The invention discloses a locking and releasing mechanism of an inverted Mars helicopter. The coaxial helicopter (4) is embedded in the lander (5), an installation platform (1) is arranged on a landing platform (5-1) of the lander (5), a helicopter body locking assembly (2) is arranged in the center of the installation platform (1), and a memory alloy locking device (3) and a helicopter body locking assembly (2) are sequentially arranged in the helicopter body locking assembly (2) from top to bottom. The invention is used for solving the problem that the helicopter is difficult to bear large vibration and high load in the process of transporting the coaxial helicopter to the surface of Mars in the existing Mars flight detection task.

    本发明公开了一种倒立布置的火星直升机锁紧释放机构。所述着陆器(5)内嵌套共轴直升机(4),所述着陆器(5)的着陆平台(5‑1)上设置安装平台(1),所述安装平台(1)的中心设置机体锁紧组件(2),所述机体锁紧组件(2)内从上到下依次设置记忆合金锁紧装置(3)与机体锁紧组件(2)。本发明用以解决现有火星飞行探测任务将共轴式直升机运输至火星地表的过程中直升机难以承受大振动与高负载的问题。


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    Titel :

    Locking and releasing mechanism of inverted Mars helicopter


    Weitere Titelangaben:

    一种倒立布置的火星直升机锁紧释放机构


    Beteiligte:
    TANG DEWEI (Autor:in) / WU QI (Autor:in) / QUAN QIQUAN (Autor:in) / CAI HAO (Autor:in) / ZHU KAIJIE (Autor:in) / DONG YACHAO (Autor:in) / DENG ZONGQUAN (Autor:in)

    Erscheinungsdatum :

    2023-08-04


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64U



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