The invention provides a vibration isolation device of a satellite control moment gyro, which is used for vibration isolation of the control moment gyro and comprises vibration isolator assemblies and a cellular plate, wherein the vibration isolator assemblies are disposed on the cellular plate; the vibration isolator assembly comprises a sealing cover, a connecting rod, a vibration isolator, a damping layer, a switch-over part and a base, the connecting rod, the vibration isolator, the damping layer, the switch-over part and the base are connected in sequence; the sealing cover is disposed on the outer side of the connecting rod, the vibration isolator and the damping layer; the base is connected to the cellular plate; and the connecting rod is used to connect the control moment gyro. Quantity of the vibration isolator assemblies is four; the four vibration isolator assemblies are distributed in a rectangular manner; and the two adjacent vibration isolator assemblies are distributed symmetrically. The vibration isolation device of the satellite control moment gyro provided by the invention is rational in structural design, can significantly reduce interference of micro-vibration responses caused by the control moment gyro during in-track running to a sensitive load, and ensures stability, reliability and safety of the high-precision sensitive load on a satellite during the in-track running.


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    Titel :

    Vibration isolation device of satellite control moment gyro


    Beteiligte:
    YU ZIFEI (Autor:in) / ZHOU XUBIN (Autor:in) / SHEN JUNFENG (Autor:in) / MAN XIAOYING (Autor:in) / HUANG JUNJIE (Autor:in) / SHI XINYU (Autor:in)

    Erscheinungsdatum :

    2015-11-11


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS / F16F SPRINGS , Federn



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