The invention relates to a spacecraft docking potential control test method. The method comprises the steps: a, a potential control test system is built; b, on-orbit charging of the spacecraft is simulated; c, on-orbit docking of the spacecraft is simulated; and d, discharge current characteristics is tested. According to the spacecraft docking potential control test method, test verification is carried out on potential control on the ground during spacecraft on-orbit docking, related research results of the spacecraft docking potential control test method can be applied to test verification of spacecraft docking potential control in the future after engineering transformation, and the spacecraft docking potential control performance is ensured to meet the requirement.

    本发明涉及一种航天器对接电位控制试验方法,包括步骤:a.搭建电位控制试验系统;b.模拟航天器在轨充电;c.模拟航天器在轨对接;d.测试放电电流特性。根据本发明的航天器对接电位控制试验方法,对航天器在轨对接时电位控制在地面进行了试验验证,其相关研究成果经工程转化后,可应用于未来航天器对接电位控制的试验验证,保证航天器对接电位控制性能满足要求。


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    Titel :

    Spacecraft docking potential control test method


    Weitere Titelangaben:

    航天器对接电位控制试验方法


    Beteiligte:
    LIANG XIAOFENG (Autor:in) / WANG HONGJIA (Autor:in) / WANG LINTAO (Autor:in) / WANG ZHIYING (Autor:in)

    Erscheinungsdatum :

    2020-04-24


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    G01R Messen elektrischer Größen , MEASURING ELECTRIC VARIABLES / B64G Raumfahrt , COSMONAUTICS



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