The invention relates to an electric propulsion device thrust inversion method based on a single-frame control moment gyroscope, and relates to the technical field of spacecraft electric propulsion, the single-frame control moment gyroscope is adopted to control the attitude of a satellite, and an electric propulsion device is installed on a satellite body in an offset mode. A satellite attitude dynamic model adopting a single-frame control moment gyroscope as an attitude control system execution mechanism is established, and an analytical expression of the electric thrust moment of the electric propulsion device is obtained according to the difference of satellite attitude dynamic equations of the electric propulsion device in in-orbit ignition and T seconds before ignition. On the basis, telemetry data before ignition and within T seconds during ignition are fitted through a least square method, the electric thrust moment is solved, and the thrust of the electric propulsion device is obtained through data processing and error analysis. According to the method, the thrust value of the electric propulsion device can be accurately measured and calculated under the condition that the satellite attitude and orbit are kept stable, and the method has the advantages that the measuring and calculating method is simple, the measuring and calculating time is short, the measuring and calculating precision is high, and engineering is easy to achieve.

    本发明涉及一种基于单框架控制力矩陀螺的电推进装置推力反演方法,涉及航天器电推进技术领域,本发明采用单框架控制力矩陀螺控制卫星姿态,在卫星本体偏置安装电推进装置。建立采用单框架控制力矩陀螺作为姿态控制系统执行机构的卫星姿态动力学模型,根据电推进装置在轨点火中和点火前T秒内的卫星姿态动力学方程作差,得到电推进装置电推力矩的解析表达式。在此基础上,利用最小二乘法拟合点火前和点火中T秒内的遥测数据,求解电推力矩,通过数据处理和误差分析得到电推进装置的推力。本发明可在卫星姿态和轨道均保持稳定的情况下,精确测算电推进装置的推力数值,具有测算方法简单、测算时间短、测算精度高且工程易于实现的优点。


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    Titel :

    Thrust inversion method of electric propulsion device based on single-frame control moment gyroscope


    Weitere Titelangaben:

    一种基于单框架控制力矩陀螺的电推进装置推力反演方法


    Beteiligte:
    SUN LIANG (Autor:in) / NIU XIAOJIE (Autor:in) / HUANG HAI (Autor:in) / ZHAO GUOWEI (Autor:in) / ZHAO ZELIN (Autor:in) / ZHAO XURUI (Autor:in) / KANG LIN (Autor:in) / LIU YU (Autor:in)

    Erscheinungsdatum :

    2024-03-22


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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