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    AIRCRAFT ASSEMBLY AND METHOD
    3.
    发明申请
    AIRCRAFT ASSEMBLY AND METHOD 审中-公开

    公开(公告)号：US20180170529A1

    公开(公告)日：2018-06-21

    申请号：US15834873

    申请日：2017-12-07

    申请人： Safran Landing Systems UK LTD

    发明人： Robert Kyle Schmidt

    IPC分类号： B64C25/28 ,  B64D45/00

    CPC分类号： B64C25/28 ,  B64C13/16 ,  B64C25/26 ,  B64C2025/003 ,  B64D45/0005 ,  B64D45/04 ,  G05D1/0676

    摘要： An aircraft assembly having landing gear with a known deployment value, apparatus for permitting landing gear deployment, down-lock sensing apparatus, a navigation system, a landing gear control system, a flight control system, and a deployment controller. The deployment controller is configured to: calculate a touch down value using the aircraft position and speed information provided by the aircraft navigation system; command the landing gear control system to provide the deploy signal when the touch down value reaches a deployment threshold value which is greater than the landing gear deployment value; and command the flight control system to execute a landing abort sequence if the controller does not receive the down-lock signal from the landing gear sensing apparatus within a deployment value window which is greater than or equal to the known deployment value for the landing gear but less than the touch down value.

    Landing Gear Noise Abatement Devices
    7.
    发明申请
    Landing Gear Noise Abatement Devices 有权
    起落架降噪装置

    公开(公告)号：US20160375990A1

    公开(公告)日：2016-12-29

    申请号：US14048914

    申请日：2013-10-08

    申请人： Goodrich Corporation

    发明人： Rony Giovanni Ganis

    IPC分类号： B64C25/16 ,  B64C7/00

    CPC分类号： B64C25/16 ,  B64C7/00 ,  B64C25/001 ,  B64C2025/003

    摘要： A noise abatement system for an aircraft landing gear is provided. The system may have a retention member and a covering member. In this regard, the system may be configured to block the airflow through a structural void to abate noise. Moreover, the system may be shaped to diminish aerodynamic drag.

    摘要翻译： 提供一种用于飞机起落架的噪声消除系统。 系统可以具有保持构件和覆盖构件。 在这方面，该系统可被配置为阻挡通过结构空隙的气流以消除噪音。 此外，该系统可以被成形为减小空气动力学阻力。

    METHOD FOR OPERATING A LANDING GEAR SYSTEM
    8.
    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

    申请人： AIRBUS OPERATIONS, S.L. ,  AIRBUS OPERATIONS S.A.S. ,  AIRBUS OPERATIONS LTD.

    发明人： Ramon Abarca Lopez ,  Marcus Barth ,  Norman Wood

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

    CPC分类号： B64C25/18 ,  B64C25/00 ,  B64C25/04 ,  B64C25/16 ,  B64C25/30 ,  B64C2025/003

    摘要： 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.

    摘要翻译： 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。

    Method of attenuating noise in aircraft landing gear and structure
    9.
    发明授权
    Method of attenuating noise in aircraft landing gear and structure 有权
    减少飞机起落架噪声和结构的方法

    公开(公告)号：US09327829B2

    公开(公告)日：2016-05-03

    申请号：US13255759

    申请日：2010-03-26

    申请人： Kazuhide Isotani ,  Kenji Hayama ,  Toshiyuki Kumada ,  Masaru Ono

    发明人： Kazuhide Isotani ,  Kenji Hayama ,  Toshiyuki Kumada ,  Masaru Ono

    IPC分类号： B64C23/00 ,  B64C25/16 ,  B64C25/00 ,  B64F5/00

    CPC分类号： B64C25/001 ,  B64C2025/003 ,  B64F5/00 ,  Y10T29/49764

    摘要： A method for attenuating aerodynamic noise from a landing gear may include researching a start point of a shear layer as a flow field characteristic of a region in the vicinity of an original shape of the landing gear, and adding a plate-shaped object in the vicinity of the start point, changing the start point to an edge portion of the plate-shaped object to make the shear layer farther from the original shape. Another method for attenuating aerodynamic noise from a landing gear may include researching a static pressure and an airflow velocity in a region in the vicinity of the landing gear as a flow field characteristic of the region, and adding a plate-shaped object covering a surface of the landing gear which is different from a surface facing an upstream side in an airflow direction, increasing the static pressure in the region to reduce the airflow velocity.

    摘要翻译： 用于衰减起落架的空气动力学噪声的方法可以包括研究剪切层的起点作为起落架原始形状附近的区域的流场特征，并在附近添加板状物体 的起始点，将起点改变为板状物体的边缘部分，使剪切层离原始形状更远。 用于衰减来自起落架的空气动力学噪声的另一种方法可包括：研究作为该区域的流场特征的起落架附近的区域中的静压力和气流速度，以及将覆盖表面的板状物体 起落架不同于在气流方向上面向上游侧的表面，增加了该区域中的静压力以降低气流速度。

    Nose landing gear arrangement for aircraft and method of assembly
    10.
    发明授权
    Nose landing gear arrangement for aircraft and method of assembly 有权
    用于飞机的鼻子起落架布置和组装方法

    公开(公告)号：US09302767B2

    公开(公告)日：2016-04-05

    申请号：US13674303

    申请日：2012-11-12

    申请人： Gulfstream Aerospace Corporation

    发明人： Brian G. Cook ,  John Louis ,  Thomas Van de Ven ,  Robert M. Vieito

    IPC分类号： B64C25/00 ,  B64C25/16 ,  B64C25/14

    CPC分类号： B64C25/001 ,  B64C25/14 ,  B64C25/16 ,  B64C2025/003 ,  B64C2025/006 ,  Y10T29/49826

    摘要： A nose landing gear arrangement for an aircraft and a method of assembling the nose landing gear arrangement are disclosed herein. The nose landing gear arrangement includes, but is not limited to, a wheel assembly, a shock strut extending upwards from the wheel assembly towards a fuselage of the aircraft, and a torque arm assembly coupled to the wheel assembly and to the shock strut. The torque arm assembly is configured to transmit torque to the wheel assembly. The torque arm assembly is disposed forward of the shock strut with respect to a direction of travel of the aircraft.

    摘要翻译： 本文公开了一种用于飞行器的前起落架装置和组装前起落架装置的方法。 前起落架装置包括但不限于轮组件，从车轮组件向上延伸到飞行器的机身的冲击支柱，以及联接到车轮组件和冲击支柱的扭矩臂组件。 扭矩臂组件构造成将扭矩传递到车轮组件。 扭矩臂组件相对于飞行器的行进方向设置在冲击支柱的前方。