A LANDING GEAR SYSTEM
    4.
    发明申请
    METHOD FOR OPERATING A LANDING GEAR SYSTEM 审中-公开
    一种行驶齿轮系统的运行方法

    公开(公告)号：US20160362177A1

    公开(公告)日：2016-12-15

    申请号：US15183428

    申请日：2016-06-15

    Applicant: AIRBUS OPERATIONS, S.L. ,  AIRBUS OPERATIONS S.A.S. ,  AIRBUS OPERATIONS LTD.

    Inventor： Ramon Abarca Lopez ,  Marcus Barth ,  Norman Wood

    IPC: B64C25/18 ,  B64C25/04 ,  B64C25/16 ,  B64C25/30

    CPC classification number: B64C25/18 ,  B64C25/00 ,  B64C25/04 ,  B64C25/16 ,  B64C25/30 ,  B64C2025/003

    Abstract: The present disclosure refers to a method for operating a landing gear system, preferably in a tricycle configuration, wherein main landing gear (MLG) and the nose landing gear (NLG) are operable from a retracted position where they are housed respectively inside landing gear bays, to a fully extended position where they are extended for landing the aircraft. According to the disclosure, the extension of the nose landing gear (NLG) is delayed in time with respect to the extension of the main landing gear (MLG), and the nose landing gear (NLG) is kept retracted during a major part of the time that the main landing gear doors (MLGD) are extended. In this manner, vibrations on the main landing gear doors are reduced and incidents caused by fatigue are also reduced, which in turn implies that the maintenance cost of the aircraft is greatly reduced.

    Abstract translation: 本公开涉及一种用于操作起落架系统的方法，优选地在三轮车配置中，其中主起落架（MLG）和前起落架（NLG）可以从收起位置操作，其中它们分别容纳在起落架舱内 ，到一个完全延伸的位置，它们被延伸以着陆飞机。 根据本发明，前起落架（NLG）的延伸相对于主起落架（MLG）的延伸在时间上延迟，并且前起落架（NLG）在主要起落架 主起落架门（MLGD）延伸的时间。 以这种方式，主起落架门的振动减少，疲劳引起的事故也减少，这又意味着飞机的维护成本大大降低。

    Fixed wing of an aircraft
    5.
    发明授权
    Fixed wing of an aircraft 有权
    一架飞机的固定翼

    公开(公告)号：US09056671B2

    公开(公告)日：2015-06-16

    申请号：US13650457

    申请日：2012-10-12

    Applicant: Airbus Operations GmbH ,  Airbus Operations Ltd.

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

    IPC: 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。

    FIXED WING OF AN AIRCRAFT
    7.
    发明申请
    FIXED WING OF AN AIRCRAFT 有权

    公开(公告)号：US20130277504A1

    公开(公告)日：2013-10-24

    申请号：US13650457

    申请日：2012-10-12

    Applicant: AIRBUS OPERATIONS GMBH ,  AIRBUS OPERATIONS LTD.

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

    IPC: 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.

    Control system and method for landing gear extension/retraction
    9.
    发明授权
    Control system and method for landing gear extension/retraction 有权

    公开(公告)号：US11136114B2

    公开(公告)日：2021-10-05

    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.

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