利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

11 条记录 (耗时 0.01 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。

    A LEADING EDGE WITH LAMINAR FLOW CONTROL AND MANUFACTURING METHOD THEREOF
    6.
    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
    7.
    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。

    THERMOPLASTIC MOULDED INJECTED TIP STRUCTURE FOR AN AIRCRAFT
    10.
    发明公开
    THERMOPLASTIC MOULDED INJECTED TIP STRUCTURE FOR AN AIRCRAFT 审中-公开
    用于飞机的热塑性模制注射头结构

    公开(公告)号：EP3272646A1

    公开(公告)日：2018-01-24

    申请号：EP16382351.1

    申请日：2016-07-20

    申请人： Airbus Operations, S.L.

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

    IPC分类号： B64C3/00 ,  B64D37/32

    摘要： The invention refers to the configuration of a tip structure (1) for an aircraft airfoil, such as a control surface (ailerons, flaps, elevators, rudders, etc) and/or a lifting surface (wings, HTP's, VTP's). The tip structure (1) is a unitary body and comprises a tip shell (2) and a metallic material on the outer surface of the tip shell (2) suitable to withstand a lighting strike, wherein the tip shell (2) has been obtained by a single-stage injection molding process using a thermoplastic composite material having fibers dispersed therein, and wherein the metallic material has been integrally formed with the tip shell (2). The invention provides a tip configuration that can be manufactured in one-shot process, fulfilling structural, operational and aerodynamic requirements and achieving thereby high production rates and reducing manufacturing costs.

    摘要翻译： 本发明涉及用于诸如控制表面（副翼，襟翼，电梯，方向舵等）和/或提升表面（机翼，HTP，VTP）的飞行器翼型的尖端结构（1）的构造。 尖端结构（1）是整体，并且包括尖端外壳（2）和在尖端外壳（2）的外表面上适于承受照明冲击的金属材料，其中尖端外壳（2）已经获得 通过使用其中分散有纤维的热塑性复合材料的单级注射成型工艺，并且其中金属材料已经与尖端外壳（2）一体地形成。 本发明提供了可以一次性工艺制造的尖端构造，满足结构，操作和空气动力学要求并由此实现高生产率和降低制造成本。