The invention provides an aircraft trailing edge flap capable of reducing flap side edge noise and compensating lift force loss. The aircraft trailing edge flap is arranged at a trailing edge portion of an aircraft main wing so as to be deployable and stowable, and is provided with a flap main body extending in a wing length direction of the main wing, in a case where a leading edge portion of the flap main body is divided into an outer end leading edge portion and a main body leading edge portion in the wing length direction, at the outer end leading edge portion of the flap main body, at least a part of the outer-end leading edge portion is notched with respect to the main body leading edge portion to form a space in which a slit between the trailing edge portion of the main wing and the outer-end leading edge portion of the flap main body is enlarged when the aircraft trailing edge flap is unfolded, and the space is filled with a porous medium having an outer contour that coincides with the main body leading edge portion.
本发明提供一种既能够降低襟翼侧缘噪声、又能够补偿升力损失的飞机后缘襟翼。飞机后缘襟翼以能够展开及收起的方式设在飞机主翼的后缘部,且具备沿着主翼的翼长方向延伸的襟翼主体,其中,在将襟翼主体的前缘部沿着翼长方向划分为外端前缘部及主体前缘部的情况下,在襟翼主体的外端前缘部,通过使外端前缘部的至少一部分相对于主体前缘部切缺而形成有使飞机后缘襟翼展开时的主翼的后缘部与襟翼主体的外端前缘部之间的缝道增大的空间,并且在该空间中填充有外轮廓与主体前缘部一致的多孔介质。
Aircraft trailing edge flap
飞机后缘襟翼
2021-04-20
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
Europäisches Patentamt | 2015
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