The invention relates to a trailing edge variable camber mechanism based on knuckle type connecting rod driving. A compliant mechanism is designed around a skin based on a rigid-flexible coupling design thought, the skin cannot be bent when a rigid mechanism is greatly deformed, and a large-deformation wing can greatly improve the lift-drag ratio of an aircraft, save fuel consumption and improve the cruising ability. A flexible mechanism design method is adopted, a plurality of feature points on the wing skin are taken as optimization targets, and the displacement of the target points is met at the same time, so that the trailing edge deformation of the wing is smooth and continuous. A flexible mechanism is driven by the rigid mechanism, namely, the design idea of rigid-flexible coupling is adopted, the bearing capacity can be met while large deformation is achieved, and stable and reliable flight of the aircraft is guaranteed.

    本发明涉及一种基于“指节式”连杆驱动的后缘变弯度机构,基于刚柔耦合设计思想,蒙皮周围设计柔顺机构,在刚性机构发生大变形时,蒙皮不会产生屈曲,大变形机翼将会大幅度提高飞行器的升阻比,节省燃油消耗,增加续航能力。采用柔性机构设计方法,以机翼蒙皮上多个特征点为优化目标,同时满足这些目标点的位移,从而使得机翼的后缘变形光滑连续。通过刚性机构驱动柔性机构,即刚柔耦合的设计思想,可以在实现大变形的同时,满足承载能力,保证飞机的稳定可靠飞行。


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    Titel :

    Trailing edge variable camber mechanism based on knuckle type connecting rod driving


    Weitere Titelangaben:

    基于指节式连杆驱动的后缘变弯度机构


    Beteiligte:
    GE WENJIE (Autor:in) / WANG JUNNAN (Autor:in) / ZHANG YONGHONG (Autor:in) / ZHU XUYAO (Autor:in) / ZHANG XU (Autor:in)

    Erscheinungsdatum :

    2020-12-29


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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