The invention relates to the technical field of helicopter rotor composite material structure design, in particular to a blade root low-shimmy stiffness configuration. Comprising a filling block assembly, a lining, a girder belt, supporting foam and skin. Due to the adoption of the structure, the shimmy rigidity of the roots of the blades can be effectively reduced on the premise that the flapping rigidity and the torsional rigidity of the roots of the blades are slightly changed, so that the load of the propeller hub is reduced, and the strength of the blades and the strength of the propeller hub of the helicopter are not changed. The propeller blade adopting the structure can adopt mature materials and forming processes of current helicopter propeller blades, and special key technologies do not exist, so that the scheme is high in realizability, and the propeller blade adopting the structure is high in operability and extremely low in propeller blade replacement cost especially based on the condition that a propeller blade design scheme needs to be replaced on the basis of an existing rotor wing product.

    本发明涉及直升机旋翼复合材料结构设计技术领域,涉及一种桨叶根部低摆振刚度构型。包括填块组件、衬套、大梁带、支撑泡沫、蒙皮;采用这种构型,可在仅小幅改变桨叶根部挥舞刚度和扭转刚度的前提下,有效降低了桨叶根部的摆振刚度,从而降低了桨毂的载荷,保证直升机桨叶和桨毂强度不发生变化。采用该构型的桨叶,可采用当前直升机桨叶成熟的材料和成型工艺,不存在特殊关键技术,因此方案可实现性强,尤其基于现有旋翼产品,需要更换桨叶设计方案的情况,本构型的可操作性强,桨叶更换成本极低。


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    Title :

    Blade root low shimmy stiffness configuration


    Additional title:

    一种桨叶根部低摆振刚度构型


    Contributors:
    CHEN ZHONGMING (author) / ZHAO XIN (author) / JIANG JIAJI (author) / TANG XINKAI (author)

    Publication date :

    2024-10-15


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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