The invention discloses a trailing edge distributed ducted blown flap lift augmentation system of a short take-off and landing aircraft, which comprises a main wing box provided with a strip-shaped wing structure, one end of the main wing box is provided with a ducted lift augmentation flap, and the ducted lift augmentation flap is composed of a lifting force surface, a lower lifting force surface and a vertical partition plate; the upper force surface and the lower force surface are symmetrically arranged, and the surfaces of the upper force surface and the lower force surface form a ducted high lift flap side wall surface structure; and the vertical partition plates are arranged between the rising force surface and the lower force surface at equal intervals. According to the trailing edge distributed ducted blowing flap lift augmentation system of the short-distance take-off and landing aircraft, a main wing box and a lower lifting surface in the device form a smooth circulation path, gas enters a ducted lift augmentation flap formed by a lifting surface and the lower lifting surface, the internal space of a duct is differentiated under the distribution of a vertical partition plate, and the internal space of the duct is separated; therefore, the proportion of the lift force area of drainage infiltration of the rotor fan to the area of the full-wing box is greatly increased.
本发明公开了一种短距起降飞行器的后缘分布式涵道吹气襟翼增升系统,包括:主翼盒,其设置有长条状机翼结构,所述主翼盒一端设置有涵道增升襟翼,且涵道增升襟翼由上升力面、下升力面和垂直隔板组成,所述上升力面与下升力面对称设置,且上升力面与下升力面表面构成涵道增升襟翼侧壁面结构;垂直隔板,其等距设置在所述上升力面与下升力面之间。该短距起降飞行器的后缘分布式涵道吹气襟翼增升系统,装置内部的主翼盒与下升力面构成光滑的流通路线,气体进入上升力面与下升力面构成的涵道增升襟翼内部,在垂直隔板分布下对涵道内部空间分化,使得转子风扇引流浸润的升力面积占全翼盒的面积比例大大增加。
Tailing edge distributed duct blowing flap lift augmentation system of short-distance take-off and landing aircraft
一种短距起降飞行器的后缘分布式涵道吹气襟翼增升系统
2023-12-26
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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