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    Leading edge for an aircraft lifting surface
    3.
    发明授权
    Leading edge for an aircraft lifting surface 有权
    飞机起重面的前沿

    公开(公告)号：US09381992B2

    公开(公告)日：2016-07-05

    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 ,  B64C3/28 ,  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。

    LEADING EDGE FOR AN AIRCRAFT LIFTING SURFACE
    4.
    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。

    MULTIFUNCTIONAL COMPOSITE MATERIAL INCLUDING A VISCOELASTIC INTERLAYER
    5.
    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，

    Highly integrated leading edge of an aircraft lifting surface
    7.
    发明授权
    Highly integrated leading edge of an aircraft lifting surface 有权
    高度集成的飞机起升面前沿

    公开(公告)号：US09322276B2

    公开(公告)日：2016-04-26

    申请号：US13943115

    申请日：2013-07-16

    Applicant: AIRBUS OPERATIONS S.L.

    Inventor： Enrique Guinaldo Fernandez ,  Francisco Javier Honorato Ruiz ,  Francisco Jose Cruz Dominguez

    IPC: B64C1/00 ,  F01D5/14 ,  B64C3/28

    CPC classification number: F01D5/14 ,  B29D99/0028 ,  B64C3/28 ,  Y10T29/49336

    Abstract: A method for manufacturing a leading edge profile section of an aircraft lifting surface is provided. The method comprises the following steps: a) providing a set of laminated preforms of a composite material configured with a suitable shape for constituting the leading edge profile section; b) arranging said laminated preforms in a curing tooling and subjecting the assembly to an autoclave cycle to co-cure said laminated preforms; c) demolding the curing tooling in a spanwise direction towards the aircraft symmetry plane. The invention also comprises a leading edge profile section manufactured by said method comprising in addition to the skin of the leading edge profile section, one or more of the following structural elements: an auxiliary spar, a longitudinal stiffener reinforcing an auxiliary spar, a longitudinal stringer reinforcing the skin of the leading edge profile.

    Abstract translation: 提供一种用于制造飞行器提升表面的前缘轮廓部分的方法。 该方法包括以下步骤：a）提供一组复合材料的叠层预成型件，该复合材料被构造成用于构成前缘型材部分的合适形状; b）将所述层压预制件布置在固化工具中，并使组件经受高压釜循环以共同固化所述层压预制件; c）沿翼展方向朝向飞机对称平面脱模固化工具。 本发明还包括通过所述方法制造的前缘轮廓部分，除了前缘轮廓部分的皮肤之外，还包括一个或多个以下结构元件：辅助翼梁，加强辅助翼梁的纵向加强筋，纵向纵梁 加强前缘轮廓的皮肤。

    AIRCRAFT CONTROL SURFACE
    8.
    发明申请
    AIRCRAFT CONTROL SURFACE 有权
    飞机控制面

    公开(公告)号：US20150197328A1

    公开(公告)日：2015-07-16

    申请号：US14580456

    申请日：2014-12-23

    Applicant: Airbus Operations S.L.

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

    IPC: B64C5/10 ,  B64C9/02 ,  B64C5/02

    CPC classification number: B64C9/02 ,  B64C3/185 ,  B64C3/187 ,  B64C5/02 ,  B64C9/00 ,  B64C2009/005 ,  Y02T50/44

    Abstract: An optimized structure of a control surface for aircrafts, such as elevators, rudders, landing flaps, ailerons, and other similar lifting surfaces. The control surface includes a front spar, a rear spar, a plurality of ribs and at least one hinge fitting, as well as and an actuator fitting joined with the front spar. At least one rib is connected with the actuator fitting and it is arranged so as to define an oblique angle with the front spar. One or more ribs are located in correspondence with the main torsion and bending load paths created in the control surface during flight, landing or takeoff, so the same structural behavior of the control surface is achieved, but, with a reduced number of ribs, so that the weight of the control surface is reduced.

    Abstract translation: 用于飞机的控制面的优化结构，例如电梯，方向舵，落地襟翼，副翼和其他类似的提升表面。 控制表面包括前翼梁，后翼梁，多个肋和至少一个铰接配件，以及与前翼梁连接的致动器配件。 至少一个肋与致动器配件连接，并且其布置成与前翼梁形成倾斜的角度。 一个或多个肋对应于在飞行，着陆或起飞期间在控制表面中产生的主扭转和弯曲载荷路径，因此实现了控制表面的相同结构特性，但是随着肋的数量减少， 控制面的重量减小。

    MAIN SUPPORTING STRUCTURE OF AN AIRCRAFT LIFTING SURFACE
    9.
    发明申请
    MAIN SUPPORTING STRUCTURE OF AN AIRCRAFT LIFTING SURFACE 有权
    飞机提升表面的主要支撑结构

    公开(公告)号：US20140151505A1

    公开(公告)日：2014-06-05

    申请号：US14083531

    申请日：2013-11-19

    Applicant: Airbus Operations S.L.

    Inventor： Enrique Guinaldo Fernandez ,  Francisco Cruz Dominguez ,  Francisco Javier Honorato Ruiz ,  Paula Mas Mas ,  Iker Velez de Mendizabal Alonso ,  Carlos Garcia Nieto

    IPC: B64C3/18

    CPC classification number: B64C3/187 ,  B64C3/185 ,  B64C5/02 ,  Y10T29/49622

    Abstract: An aircraft lifting surface with a main supporting structure comprising upper and lower faces defining its aerodynamic profile, front and rear faces oriented towards, respectively, the leading and trailing edges, a first set of transverse ribs extended from the front face to the rear face and a second set of transverse ribs crossing the front face and/or the rear face. The integration of leading and trailing edge ribs in the main supporting structure allows a weight and cost reduction of aircraft lifting surfaces. A manufacturing method of said main supporting structure is also disclosed.

    Abstract translation: 具有主支撑结构的飞行器提升表面包括限定其空气动力学轮廓的上表面和下表面，前表面和后表面分别面向前缘和后缘，第一组横向肋从前表面延伸到后表面，并且 横过前表面和/或后表面的第二组横向肋。 主支撑结构中的前缘和后缘肋骨的集成允许飞机提升表面的重量和成本降低。 还公开了所述主支撑结构的制造方法。

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