摘要
针对高超声速飞机飞行时的严重发热会极大程度上影响飞行器性能的问题,基于某型超声速飞机的热管理系统,提出了一种可行的冷却设计方案。使用AMEsim软件对提出的冷却设计方案建模,通过循环回路中设置的温度传感器对管路各个位置的温度进行检测,并通过更改循环回路中的制冷剂种类和流速得到了相关部件的运行时间—温度特性。最后对得出的数值仿真结果进行分析,得到了不同循环过程中的典型部件的温度变化规律。仿真结果表明,制冷剂的流速越快,循环回路的冷却效果越好;制冷剂的比热容越大,循环回路的冷却效果越好。
A feasible cooling design scheme is proposed based on the thermal management system of a certain type of supersonic aircraft to address the issue of severe heat generation during flight,which greatly affects the performance of the aircraft.Then,AMEsim software is used to model the proposed cooling design scheme.The temperature sensors set in the circulation loop are used to detect the temperature at various positions of the pipeline,and the operating time temperature characteristics of relevant components are obtained by changing the refrigerant type and flow rate in the circulation loop.Finally,the numerical simulation results were analyzed to obtain the temperature variation patterns of typical components during different cyclic processes.The simulation results show that the faster the flow rate of the refrigerant,the better the cooling effect of the circulation circuit;the higher the specific heat of the refrigerant,the better the cooling effect of the circulation circuit.
作者
马骁
贾惟
MA Xiao;JIA Wei(College of Safety Science and Engineering,Civil Aviation University of China,Tianjin 300300,China)
出处
《桂林航天工业学院学报》
2025年第3期366-378,共13页
Journal of Guilin University of Aerospace Technology
关键词
超声速飞机
热管理系统
AMESIM仿真
发热分析
supersonic aircraft
thermal management system
AMESim simulation
exothermic analysis
