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    AIRCRAFT WITH A PROTECTIVE SHIELD AGAINST AN ENGINE BLADE RELEASE
    2.
    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 with fuselage-mounted engines and an internal shield
    7.
    发明授权
    Aircraft with fuselage-mounted engines and an internal shield 有权
    具有机身安装引擎和内部防护罩的飞机

    公开(公告)号：US09359085B2

    公开(公告)日：2016-06-07

    申请号：US13724360

    申请日：2012-12-21

    Applicant: AIRBUS OPERATIONS S.L.

    Inventor： Diego Folch Cortés ,  Eduardo Vinué Santolalla ,  Esteban Martino González ,  Julien Guillemaut ,  Pablo Goya Abaurrea

    IPC: B64D45/00 ,  B64C1/06 ,  B64D27/14 ,  B64D27/02 ,  B64C1/10 ,  B64D27/20 ,  B64D27/00

    CPC classification number: B64D45/00 ,  B64C1/06 ,  B64C1/10 ,  B64D27/02 ,  B64D27/14 ,  B64D27/20 ,  B64D2027/005 ,  Y02T50/66

    Abstract: Internal shield in the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it; the rear fuselage having at least a vertical symmetry plane; the rear fuselage being made of a composite material; the internal shield being located in said vertical symmetry plane and extended in an area that covers the possible trajectories of a set of pre-defined fragments detached from one of said engines in a failure event that would impact on critical elements of the opposite engine; the internal shield having a flat shape and an energy absorption capability that allows stopping said fragments. The invention also refers to a method for determining the area of an internal shield and to an aircraft having said internal shield.

    Abstract translation: 具有由安装在其每侧的两个发动机形成的推进系统的飞行器的后机身中的内部盾构; 后机身至少具有垂直对称平面; 后机身由复合材料制成; 所述内部屏蔽件位于所述垂直对称平面中，并且延伸在覆盖一组预定义片段的可能轨迹的区域中，所述一组预先定义的片段在将影响相对发动机的关键元件的故障事件中与所述发动机中的一个分离; 内部屏蔽具有平坦的形状和能量吸收能力，其允许停止所述碎片。 本发明还涉及一种用于确定内部屏蔽件和具有所述内部屏蔽件的飞行器的面积的方法。

    FLAT KINKED REAR PRESSURE BULKHEAD
    9.
    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
    10.
    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。

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