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介绍了一套自行设计的燃料冷却模拟系统，该装置适用于模拟研究各种吸热型碳氢燃料在飞行器上不同冷却模式下的冷却特性， 为燃料将来在飞行器上的工程应用提供实验依据。仪器空白漏热标定结果表明其稳定性良好。在此装置上研究了吸热燃料在两种压力下的冷却情况， 实验发现在通燃料后， 反应管温度下降最低可达９０．６℃， 冷却效果较好； 随着外部热环境的变化， 反应管不同部位的吸热情况发生复杂变化， 尾部出现结焦； 燃料热沉测量值与文献值接近。
A set of self-designed fuel cooling simulation system is introduced. The device is suitable for simulating the cooling characteristics of various endothermic hydrocarbon fuels in different cooling modes and provides an experimental basis for the future application of fuel in aircraft. Instrument leak calibration results show good stability. In this device, the cooling of endothermic fuel under two pressures was studied. It was found that after the fuel was passed, the temperature drop of the reaction tube reached a minimum of 90.6 ℃ and the cooling effect was better. With the change of external thermal environment, The heat absorption in different parts of the reaction tube changed complicatedly and the tail appeared coking. The measured value of the fuel heat sink was close to the literature value.