The invention belongs to the technical field of helicopter rotors, and particularly relates to a helicopter four-blade rotor folding system and folding method. The propeller hub is divided into two parts, one part is fixedly connected with the rotor shaft, the other part can be driven by the actuator to rotate around the axis of the rotor shaft, each part of the propeller hub is connected with thetwo blades, the two parts can rotate relatively to enable the angle between variable pitch axes of the blades to be reduced to be within 45 degrees, and the rotor shaft can be positioned at a determined azimuth angle. An angular bisector with an angle smaller than 45 degrees is formed between the two blades to coincide with the course of the helicopter, the complexity of a four-blade rotor wing folding system is greatly reduced, rapid folding of the rotor wing can be achieved, and operation is easy and convenient.

    本发明属于直升机旋翼技术领域,具体涉及一种直升机四桨叶旋翼折叠系统及折叠方法。通过将桨毂分成两部分,其中一部分与旋翼轴固定连接,另一部分可以在作动器驱动下绕旋翼轴轴线旋转,桨毂的每部分连接两片桨叶,这两部分可以相对转动使桨叶变距轴线之间的角度减小至45度以内,旋翼轴可定位在确定的方位角上,使两片桨叶之间构成小于45度角的角平分线与直升机航向重合,将大幅降低四桨叶旋翼折叠系统的复杂度,并且能够实现旋翼快速折叠,操作简便。


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    Title :

    Helicopter four-blade rotor wing folding system and folding method


    Additional title:

    一种直升机四桨叶旋翼折叠系统及折叠方法


    Contributors:
    LI MANFU (author) / WANG JIAN (author) / LIN ZHAN (author)

    Publication date :

    2021-02-26


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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