The invention discloses a separating device with a buffering structure. The separating device comprises a main body component, a separating component, pull rods and a pull rod cutting mechanism, wherein the pull rods are connected with the main body component and the separating component and press the main body component on the supporting surface of the separating component. A satellite is provided with a flange, and the ends, connected with the main body component, of the pull rods penetrate from one side of the flange and are locked through fasteners on the other side of the flange. The separating device is characterized in that buffering parts are installed on the side, with the fasteners fixed, of the flange, directly face the ends of the pull rods and are used for preventing half broken pull rods from exiting from the flange. The invention further discloses a satellite and rocket separating device with the buffering structure. According to the invention, the buffering parts are arranged at the ends of the pull rods for absorbing impact generated when the pull rods are broken, a separating buffering device is fixed through a pure mechanical structure, the shock absorbing and buffering effect is remarkable, the structure is simple, installation is convenient, the work is stable, and the development cost is low.


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    Titel :

    Separating device and satellite and rocket separating device with buffering structure


    Beteiligte:
    TENG LAI (Autor:in) / JIN ZHONGHE (Autor:in)

    Erscheinungsdatum :

    2016-02-03


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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