The invention provides an on-orbit unfolding mechanism suitable for an Einstein probe satellite. The on-orbit unfolding mechanism comprises a sunshade turnover mechanism and a shading cylinder. The top of the shading cylinder is provided with a shading turnover mechanism which is used for protecting the focus lens in the ground period and unfolding the focus lens at 240 degrees in orbit; a star sensor bracket is arranged on the side surface of the shading cylinder and is used for mounting a star sensor and realizing source positioning in orbit; the sunshade turnover mechanism comprises an unfolding locking mechanism, a locking releasing device and a protective cover; the sunshade turnover mechanism and the shading cylinder are connected into a whole through the unfolding locking mechanism, the sunshade turnover mechanism rotates around the center shaft after being unlocked, the protection cover is pressed by the locking releasing device, and closing of the sunshade turnover mechanism is kept. The protective cover is a main body structure of the sunshade turnover mechanism and is connected with the unfolding locking mechanism and the locking releasing device; the shading cylinder comprises an upper cylinder body of the shading cylinder, a star sensor bracket and a lower cylinder body of the shading cylinder; and the respective turnups of the shading cylinder upper cylinder body and the shading cylinder lower cylinder body are connected with the heat insulation film flange. According to the invention, on-orbit unfolding can be better realized.

    本发明提供一种适用于爱因斯坦探针卫星的在轨展开机构,包括遮阳翻转机构和遮光筒;所述遮光筒的顶部安装遮阳翻转机构,用于在地面时期保护聚焦镜,在轨240°展开;遮光筒的侧面设有星敏支架,用于安装星敏感器,在轨实现源定位;所述遮阳翻转机构包括展开锁定机构、锁紧释放装置、保护盖;展开锁定机构将遮阳翻转机构和遮光筒连接为一个整体,并在解锁后绕着中心轴旋转,锁紧释放装置压紧保护盖,保持遮阳翻转机构的闭合;保护盖为遮阳翻转机构的主体结构,连接展开锁定机构、锁紧释放装置;所述遮光筒包括遮光筒上筒体、星敏支架及遮光筒下筒体;遮光筒上筒体、遮光筒下筒体的各自翻边与隔热膜法兰相连。本发明能够更好地实现在轨展开。


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    Titel :

    On-orbit unfolding mechanism suitable for Einstein probe satellite


    Weitere Titelangaben:

    一种适用于爱因斯坦探针卫星的在轨展开机构


    Beteiligte:
    WANG JUAN (Autor:in) / WANG MING (Autor:in) / LI LIN (Autor:in) / CHEN YONG (Autor:in) / CUI WEIWEI (Autor:in) / XIAO GANG (Autor:in)

    Erscheinungsdatum :

    23.08.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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