The invention provides a distributed power-induced lift-increasing double-wing vertical take-off and landing aircraft, and relates to the technical field of vertical take-off and landing of aviation aircrafts, the distributed power-induced lift-increasing double-wing vertical take-off and landing aircraft comprises a fuselage, fixed main wings and tilting induction wings are arranged on the two sides of the fuselage, and the induction wings are located above the rear portions of the main wings and are arranged in series with the main wings front and back; the distributed electric drive propellers are arranged at the front edges of the induction wings, and the distributed electric drive propellers and the induction wings synchronously tilt; the vertical empennage is arranged on the upper side of the rear end of the fuselage, tilting horizontal empennages are arranged on the two sides of the vertical empennage, and a torque balancing propeller is arranged on the front edge of each horizontal empennage; the problem that thrust needed in different flight stages is difficult to match due to the fact that the thrust-weight ratio of an existing fixed-wing vertical take-off and landing aircraft in the vertical take-off and landing stage is too large is solved through the induced lift increasing effect of the distributed propellers, and vertical take-off and landing and hovering with the thrust-weight ratio smaller than 1 are achieved.

    本发明提供一种分布式动力诱导増升双机翼垂直起降飞行器,涉及航空飞行器垂直起降技术领域,包括:机身,机身的两侧设置有固定式的主机翼和可倾转式的诱导机翼,诱导机翼处于主机翼的后上方,与主机翼前后串列布置;分布式电驱动螺旋桨,分布式电驱动螺旋桨设置在所述诱导机翼的前缘,与所述诱导机翼同步倾转;垂直尾翼,垂直尾翼设置在机身的后端上侧,垂直尾翼的两侧设置有可倾转式的水平尾翼,水平尾翼的前缘设置有力矩配平螺旋桨;本发明利用分布式螺旋桨的诱导増升作用解决现有固定翼垂直起降飞机因垂直起降阶段推重比过大导致不同飞行阶段需用推力难以匹配的问题,实现推重比小于1的垂直起降和悬停。


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    Titel :

    Distributed power-induced lift-increasing double-wing vertical take-off and landing aircraft


    Weitere Titelangaben:

    一种分布式动力诱导増升双机翼垂直起降飞行器


    Beteiligte:
    WANG HONGBO (Autor:in) / CHE DONGXIA (Autor:in) / YI ZHISHENG (Autor:in) / CHE CHI (Autor:in) / MIAO SHUAI (Autor:in)

    Erscheinungsdatum :

    18.02.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64U / B64C AEROPLANES , Flugzeuge



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