The invention belongs to the technology of passive vibration reduction of helicopters, and relates to a dynamic vibration absorber structure for helicopter vibration reduction. The structure comprisesa constraint structure, a supporting structure, a first balance weight structure and a second balance weight structure, the constraint structure fixes the supporting structure below a cockpit floor,the supporting structure is symmetrical relative to the constraint structure, and the first balance weight structure and the second balance weight structure are the same in mass and are symmetricallyarranged at the two ends of the supporting structure in a suspended state. The frequency of the dynamic vibration absorber can be changed by adjusting the balance weight mass of the dynamic vibrationabsorber, the purpose of vibration absorption is finally achieved, the structure is simple, installation and adjustment are easy, and the vibration reduction effect is good.

    本发明属于直升机被动减振技术,涉及一种用于直升机减振的动力吸振器结构。包括:约束结构、支撑结构、第一配重结构、第二配重结构,其中,约束结构将支撑结构固定在座舱地板下方,支撑结构相对于约束结构对称,第一配重结构和第二配重结构质量相同并且对称设置在支撑结构两端呈悬空状态。能够通过调整动力吸振器配重质量,改变动力吸振器频率,最终达到吸振的目的,结构简单、易安装调整,减振效果良好。


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    Titel :

    Dynamic vibration absorber structure for helicopter vibration reduction


    Weitere Titelangaben:

    一种用于直升机减振的动力吸振器结构


    Beteiligte:
    ZHAO ZEQIAN (Autor:in) / SUN XIUWEN (Autor:in) / WANG JINLIANG (Autor:in) / XIA SHUANGMAN (Autor:in) / XIA FALING (Autor:in) / YU RENYE (Autor:in) / HU WENGANG (Autor:in) / YIN ZHONGWEI (Autor:in)

    Erscheinungsdatum :

    2021-02-23


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F16F SPRINGS , Federn



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