首页> 外国专利> Aircraft wing trailing edge composite flap - has leading edge of sharp curvature and pivoted straight trailing edge

Aircraft wing trailing edge composite flap - has leading edge of sharp curvature and pivoted straight trailing edge

机译:飞机机翼后缘复合材料襟翼-具有锋利的曲率前缘和可旋转的直后缘

摘要

The profiled extendable flap consists of at least two relatively moving sections for changing the flap configuration. The flap geometry is designed so that the air flow is not separated from the flap upper face even if the flap angle of attitude is very large. The trailing edge profile (22) of the first, forward component (6) of the flap moves in a slot (23) of the rear component (7). The curvature of the composite flap, which has relatively small radii of curvature at the leading edge, becomes straighter towards the trailing edge. The rear component is pivoted with a radius (R) which is larger than the radius (r) of the leading edge curvature.
机译:异形的可伸展襟翼包括至少两个相对运动的部分,用于改变襟翼的构造。襟翼的几何形状设计使得即使襟翼的姿态角很大,气流也不会与襟翼上表面分离。襟翼的第一前部部件(6)的后缘轮廓(22)在后部部件(7)的狭槽(23)中移动。复合翼片的曲率在前缘处具有相对较小的曲率半径,向后缘变得更直。后部组件以大于前缘曲率半径(r)的半径(R)枢转。

著录项

  • 公开/公告号DE000002135629C3

    专利类型

  • 公开/公告日1976-09-02

    原文格式PDF

  • 申请/专利权人

    申请/专利号DE2135629A

  • 发明设计人

    申请日1971-07-16

  • 分类号B64C3/50;

  • 国家 DE

  • 入库时间 2022-08-23 02:10:18

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