The invention relates to a spacecraft high-integration-level single-phase fluid loop driving device and a thermal control driving device. The outer side wall of an integrated box body of the spacecraft high-integration-level single-phase fluid loop driving device is provided with a plurality of quick-break interfaces; the inlet end of the fluid driving part is connected with one end of a driving inlet pipeline, and the other end of the driving inlet pipeline is connected with a heat exchanger cold side quick-break connector. The outlet end of the fluid driving part is connected with one end of the driving outlet pipeline, and the other end of the driving outlet pipeline is connected with the first load quick-break connector. The driving outlet pipeline is further connected with a heat dissipation branch in parallel. A gas-liquid separator, a filter and an energy accumulator are sequentially connected to the driving inlet pipeline in the fluid flowing direction, one end of the bypass is connected to the driving inlet pipeline on the upstream of the gas-liquid separator, and the other end of the bypass is connected to the driving outlet pipeline on the upstream of the heat dissipation branch; the two branches of the heat dissipation branch loop are connected with the load quick-break connector respectively, and a confluence pipeline of the two branches of the heat dissipation branch loop is connected with the heat exchanger hot side quick-break connector.

    本发明涉及航天器高集成度单相流体回路驱动装置及热控驱动装置,航天器高集成度单相流体回路驱动装置的集成箱体的外侧壁上设有多个快断接口;流体驱动部的入口端连接驱动入口管路的一端,驱动入口管路的另一端连接换热器冷侧快断接口;流体驱动部的出口端连接驱动出口管路的一端,驱动出口管路的另一端连接第一载荷快断接口;驱动出口管路上还并联有散热支路;驱动入口管路上沿流体流动方向依次连接有气液分离器、过滤器和储能器,旁路的一端接入气液分离器上游的驱动入口管路上,旁路的另一端接入散热支路上游的驱动出口管路上;散热支路回路的两个支路分别连接载荷快断接口,散热支路回路的两个支路的汇流管路连接换热器热侧快断接口。


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    Titel :

    Spacecraft high-integration-level single-phase fluid loop driving device and thermal control driving device


    Weitere Titelangaben:

    航天器高集成度单相流体回路驱动装置及热控驱动装置


    Beteiligte:
    YANG LEI (Autor:in) / GUO DONG (Autor:in) / WANG KE (Autor:in) / FAN LIANWEN (Autor:in) / QIAO ZHIHONG (Autor:in) / LI ZETAO (Autor:in) / LIU RONGHUI (Autor:in) / SHENG QIANG (Autor:in)

    Erscheinungsdatum :

    2024-01-05


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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