The invention discloses a synchronous orbit satellite deorbiting method and device. The method comprises the steps: determining a deorbiting control strategy of a synchronous orbit satellite accordingto characteristic parameters of a synchronous orbit satellite, wherein the characteristic parameters are used for representing the characteristics of the synchronous orbit satellite; determining a first mass of a residual propellant of the synchronous orbit satellite, and selecting a fuel emptying strategy corresponding to the propellant from preset fuel emptying strategies according to a first mass; and making the synchronous orbit satellite execute an deorbiting operation according to the fuel emptying strategy and the deorbiting parameter. A technical problem that in the prior art, a technology of executing the deorbiting operation on an overdue service satellite is still a blank technology is solved.

    本申请公开了一种同步轨道卫星离轨的方法及装置,该方法包括:根据同步轨道卫星的特性参数确定所述同步轨道卫星的离轨控制策略,其中,所述特性参数用于表征所述同步轨道卫星特性的参数;确定所述同步轨道卫星的剩余推进剂的第一质量,并根据所述第一质量从预设的燃料排空策略中选择出所述推进剂所对应的燃料排空策略;根据所述燃料排空策略以及所述离轨参数控制所述同步轨道卫星执行离轨操作。本申请解决了现有技术中对于超期服役的卫星执行离轨操作还处于空白的技术问题。


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    Titel :

    Synchronous orbit satellite deorbiting method and device


    Weitere Titelangaben:

    一种同步轨道卫星离轨的方法及装置


    Beteiligte:
    ZHAO YUE (Autor:in) / YANG XUEMENG (Autor:in) / LI JUAN (Autor:in) / GE QICHAO (Autor:in)

    Erscheinungsdatum :

    2020-09-04


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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