A control moment gyro according to an embodiment of the present invention includes a damper assembly for damping vibration and buffering an external shock. The damper assembly includes: a damper arm formed long in a first axial direction and having one end coupled to a gimbal housing; a damper housing surrounding the damper arm in a second axial direction crossing the first axis and a third axial direction crossing both the first axis and the second axis; and an anti-vibration body coupled to the damper housing and supporting the other end of the damper arm in the first axial direction. Therefore, an embodiment of the present invention can provide the control moment gyro that is protected from vibrations and shocks generated in a process of launching a satellite and can reduce minute vibrations generated when operating in space.

    본 발명의 실시예에 따른 제어 모멘트 자이로는 진동을 감쇄하고 외부에서 가해지는 충격을 완충시키는 댐퍼 조립체를 포함하며, 상기 댐퍼 조립체는 제1 축 방향으로 길게 형성되며 일단이 상기 짐벌 하우징과 결합되는 댐퍼암과, 상기 제1 축과 교차하는 제2 축 방향과 상기 제1 축 및 상기 제2 축과 모두 교차하는 제3 축 방향에서 상기 댐퍼암을 둘러싸는 댐퍼 하우징, 그리고 상기 댐퍼 하우징에 결합되어 상기 댐퍼암의 상기 제1 축 방향 타단을 지지하는 방진체를 포함한다.


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    Title :

    CONTROL MOMENT GYRO


    Additional title:

    제어 모멘트 자이로


    Contributors:
    BAN SANGKWUN (author) / CHOI CHINTAE (author) / SONG JUNGMIN (author) / CHOI YOHAN (author) / KIM DAEJUN (author) / KIM HEECHEL (author) / JANG SOONSIK (author)

    Publication date :

    2023-03-07


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Korean


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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