The invention discloses a vertical/short-distance take-off and landing aircraft with distributed power coupling lift augmentation airfoils, and belongs to the field of aviation aircrafts. The aircraft comprises lift fans, an aircraft body, wings, high lift airfoils, distributed ducted fans and a motion mechanism, wherein the fuselage and the wings are in a flying wing layout with a fused wing body; the lift fan is embedded in the middle of the nose, is in a coaxial contra-rotating form and is used for generating a vertical upward lifting force; the distributed ducted fans are symmetrically distributed at the tail of the fuselage, and the side walls of the two ends of each distributed ducted fan are hinged to side plates fixed to the fuselage through rotating shafts correspondingly. The high-lift airfoil comprises an upper straight wing and a lower straight wing which are arranged in parallel and located at the upper end and the lower end of the outer side of an outlet of the distributed ducted fan respectively, and the two ends of each straight wing are connected with the side plates through movement mechanisms respectively and can tilt relative to the fuselage along the movement mechanisms. Hovering, vertical/short-distance taking-off and landing and cruising level flight of the aircraft in the air can be achieved, and due to the fact that lift force is provided in a lift augmentation airfoil mode, the aircraft can fly more safely and stably in a transition mode.

    本发明一种分布式动力耦合增升翼面的垂直/短距起降飞行器,属于航空飞行器领域;包括升力风扇、机身、机翼、增升翼面、分布式涵道风扇和运动机构;所述机身和机翼为翼身融合的飞翼布局;所述升力风扇内嵌于机头中部,为共轴对转形式,用于产生竖直向上的升力;所述分布式涵道风扇对称分布于机身尾部,其两端侧壁分别通过转轴与固定于机身的侧板铰接;所述增升翼面包括上、下两段平行设置的直机翼、并分别位于分布式涵道风扇的出口外侧上下端,直机翼两端分别通过运动机构与侧板连接,能够沿运动机构相对机身倾转。本发明可以实现飞行器在空中的悬停、垂直/短距起降,巡航平飞,由于采用增升翼面的形式提供升力,飞机过渡飞行更加安全稳定。


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    Titel :

    Vertical/short-distance take-off and landing aircraft with distributed power coupling lift augmentation airfoils


    Weitere Titelangaben:

    一种分布式动力耦合增升翼面的垂直/短距起降飞行器


    Beteiligte:
    ZHOU ZHOU (Autor:in) / WANG ZHENGPING (Autor:in) / WANG KELEI (Autor:in) / LI XU (Autor:in) / GUO JIAHAO (Autor:in)

    Erscheinungsdatum :

    2021-04-30


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge




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