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    SUSPENSION SYSTEM FOR AN AIRCRAFT AUXILIARY POWER UNIT
    222.
    发明申请
    SUSPENSION SYSTEM FOR AN AIRCRAFT AUXILIARY POWER UNIT 审中-公开

    公开(公告)号：US20170166321A1

    公开(公告)日：2017-06-15

    申请号：US15379879

    申请日：2016-12-15

    Applicant: AIRBUS OPERATIONS, S.L.

    Inventor： Guilherme BARSALI ,  Víctor BARREIRO RODRÍGUEZ

    IPC: B64D41/00

    Abstract: A suspension system for an aircraft auxiliary power unit (1) located in a fuselage structure (2) including: auxiliary power unit attachment brackets (3) arranged to be attached to the auxiliary power unit (1); fuselage attachment brackets (4) attached to the auxiliary power unit attachment brackets (3) and coupled to the fuselage structure (2); two longitudinal elements (5) arranged to be attached to the fuselage structure (2) in the longitudinal direction of the aircraft for supporting the auxiliary power unit (1), the two longitudinal elements (5) and the plurality of fuselage attachment brackets (4) being connected such that the two longitudinal elements (5) support the plurality of fuselage attachment brackets (4), being the fuselage attachment brackets (4) slidably movable along the longitudinal elements (5) for introducing or extracting the auxiliary power unit (1) into the fuselage structure (2).

    Ultrasound inspection system and ultrasonic quality control method
    226.
    发明授权
    Ultrasound inspection system and ultrasonic quality control method 有权
    超声检查系统和超声波质量控制方法

    公开(公告)号：US09557302B2

    公开(公告)日：2017-01-31

    申请号：US14094979

    申请日：2013-12-03

    Applicant: Airbus Operations S.L.

    Inventor： Carlos De Miguel Giraldo ,  Gildas Lambert ,  Oscar Martinez ,  Luis Elvira ,  David Romero ,  Luis Gomez Ullate ,  Francisco Montero

    IPC: G01N29/24 ,  G01N29/28

    CPC classification number: G01N29/2493 ,  G01N29/28 ,  G01N2291/0231

    Abstract: An ultrasound inspection roller provided with a wheel, a sensing system and a support for holding the sensing system inside the wheel, a wedge connected to the ultrasound sensing system at one end and provided with a curved profile at its other end facing the wheel, adapted to the curvilinear shape of the wheel, and a liquid of a density higher than 9.9*102 kg/mm3 placed inside the wheel such that the sensory system, the wheel and the wedge are acoustically coupled. The roller allows the early detection of problems during manufacturing of composites and the performance of corrective measures in real time, and assures a good coupling between the transducers and the material to be inspected in dry conditions.

    Abstract translation: 一种超声波检查辊，其设置有车轮，感测系统和用于将感测系统保持在车轮内的支撑件，在一端连接到超声波感测系统的楔块，并在其另一端面向车轮设置弯曲轮廓， 到轮的曲线形状，以及放置在车轮内部的密度高于9.9×102kg / mm3的液体，使得感觉系统，车轮和楔子声学耦合。 该辊允许早期检测复合材料制造过程中的问题并实时执行校正措施，并确保传感器与干燥条件下待检测材料之间的良好耦合。

    BOUNDARY LAYER SUCTION SYSTEM
    227.
    发明申请
    BOUNDARY LAYER SUCTION SYSTEM 审中-公开
    边界层吸收系统

    公开(公告)号：US20170023437A1

    公开(公告)日：2017-01-26

    申请号：US15215768

    申请日：2016-07-21

    Applicant: Airbus Operations, S.L.

    Inventor： José Maria DIAZ PARRILLA ,  Álvaro JARA RODELGO ,  Miguel Ángel GALLEGO LORENZO ,  José Ángel HERNANZ MANRIQUE

    IPC: G01M9/04

    Abstract: A boundary layer suction system adapted to a surface exposed to the circulation of a fluid. The system comprises a portion of the surface, a bifurcation element for bifurcating a mass of fluid flowing along the front face of the surface, comprising an airfoil-shaped cross-section such that the fluid is bifurcated into a first and a second flow, a slot located on the portion of the surface and upstream of the leading edge of the bifurcation element, the slot communicating the front and the rear faces of the portion of the surface, and an arrangement to provide a pressure difference between the front and the rear faces of the surface around the slot, such that a suction of the boundary layer is performed through the slot by the pressure difference.

    Abstract translation: 适于暴露于流体循环的表面的边界层抽吸系统。 该系统包括表面的一部分，用于将沿着表面前表面流动的大量流体分叉的分叉元件，包括翼型截面，使得流体分叉成第一和第二流动， 位于所述表面的所述部分和所述分叉元件的前缘的上游的槽，所述槽连通所述表面的所述部分的前表面和所述后表面，以及用于在所述前表面和所述后表面之间提供压差的装置 使得边界层的吸力通过压力差通过槽进行。

    METHOD FOR OPERATING A LANDING GEAR SYSTEM
    228.
    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。

    AIRCRAFT WITH A PROTECTIVE SHIELD AGAINST AN ENGINE BLADE RELEASE
    229.
    发明申请
    AIRCRAFT WITH A PROTECTIVE SHIELD AGAINST AN ENGINE BLADE RELEASE 审中-公开
    具有防护罩的飞机对发动机叶片释放

    公开(公告)号：US20160362167A1

    公开(公告)日：2016-12-15

    申请号：US15182672

    申请日：2016-06-15

    Applicant: Airbus Operations S.L. ,  Airbus Operations S.A.S.

    Inventor： Javier Toral Vazquez ,  Esteban Martino Gonzalez ,  Diego Folch Cortes ,  Pablo Goya Abaurrea ,  Vasilis Votsios ,  Michel Fouinnetau ,  Sylvain Roumegas ,  Wolfgang Brochard

    IPC: B64C1/06 ,  B64D27/10 ,  B64D37/04

    Abstract: An internal shield inside the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it. The internal shield is located in a suitable place inside the rear fuselage for covering the possible trajectories of fragments detached from one of the engines in a failure event that would impact critical elements of the opposite engine. The internal shield comprises an ensemble of fluid containers belonging to aircraft sub-systems, such as, particularly, the potable water and waste water sub-systems, with enough fluid for providing the energy absorption capability required for stopping the fragments. An aircraft having the internal shield is also disclosed.

    Abstract translation: 飞机后部机身内部有一个内部屏蔽罩，它具有由安装在其两侧的两个发动机构成的推进系统。 内部防护罩位于后机身内部的合适位置，用于覆盖可能影响对方发动机的关键元件的故障事件中与其中一个发动机分离的碎片的可能轨迹。 内部屏蔽件包括属于飞行器子系统的流体容器的集合体，特别是饮用水和废水子系统，具有足够的流体，用于提供停止碎片所需的能量吸收能力。 还公开了具有内部屏蔽的飞机。

    AIRCRAFT REAR STRUCTURE
    230.
    发明申请
    AIRCRAFT REAR STRUCTURE 审中-公开
    飞机后结构

    公开(公告)号：US20160297510A1

    公开(公告)日：2016-10-13

    申请号：US15089675

    申请日：2016-04-04

    Applicant: Airbus Operations (SAS) ,  Airbus Operations S.L.

    Inventor： Diego Folch Cortes ,  Esteban Martino Gonzalez ,  Jose Antonio Mariblanca Lopez ,  Lionel Diochon

    IPC: B64C1/26 ,  B64C5/02 ,  B64C5/06 ,  B64C1/10

    CPC classification number: B64C1/26 ,  B64C1/10 ,  B64C5/02 ,  B64C5/06

    Abstract: An aircraft rear structure comprising a substantially flat rear pressure bulkhead, with a first side and a second side, opposite to the first side. The aircraft rear structure also comprises a horizontal stabilizer and a vertical stabilizer which in turn comprises a first spar and a second spar. The first spar is attached to a first attachment zone of the second side of the rear pressure bulkhead via first attaching elements, and the second spar is attached to a second attachment zone of the second side of the rear pressure bulkhead via second attaching elements. The second attachment zone being different from the first attachment zone.

    Abstract translation: 一种飞机后部结构，包括基本上平坦的后部压力隔板，其具有与第一侧相对的第一侧和第二侧。 飞行器后部结构还包括水平稳定器和垂直稳定器，其又包括第一翼梁和第二翼梁。 第一翼梁经由第一附接元件附接到后压舱壁的第二侧的第一附接区域，并且第二翼梁经由第二附接元件附接到后压舱壁的第二侧的第二附接区域。 第二附接区域与第一附接区域不同。

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