中国空间科学技术

中国空间科学技术 ›› 2025, Vol. 45 ›› Issue (4): 70-78.doi: 10.16708/j.cnki.1000-758X.2025.0059

• 微重力流体科学及其空间应用专题 • 上一篇    下一篇

航天器用机械泵驱动两相流体回路在轨测试性能分析

孟庆亮1,2,*，韦广朗1,2，于峰1,2，杨涛1,2，赵振明1,2，朱许1,2
  

  1. 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
  • 收稿日期:2024-02-21 修回日期:2024-07-19 录用日期:2024-07-29 发布日期:2025-07-22 出版日期:2025-08-01

Performance analysis of on-orbit testing of mechanically pumped two-phase loop for spacecraft

MENG Qingliang1,2,*，WEI Guanglang1,2，YU Feng1,2，YANG Tao1,2，ZHAO Zhenming1,2，ZHU Xu1,2   

  1. 1.Beijing Institute of space mechanics and electricity, Beijing 100094, China
    2.Beijing Key Laboratory of Advanced Optical Remote Sensing Technology, Beijing 100094, China
  • Received:2024-02-21 Revision received:2024-07-19 Accepted:2024-07-29 Online:2025-07-22 Published:2025-08-01

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摘要： 机械泵驱动两相流体回路（Mechanically Pumped Two-phase Loop, MPTL）是通过流动沸腾过程中气液相变潜热的释放而具有极强传热能力的两相传热装置，其在航天器热控领域具有广泛的研究前景。为研究MPTL产品的在轨微重力环境下的工作性能和稳定性，设计并研制了一套包含屏蔽式离心泵、两相控温型储液器和微小流道蒸发器的MPTL，并在某卫星上对其启动特性、相变传热特性、控温特性进行了测试。测试结果表明，微重力下MPTL展现了良好的传热特性。微重力下两相控温型储液器的控温性能达到±0.1K精度，被动冷却功能得到验证，降温速率达到1℃/min。微泵运转时，储液器气相和液相两个测点形成的温差在0.3～1.0K区间内。两个转速下，蒸发器的控温精度在±0.1～±0.3K区间内。回路发生相变过程时会出现过热现象，并导致蒸发器出口测温点温度高于储液器控温点7～8K。通过对比两个转速下的结果，发现过热时间和过热温度与转速相关。采用毛细结构的两相控温型储液器可以有效保证微重力下MPTL的高精度控温和高效两相流管控功能，气液两相转变特性与回路流量大小相关，蒸发器温度稳定性与其内部流体干度大小相关。

关键词: 航天器热控, 机械泵驱动两相流体回路（MPTL）, 在轨测试, 对流换热, 微重力

Abstract: Mechanistically pumped two-phase loop (MPTL) is a two-phase heat transfer device, which possesses the strong heat transfer ability through the release of latent heat of liquid and vapor phase change during flow boiling process. MPTL shows a promising prospect in thermal control of spacecraft.The objective of the present study is to focus on the working characteristics and stability of MPTL under the microgravtiy environment on orbit. One MPTL, which included one shield centrifugal pump, one two-phase temperature controlling accumulator and one micro channel evaporator, was designed and constructed to investigate the characteristics of start-up, phase-changing heat transfer, and temperature-controlling for MPTL aboard one satellite. Test results shows that MPTL shows good working performance and stable operating behavior in microgravity environment. The two-phase accumulator presents good heat transfer performance under microgravity condition. Its temperature control accuracy reaches to ±0.1K. The passive cooling function of accumulator is validated, and its cooling rate reaches to 1℃/min. The temperature difference between the measuring points of vapor and liquid phase for the accumulator are in the range of 0.3～1.0K when the pump is working. The temperature control accuracy of the evaporator is in the range of ±0.1～±0.3K at the two rotation speeds. Superheating phenomenon takes place during the phase changing process of the loop and it leads to a higher 7～8K temperature at the evaporator’s outlet than the temperature control point. By comparing the results under the two rotation speeds, the superheat time and superheat temperature are related with the rotation speeds. The two-phase temperature controlling accumulator using the capillary structures can assure the function of high-precision temperature control and high-efficiency two-phase fluid management and control for MPTL under the microgravity condition. The phase transition characteristic for vapor-liquid is related to the mass flowrate of the loop. The stability of temperature on the evaporator is related to the fluid quality of its interior fluid. The study would contribute to the engineering design basis for the technology of two-phase flow and heat transfer, and would promote the development of active two-phase thermal control technology for space.


Key words: spacecraft thermal control, mechanically pumped two-phase loop (MPTL), on-orbit testing, convection heat transfer, microgravity