The invention discloses a spacecraft vacuum thermal environment simulation structure and a temperature control method. The simulation structure comprises a vacuum container, and a supporting frame is arranged at the bottom in the vacuum container; the simulation structure further comprises a beam type frame fixed in the middle of the supporting frame, satellite installation frames symmetrically fixed to the beam type frame, satellites installed on the satellite installation frames, inter-satellite main cooling plates vertically fixed to the beam type frame and located between the adjacent satellite installation frames, and lower cooling plates arranged at the bottoms of the satellites respectively; the upper surface and the lower surface of each satellite are provided with a lamp array and a temperature sensor for measuring temperature; and the lamp array is used for heating and providing a thermal environment. The multiple satellites are symmetrically arranged on the beam type frame in the vacuum container, the cooling plates are arranged below the satellites and between the two adjacent satellites, and temperature simulation errors caused by too large background heat flow of a satellite thermal test are avoided; and background heat flow consistency of two satellites and heat flow non-interference between the satellites are successfully realized in one container.

    本申请公开了一种航天器真空热环境模拟结构及控温方法,其中模拟结构包括真空容器,真空容器内底部设置有支撑架;还包括固定在支撑架中部的梁式框架、若干对称固定在梁式框架上的卫星安装架、安装在卫星安装架上的卫星、竖直固定在梁式框架上且位于相邻的卫星安装架之间的星间主冷板、设置在每颗卫星底部的下冷板;每颗卫星的上表面及下表面设有灯阵及用于测温的温度传感器;灯阵用于加热,提供热环境。本申请通过在真空容器内将多颗卫星对称式布置在一梁式框架上,在卫星正下方与相邻两颗卫星之间设置冷板,避免了卫星热试验背景热流过大而引起温度模拟误差;在一个容器内成功实现了两颗卫星背景热流一致性和卫星间的热流无扰。


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Spacecraft vacuum thermal environment simulation structure and temperature adjusting method


    Weitere Titelangaben:

    一种航天器真空热环境模拟结构及温度调节方法


    Beteiligte:
    WANG JING (Autor:in) / LI RIHUA (Autor:in) / DU CHUNLIN (Autor:in) / QIN JIAYONG (Autor:in) / LIU BO (Autor:in) / WU DONGLIANG (Autor:in) / YU CHEN (Autor:in) / AN WANQING (Autor:in) / ZHU LIN (Autor:in) / ZHANG LINA (Autor:in)

    Erscheinungsdatum :

    2021-11-05


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS / G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung



    Spacecraft thermal vacuum testing

    Elam, B. F. / Lancaster, L. D. | NTRS | 1972


    The Thermal Simulation and Control Technology in Spacecraft Vacuum Thermal Test

    Liu, Chang / Pei, Yi-Fei / Zhang, Jing-Chuan | Tema Archiv | 2013


    METHOD OF SPACECRAFT THERMAL VACUUM TESTING

    ZAJTSEV SERGEJ EDUARDOVICH / POZHALOV VYACHESLAV MIKHAJLOVICH / SMIRNOV ALEKSANDR SERGEEVICH et al. | Europäisches Patentamt | 2020

    Freier Zugriff

    Thermal vacuum testing for spacecraft

    Anderson, D. E. | NTRS | 1969


    Thermal gradient spacecraft vacuum chamber tests.

    Gordon, G. D. / Strickberger, H. P. | NTRS | 1964