发明名称 |
THERMAL STABILIZATION SYSTEM OF THE SPACECRAFT INSTRUMENT COMPARTMENT |
摘要 |
FIELD: space.SUBSTANCE: invention relates to space engineering and can be used in temperature control systems of instrument compartments. Thermal stabilization system of the spacecraft instrument compartment comprises a radiator-emitter and heat pipes. Radiator-emitter is made in the form of a cylindrical screen with circular heat pipes on the surface arranged along the edge of the screen. System providing thermal control of fuel elements includes low-temperature heat pipes arranged with a possibility for direct thermal contact with said elements and equipped with interface for connection with low-temperature heat pipe of a spacecraft for removing heat into space. Temperature control and adjustment system is equipped with electric heaters, connected with temperature sensors via control unit, located with electric heaters in heat-insulating gaps.EFFECT: invention technical result is increase in accuracy and reliability of thermal control.1 cl, 2 dwg |
申请公布号 |
RU2603690(C1) |
申请公布日期 |
2016.11.27 |
申请号 |
RU20150143003 |
申请日期 |
2015.10.08 |
申请人 |
Federalnoe gosudarstvennoe unitarnoe predprijatie "Rossijskij federalnyj jadernyj tsentr - Vserossijskij nauchno-issledovatelskij institut eksperimentalnoj fiziki" (FGUP "RFJATS-VNIIEF") |
发明人 |
CHernomaz Viktor Ivanovich;Svishchev Viktor Vladimirovich;Doronin Andrej Vitalevich;Goncharov Konstantin Anatolevich;Moisheev Aleksandr Aleksandrovich |
分类号 |
B64G1/50 |
主分类号 |
B64G1/50 |
代理机构 |
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代理人 |
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地址 |
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