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    AIRCRAFT TAIL CONE
    1.
    发明申请
    AIRCRAFT TAIL CONE 审中-公开
    飞机尾灯

    公开(公告)号：US20160229513A1

    公开(公告)日：2016-08-11

    申请号：US15018481

    申请日：2016-02-08

    申请人： Airbus Operations (SAS) ,  Airbus Operations GmbH ,  Airbus Operations S.L.

    发明人： Henning Scheel ,  Eric Bouchet ,  Julien Guillemaut ,  Esteban Martino-Gonzalez

    IPC分类号： B64C1/14 ,  B64C1/16 ,  B64C1/10

    CPC分类号： B64C1/1446 ,  B64C1/10 ,  B64C1/16 ,  B64D27/14 ,  B64D27/20 ,  B64D29/08 ,  B64D37/005 ,  B64D2041/002 ,  Y02T50/44

    摘要： An aircraft tail cone comprising a fuselage in which avionic equipment is housed. The tail cone comprises two lateral hatches formed in the fuselage, at least one hatch being formed on each of the two opposite sides of the fuselage. Each hatch is mounted removably with respect to the fuselage so as to take up a closed first position in which the hatch closes a lateral opening in the fuselage, and an open second position in which the open hatch allows access to the inside of the tail cone through the corresponding opening The avionic equipment that requires regular inspection and/or maintenance operations is housed in a part of the tail cone which is accessible through the two lateral openings in the fuselage to a person who remains on the outside of the fuselage.

    摘要翻译： 飞机尾锥包括机身，其中安装有航空电子设备。 尾锥包括形成在机身中的两个横向舱口，至少一个舱口形成在机身的两个相对的两侧上。 每个舱口相对于机身可移除地安装，以便收起闭合的第一位置，其中舱口关闭机身中的侧向开口，以及打开的第二位置，打开的舱口允许进入尾锥体的内部 通过相应的开口需要定期检查和/或维护操作的航空电子设备被容纳在尾锥的一部分中，该尾锥可以通过机身中的两个侧向开口接近留在机身外部的人。

    Aircraft with fuselage-mounted engines and an internal shield
    4.
    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

    申请人： AIRBUS OPERATIONS S.L.

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

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

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

    摘要： 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.

    摘要翻译： 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。

    PROPELLER FOR AN AIRCRAFT TURBOMACHINE, INCLUDING A BLADE RETAINING STRUCTURE THROUGH WHICH THE AERODYNAMIC PART OF EACH BLADE PASSES
    6.
    发明申请
    PROPELLER FOR AN AIRCRAFT TURBOMACHINE, INCLUDING A BLADE RETAINING STRUCTURE THROUGH WHICH THE AERODYNAMIC PART OF EACH BLADE PASSES 有权
    螺旋桨用于飞机涡轮机，包括通过每个叶片的空气动力部分通过的叶片保持结构

    公开(公告)号：US20160176532A1

    公开(公告)日：2016-06-23

    申请号：US14977049

    申请日：2015-12-21

    申请人： Airbus Operations (SAS)

    发明人： Julien Guillemaut ,  Guillaume Gallant

    IPC分类号： B64D27/14 ,  B64C11/06 ,  B64C11/20

    CPC分类号： B64D27/14 ,  B64C11/001 ,  B64C11/06 ,  B64C11/20 ,  B64D2027/005 ,  Y02T50/66

    摘要： A propeller for a turbomachine intended to be driven in rotation about a propeller rotation axis and including variable pitch blades. The propeller further includes a structure for radial retention of the blades in the event of them breaking. The retaining structure extends around the propeller rotation axis and has the aerodynamic part of each blade of the propeller pass through it. Moreover, each aerodynamic part is equipped with an abutment configured to be retained radially by the retaining structure in the event of a blade fracture causing a fracture in the aerodynamic part radially inside the abutment.

    摘要翻译： 用于涡轮机的推进器旨在围绕螺旋桨旋转轴线旋转并且包括可变桨距叶片。 螺旋桨还包括用于在它们断裂的情况下径向保持叶片的结构。 保持结构围绕螺旋桨旋转轴线延伸，并且螺旋桨的每个叶片的空气动力学部分通过它。 此外，每个空气动力部件配备有一个邻接构造，以在叶片断裂的情况下由保持结构径向地保持，从而在邻接部的径向内部的空气动力部分中断裂。

    SECURE BEAM, IN PARTICULAR STRONG FRAME OF FUSELAGE, AND AIRCRAFT FUSELAGE PROVIDED WITH SUCH FRAMES
    8.
    发明申请
    SECURE BEAM, IN PARTICULAR STRONG FRAME OF FUSELAGE, AND AIRCRAFT FUSELAGE PROVIDED WITH SUCH FRAMES 审中-公开
    安全梁，特别是紧固的框架，以及提供这种框架的飞机熔接

    公开(公告)号：US20130157017A1

    公开(公告)日：2013-06-20

    申请号：US13714789

    申请日：2012-12-14

    申请人： Airbus Operations (SAS)

    发明人： Julien Guillemaut ,  Guillaume Gallant ,  Jerome Colmagro

    IPC分类号： B64C1/06

    CPC分类号： B64C1/062 ,  B64C1/061 ,  Y10T428/24612 ,  Y10T428/24628 ,  Y10T428/249923

    摘要： An arrangement for freeing the structures of fail-safe type from the damage tolerance criterion and to allow a significantly improved fatigue resistance, while producing a weight saving. This is provided by forming a composite hybrid structure in a configuration that makes it possible to combine the advantages of metal and of composite material. In a secure hybrid structure, at least two longitudinal structural spars are joined back to back by fastening means. One of the spars is metal and equipped with stability partitions, whereas another spar is made of a composite material with carbon fibers oriented in the direction of the forces to be predicted such that this spar exhibits a rigidity equivalent to that of the metal spar.

    摘要翻译： 一种用于从故障公差标准中释放故障安全型结构并允许显着提高耐疲劳性的装置，同时节省重量。 这通过形成能够结合金属和复合材料的优点的构造的复合混合结构来提供。 在安全的混合结构中，至少两个纵向结构翼梁通过紧固装置背对背连接。 其中一个翼梁是金属并具有稳定的隔板，而另一个翼梁由复合材料制成，碳纤维沿着待预测的力的方向定向，使得该翼梁具有与金属翼梁相当的刚度。