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根据某探测器的具体结构及工作条件,分析和计算探测器上火箭发动机的热环境参数.利用有限元法计算火箭发动机固壁辐射热流密度,依据热流边界条件设计热防护方案;利用有效发射率表征多层隔热材料隔热性能并进行温度场数值仿真.由于多层隔热材料性能参数的不易确定性,计算了参数在较大范围内的热防护效果.通过仿真计算验证热防护方案的有效性和可靠性,并分析影响热防护效果的主要因素;计算结果表明多层隔热材料的有效发射率是影响隔热性能最重要的因素,比热容、表面发射率、密度对热防护性能影响很小.
According to the specific structure and working conditions of a detector, the thermal environment parameters of the rocket engine on the detector are analyzed and calculated.The thermal radiation density of the rocket engine solid wall radiation is calculated by the finite element method, and the thermal protection scheme is designed according to the heat flow boundary conditions. The thermal insulation performance of multi-layer insulation materials is characterized and the numerical simulation of temperature field is performed. The thermal protection effect of the parameters in a wide range is calculated due to the hard to determine the performance parameters of multi-layer insulation materials. The results show that the effective emissivity of multi-layer thermal insulation material is the most important factor affecting the thermal insulation performance. The influence of specific heat capacity, surface emissivity and density on the thermal protection performance Very small.