The invention belongs to the technical field of rotor blade design, and relates to a single-pin blade root with fork lugs. Comprising a root bushing (1), a first joint filling block (2), a first root girder (3), a first girder plugging block (4), a second girder plugging block (5), a fork lug bushing (6), a second joint filling block (7) and a second root girder (8). According to the single-pin blade root structure with the fork lugs, the driving force of the actuator cylinder of the folding system is transmitted to the blades through the fork lug bushings (6), meanwhile, the blades rotate around the root bushings (1) by means of the dead weight of the blades, then rotor wing folding is achieved, and the basic function of transmitting the blade load to a propeller hub is achieved; the number of additional parts and the additional weight caused by automatic folding of the rotor wing are reduced, and a good effect can be achieved.

    本发明属于旋翼桨叶设计技术领域,涉及一种带有叉耳的单销桨叶根部。包括根部衬套(1)、第一接头填块(2)、第一根部大梁(3)、第一大梁堵块(4)、第二大梁堵块(5)、叉耳衬套(6)、第二接头填块(7)、第二根部大梁(8)。本发明的带叉耳的单销桨叶根部结构,通过将折叠系统的作动筒驱动力通过叉耳衬套(6)传递给桨叶,同时利用桨叶自重,实现桨叶绕根部衬套(1)转动,进而实现旋翼折叠,满足将桨叶载荷传递到桨毂的基础功能,降低了旋翼自动折叠带来的附加零部件数量和附加重量,可以获得良好的效果。


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    Title :

    Single-pin blade root structure with fork lugs and helicopter


    Additional title:

    一种带有叉耳的单销桨叶根部结构及直升机


    Contributors:
    LI YANXIU (author) / YU GUORUI (author) / TANG XINKAI (author) / XIONG SHAOHAI (author) / YUAN XIANG (author)

    Publication date :

    2024-02-23


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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