空间遥感器用环路热管瞬态数值模拟与在轨验证  

Transient numerical simulation and on-orbit verification of loop heat pipe used for space remote sensor

作　　者：孟庆亮[1,2] 杨涛 于志[1,2] 赵振明 赵宇[1,2] 于峰 MENG Qingliang;YANG Tao;YU Zhi;ZHAO Zhenming;ZHAO Yu;YU Feng(Beijing Institute of Space Mechanics and Electricity,Beijing 100094,China;Beijing Key Laboratory of Advanced Optical Remote Sensing Technology,Beijing 100094,China)

机构地区：[1]北京空间机电研究所,北京100094 [2]先进光学遥感技术北京市重点实验室,北京100094

出　　处：《北京航空航天大学学报》2020年第11期2045-2055,共11页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家自然科学基金(51806010)。

摘　　要：为满足空间遥感器环路热管(LHP)在轨应用需求,建立了高分九号卫星电荷耦合器件(CCD)用LHP瞬态数值模型。模型采用了节点-网络法和流动与传热关系式耦合的方法,考虑了蒸发器与储液器之间的传热传质过程。通过仿真与在轨数据的对比,发现LHP内部组件温度偏差为0.2~0.4℃,冷凝器测点温度偏差为0.5~2.0℃;预热器通过干度的变化调节了冷凝器外热流和热源工作模式的影响;热源的工作模式对蒸发器向储液器漏热、回路流阻及两相段长度均有影响。所提模型可用于不同轨道外热流及热源工作模式下,研究LHP内部各参数的变化规律,预测LHP系统的瞬态工作特性,并指导后续产品的设计与研发。For the purpose of meeting the requirement of application on-orbit for Loop Heat Pipe(LHP),a transient numerical model of LHP,which is used for the thermal control of Charge-Coupled Device(CCD)of GF-9 satellite,is developed by using the node-network method and flow and heat transfer relation formula.The processes of heat and mass transfer between evaporator and accumulator are considered.By comparison between simulation and on-orbit results,it is found that the temperature differences are 0.2-0.4℃and 0.5-2.0℃,for the interior components and condensers,respectively.The influence of orbital external heat flux and working mode of heat source can be adjusted by the degree of dryness in the pre-heater.The heat leak from evaporator to accumulator,flow resistance of loop,and the length of two-phase loop can be affected by the working mode of heat sources.The model can be used to study the variation of LHP interior parameters under different orbital external heat flux and heat source working modes,and predict the transient behavior of LHP system,which can also be used to guide the design and development of subsequent products.

关 键 词：环路热管(LHP) 空间遥感器 精密控温 传热传质 数值模拟 

分 类 号：V416[航空宇航科学与技术—航空宇航推进理论与工程] TK124[动力工程及工程热物理—工程热物理]