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改进并重新组装了自行研制的高温热导型流动热量计 ,利用电标定法测定了该仪器在 70 0℃和 80 0℃的热量常数。为检验仪器的可靠性 ,本仪器测定了氮气的热沉 ,结果表明实验值与用氮气的热容公式计算所得的计算值基本吻合。对自制的吸热型碳氢燃料 (FRA)和作为模型化合物的正庚烷的热沉进行了测定 ,发现在 70 0℃时两者的热沉值比较接近 ,分别为 3 0 7MJ kg和 3 2 3MJ kg。在 80 0℃时 ,两者都具有较高的热沉值 ,分别达到 5 6 9MJ kg和 6 6 0MJ kg ,该热沉值能够满足超高音速飞行器的热管理要求。
The self-developed high-temperature thermal conductivity flow calorimeter was improved and reassembled. The thermal constants of the instrument at 70 ℃ and 80 ℃ were determined by electric calibration. In order to test the reliability of the instrument, the instrument measured the nitrogen heat sink, the results show that the experimental value and calculated using the heat capacity of nitrogen calculated results are basically consistent. The home-made endothermic hydrocarbon fuel (FRA) and n-heptane as a model compound were measured and found to have a very close relationship between the heat sinks at 70 0 C and 370 KJ 2 3MJ kg. At 80 ° C, both have higher heat sink values of 569MJ kg and 6600MJ kg, respectively, which can meet the thermal management requirements of ultra-high-speed aircraft.