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论述了发射组件强迫风冷系统的热设计方法,介绍了强迫风冷体积流量的理论估算。用ICEPAK CFD热分析软件进行热仿真,包括建模、加载边界条件、检查结果等。在仿真时根据最高温度、风扇的工作点、出风口和入风口的温度差,对翅片的厚度、齿间距进行优化,模块产生的热量通过流过散热器翅片间的强迫流动的空气散发出去,最终满足发射组件热设计的要求。元器件工作在允许的温度范围内,确保发射模块正常工作。测试数据与仿真数据基本符合表明热仿真的正确性。
The thermal design method of forced air cooling system of launch module is discussed. The theoretical estimation of forced air cooling volume flow is introduced. Thermal simulation with ICEPAK CFD thermal analysis software, including modeling, loading of boundary conditions, inspection results and more. During simulation, the thickness and spacing of the fins are optimized based on the maximum temperature, the operating point of the fan, the temperature difference between the air outlet and the air inlet, and the heat generated by the module is dissipated through forced air flowing through the radiator fins Go out and eventually meet the thermal design requirements of the launch module. Components work in the allowable temperature range, to ensure that the transmitter module to work properly. Test data and simulation data are basically in line with the correctness of thermal simulation.