The invention relates to the field of satellite vibration isolation configuration design, and provides a two-stage active vibration isolation satellite platform configuration which comprises a satellite platform, a rear-end magnetic levitation actuator, a load rear end, a middle cabin section, a front-end magnetic levitation actuator and a load front end, and the load front end is connected with the middle cabin section of a satellite through the front-end magnetic levitation actuator. The rear end of the load is connected with the satellite platform through the rear-end magnetic levitation actuators. The number of the rear-end magnetic levitation actuators is eight, and the number of the front-end magnetic levitation actuators is eight. The load rear end and the load front end achieve vibration isolation of the satellite platform through the rear end magnetic levitation actuator and the front end magnetic levitation actuator respectively, and alignment of the load rear end and the load front end is achieved by adjusting the pointing direction and the position of the load rear end. A quiet working environment can be provided for the front end and the rear end of the split type load at the same time, and decoupling control over the two parts of loads is achieved; the device is simple in structure, can be used in high and low orbit satellites, and is wide in application range.

    本发明提供了一种涉及卫星隔振构型设计领域的两级主动隔振卫星平台构型,包括卫星平台、后端磁浮作动器、载荷后端、中间舱段、前端磁浮作动器以及载荷前端,载荷前端通过前端磁浮作动器与卫星的中间舱段连接,载荷后端通过后端磁浮作动器与卫星平台连接,后端磁浮作动器和前端磁浮作动器的数量分别为八台;载荷后端和载荷前端分别通过后端磁浮作动器和前端磁浮作动器实现对卫星平台的振动隔离,并通过调整载荷后端指向和位置实现载荷后端和载荷前端的对准。本发明能够为分体式载荷前端和后端同时提供安静的工作环境,实现两部分载荷的解耦控制;构型简单,可在高低轨道卫星中使用,适用范围广。


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    Titel :

    Two-stage non-contact magnetic levitation active vibration isolation pointing satellite platform configuration


    Weitere Titelangaben:

    两级非接触磁浮主动隔振指向卫星平台构型


    Beteiligte:
    ZHOU LIPING (Autor:in) / ZHANG DANDAN (Autor:in) / XU YING (Autor:in) / XIANG XIUJUAN (Autor:in) / ZHANG RUBIAN (Autor:in) / XUE JIUMING (Autor:in) / ZHOU XUBIN (Autor:in) / SHEN YILI (Autor:in) / ZHANG JIAN (Autor:in)

    Erscheinungsdatum :

    2024-04-12


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS




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