The invention belongs to the technical field of helicopter rotor tests, and particularly relates to a rotor test bench in-shaft variable-pitch pull rod relay control mechanism which is characterized by comprising an upper variable-pitch driving unit, an in-shaft variable-pitch pull rod assembly and a lower variable-pitch driving unit. The lower variable-pitch driving unit and the upper variable-pitch driving unit are distributed in a quasi-symmetric mode along the center of the in-shaft variable-pitch pull rod assembly, the lower driving unit serves as a power source, and the power source is transmitted to the upper variable-pitch driving unit through the in-shaft variable-pitch pull rod assembly to drive the torsion angle of a rotor hub to change, so that the change of the total pitch and the periodic variable pitch of an upper rotor system is achieved.

    本发明属于直升机旋翼试验技术领域,具体涉及一种旋翼试验台轴内变距拉杆中继操纵机构,其特征在于,所述操纵机构由上变距驱动单元、轴内变距拉杆组件、下变距驱动单元;所述下变距驱动单元与上变距驱动单元沿轴内变距拉杆组件中心呈准对称分布,所述下驱动单元作为动力源,经轴内变距拉杆组件传递至上变距驱动单元带动旋翼桨毂扭转角变化,从而实现对上旋翼系统总距和周期变距的变化。


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    Title :

    In-shaft variable-pitch pull rod relay control mechanism of rotor wing test bed


    Additional title:

    一种旋翼试验台轴内变距拉杆中继操纵机构


    Contributors:
    LI KAICHENG (author) / ZHOU WEIWEI (author) / TANG YONG (author) / LI DAHAI (author) / CHEN CHUN (author)

    Publication date :

    2023-03-07


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen



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