The invention discloses a multi-control and multi-reference design method of a satellite attitude control system. The method comprises the following steps: step 1, attitude reference validity setting;2, selecting an attitude reference determination criterion; 3, determining an attitude reference and controlling attitude assignment; 4, a mode control algorithm is adopted, and selection and assignment of parameters are controlled; and step 5, control output calculation. According to the invention, the fault isolation capability of the attitude measurement single machine is stronger, the attitude reference switching autonomy is more convenient, and the control mode maintainability is better.

    本发明公开了一种卫星姿态控制系统的多控制多基准的设计方法,所述方法包括如下步骤:步骤一:姿态基准有效性设置;步骤二:姿态基准确定准则的选择;步骤三:姿态基准的确定和控制姿态赋值;步骤四:模式控制算法、控制参数的选择及赋值;步骤五:控制输出计算。本发明使姿态测量单机的故障隔离能力更强,姿态基准切换自主性更方便,控制模式维持性更好。


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    Titel :

    Multi-control and multi-reference design method of satellite attitude control system


    Weitere Titelangaben:

    一种卫星姿态控制系统的多控制多基准的设计方法


    Beteiligte:
    XIANG KUN (Autor:in) / WANG JINGJI (Autor:in) / CHEN YINHE (Autor:in) / XIU YANHONG (Autor:in) / MENG QICHEN (Autor:in)

    Erscheinungsdatum :

    26.06.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS / G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung



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