吊舱液冷系统低温工作及启动特性研究  

Low-temperature Operation and Startup Characteristics of Liquid Cooling System for Pod

作　　者：龚文驰 GONG Wenchi(The 29th Research Institute of CETC,Chengdu 610036,China)

机构地区：[1]中国电子科技集团公司第二十九研究所,成都610036

出　　处：《装备环境工程》2025年第4期135-140,共6页Equipment Environmental Engineering

摘　　要：目的考察低温环境对吊舱液冷系统工作和启动特性的影响。方法基于某型吊舱液冷系统,模拟–55~25℃场景,开展温度对系统供液压力、膨胀罐液位、稳态电流、稳态功率及瞬态启动电流影响的试验研究。结果供液压力随温度降低先增大、后减小,并于5℃下达到最大压力469.74 kPa。膨胀罐液位随温度降低逐渐减小,且在25~5℃降幅显著。稳态电流和功率随温度降低逐渐增大,供电电流由3.6 A增大至8.1 A,供电功率由100.8 W增大至226.8 W,增幅为125%。瞬态启动电流随温度降低逐渐增大,由5.44 A增大至13.40 A,且显著大于对应温度下的稳态电流。结论低温使得系统体积收缩及冷却液黏度增大,吊舱液冷系统设计需充分考虑气蚀及过流风险。The work aims to investigate the impact of the low-temperature environment on the operation and startup characteristics of the liquid cooling system for pod.Based on a certain type of pod liquid cooling system,the scenarios from–55℃to 25℃were simulated and the experimental research was carried out to study the impact of temperature on the liquid supply pressure,the liquid level of the expansion tank,the steady-state current and power,and the instantaneous startup current.The liquid supply pressure firstly increased and then decreased as the temperature dropped,reaching the maximum pressure of 469.74 kPa at 5℃.The liquid level of the expansion tank gradually decreased as the temperature dropped,and the decline was significant within the range of 25℃to 5℃.The steady-state current and power gradually increased as the temperature dropped.The power supply current increased from 3.6 A to 8.1 A,and the power supply power increased from 100.8 W to 226.8 W,with an increase amplitude of 125%.The instantaneous startup current gradually increased as the temperature dropped,from 5.44 A to 13.40 A,and was significantly greater than the steady-state current at the corresponding temperature.Low temperature causes the system volume to shrink and the viscosity of the coolant to increase.The design of the liquid cooling system for pod needs to fully consider the risks of cavitation and overcurrent.

关 键 词：吊舱液冷系统 低温工作 低温启动 供液压力 液位 稳态功率 启动电流 

分 类 号：V216[航空宇航科学与技术—航空宇航推进理论与工程]