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    AIRCRAFT WITH A PROTECTIVE SHIELD AGAINST AN ENGINE BLADE RELEASE
    3.
    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
    4.
    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。

    FLAT KINKED REAR PRESSURE BULKHEAD
    8.
    发明申请
    FLAT KINKED REAR PRESSURE BULKHEAD 审中-公开
    平压式后压大理石

    公开(公告)号：US20160244142A1

    公开(公告)日：2016-08-25

    申请号：US15043672

    申请日：2016-02-15

    Applicant: Airbus Operations, S.L.

    Inventor： Esteban Martino Gonzalez ,  Pablo Goya Abaurrea ,  Diego Folch Cortes ,  Sandra Linares Mendoza

    IPC: B64C1/10

    CPC classification number: B64C1/10

    Abstract: An aircraft fuselage comprising a pressurized cabin and an unpressurized rear section separated by a rear pressure bulkhead. The bulkhead comprises flat portions forming one or more kinks between them. One of the kinks is contiguous to a rear border of a floor that divides a space of the pressurized cabin into upper and lower compartments.

    Abstract translation: 飞机机身包括加压舱和由后压舱隔开的未加压后段。 隔板包括在它们之间形成一个或多个扭结的平坦部分。 其中一个扭结是连接到地板的后边界，将加压舱的空间分成上部和下部隔室。

    Propeller blade for an aircraft engine
    9.
    发明申请
    Propeller blade for an aircraft engine 审中-公开
    用于飞机发动机的螺旋桨叶片

    公开(公告)号：US20160176509A1

    公开(公告)日：2016-06-23

    申请号：US14757591

    申请日：2015-12-23

    Applicant: Airbus Operations, S.L.

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

    IPC: B64C11/20 ,  B64D45/00

    CPC classification number: B64C11/26 ,  B64D2201/00

    Abstract: The disclosure refers to a propeller blade for an aircraft engine that includes an airbag system contained inside the blade and comprising at least one bag and at least one gas generator, the at least one gas generator in fluid communication with at least one bag for inflating the bag, a detecting system for detecting a rupture of a part of the blade, a trigger for activating the at least one gas generator when the rupture is detected by the detecting system, and the blade skin being configured for allowing the at least one bag to pass through the blade skin for being expanded outside the blade upon the bag inflation by the gas generator.

    Abstract translation: 本发明涉及一种用于飞行器发动机的螺旋桨叶片，其包括包含在叶片内部并包括至少一个袋和至少一个气体发生器的气囊系统，所述至少一个气体发生器与至少一个袋流体连通，用于使 袋，用于检测叶片的一部分破裂的检测系统，用于当由检测系统检测到破裂时启动至少一个气体发生器的触发器，并且叶片皮肤被配置为允许至少一个袋子 穿过叶片皮肤，以在气体发生器的袋子充气时在叶片外部膨胀。

    IMPACT PROTECTIVE MULTI-LAYERED FABRIC
    10.
    发明申请
    IMPACT PROTECTIVE MULTI-LAYERED FABRIC 审中-公开
    冲击保护多层织物

    公开(公告)号：US20160161223A1

    公开(公告)日：2016-06-09

    申请号：US14963535

    申请日：2015-12-09

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

    Inventor： Javier Toral Vazques ,  Pablo Goya Abaurrea ,  Esteban Martino Gonzalez ,  Diego Folch Cortes ,  Vasilis Votsios ,  Michel Fouinnetau

    IPC: F41H5/04

    CPC classification number: F41H5/0485 ,  D03D1/0052

    Abstract: The disclosure refers to an impact protective multi-layered fabric comprising a pile of layers of a dry-fabric material, wherein at least one of the layers is conformed to have least one closed fold extending longitudinally across the layer, the closed fold having first and second walls substantially facing each other, and wherein the first and second walls are stitched to each other by means of at least one yarn of a dry-fabric material. According to an aspect, the first and second walls of the closed fold, are stitched to each other by means of two or more stitching lines are arranged one above the other within the closed fold, such as when an object impact on the fabric layer, the stitches of the stitching lines break sequentially one after the other, such the energy absorption capability of the layer is increased in a simple manner and without increasing its weight.

    Abstract translation: 本公开涉及一种防冲击保护性多层织物，其包括一堆干织物材料层，其中至少一层被配合为具有纵向延伸穿过该层的至少一个闭合折叠，封闭折叠具有第一和第 第二壁基本上彼此相对，并且其中第一和第二壁通过至少一根干织物材料的纱线彼此缝合。 根据一个方面，通过两个或更多个缝合线将闭合折叠的第一和第二壁彼此缝合，所述两条或更多条缝合线在闭合折叠内彼此上下排列，例如当物体对织物层的冲击时， 缝合线的线迹依次断开，层的能量吸收能力以简单的方式增加，而不增加其重量。

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