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    AIRCRAFT LANDING GEAR ASSEMBLY
    14.
    发明申请
    AIRCRAFT LANDING GEAR ASSEMBLY 有权
    飞机接地齿轮总成

    公开(公告)号：US20160272303A1

    公开(公告)日：2016-09-22

    申请号：US15072974

    申请日：2016-03-17

    Applicant: Messier-Dowty Limited

    Inventor： ROBERT KYLE SCHMIDT

    IPC: B64C25/20 ,  B64C25/34 ,  B64C25/58

    CPC classification number: B64C25/20 ,  B64C25/26 ,  B64C25/34 ,  B64C25/58

    Abstract: An aircraft landing gear assembly includes a bi-stable, split line tube biased to assume a tubular condition to serve in place of a lock link or side stay and an actuator configured to radially enlarge the tube at a region for folding.

    Abstract translation: 一种飞机起落架组件包括一个双稳态分裂线管，其被偏压以呈现管状状态以代替锁定连杆或侧撑，以及构造成在折叠区域处径向放大管的致动器。

    Method and apparatus for changing a deployed position for a tail skid assembly
    16.
    发明授权
    Method and apparatus for changing a deployed position for a tail skid assembly 有权
    用于改变尾部滑行组件的展开位置的方法和装置

    公开(公告)号：US09248906B2

    公开(公告)日：2016-02-02

    申请号：US14340521

    申请日：2014-07-24

    Applicant: The Boeing Company

    Inventor： Justin Duane Cottet

    IPC: B64C25/00 ,  B64C25/32 ,  B64C25/52 ,  B64C25/58

    CPC classification number: B64C25/32 ,  B64C25/52 ,  B64C25/58 ,  B64C2025/005

    Abstract: A method and apparatus for positioning a tail skid assembly for a maximum rotation angle for an aircraft may be provided. A determination may be made as to whether the tail skid assembly is to be deployed for takeoff or landing. A set of parameters may be identified based on a determination of whether the tail skid assembly is to be deployed for takeoff or landing. A desired maximum rotation angle for the aircraft may be identified using the set of parameters. The tail skid assembly may be deployed to allow the desired maximum rotation angle for the aircraft.

    Abstract translation: 可以提供一种用于定位用于飞行器的最大旋转角度的尾部滑行组件的方法和装置。 可以确定尾部滑行组件是否要用于起飞或着陆。 可以基于是否将部署用于起飞或着陆的尾部滑行组件的确定来识别一组参数。 可以使用该组参数来识别用于飞行器的期望的最大旋转角度。 尾部滑行组件可以被部署以允许飞机的期望的最大旋转角度。

    ACTIVE LANDING GEAR DAMPER
    17.
    发明申请
    ACTIVE LANDING GEAR DAMPER 有权
    主动起落架减震器

    公开(公告)号：US20150239554A1

    公开(公告)日：2015-08-27

    申请号：US14188589

    申请日：2014-02-24

    Applicant: The Boeing Company

    Inventor： Terrence S. Birchette ,  Akif O. Bolukbasi

    IPC: B64C25/60 ,  B64D45/00

    CPC classification number: B64C25/60 ,  B64C25/58 ,  B64D45/00

    Abstract: An active landing gear damping system and method for decelerating a vehicle during a terrain impact event, such as an aircraft landing or crash. The system monitors aircraft state data and terrain information to predict an impact of the vehicle with the terrain. The system can then determine a target damper force for each landing gear of the vehicle and a predicted damper velocity at the time of impact. Each landing gear can include an adjustable damper valve, wherein adjustment of the damper valves varies the damping coefficient of the respective dampers. The system can adjust valves of the respective dampers to provide the target force based on the predicted damper velocity. After an impact begins, the system can continuously monitor and adjust the valve to maintain the target force.

    Abstract translation: 一种用于在诸如飞机着陆或碰撞的地形撞击事件期间使车辆减速的主动起落架阻尼系统和方法。 系统监控飞机状态数据和地形信息，以预测车辆与地形的冲击。 然后，系统可以确定车辆的每个起落架的目标阻尼器力和冲击时预测的阻尼器速度。 每个起落架都可以包括一个可调节的阻尼阀，其中减震阀的调节改变各个风门的阻尼系数。 该系统可以根据预测的阻尼器速度调节相应阻尼器的阀门以提供目标力。 冲击开始后，系统可以持续监控和调整阀门以保持目标力。

    DEVICE FOR COUPLING AN ACTUATOR FOR CONTROLLING THE LANDING GEAR OF AN AIRCRAFT
    18.
    发明申请
    DEVICE FOR COUPLING AN ACTUATOR FOR CONTROLLING THE LANDING GEAR OF AN AIRCRAFT 有权
    用于联接执行机构以控制飞机的起落架的装置

    公开(公告)号：US20140209738A1

    公开(公告)日：2014-07-31

    申请号：US14238534

    申请日：2012-09-07

    Applicant: Thierry Blanpain ,  Dominique Ducos ,  Edouard Campbell

    Inventor： Thierry Blanpain ,  Dominique Ducos ,  Edouard Campbell

    IPC: B64C25/20

    CPC classification number: B64C25/20 ,  B64C25/26 ,  B64C25/58 ,  B64C25/62

    Abstract: A device for coupling an actuator for operating an aircraft undercarriage to an aircraft structure. The device comprises a lever having a first end for hinging to the structure of the aircraft, and a second end to which the actuator is hinged, a pre-loading structure acting on the lever to urge it towards a stable rest position that is occupied by the lever in the absence of any force transiting through the actuator; and an abutment structure defining at least one working position for the lever when the actuator is activated.

    Abstract translation: 一种用于将用于操作飞行器起落架的致动器联接到飞机结构的装置。 该装置包括杠杆，其具有用于铰接到飞行器的结构的第一端和致动器铰接的第二端，作用在杠杆上的预加载结构，以将其推向稳定的休止位置，该静止位置由 没有任何力通过致动器的杠杆; 以及当所述致动器被致动时限定所述杠杆的至少一个工作位置的邻接结构。

    AIRCRAFT LANDING GEAR
    19.
    发明申请
    AIRCRAFT LANDING GEAR 有权
    飞机起落架

    公开(公告)号：US20140158820A1

    公开(公告)日：2014-06-12

    申请号：US14178141

    申请日：2014-02-11

    Applicant: Fraser WILSON ,  Jeremy BEDARRIDES ,  Vladimir PLATAGEA

    Inventor： Fraser WILSON ,  Jeremy BEDARRIDES ,  Vladimir PLATAGEA

    IPC: B64C25/40

    CPC classification number: B64C25/405 ,  B64C25/58 ,  Y02T50/823

    Abstract: An aircraft landing gear comprising: a shock-absorbing main leg having a sprung part for attachment to an aircraft and an un-sprung part including a slider and an axle carrying at least one wheel, the wheel having a toothed ring gear; a drive transmission mounted externally on the sprung part, or on the un-sprung part, of the main leg, the drive transmission having at least one motor and a drive pinion for meshing with the toothed ring of the wheel; and an actuator for lifting the drive transmission into and out of driving engagement with the toothed ring and for maintaining the driving engagement as the landing gear deflects during a ground taxiing operation. Also, a method of operating the aircraft landing gear.

    Abstract translation: 1.一种飞机起落架，包括：具有用于附接到飞行器的弹簧部件的减震主支腿和包括滑动件和支撑至少一个轮的轴的非弹簧部件，所述轮具有齿形齿圈; 驱动传动装置外部安装在主支腿的弹簧部分或非弹簧部分上，驱动传动装置具有至少一个马达和用于与轮的齿环啮合的驱动小齿轮; 以及致动器，用于将驱动变速器提升进入和脱离与齿环的驱动接合，并且用于在地面滑行操作期间起落架偏转时保持驱动接合。 另外，一种操作飞机起落架的方法。

    Landing gear
    20.
    发明授权
    Landing gear 有权
    起落架

    公开(公告)号：US08398020B2

    公开(公告)日：2013-03-19

    申请号：US13332680

    申请日：2011-12-21

    Applicant: Ian Bennett ,  Richard Charles Lang ,  Robert Anthony Menezes

    Inventor： Ian Bennett ,  Richard Charles Lang ,  Robert Anthony Menezes

    IPC: B64C25/00 ,  B64C25/58

    CPC classification number: B64C25/60 ,  B64C25/22 ,  B64C25/34 ,  B64C25/58

    Abstract: An auxiliary mechanism includes a lever unit, a spring unit and a positioning unit. One of the units pivotally connects to the upper portion of a main shock absorber strut so as to pivot between a predetermined lower position for take-off and landing and an upper position. Another unit pivotally connects at an upper end to the upper portion of the main shock absorber strut and pivotally connects at a lower end to the first unit. A third unit pivotally connects at a lower end to the bogie beam at an auxiliary pivot and connects at an upper end to the lever. The positioning unit assumes either a contracted state or extended state for taxiing, take-off and landing, and assumes the other state for stowing the landing gear after take-off. The spring unit provides spring resistance to pivotal movements of the bogie beam about the main pivot during taxiing.

    Abstract translation: 辅助机构包括杠杆单元，弹簧单元和定位单元。 其中一个单元枢转地连接到主减震器支柱的上部，以便在用于起飞和着陆的预定下部位置和上部位置之间枢转。 另一个单元在上端枢转地连接到主减震器支柱的上部，并且在下端枢转地连接到第一单元。 第三单元在下端处以辅助枢轴枢转地连接到转向架梁，并且在上端连接到杠杆。 定位单元承担滑行，起飞和着陆的承包状态或延长状态，并在起飞后采取起落架的另一种状态。 弹簧单元在滑行期间提供弹簧抵抗转向架梁绕主枢轴的枢转运动。

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