The invention discloses a space radiation radiator. The space radiation radiator comprises a main pipeline; the heat dissipation assembly is provided with a hollow cavity, the cavity is communicated with the main pipeline, a heat-carrying working medium is arranged in the cavity and used for absorbing heat of the spacecraft, and at least one side wall of the heat dissipation assembly is an infrared glass plate so that the heat of the heat-carrying working medium can penetrate through the infrared glass plate to be radiated outwards. The heat dissipation assembly comprises two infrared glass plates arranged in parallel and two branch pipelines arranged in parallel. And the branch pipelines are located at the two ends of the cavity correspondingly, both the branch pipelines are connected with the main pipeline, and the branch pipelines communicate with the cavity so that the heat-carrying working medium can enter the cavity through the branch pipelines. By the adoption of the method, the heat dissipation efficiency of the spacecraft can be effectively improved, compared with a traditional mode, the system structure is simplified, and then the machining difficulty and the production cost are reduced.

    本申请公开了一种空间辐射散热器,包括:主管道;散热组件,具有中空的腔体,所述腔体与所述主管道连通,所述腔体内设置有载热工质,所述载热工质用于吸收航天器的热量,所述散热组件的至少一个侧壁为红外玻璃板,以使所述载热工质的热量透过所述红外玻璃板向外辐射。所述散热组件包括两个平行设置的红外玻璃板以及两个并行设置的支管道;所述支管道位于分别所述腔体的两端,所述支管道均与所述主管道相连,且所述支管道与所述腔体连通,以使所述载热工质通过所述支管道进入所述腔体内。通过采用本申请,能够有效提高航天器的散热效率,而且相对于传统方式,系统结构得到简化,进而降低了加工难度和生产成本。


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    Titel :

    Space radiation radiator and spacecraft


    Weitere Titelangaben:

    一种空间辐射散热器及航天器


    Beteiligte:
    ZHAO XINGBIN (Autor:in) / ZHUANG NAILIANG (Autor:in) / TANG XIAOBIN (Autor:in) / YANG CHENHAO (Autor:in)

    Erscheinungsdatum :

    2022-12-09


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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