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文章针对高超声速飞行器需面临极端高温有氧热环境以及舱体表面单侧面受热的特点,建立了由硅钼发热体作为热源的红外辐射式超高温、时变、单侧面加热试验测试系统,开展了高达1700℃的有氧环境下高超声速飞行器轻质防热材料的隔热性能试验。另外,为了研究和优选高效隔热方式,对高超声速飞行器用单层轻质陶瓷隔热材料和陶瓷/纳米材料叠层复合结构在1700℃高温有氧环境下的隔热特性进行了试验测试;通过试验结果的对比分析,发现陶瓷/纳米材料复合叠层结构比单层轻质陶瓷材料的隔热效果提高近50%。
In this paper, a hyperthermothermal, time-varying and one-sided heating test system based on silicon-molybdenum heating element as heat source is established to deal with the hyperthermic aeronautical environment that is exposed to extreme high temperature aerobic heat environment and the unilateral heating of the cabin surface. Thermal insulation performance test of a lightweight heat-resistant material for a hypersonic vehicle up to 1700 ℃ in aerobic environment. In addition, in order to study and optimize the efficient heat insulation method, the heat insulation characteristics of single layer lightweight ceramic insulation and ceramic / nano-material composite structure of hypersonic vehicle were tested in 1700 ℃ high temperature aerobic environment. Through the comparative analysis of the test results, it is found that the thermal insulation effect of the ceramic / nanocomposite composite laminate structure is increased by nearly 50% compared with that of the single-layer lightweight ceramic material.