The invention provides a buffer mechanism and an aircraft landing gear. The buffer mechanism comprises a piston cylinder, a piston column and an elastic body. One end of the piston column is arranged in the piston cylinder in a sliding mode. The elastic body is arranged between the piston column and the piston cylinder in the sliding direction of the piston column. And the elastomer is made of a nonlinear elastic material. The buffering mechanism can be installed on an undercarriage of an airplane, and when the airplane wheel is impacted, the piston column moves towards the interior of the piston cylinder, and then the elastic body is extruded. The elastic body is made of a nonlinear elastic material, more than 70% of impact kinetic energy borne by the piston column can be absorbed by the elastic body, and after a part of the remaining released energy is dissipated in a heat energy form, the remaining energy is not enough to enable the aircraft to bounce.

    本发明提供一种缓冲机构和飞机起落架,包括活塞缸、活塞柱和弹性体。活塞柱的一端可滑动的设置在活塞缸内。弹性体沿活塞柱的滑动方向设置在活塞柱与活塞缸之间。弹性体为非线性弹性材料。该缓冲机构可被安装在飞机的起落架上,当机轮受到冲击时,活塞柱向活塞缸内部运动,进而挤压弹性体。本申请的弹性体的材料为非线性弹性材料,活塞柱受到的冲击动能会被弹性体吸收70%以上,剩余被释放的能量中一部分以热能的形式耗散后,剩余能量不足以使飞机弹跳。


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    Titel :

    Buffer mechanism and aircraft landing gear


    Weitere Titelangaben:

    缓冲机构和飞机起落架


    Beteiligte:
    ZOU XIANGFU (Autor:in) / LI FUYOU (Autor:in)

    Erscheinungsdatum :

    2024-02-06


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    F16F SPRINGS , Federn / B64C AEROPLANES , Flugzeuge



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