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    Flap system for an aircraft, method for adjusting the lift of an aircraft and aircraft comprising a main wing and at least one flap system
    3.
    发明授权
    Flap system for an aircraft, method for adjusting the lift of an aircraft and aircraft comprising a main wing and at least one flap system 有权
    阀系统用于飞行器，为的飞机和飞机姿态与主翼的浮力和至少一个襟翼系统过程

    公开(公告)号：EP2746151B1

    公开(公告)日：2017-04-12

    申请号：EP12198226.8

    申请日：2012-12-19

    申请人： Airbus Operations GmbH

    发明人： Saliveros, Efstratios ,  Friedel, Hendrik

    IPC分类号： B64C3/50 ,  B64C9/04 ,  B64C9/06 ,  B64C9/18

    CPC分类号： B64C9/18 ,  B64C3/50 ,  B64C9/04 ,  B64C9/06

    摘要： A flap system (2) for an aircraft comprises a flow body (4, 36), a trailing flap (6) and a movement means (18, 20). The flow body (4, 36) comprises an upper surface (13) and a lower surface (15), the lower surface (15) having a recess (28). The movement means (18, 20) is attachable to the flow body (4, 36) and the trailing flap (6). The trailing flap (6) comprises a shape that corresponds to the recess (28) in the lower surface (15). The movement means (18, 20) is adapted for conducting at least a chordwise movement of the trailing flap (6) such that it is movable out of and into the recess (28) of the flow body (4, 36) in absence of a gap between the leading edge of the trailing flap (6) and the flow body (4, 36). Thereby, a clear increase in a lift coefficient may be achieved, while at the same time maintaining a low complexity and a high reliability of the flap system.

    AIRCRAFT
    4.
    发明公开
    AIRCRAFT 审中-公开
    飞机

    公开(公告)号：EP3093235A1

    公开(公告)日：2016-11-16

    申请号：EP16166183.0

    申请日：2016-04-20

    申请人： Rolls-Royce plc

    发明人： Moxon, Matthew

    IPC分类号： B64C15/00 ,  B64C21/00 ,  B64D27/00 ,  B64D33/02 ,  B64D27/02

    CPC分类号： B64D33/02 ,  B64C3/50 ,  B64C11/001 ,  B64C15/00 ,  B64C21/00 ,  B64D27/02 ,  B64D27/10 ,  B64D27/24 ,  B64D29/04 ,  B64D33/04 ,  B64D2027/026 ,  B64D2033/0226 ,  Y02T50/166 ,  Y02T50/44

    摘要： An aircraft (10) comprises trailing edge flaps (17), a wing mounted propulsor (26) positioned such that the flaps (17) are located in a slipstream of the first propulsor in use when deployed. The aircraft (10) further comprises a thrust vectorable propulsor configured to selectively vary the exhaust efflux vector of the propulsor in at least one plane. The thrust vectorable propulsor comprises a ducted fan (30) configurable between a first mode, in which the fan (30) provides net forward thrust to the aircraft (10), and a second mode in which the fan (30) provides net drag to the aircraft. (10). The fan (30) is positioned to ingest a boundary layer airflow in use when operating in the first mode.

    摘要翻译： 飞机（10）包括后缘襟翼（17），机翼安装的推进器（26），其定位成使得襟翼（17）在展开时位于第一推进器的滑流中。 飞机（10）还包括推力可推动推进器，其被构造成选择性地改变推进器在至少一个平面中的排气流出矢量。 推力矢量推进器包括可在第一模式和第二模式之间配置的管道风扇（30），在第一模式中风扇（30）向飞机（10）提供净向前推力，在第二模式中风扇（30） 飞机。 （10）。 当以第一模式操作时，风扇（30）定位成摄取使用中的边界层气流。

    MORPHING AIRFOIL LEADING EDGE
    8.
    发明公开
    MORPHING AIRFOIL LEADING EDGE 审中-公开
    变形翼型领先优势

    公开(公告)号：EP2915741A1

    公开(公告)日：2015-09-09

    申请号：EP14196306.6

    申请日：2014-12-04

    申请人： The Boeing Company

    发明人： Grip, Robert E. ,  Brown, John J. ,  Harrison, Neal A. ,  Rawdon, Blaine K. ,  Vassberg, John C.

    IPC分类号： B64C3/48 ,  B64C3/50 ,  B64C3/28

    CPC分类号： B64C9/24 ,  B64C3/26 ,  B64C3/28 ,  B64C3/38 ,  B64C3/48 ,  B64C3/50 ,  B64C2003/445 ,  Y02B10/30 ,  Y02T50/14

    摘要： An airfoil may include a leading edge 200 and a shape control mechanism 400. The leading edge may include a flexible leading edge skin 214 having a first end 216, a second end 218, and an arc length defined therebetween. The shape control mechanism may be attached to the flexible leading edge skin at a plurality of support locations 224 and may transition the flexible leading edge skin from a first shape 228 having a first curvature profile 230 to a second shape 232 having a second curvature profile 234 different than the first curvature profile without a change in the arc length.

    摘要翻译： 翼型件可以包括前缘200和形状控制机构400.前缘可以包括具有第一端216，第二端218和限定在其间的弧长的柔性前缘蒙皮214。 形状控制机构可以在多个支撑位置224附接到柔性前缘蒙皮，并且可以将柔性前缘蒙皮从具有第一曲率轮廓230的第一形状228过渡到具有第二曲率轮廓234的第二形状232 不同于第一曲率轮廓而不改变弧长。

    HIGH-LIFT-GENERATING DEVICE, WING, AND NOISE-REDUCTION DEVICE FOR HIGH-LIFT-GENERATING DEVICE
    10.
    发明公开
    HIGH-LIFT-GENERATING DEVICE, WING, AND NOISE-REDUCTION DEVICE FOR HIGH-LIFT-GENERATING DEVICE 有权
    HOCHAUFTRIEBGENERATOR，FLÜGELUND RAUSCHVERRINGERUNGSSTRUKTURFÜRDEN HOCHAUFTRIEBGENERATOR

    公开(公告)号：EP2455282A1

    公开(公告)日：2012-05-23

    申请号：EP10799817.1

    申请日：2010-07-12

    申请人： Mitsubishi Heavy Industries, Ltd. ,  Japan Aerospace Exploration Agency

    发明人： HIRAI, Makoto ,  TAKENAKA, Keizo ,  IMAMURA, Taro ,  YAMAMOTO, Kazuomi ,  YOKOKAWA, Yuzuru

    IPC分类号： B64C9/16 ,  B64C3/50

    CPC分类号： B64C3/48 ,  B64C3/50

    摘要： In a high-lift-device, a wing, and noise reduction device for a high-lift-device that are capable of reducing noise generated when a flap is extended, preventing deterioration of aerodynamics characteristic when retracting the flap, and preventing an increase in weight, a flap main body (5) disposed so as to be extendable/retractable relative to a main wing and a protruding portion (6A-1) that smoothly protrudes at least at the vicinity of one end portion of a positive-pressure surface (PS) of the flap main body (5) in a direction away from the flap main body (5) are provided.

    摘要翻译： 在用于高升力装置的高升力装置，机翼和降噪装置中，能够减少当翼片延伸时产生的噪音，防止在缩回翼片时空气动力特性的劣化，并防止增加 重量，相对于主翼设置成能够伸缩的翼片主体（5）和至少在正压表面的一个端部附近平滑地突出的突出部分（6A-1） 提供了一种离开皮瓣主体（5）的方向上的皮瓣主体（5）的PS）。