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    MORPHING AEROFOIL
    1.
    发明授权
    MORPHING AEROFOIL 有权
    变形的油

    公开(公告)号：EP2844555B1

    公开(公告)日：2016-09-28

    申请号：EP13719156.5

    申请日：2013-04-26

    申请人： Airbus Operations Limited

    发明人： WOOD, Norman

    IPC分类号： B64C3/44 ,  B64C3/48

    CPC分类号： B64C3/44 ,  B64C3/48 ,  B64C2003/445

    摘要： A morphing aerofoil comprising: a leading edge; a trailing edge; and upper and lower surfaces extending between the leading and trailing edges. An upper thermal actuation member is provided proximate the upper surface; and a lower thermal actuation member is provided proximate the lower surface opposite the upper thermal actuator. The upper and lower thermal actuation members have different thermal expansion coefficients and are positioned such that they cause the trailing edge to deflect when they expand or contract by different amounts in response to a change in ambient temperature, thereby changing a camber of the aerofoil.

    摘要翻译： 变形机翼包括：前缘; 后缘 以及在前缘和后缘之间延伸的上表面和下表面。 上部热致动构件设置在上表面附近; 并且下部热致动构件设置在与上部热致动器相对的下表面附近。 上部和下部热致动构件具有不同的热膨胀系数，并且被定位成使得当它们响应于环境温度的变化而膨胀或收缩不同量，从而改变机翼的弯度时，它们使后缘偏转。

    MORPHING WING FOR AN AIRCRAFT
    2.
    发明公开
    MORPHING WING FOR AN AIRCRAFT 有权
    ADAPTIVERFLÜGELFÜRFLUGZEUG

    公开(公告)号：EP2864195A1

    公开(公告)日：2015-04-29

    申请号：EP13735135.9

    申请日：2013-06-21

    申请人： Bombardier Inc. ,  Learjet Inc.

    发明人： XI, Fengfeng ,  FINISTAURI, Allan, Daniel ,  MOOSAVIAN, Amin

    IPC分类号： B64C3/44 ,  B64C3/52

    CPC分类号： B64C3/38 ,  B64C3/385 ,  B64C3/40 ,  B64C3/44 ,  B64C3/52 ,  B64C3/54 ,  B64C2003/445 ,  B64C2003/543 ,  Y02T50/14

    摘要： A morphing wing for an aircraft includes a top surface, a bottom surface, a leading edge, a trailing edge, a tip, and a root. A plurality of structural ribs is disposed between the root and tip so that they extend between the top surface and the bottom surface and intersect with a lateral axis thereof. At least one active member connects between two adjacent structural ribs along or at a first angle to the lateral axis. The active member is actively adjustable. At least one passive member connects between the two adjacent structural ribs along or at a second angle to the lateral axis. The passive member is passively adjustable. Adjustment of at least one active member moves the adjacent structural ribs with respect to one another, thereby morphing the wing from a first configuration to a second configuration.

    摘要翻译： 用于飞行器的变形翼包括顶表面，底表面，前缘，后缘，尖端和根部。 多个结构肋设置在根部和尖端之间，使得它们在顶表面和底表面之间延伸并且与其横向轴线相交。 至少一个有源构件沿着或相对于横向轴线以第一角度连接在两个相邻结构肋之间。 活动构件可以主动调节。 至少一个被动构件沿着或相对于横向轴线的第二角度在两个相邻的结构肋之间连接。 被动元件被动调节。 至少一个活动构件的调整使相邻的结构肋相对于彼此移动，从而使机翼从第一构型变形到第二构型。

    BLADE WITH A VARIABLE PROFILE AND SHAPE
    5.
    发明公开
    BLADE WITH A VARIABLE PROFILE AND SHAPE 审中-公开
    KLINGE MITVERÄNDERLICHEMPROFIL UNDVERÄNDERLICHERFORM

    公开(公告)号：EP2527247A1

    公开(公告)日：2012-11-28

    申请号：EP10843778.1

    申请日：2010-01-20

    申请人： Soluciones Energeticas, S.A.

    发明人： VELA VICO, Antonio ,  GANDIA AGÜERA, Fernando ,  RODRIGUEZ SEVILLANO, Angel ,  BARCALA MONTEJANO, Miguel A.

    IPC分类号： B64C3/44 ,  F03D1/06

    CPC分类号： F03D1/0633 ,  B64C3/44 ,  B64C2003/445 ,  F03D1/0675 ,  F05B2240/311 ,  Y02E10/721 ,  Y02P70/523

    摘要： Blade with variable profile and shape, having a profile (11) manufactured in a flexible material, provided internally with two parallel holes (13) stretching along the entire length of the blade (1), in which bars (2) are fixed, which, when twisted, cause a variation in the shape of the blade (1) and therefore in its aerodynamic features. This blade can work as a variable pitch blade for propellers, with the possibility of being positioned in a flag arrangement; wing, semiwing or aileron, whose profile and shape may vary, forcing a bending of the area closest to its trailing and/or leading edge towards the blade's intrados or extrados, or by means of a diagonal bending of its furthest part or its intermediate part towards the intrados and/or the extrados; o by means of the multiple and combined variation of several bars to obtain various camber movements of the blades.

    摘要翻译： 具有可变轮廓和形状的刀片，具有以柔性材料制造的轮廓（11），其内部设置有沿刀片（1）的整个长度延伸的两个平行的孔（13），杆（2）固定在其中， 当扭曲时，引起叶片（1）的形状的变化，并因此导致其空气动力学特征。 该叶片可以用作螺旋桨的可变桨距叶片，可能被定位在船旗布置中; 翼，半牵引或副翼，其轮廓和形状可能变化，迫使最靠近其后缘和/或前缘的区域朝向叶片的内部或外部的弯曲，或者通过其最远部分或其中间部分的对角弯曲 朝向intrados和/或extrados; o通过多个杆的多个和组合的变化来获得叶片的各种外倾运动。

    AEROFOIL WITH VARIABLE GEOMETRY EXPANSION SURFACE
    8.
    发明公开
    AEROFOIL WITH VARIABLE GEOMETRY EXPANSION SURFACE 失效
    翅膀变STRETCH表面轮廓。

    公开(公告)号：EP0596976A1

    公开(公告)日：1994-05-18

    申请号：EP92916427.0

    申请日：1992-07-28

    申请人： THE SECRETARY OF STATE FOR DEFENCE IN HER BRITANNIC MAJESTY'S GOVERNMENT OF THE UNITED KINGDOM OF GREAT BRITAIN AND NORTHERN

    发明人： ASHILL, Patrick, Ralph ,  FULKER, John, Leslie Woodcote Lodge Road

    IPC分类号： B64C3 ,  B64C23

    CPC分类号： B64C23/00 ,  B64C3/44 ,  B64C3/48 ,  Y02T50/14

    摘要： PCT No. PCT/GB92/01396 Sec. 371 Date May 25, 1994 Sec. 102(e) Date May 25, 1994 PCT Filed Jul. 28, 1992 PCT Pub. No. WO93/02915 PCT Pub. Date Feb. 18, 1993.A wing, or similar article of airfoil section, has a variable geometry surface for the active control of shock strength and transonic wave drag. In one embodiment, the wing has a region of distensible skin (4) aft of the line of maximum section, which extends along the span of the wing in those areas that experience drag. Pressure means (10, 20, 30) within the wing outwardly deflect the distensible region and produce a local bulge in the expansion surface. This bulge induces pre-shock compression and reduces the effect of the shock. The bulge is retracted by the natural elasticity of the skin material (which can be a conventional aluminum alloy) upon removal of the applied pressure. In another embodiment, the wing has a ramp portion (14) which is outwardly deflectable for the same purpose. The invention is applicable to supercritical and natural laminar flow wings.