论文部分内容阅读
耐热合金蜂窝夹芯结构是高超音速飞行器热防护系统外面板的理想候选方案。针对Hastelloy X耐热合金蜂窝夹芯结构开展了稳态传热实验,通过控制加热板温度,获得了一组热平衡时蜂窝夹芯结构的热、冷面温度,结合Stefan-Bolt-zmann定律和大空间自然对流实验关联式,采用热阻分析方法得到了Hastelloy X耐热合金蜂窝随温度变化的宏观等效热导率,并采用Swan-Pittman半经验模型预测了该蜂窝的等效热导率,与实验结果对比一致性较好。
The heat-resistant alloy honeycomb sandwich structure is an ideal candidate for the outer panel of a hypersonic aircraft thermal protection system. Steady-state heat transfer experiments were carried out on Hastelloy X heat-resistant alloy honeycomb sandwich structure. By controlling the temperature of the hot plate, the heat and cold surface temperatures of the honeycomb sandwich structure were obtained when the heat balance was achieved. Combined with the Stefan-Bolt-zmann law and the large Space natural convection experiment correlation, the macro-equivalent thermal conductivity of Hastelloy X alloy with temperature change was obtained by thermal resistance analysis method, and the equivalent thermal conductivity of the honeycomb was predicted by Swan-Pittman semi-empirical model. Comparison with the experimental results is better.