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    AIRCRAFT WITH A TRIMMABLE HORIZONTAL STABILIZER HAVING THE PIVOT ELEMENTS IN ITS FORWARD SIDE
    72.
    发明申请
    AIRCRAFT WITH A TRIMMABLE HORIZONTAL STABILIZER HAVING THE PIVOT ELEMENTS IN ITS FORWARD SIDE 有权
    具有在其前端的转向元件的可手动水平稳定器的飞机

    公开(公告)号：US20150183509A1

    公开(公告)日：2015-07-02

    申请号：US14587590

    申请日：2014-12-31

    Applicant: AIRBUS OPERATIONS S.L.

    Inventor： Raúl LLAMAS SANDÍN ,  Miguel LUQUE BUZO ,  José Luis MARTÍNEZ MUÑOZ

    IPC: B64C9/08

    CPC classification number: B64C9/08 ,  B64C1/26 ,  B64C5/02 ,  B64C9/02 ,  B64C13/28

    Abstract: The invention provides an aircraft with a trimmable horizontal stabilizer (13) that not requires a cut-out in resistant areas of the rear fuselage and that occupies less space that in conventional horizontal stabilizers. The rear fuselage (5) comprises at least a first section (9) having a resistant fuselage and a second section (11), aft of the first section, having a non-resistant fuselage (i.e. a fairing). The load-bearing structure (30) of the horizontal stabilizer and the trimming actuator (50) are disposed inside said second section (11). The pivot element (41) is mounted on its forward side and coupled to the first section (9) of the rear fuselage. The connection fitting (21) is mounted on its rearward side and the trimming actuator (50) is disposed so that it exerts a force in the direction of the Z-axis of the aircraft on the connection fitting (21) during a trimming operation.

    Abstract translation: 本发明提供了具有可调节水平稳定器（13）的飞行器，其不需要在后机身的阻力区域中的切口，并且在常规水平稳定器中占据较少的空间。 后部机身（5）至少包括具有耐机构的第一部分（9）和第二部分（11），第一部分的后部具有非抵抗机身（即整流罩）。 水平稳定器和修剪致动器（50）的承载结构（30）设置在所述第二部分（11）内。 枢轴元件（41）安装在其前侧并且联接到后机身的第一部分（9）。 连接配件（21）安装在其后侧，并且修整致动器（50）被设置成在修整操作期间在飞行器的Z轴方向上在连接配件（21）上施加力。

    LEADING EDGE FOR AN AIRCRAFT LIFTING SURFACE
    73.
    发明申请
    LEADING EDGE FOR AN AIRCRAFT LIFTING SURFACE 有权
    飞机升降面的领先边缘

    公开(公告)号：US20150175253A1

    公开(公告)日：2015-06-25

    申请号：US14579717

    申请日：2014-12-22

    Applicant: Airbus Operations S.L.

    Inventor： Fernando Pereira Mosqueira ,  Enrique Guinaldo Fernandez ,  Carlos Garcia Nieto ,  Francisco Javier Honorato Ruiz ,  Andrea Ivan Marasco

    IPC: B64C3/18 ,  B64C3/26

    CPC classification number: B64C3/185 ,  B64C3/26 ,  B64C3/28

    Abstract: An optimized leading edge for an aircraft lifting or supporting surfaces, such as wings and stabilizers, wherein the leading edge includes inboard and outboard leading edge sections that are span-wise arranged so as to form together an aerodynamic surface of the leading edge. Each of the leading edge sections includes a skin panel and a support structure formed by spars that are internally arranged in the skin panel. These two support structures are designed taking into account the different load requirements of those two different sections, so that the number of spars in each leading edge section is progressively reduced from root to tip of the leading edge, in such a way that the support structure of the outboard leading edge section, has less spars than the inboard leading edge section. Hence the weight of the leading edge is reduced while still maintaining the required structural behavior.

    Abstract translation: 用于飞行器提升或支撑表面（例如翼和稳定器）的优化前缘，其中前缘包括横跨方向布置以一起形成前缘的空气动力学表面的内侧和外侧前缘部分。 每个前缘部分包括皮肤面板和由内部布置在皮肤面板中的翼梁形成的支撑结构。 这两个支撑结构被设计成考虑到这两个不同部分的不同负载要求，使得每个前缘部分中的翼梁的数量从前端的根部到尖端逐渐减小，使得支撑结构 的外侧前缘部分，具有比内侧前缘部分更少的翼梁。 因此，前沿的重量减小，同时仍然保持所需的结构行为。

    OPTIMIZED TORSION BOX FOR AN AIRCRAFT
    76.
    发明申请
    OPTIMIZED TORSION BOX FOR AN AIRCRAFT 有权
    优化的机舱扭矩箱

    公开(公告)号：US20140138486A1

    公开(公告)日：2014-05-22

    申请号：US14085381

    申请日：2013-11-20

    Applicant: AIRBUS OPERATIONS S.L.

    Inventor： Enrique GUINALDO FERNADEZ ,  Francisco CRUZ DOMINGUEZ ,  Francisco Javier HONORATO RUIZ ,  Paula MÁS MÁS ,  Iker VÉLEZ DE MENDIZÁBAL ALONSO ,  Carlos GARCIA NIETO

    IPC: B64C3/18

    CPC classification number: B64C3/185 ,  B64C3/18 ,  B64C3/187 ,  Y10T156/10

    Abstract: The invention provides an aircraft lifting surface with a torsion box (13) of a composite material comprising an upper skin (21), a lower skin (23), a front spar (18), a rear spar (20), one or more intermediate spars (19, 19′) and a plurality of transverse ribs (25, 25′, . . . ) arranged between the rear spar (20) and its adjacent intermediate spar (19′) and/or between the front spar (18) and the adjacent intermediate spar (19) for improving its structural behavior. The invention also provides a manufacturing method of said torsion box.

    Abstract translation: 本发明提供一种具有复合材料的扭转箱（13）的飞机提升表面，该复合材料包括上皮（21），下皮（23），前翼梁（18），后翼梁（20），一个或多个 中间翼梁（19,19'）和布置在后翼梁（20）和其相邻的中间翼梁（19'）之间和/或前翼梁（18）之间的多个横向肋（25,25'...） ）和相邻的中间梁（19），用于改善其结构行为。 本发明还提供了所述扭转箱的制造方法。

    MULTIFUNCTIONAL COMPOSITE MATERIAL INCLUDING A VISCOELASTIC INTERLAYER
    77.
    发明申请
    MULTIFUNCTIONAL COMPOSITE MATERIAL INCLUDING A VISCOELASTIC INTERLAYER 有权
    多功能复合材料，包括粘弹性层间隔层

    公开(公告)号：US20140011006A1

    公开(公告)日：2014-01-09

    申请号：US13929166

    申请日：2013-06-27

    Applicant: Airbus Operations, S.L.

    Inventor： Enrique Guinaldo Fernandez ,  Tamara Blanco Varela

    IPC: B64C1/40

    CPC classification number: B64C1/40 ,  B32B5/022 ,  B32B5/024 ,  B32B5/12 ,  B32B5/26 ,  B32B7/02 ,  B32B7/045 ,  B32B7/12 ,  B32B2260/023 ,  B32B2260/046 ,  B32B2262/101 ,  B32B2262/106 ,  B32B2307/102 ,  B32B2307/202 ,  B32B2307/558 ,  B32B2605/18 ,  Y10T428/24851 ,  Y10T428/24995 ,  Y10T428/249951

    Abstract: Provided is a structure of composite material, comprising a continuous first layer of composite material, a second layer of viscoelastic material, and a continuous impact-protection third layer. The first layer is formed by structural components in the form of a matrix and fibers. The second layer of viscoelastic material is added on top of the first layer and said second layer can be continuous or non-continuous. If a non-continuous second layer is used, elongate, circular or square cavities are arranged inside the layer. Optionally, reinforcements comprising carbon nanofibers or nanotubes are provided in either of the first and second layers. The third layer of impact-protection material is added in a continuous manner on top of the second layer, the third layer forming the outermost layer of the composite material. In addition, this third layer is electrically conductive. The composite material has noise attenuation,

    Abstract translation: 提供了复合材料的结构，其包括连续的第一复合材料层，第二层粘弹性材料和连续冲击保护第三层。 第一层由基质和纤维形式的结构组分形成。 第二层粘弹性材料被添加在第一层的顶部上，而第二层可以是连续的或不连续的。 如果使用非连续的第二层，则在层内布置细长的圆形或方形空腔。 任选地，包含碳纳米纤维或纳米管的增强件设置在第一层和第二层中的任一层中。 第三层冲击保护材料以连续的方式添加到第二层的顶部，第三层形成复合材料的最外层。 另外，该第三层是导电的。 复合材料具有噪声衰减，

    OUTER FUEL TANK ACCESS COVER, WING AND AIRCRAFT DESCRIPTION
    78.
    发明申请
    OUTER FUEL TANK ACCESS COVER, WING AND AIRCRAFT DESCRIPTION 有权
    外燃油舱盖，盖子和飞机说明

    公开(公告)号：US20130306796A1

    公开(公告)日：2013-11-21

    申请号：US13828499

    申请日：2013-03-14

    Applicant: AIRBUS OPERATIONS S.L.

    Inventor： Marcos Alazraki

    IPC: B64D37/32

    CPC classification number: B64D37/32 ,  B64C1/14 ,  B64C1/1446 ,  B64C3/34 ,  B64D37/005 ,  Y02T50/44

    Abstract: The present invention describes an outer fuel access tank cover (FTAC) of an aircraft, a wing comprising such outer FTAC of an aircraft and an aircraft. The invention belongs to the field of “designing auxiliary pieces in the wing of aircrafts to control the risk of gases from an explosion occurred in the FTAC entering the fuel tank”.

    Abstract translation: 本发明描述了一种飞行器的外部燃料存取箱盖（FTAC），一种包括飞机和航空器的外部FTAC的机翼。 本发明属于“设计飞机机翼辅助件，控制进入燃油箱的FTAC发生爆炸的危险”的领域。

    METHOD FOR EVALUATING THE INSTALLATION OF BLIND RIVETS, METHOD AND SYSTEM FOR INSTALLING BLIND RIVETS, METHOD AND SYSTEM FOR OBTAINING A PATTERN, AND AIRCRAFT
    79.
    发明申请
    METHOD FOR EVALUATING THE INSTALLATION OF BLIND RIVETS, METHOD AND SYSTEM FOR INSTALLING BLIND RIVETS, METHOD AND SYSTEM FOR OBTAINING A PATTERN, AND AIRCRAFT 审中-公开
    用于评估安装蓝牙的方法，用于安装盲孔的方法和系统，用于获得图案的方法和系统以及飞机

    公开(公告)号：US20130250730A1

    公开(公告)日：2013-09-26

    申请号：US13828815

    申请日：2013-03-14

    Applicant: AIRBUS OPERATIONS, S.L.

    Inventor： Desirée GUZMAN RABANILLO ,  Juan Ramón Astorga Ramírez ,  Javier CAMACHO DE MIGUEL ,  Agustín Sáenz Fernandez ,  Maria Asunción RIVERO RASTRERO

    IPC: G01N29/07

    CPC classification number: G01N29/07 ,  B21J15/28 ,  B21J15/285 ,  G01N29/348 ,  G01N2291/2691

    Abstract: A method for evaluating installation of blind rivets including measuring the “cycle time” represented “y0”, transmitting sound waves through the blind rivet installed in the structure, measuring the “travel time” represented “x0”, relating “travel time” and “cycle time”, and obtaining a pair of times (x0,y0), providing a time relation pattern establishing a borderline between an area of suitable rivets and an area of unsuitable rivets, the border represented y=f(x), so for cycle time values greater than y=f(x), it is considered a “suitable area”, for cycle time values less than y=f(x), it is considered an “unsuitable area”, representing pair (x0,y0) in the graphic representation and verifying if the value of y0 is greater or less than the value of y=f(x0), classifying installation of the rivet as suitable or unsuitable according to the verification.

    Abstract translation: 一种用于评估盲铆钉的安装的方法，包括测量表示为“y0”的“循环时间”，通过安装在结构中的盲铆钉传输声波，测量表示为“x0”的“行驶时间”，将“行进时间”和“ 循环时间“，并获得一对时间（x0，y0），提供在适当的铆钉的区域和不适合的铆钉的区域之间建立边界线的时间关系模式，所述边界表示为y = f（x） 时间值大于y = f（x），对于小于y = f（x）的周期时间值，它被认为是“适合的区域”，它被认为是“不合适的区域”，表示对（x0，y0） 图形表示和验证y0的值是否大于或小于y = f（x0）的值，根据验证将铆钉的安装分类为合适或不合适。

    AIRCRAFT WITH FUSELAGE-MOUNTED ENGINES AND AN INTERNAL SHIELD
    80.
    发明申请
    AIRCRAFT WITH FUSELAGE-MOUNTED ENGINES AND AN INTERNAL SHIELD 审中-公开
    带有安装引擎和内部防护罩的飞机

    公开(公告)号：US20130214090A1

    公开(公告)日：2013-08-22

    申请号：US13724360

    申请日：2012-12-21

    Applicant: AIRBUS OPERATIONS S.L.

    Inventor： Diego FOLCH CORTÉS ,  Eduardo VINUÉ SANTOLALLA ,  Esteban MARTINO GONZALEZ ,  Julien GUILLEMAUT ,  Pablo GOYA ABAURREA

    IPC: B64D45/00 ,  B64D27/02

    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。

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