The invention relates to a satellite configuration suitable for high-precision space magnetic field detection, and belongs to the field of satellite configuration design. The platform cabin is horizontally arranged; the conical section is arranged at the top of the platform cabin; the satellite-rocket interface is arranged at the bottom of the platform cabin; the body-mounted solar cell array is arranged on the side walls of the platform cabin and the conical section; the root of the extension rod mechanism is mounted at the top of the conical section; electronic equipment such as satellite service and energy required by a satellite is mounted in an inner cavity of the platform cabin; the satellite-rocket interface is in butt joint with an internal bracket of an external rocket, so that a satellite is in a vertical launching state in an inner cavity of the external rocket; the conical section is of a pyramid structure; the axial direction of the extension rod mechanism is parallel to the side wall of the conical section, and the extension rod mechanism is attached to the side wall of the conical section; the conical section provides a pressing surface for the extension rod mechanism; after a satellite enters an orbit, energy is provided through a body-mounted solar cell array; the influence of various on-orbit interference factors such as residual magnetism, flexible vibration, on-orbit thermal alternation and rarefied atmospheric resistance can be comprehensively considered and reduced, and the requirement for high-precision magnetic field detection is met.

    本发明涉及一种适用于高精度空间磁场探测的卫星构型,属于卫星构型设计领域;平台舱水平放置;锥段设置在平台舱的顶部;星箭接口设置在平台舱的底部;体装式太阳电池阵设置在平台舱和锥段的侧壁上;伸杆机构的根部安装在锥段的顶部;所述平台舱内腔安装卫星所需星务、能源等电子设备;星箭接口实现与外部火箭的内部支架对接,实现卫星在外部火箭内腔中呈竖直发射状态;锥段为棱锥结构;伸杆机构的轴向与锥段的侧壁平行,贴放在锥段的侧壁上;锥段为伸杆机构提供压紧面;卫星入轨后,通过体装式太阳电池阵提供能源;本发明能够综合考虑并降低自身剩磁、柔性振动、在轨热交变、稀薄大气阻力等各种在轨干扰因素的影响,满足高精度磁场探测的需求。


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    Titel :

    Satellite configuration suitable for high-precision space magnetic field detection


    Weitere Titelangaben:

    一种适用于高精度空间磁场探测的卫星构型


    Beteiligte:
    HAN JIANBIN (Autor:in) / LIU JIANG (Autor:in) / YUAN SHIGENG (Autor:in) / XU SEN (Autor:in) / TAN JIYU (Autor:in)

    Erscheinungsdatum :

    2024-02-27


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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