The invention belongs to the technical field of aviation unmanned aerial vehicle structures, and particularly relates to a flying wing unmanned aerial vehicle with a geometric torsion structure. According to the flying wing unmanned aerial vehicle with the geometric torsion structure, in order to improve the phenomenon that a moment characteristic curve tilts upwards due to the fact that a sweepback wing tip is separated too early as well as to improve lift distribution of wings in the unfolding direction, geometric torsion is adopted at the wing turning position and the wing tip position; through wind tunnel tests and simulation comparison of different torsion schemes, an optimal torsion form is obtained, the installation angle of the wing root is 0 degree, the torsion angle from the separation surface of the wing 2 and the fuselage 1 to the 60% half-span position is gradually twisted from 0 degree to -3 degrees, and the torsion angle from the 60% half-span position to the wing tip 3is gradually twisted from -3 degrees to -6 degrees. The geometric torsion distribution is adopted for the small-aspect-ratio and large-sweepback flying wing unmanned aerial vehicle, distribution of airflow in the aspect direction can be effectively controlled, airflow separation is restrained, resistance is reduced, the lift-drag ratio is increased, and the large controllable attack angle range can be kept.

    本申请属于航空无人机结构技术领域,特别涉及一种具有几何扭转结构的飞翼无人机。本申请的具有几何扭转结构的飞翼无人机,为了改善后掠翼翼尖过早出现分离而导致的力矩特性曲线出现上翘现象,同时也为了改善机翼沿展向的升力分布,在机翼转折处、翼尖处采用了几何扭转,通过不同扭转方案的风洞试验和仿真对比,获得了最优的扭转形式,翼根0°安装角,从机翼2与机身1的分离面至60%半展长位置的扭转角由0°逐渐扭转为‑3°,从60%半展长位置至翼尖3的扭转角由‑3°逐渐扭转为‑6°。本申请对于小展弦比大后掠飞翼无人机采用本申请的几何扭转分布可以有效控制气流沿展向的分布,抑制气流分离,降低阻力,提高升阻比,同时可保持较大的可控迎角范围。


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    Titel :

    Flying wing unmanned aerial vehicle with geometric torsion structure


    Weitere Titelangaben:

    一种具有几何扭转结构的飞翼无人机


    Beteiligte:
    WANG YONG'EN (Autor:in) / GUO WANGLIU (Autor:in) / LIU XIAODONG (Autor:in) / ZHANG PEILIANG (Autor:in) / HE GUANGHONG (Autor:in) / YI RAN (Autor:in) / CHEN ZHENLONG (Autor:in)

    Erscheinungsdatum :

    12.03.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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