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12 条记录 (耗时 0.015 秒)

    AIRCRAFT AERODYNAMIC SURFACE WITH A DETACHABLE LEADING EDGE
    2.
    发明公开
    AIRCRAFT AERODYNAMIC SURFACE WITH A DETACHABLE LEADING EDGE 审中-公开
    具有可拆卸的前缘的飞机气动曲面

    公开(公告)号：EP3216693A1

    公开(公告)日：2017-09-13

    申请号：EP16382106.9

    申请日：2016-03-10

    申请人： Airbus Operations, S.L.

    发明人： CEBOLLA GARROFE, Pablo ,  VÉLEZ DE MENDIZÁBAL ALONSO, Iker ,  CRESPO PEÑA, Soledad ,  CALERO CASANOVA, Álvaro ,  GARCÍA NIETO, Carlos ,  GUINALDO, Enrique ,  HONORATO RUIZ, Francisco, Javier ,  TORRES SALAS, Álvaro

    IPC分类号： B64C3/28 ,  B64C21/06 ,  B64D45/00

    CPC分类号： B64C3/26 ,  B64C3/185 ,  B64C3/28 ,  B64C5/02 ,  B64C21/06 ,  B64D2045/0095 ,  Y02T50/166

    摘要： The invention refers to an aircraft aerodynamic surface (10) comprising a torsion box having an upper skin (11), a lower skin (12), and a front spar (9), and a leading edge (1) having an external shell (7) and an impact resisting structure (8). The external shell (7) may be shaped with an aerodynamic leading edge profile, being configured to provide Laminar Flow Control (LFC) to the leading edge. The impact resisting structure (8) is spanwise arranged between the external shell (7) and the front spar (9), and is configured for absorbing a bird strike to prevent damage in the front spar (9). Also, at least one of the external shell (7) and the impact resisting structure (8) is fitted with the upper and lower skins (11, 12) of the torsion box to thereby facilitate leading edge exchange.

    摘要翻译： 本发明涉及一种飞机空气动力学表面（10），其包括具有上蒙皮（11），下蒙皮（12）和前翼梁（9）的扭转箱以及具有外壳（11）的前缘（1） 7）和抗冲击结构（8）。 外壳（7）可以被成形为具有空气动力学前缘轮廓，被配置为向前缘提供层流控制（LFC）。 抗冲击结构（8）在外壳（7）和前翼梁（9）之间展向布置，并且构造成用于吸收鸟击以防止前翼梁（9）中的损坏。 而且，外壳（7）和耐冲击结构（8）中的至少一个与扭转箱的上表皮和下表皮（11,12）配合，从而便于前缘更换。

    LEADING EDGE WITH LAMINAR FLOW CONTROL
    3.
    发明公开
    LEADING EDGE WITH LAMINAR FLOW CONTROL 审中-公开
    带有层流控制的前沿

    公开(公告)号：EP3173328A1

    公开(公告)日：2017-05-31

    申请号：EP15382588.0

    申请日：2015-11-26

    申请人： Airbus Operations, S.L.

    发明人： GUINALDO FERNANDEZ, Enrique ,  CEBOLLA GARROFE, Pablo ,  VÉLEZ DE MENDIZABAL ALONSO, Iker ,  CRESPO PEÑA, Soledad ,  GARCÍA NIETO, Carlos ,  HONORATO RUIZ, Francisco, Javier ,  CALERO CASANOVA, Alvaro ,  TORRES SALAS, Álvaro

    IPC分类号： B64C21/06

    摘要： The present invention refers to the configuration of a leading edge section (1) with laminar flow control, wherein the leading edge comprises: a perforated outer skin (2), an inner surface (3), a plurality of suction chambers (4) formed between the outer skin (2) and the inner surface (3) and a plurality of radial structural elements (5) to withstand structural loads at the leading edge. The radial structural elements (5) are arranged to define the suction chambers (4) together with the outer skin (2) and the inner surface (3), and the radial structural elements (5) and/or the inner surface (3) are perforated, such that an exterior region of the leading edge is communicated with an interior region of the leading edge through said suction chambers (4). The invention provides an optimized leading edge with a laminarflow control system, from a structural point of view, including improved bird impact performance.

    摘要翻译： 本发明涉及具有层流控制的前缘部分（1）的构造，其中前缘包括：穿孔外蒙皮（2），内表面（3），形成的多个抽吸室（4） 在所述外蒙皮（2）和所述内表面（3）之间以及多个径向结构元件（5）以承受所述前缘处的结构载荷。 径向结构元件（5）布置成与外壳（2）和内表面（3）以及径向结构元件（5）和/或内表面（3）一起限定吸入室（4） 被穿孔，使得前缘的外部区域通过所述抽吸室（4）与前缘的内部区域连通。 从结构的角度来看，本发明提供了具有层流控制系统的优化的前缘，包括改进的鸟撞击性能。

    ARMOURED LEADING EDGE AND MANUFACTURING METHOD THEREOF
    5.
    发明公开
    ARMOURED LEADING EDGE AND MANUFACTURING METHOD THEREOF 审中-公开
    装甲的前沿及其制造方法

    公开(公告)号：EP3248864A1

    公开(公告)日：2017-11-29

    申请号：EP16382226.5

    申请日：2016-05-24

    申请人： Airbus Operations, S.L.

    发明人： VELEZ DE MENDIZABAL ALONSO, Iker ,  GUINALDO FERNANDEZ, Enrique ,  GARCÍA NIETO, Carlos ,  HONORATO RUIZ, Francisco, Javier ,  VOTSIOS, Vasilis

    IPC分类号： B64C3/28 ,  B64D7/00 ,  B64D33/02

    CPC分类号： B64C3/28 ,  B64D7/00 ,  B64D2033/022

    摘要： The invention refers to an aerodynamic surface (1) for an aircraft comprising a torsion box having a front spar (5), and a composite leading edge section that comprises an outer surface (2) shaped with an aerodynamic leading edge profile, an inner surface (3) internally arranged with respect to the outer surface (2), and a blanket (4) spanwise arranged between the outermost point of the inner surface (3) and the front spar (5), wherein the blanket is made of fibre material having a specific energy absorption ranging from 47 to 72 J•g- 1 and a longitudinal wave speed ranging from 6 to 15 km•s -1 , wherein the major part of the blanket (4) is of dry fibre material, and wherein the blanket (4) is joined to at least two opposing areas of the inner surface (3) for absorbing a bird strike, to prevent the damage of the front spar (5).

    摘要翻译： 本发明涉及一种用于飞行器的空气动力学表面（1），其包括具有前翼梁（5）的扭转箱以及复合前缘部分，所述复合前缘部分包括形成有空气动力学前缘轮廓的外表面（2），内表面 （3）相对于外表面（2）内部布置，以及在内表面（3）的最外点和前翼梁（5）之间翼展布置的橡皮布（4），其中橡皮布由纤维材料 具有47至72J·g -1的特定能量吸收和6至15km·s-1的纵波速度，其中，橡皮布（4）的主要部分是干纤维材料，并且其中 橡皮布（4）连接到内表面（3）的至少两个相对区域以吸收鸟击，以防止前翼梁（5）的损坏。

    A LEADING EDGE WITH LAMINAR FLOW CONTROL AND MANUFACTURING METHOD THEREOF
    7.
    发明公开
    A LEADING EDGE WITH LAMINAR FLOW CONTROL AND MANUFACTURING METHOD THEREOF 有权
    具有层流控制的主导边及其制造方法

    公开(公告)号：EP3192736A1

    公开(公告)日：2017-07-19

    申请号：EP16382009.5

    申请日：2016-01-12

    申请人： Airbus Operations, S.L.

    发明人： GARCÍA NIETO, Carlos ,  GUINALDO FERNÁNDEZ, Enrique ,  CEBOLLA GARROFE, Pablo ,  VÉLEZ DE MENDIZABAL ALONSO, Iker ,  CRESPO PEÑA, Soledad ,  HONORATO RUIZ, Francisco, Javier ,  TORRES SALAS, Álvaro ,  CALERO CASANOVA, Álvaro

    IPC分类号： B64C21/06

    CPC分类号： B64C21/06 ,  B64C3/182 ,  B64C3/26 ,  B64C2001/0072 ,  B64C2001/0081 ,  B64F5/00 ,  Y02T50/166

    摘要： The invention refers to a leading edge section (1) with laminar flow control, which comprises: a perforated outer skin (2), a perforated inner skin (3), and a plurality of suction chambers (4) formed between the outer skin and the inner skin. The leading edge section comprises a plurality of stringers (5) span-wise arranged at the leading edge section, and integrally formed with the outer skin, such as the inner skin is joined to the stringers. The invention also refers to a method for manufacturing a leading edge section integrating a laminar flow control system, wherein a perforated inner skin is joined with a perforated outer skin having a plurality of stringers (5) integrally formed with the outer skin, such as suction chambers (4) are defined by a part of the outer skin, a part of the inner skin and a pair of stringers.

    摘要翻译： 本发明涉及一种具有层流控制的前缘部分（1），其包括：穿孔的外蒙皮（2），穿孔的内蒙皮（3）以及形成在外蒙皮与外壳之间的多个抽吸室（4） 内在的皮肤。 前缘部分包括多个纵向布置在前缘部分处的纵梁（5），并且与外壳整体形成，诸如内蒙皮与纵梁连接。 本发明还涉及一种用于制造整合层流控制系统的前缘部分的方法，其中穿孔的内蒙皮与具有与外蒙皮整体形成的多个桁条（5）的穿孔外蒙皮相接合，例如抽吸 腔室（4）由外壳的一部分，内壳的一部分和一对桁条限定。

    LEADING EDGE WITH LAMINAR FLOW CONTROL AND MANUFACTURING METHOD THEREOF
    8.
    发明公开
    LEADING EDGE WITH LAMINAR FLOW CONTROL AND MANUFACTURING METHOD THEREOF 审中-公开
    具有层流控制的主导边缘及其制造方法

    公开(公告)号：EP3159259A1

    公开(公告)日：2017-04-26

    申请号：EP15382516.1

    申请日：2015-10-20

    申请人： Airbus Operations, S.L.

    发明人： GARCÍA NIETO, Carlos ,  GUINALDO FERNÁNDEZ, Enrique ,  CEBOLLA GARROFE, Pablo ,  VÉLEZ DE MENDIZABAL ALONSO, Iker ,  CRESPO PEÑA, Soledad ,  HONORATO RUIZ, Francisco, Javier ,  TORRES SALAS, Álvaro ,  CALERO CASANOVA, Álvaro

    IPC分类号： B64C21/06

    CPC分类号： B64C21/06 ,  B64C2230/04 ,  B64C2230/22 ,  Y02T50/166

    摘要： The invention refers to a leading edge (1) with a laminar flow control comprising: a perforated outer skin (3), a perforated inner skin (5), and a plurality of perforated tubular members (16) span-wise arranged in the leading edge and placed between the outer and inner skins (3,5) to form suction chambers (2). The outer skin, the inner skin and the tubular members are cured together in the same curing cycle, such as the leading edge is obtained as an integral component. The invention also refers to a manufacturing method to produce a section of leading edge with laminar flow control, wherein an outer skin pre-form (13), an inner skin pre-form (14), and a plurality of tubular members pre-forms (15), are conformed separately and then assembled and cured together. Since the leading edge of the invention, can be manufactured in one-shot manufacturing time and production costs are significantly reduced.

    摘要翻译： 本发明涉及一种具有层流控制的前缘（1），其包括：穿孔外蒙皮（3），穿孔内蒙皮（5）和多个穿孔管状构件（16） 边缘并放置在外表皮和内表皮（3,5）之间以形成吸入室（2）。 外皮，内皮和管状部件在相同的固化周期中一起固化，例如前缘作为整体部件获得。 本发明还涉及制造具有层流控制的前缘部分的制造方法，其中外蒙皮预成型件（13），内蒙皮预成型件（14）和多个管件预成型件 （15）分开制造，然后组装并固化在一起。 由于本发明的领先优势，可以在一次性制造时间内制造，并且生产成本显着降低。