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82 条记录 (耗时 0.013 秒)

    Wing trailing edge geometry control mechanism
    41.
    发明授权
    Wing trailing edge geometry control mechanism 无效
    翼后缘几何控制机制

    公开(公告)号：EP1488998B1

    公开(公告)日：2006-11-22

    申请号：EP04013923.0

    申请日：2004-06-14

    申请人： The Boeing Company

    发明人： Vassberg, John Charles ,  Gregg, Robert D. III

    IPC分类号： B64C3/14 ,  B64C3/58

    CPC分类号： B64C3/50 ,  B64C3/58 ,  B64C9/00 ,  B64C39/12 ,  B64C2003/145 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/32 ,  Y02T50/44

    摘要： A mobile platform lift increasing system includes at least one wing-shaped structure having a leading edge (18), a trailing edge (20) and a chord length (22) perpendicularly measurable between the leading and trailing edges (18, 20). A rotatable control surface (34) is located near a trailing edge undersurface (42). The control surface length is approximately one to five percent of the chord length (22). A deployment device (48, 50) is positioned between the wing shaped structure and the control surface (34). The deployment device operably rotates the control surface through a plurality of positions ranging between an initial position (52) and a fully deployed position (58). Wing lift is increased at speeds up to approximately transonic speed by continuously rotating the control surface to accommodate variables including mobile platform weight change from fuel usage.

    Aircraft lift arrangement
    42.
    发明公开
    Aircraft lift arrangement 审中-公开
    Flugzeuge AuftriebsanordnungfürFlugzeuge

    公开(公告)号：EP1104741A1

    公开(公告)日：2001-06-06

    申请号：EP00500254.8

    申请日：2000-11-29

    申请人： Munoz Saiz, Manuel

    发明人： Munoz Saiz, Manuel

    IPC分类号： B64C39/08 ,  B64C39/06

    CPC分类号： B64C1/0009 ,  B64C3/58 ,  B64C5/18 ,  B64C23/005 ,  B64C39/068 ,  B64C39/08 ,  B64C39/10 ,  B64C2001/0045

    摘要： An aircraft lift arrangement that consists of fine fins (2) which are parallel among themselves and slightly curved, arranged attached along the sides of the aircraft fuselage (3), beginning at the front and running downward toward the rear, with a positive angle of attack and with the additional of small thin wings to provide lateral stability and to carry the engines, flaps and ailerons.

    摘要翻译： 一种飞行器升降机装置，它们由它们之间平行并且稍微弯曲的细翅片（2）组成，沿着飞机机身（3）的侧面安装，从前面开始并向后朝向后方，以 攻击和额外的小薄翼提供横向稳定性和携带发动机，襟翼和副翼。

    WING TIP DEVICE
    47.
    发明公开
    WING TIP DEVICE 审中-公开

    公开(公告)号：EP3392136A1

    公开(公告)日：2018-10-24

    申请号：EP18171644.0

    申请日：2011-07-07

    申请人： Airbus Operations Limited ,  Airbus Operations GmbH ,  Deutsches Zentrum für Luft- und Raumfahrt e.V.

    发明人： WRIGHT, Christopher ,  CHU, James K. ,  HIMISCH, Jan

    IPC分类号： B64C23/06 ,  B64C3/58

    CPC分类号： B64C23/065 ,  B64C3/58 ,  B64C23/069 ,  Y02T50/164 ,  Y10T29/49716

    摘要： A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection, wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees. Also, a wing with the wing tip device; an aircraft with the wing; a method of fitting, or retro-fitting, the wing tip device to a wing; a method of modifying an existing wing tip device; and a method of operating a wing with the wing tip device.