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163 条记录 (耗时 0.016 秒)

    GURNEY FLAP
    62.
    发明公开
    GURNEY FLAP 审中-公开

    公开(公告)号：EP3333068A1

    公开(公告)日：2018-06-13

    申请号：EP16203156.1

    申请日：2016-12-09

    申请人： Claverham Limited

    发明人： BREWER, Paul ,  BEKIRCAN, Suat

    IPC分类号： B64C3/50 ,  B64C9/02 ,  B64C9/08 ,  B64C9/34 ,  B64C27/615 ,  B64C3/14 ,  B64C27/72

    CPC分类号： B64C9/02 ,  B64C3/50 ,  B64C9/08 ,  B64C9/34 ,  B64C27/615 ,  B64C2003/145 ,  B64C2027/7266 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/32 ,  Y02T50/34

    摘要： A gurney flap arrangement comprising: an airfoil (2) with a trailing edge (6) and an opening (14) in a surface (8) of the airfoil (2); a gurney flap (1) having a first position in which at least a portion of the gurney flap (1) extends through the opening (14) and projects outwardly from the airfoil surface (8), and a second position in which the gurney flap (1) does not project from the airfoil surface (8) or projects outwardly from the airfoil surface (8) to a lesser extent; and a gurney flap actuator (3) for moving the gurney flap (1) between at least the first position and the second position. The gurney flap actuator (3) is arranged to move the gurney flap (1) in a direction that extends along an inclined angle with less than 90 degrees between the gurney flap (1) and a part of the airfoil surface (8) extending from the opening (14) toward the trailing edge (6) such that when moving from the second position into the first position a distal edge (16) of the gurney flap (1) moves both outward from the airfoil surface (8) and also in a direction extending along the airfoil surface (8) toward the trailing edge (6).

    FLAP AND AIRCRAFT
    63.
    发明公开
    FLAP AND AIRCRAFT 审中-公开
    FLAP和飞机

    公开(公告)号：EP3305654A1

    公开(公告)日：2018-04-11

    申请号：EP16799510.9

    申请日：2016-04-14

    申请人： Mitsubishi Aircraft Corporation ,  Japan Aerospace Exploration Agency

    发明人： HAYASHI, Kensuke ,  MURAYAMA, Mitsuhiro ,  YAMAMOTO, Kazuomi

    IPC分类号： B64C3/50 ,  B64C9/18 ,  B64C23/06

    CPC分类号： B64C9/20 ,  B64C3/50 ,  B64C9/16 ,  B64C23/06 ,  B64C23/065 ,  B64C2230/14 ,  Y02T50/164 ,  Y02T50/44

    摘要： An aircraft flap 3 is equipped with: a flap body 8 which is provided so as to be deployable with respect to a main wing 2; and inclined portions 5 which are provided so as to protrude on the upper surface 301 of at least the end 40 on the outboard OTB side in the span direction D2 of the flap body 8, and are inclined to the aircraft axial direction D1; and a protruding portion 7 which protrudes smoothly from the lower surface 302 of at least the end 40 on the outboard side. The rear end 52 of each of the inclined portions 5 is located closer to the side end edge 301A of the end 40 in the span direction D2 of the flap body 8 than the virtual line VL that passes through the front end 51 of the inclined portion 5 and is parallel to the aircraft axis direction.

    摘要翻译： 飞机襟翼3配备有：襟翼主体8，该襟翼主体8被设置成可相对于主机翼2展开; 以及倾斜部5，其设置成在翼主体8的翼展方向D2上至少在外侧OTB侧的端部40的上表面301上突出并且相对于飞行器轴向D1倾斜; 以及从外侧的至少端部40的下表面302平滑地突出的突出部7。 每个倾斜部分5的后端52位于比翼片本体8的翼展方向D2上的端部40的侧端边缘301A更靠近通过倾斜部分的前端51的假想线VL的位置 5并且平行于飞机轴线方向。

    Flap support
    67.
    发明公开
    Flap support 审中-公开
    瓣支架

    公开(公告)号：EP2578489A3

    公开(公告)日：2015-12-02

    申请号：EP12186927.5

    申请日：2012-10-02

    申请人： Airbus Operations Limited

    发明人： Soenarjo, Mochamad Agoes

    IPC分类号： B64C9/02 ,  B64C9/18 ,  B64C9/16

    CPC分类号： B64C9/18 ,  B64C3/50 ,  B64C9/02 ,  B64C9/16 ,  Y02T50/32 ,  Y02T50/44

    摘要： A flap support structure (6) for an aircraft wing (3) having a trailing edge flap (5), the flap support structure comprising: a flap support beam (10) including an aerodynamic fairing (17); and a drive unit (13) including a universal support structure (18) which rotatably receives a drive shaft (25) connected to a drive arm (14a) for moving the trailing edge flap, wherein the universal support structure also forms part of the flap support beam and supports the aerodynamic fairing.