高热流散热泵驱两相流体回路设计及飞行验证  

Design and On-Board Validation of Pumped Two-Phase Fluid Loop for High Heat Flux Removal

作　　者：于新刚[1,2] 徐侃[1,2] 苗建印[1,2] 王德伟[1,2] 赵欣[1,2] 范含林[1] 菅鲁京[1,2] 张红星[1,2] 

机构地区：[1]北京空间飞行器总体设计部,北京100094 [2]空间热控技术北京市重点实验室,北京100094

出　　处：《宇航学报》2017年第2期192-197,共6页Journal of Astronautics

基　　金：国家自然科学基金(51406009)

摘　　要：针对激光、雷达等载荷空间应用中存在的超过100 W/cm^2高热流密度散热问题,采用泵驱两相流体回路结合金刚石微槽道的方法实现了271 W/cm^2热流密度的散热。对系统设计及关键部件设计进行了研究,整个系统经过地面和在轨飞行验证,运行平稳。利用储液器控温的方式,实现了系统温度的准确控制。测试结果表明,地面和在轨飞行期间的换热及流阻相当,验证了重力无关设计的正确性。A cooling system consisting of a pumped two-phase fluid loop and a diamond micro-channel is illustrated to meet the requirement of heat removal for high power payload in space,such as laser and radar. Detailed design of this system with a cooling capability as high as 271 W / cm^2 is presented,which is verified by the on-board and terrestrial experiments. The system works very well with a two-phase accumulator to control the temperature of the micro-channel heat sinks. The similarity between the on-board and terrestrial results of the heat transfer and flow demonstrates the gravityindependent design which is critical for space applications.

关 键 词：微槽道 两相流体回路 流动沸腾 

分 类 号：V416[航空宇航科学与技术—航空宇航推进理论与工程]