The plasma contact potential of a visiting vehicle (VV), such as the Orion Service Module (SM), is determined while docking at the Orion Crew Exploration Vehicle (CEV). Due to spacecraft charging effects on-orbit, the potential difference between the CEV and the VV can be large at docking, and an electrostatic discharge (ESD) could occur at capture, which could degrade, disrupt, damage, or destroy sensitive electronic equipment on the CEV and/or VV. Analytical and numerical models of the CEV are simulated to predict the worst-case potential difference between the CEV and the VV when the CEV is unbiased (solar panels unlit: eclipsed in the dark and inactive) or biased (solar panels sunlit: in the light and active).


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    EMI from Spacecraft Docking Systems Spacecraft Charging - Plasma Contact Potentials


    Beteiligte:
    J. D. Norgard (Autor:in) / R. Scully (Autor:in) / R. Musselman (Autor:in)

    Erscheinungsdatum :

    2012


    Format / Umfang :

    5 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    EMI from Spacecraft Docking Systems Spacecraft Charging - Plasma Contact Potentials

    Norgard, John D. / Scully, Robert / Musselman, Randall | NTRS | 2012


    Spacecraft docking device and spacecraft ground docking method

    LIANG BIN / WANG XUEQIAN / XU WENFU et al. | Europäisches Patentamt | 2024

    Freier Zugriff

    Spacecraft interface, spacecraft and spacecraft docking method

    ZHAO YUNPENG / LIN SHUO / LI ZHIQIANG | Europäisches Patentamt | 2023

    Freier Zugriff

    SPACECRAFT DOCKING SYSTEM

    GHOFRANIAN SIAMAK / CHUANG LI-PING CHRISTOPHER / MOTAGHEDI PEJMUN | Europäisches Patentamt | 2023

    Freier Zugriff

    Spacecraft docking connector

    JAEGER TALBOT | Europäisches Patentamt | 2016

    Freier Zugriff