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5 条记录 (耗时 0.012 秒)

    SLIDEABLE DIVERGENT TRAILING EDGE DEVICE
    1.
    发明公开
    SLIDEABLE DIVERGENT TRAILING EDGE DEVICE 审中-公开
    VORRICHTUNG MIT VERSCHIEBBARER DIVERGIERENDER AUSTRITTSKANTE

    公开(公告)号：EP2952429A1

    公开(公告)日：2015-12-09

    申请号：EP15165345.8

    申请日：2015-04-28

    申请人： The Boeing Company

    发明人： Jamison, Flint M ,  Amorosi, Stephen R ,  Klein, Michael K

    IPC分类号： B64C3/38 ,  B64C3/14 ,  B64C3/28

    CPC分类号： B64C13/24 ,  B64C3/28 ,  B64C3/38 ,  B64C3/50 ,  B64C9/02 ,  B64C9/16 ,  B64C2003/147 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/32 ,  Y02T50/44

    摘要： A wing (130) includes a trailing edge, which may include a moveable flight control surface (230), and a divergent trailing edge device (240) slideable along an aft surface of the trailing edge or moveable flight control surface (230) between a stowed position and a fully deployed position. The divergent trailing edge device (240) is located entirely within the trailing edge or moveable flight control surface (230) when stowed, and it increases lift over drag of the wing (130) when deployed.

    摘要翻译： 机翼（130）包括后缘，其可以包括可移动的飞行控制表面（230），以及沿着后缘或可移动飞行控制表面（230）的后表面可滑动的发散后缘装置（240） 收起位置和充分部署的位置。 发散后缘装置（240）在收起时完全位于后缘或可移动飞行控制表面（230）内，并且当展开时它增加了机翼（130）的拖动力。

    Trailing edge split flap with pneumatic actuation
    2.
    发明公开
    Trailing edge split flap with pneumatic actuation 审中-公开
    Austrittspreizklappe与气动操作

    公开(公告)号：EP2548798A3

    公开(公告)日：2015-10-21

    申请号：EP12176953.3

    申请日：2012-07-18

    申请人： The Boeing Company

    发明人： Balzer, Michael A ,  Santini, Gregory M ,  Klein, Michael K

    IPC分类号： B64C9/16 ,  B64C3/46

    摘要： A system for pneumatically actuating a split flap hingedly mounted near or at a trailing edge of an airfoil. The system includes a bladder system disposed between the split flap and the upper surface of the airfoil. The split flap is a small-chord (usually 1-3% of total wing chord) long-span lower panel which separates from the airfoil trailing edge by means of a hinge or a flexible lower skin. Deployment of the split flap is actuated pneumatically by the inflatable bladder system. The split flap may exist at a fixed wing trailing edge, a moving flap trailing edge, or an empennage trailing edge. The pneumatic bladder provides distributed force to extend and retract the split flap. This pneumatic approach eliminates extra drag, reduces cost and weight, and lessens flutter concerns.

    Trailing edge split flap with pneumatic actuation
    5.
    发明公开
    Trailing edge split flap with pneumatic actuation 审中-公开
    带气动驱动的后缘分瓣

    公开(公告)号：EP2548798A2

    公开(公告)日：2013-01-23

    申请号：EP12176953.3

    申请日：2012-07-18

    申请人： The Boeing Company

    发明人： Balzer, Michael A ,  Santini, Gregory M ,  Klein, Michael K

    IPC分类号： B64C9/16

    摘要： A system for pneumatically actuating a split flap hingedly mounted near or at a trailing edge of an airfoil. The system includes a bladder system disposed between the split flap and the upper surface of the airfoil. The split flap is a small-chord (usually 1-3% of total wing chord) long-span lower panel which separates from the airfoil trailing edge by means of a hinge or a flexible lower skin. Deployment of the split flap is actuated pneumatically by the inflatable bladder system. The split flap may exist at a fixed wing trailing edge, a moving flap trailing edge, or an empennage trailing edge. The pneumatic bladder provides distributed force to extend and retract the split flap. This pneumatic approach eliminates extra drag, reduces cost and weight, and lessens flutter concerns.

    摘要翻译： 一种用于气动致动分瓣的系统，该分瓣铰接地安装在翼型的后缘附近或后缘。 该系统包括设置在分瓣和翼型上表面之间的气囊系统。 分瓣是一个小弦（通常是总翼弦的1-3％）的大跨度下面板，它通过铰链或柔性下皮从翼型后缘分离。 分体式阀瓣的展开由充气气囊系统气动驱动。 分体襟翼可以存在于固定机翼后缘，移动襟翼后缘或尾翼后缘。 气动气囊提供分布式的力来伸展和缩回分瓣。 这种气动方式消除了额外的阻力，降低了成本和重量，并减少了颤动问题。