首页 | 本学科首页   官方微博 | 高级检索  
     

可展开式辐射器热控对航天器轨道调整的适应性分析
引用本文:刘欣,梁新刚. 可展开式辐射器热控对航天器轨道调整的适应性分析[J]. 宇航学报, 2021, 42(3): 390-396. DOI: 10.3873/j.issn.1000-1328.2021.03.014
作者姓名:刘欣  梁新刚
作者单位:1.清华大学航天航空学院热科学与动力工程教育部重点实验室,北京 100084;2.中国运载火箭技术研究院,北京 100076
摘    要:为提高航天器热控系统对轨道调整的适应能力,本文研究了与流体回路耦合的可展开式辐射器热控方案在不同轨道高度下的热控性能,分析了不同轨道高度时辐射器面临的热环境的影响,在不同轨道高度下比较了固定辐射器与可展开辐射器的热控特性.结果 表明,随着辐射器展开角度的变化,辐射器吸收的空间热流随之发生变化,从而对热控系统的散热能力带...

关 键 词:航天器  可展开式辐射器  流体回路  辐射  热控
收稿时间:2020-06-08

Adaptability Analysis of Deployable Radiator ThermalControlSystem to Spacecraft Orbit Adjustment
LIU Xin,LIANG Xin gang. Adaptability Analysis of Deployable Radiator ThermalControlSystem to Spacecraft Orbit Adjustment[J]. Journal of Astronautics, 2021, 42(3): 390-396. DOI: 10.3873/j.issn.1000-1328.2021.03.014
Authors:LIU Xin  LIANG Xin gang
Affiliation:1.Key Laboratory for Thermal Science and PowerEngineering of Ministry of Education, School of Aerospace Engineering, TsinghuaUniversity, Beijing 100084, China; 2. China Academy of Launch VehicleTechnology, Beijing 100076, China
Abstract:In order to improve the adaptability of spacecraftthermal control system, this paper investigates the thermal control scheme ofthe deployable radiator coupled with a liquid loop. The thermal environmentchanges of the radiator at different orbit altitudes are analyzed. The thermalcontrol characteristics of the fixed radiator and the deployable radiator indifferent orbit environments are compared. The results show that as thedeployment angle of the radiator changes, the space heat flux absorbed by theradiator also changes, which directly affects the heat dissipation capacity ofthe thermal control system. The deployable radiator can enhance its ability ofheat dissipation. In engineering applications, based on the thermal controlliquid loop, by adjusting the deployment angle of the deployable radiator, thethermal adaptability of the spacecraft can be effectively improved.
Keywords:Spacecraft,Deployable radiator,Liquid loop  Radiation,Thermal control,
本文献已被 CNKI 等数据库收录!
点击此处可从《宇航学报》浏览原始摘要信息
点击此处可从《宇航学报》下载免费的PDF全文
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号