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    AIRCRAFT AERODYNAMIC SURFACE WITH A DETACHABLE LEADING EDGE
    4.
    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。

    Aircraft bird strike prevention
    5.
    发明公开
    Aircraft bird strike prevention 审中-公开
    Vorbeugung von Vogelschlag一个einem Flugzeug

    公开(公告)号：EP2737795A1

    公开(公告)日：2014-06-04

    申请号：EP13194092.6

    申请日：2013-11-22

    申请人： The Boeing Company

    发明人： Boren, Kelly L.

    IPC分类号： A01M29/12 ,  B64D45/00

    CPC分类号： B64D1/18 ,  A01M29/12 ,  B64D1/16 ,  B64D45/00 ,  B64D2045/0095

    摘要： An aircraft (16) comprises an aircraft body, and apparatus (30), carried by the body, for discharging a persistent vapor of bird repellant into an elevated airspace.

    摘要翻译： 飞机（16）包括飞行器主体和由本体携带的用于将悬浮剂的持续蒸气排放到升高的空域中的装置（30）。

    REDUCING BIRD DAMAGE TO AN AIRPLANE
    6.
    发明公开
    REDUCING BIRD DAMAGE TO AN AIRPLANE 有权
    SYSTEM联合国用于减少鸟害期一种平面

    公开(公告)号：EP2720946A2

    公开(公告)日：2014-04-23

    申请号：EP12715211.4

    申请日：2012-03-01

    申请人： Israel Aerospace Industries Ltd.

    发明人： YIFRACH, Aharon

    IPC分类号： B64D45/00

    CPC分类号： A01M31/002 ,  A01M29/32 ,  B64D45/00 ,  B64D2045/0095

    摘要： The presently disclosed subject matter includes, inter alia, a method and system for reducing damage to an airplane by birds. A high pressure jet is selectively triggered on to birds by a jetting system that is mounted on the airplane. Information indicative of motion of a bird in a vicinity of the airplane is received and analyzed and the high pressure jet is selectively triggered onto the bird in response to a result of the analysis of the information.

    PROCÉDÉ D'INSPECTION DES IMPACTS OBSERVÉS DANS DES CARTERS DE SOUFFLANTE.
    10.
    发明公开
    PROCÉDÉ D'INSPECTION DES IMPACTS OBSERVÉS DANS DES CARTERS DE SOUFFLANTE. 有权
    FOR检查方法，创建于风扇外壳罢工

    公开(公告)号：EP2688707A1

    公开(公告)日：2014-01-29

    申请号：EP12714785.8

    申请日：2012-03-15

    申请人： SNECMA

    发明人： TRAN, Julien ,  LAVIGNOTTE, Richard

    IPC分类号： B23P6/00 ,  F01D21/00 ,  G01N21/88 ,  F01D21/04 ,  B64D33/02

    CPC分类号： G01M13/00 ,  B64C5/06 ,  B64C2003/146 ,  B64D2045/0095 ,  F01D21/003 ,  F01D21/045 ,  F05B2280/6003 ,  F05D2260/80 ,  G01B3/00 ,  G01N17/00 ,  G01N21/8803 ,  G01N21/954 ,  Y02T50/672

    摘要： The present invention relates to a method for inspecting impacts (Ii) present on an internal face (104) of a fan casing (100), said method being characterized in that it comprises the following steps consisting in: - spotting (201) a first impact (I1) present on the internal face (104) of the fan casing (100); - delimiting (202) an inspection area (106) containing said first impact (I1); - spotting (203) the various impacts (Ii) present in the delimited inspection area (106), said various spotted impacts forming a set of impacts to be considered; - measuring (204), for each impact (Ii) that is to be considered, the depth of length of said impact (Ii); - for each impact (Ii) to be considered, determining (205) a harmfulness value, using at least one chart (300; 400) relating the depth and length of each impact to be considered to a level of harmfulness; - determining (206), for the inspection area (106) containing the first impact (I1), a total harmfulness value by adding together the harmfulness level determined for each impact (Ii) to be considered.