中文摘要：

针对高超声速飞行器新型超高温结构力/热/氧化关键性能参量试验测试的迫切需求,自行设计并建立了可实现在高达1 500℃极端高温氧化环境下进行结构断裂性能测试的辐射式热/力联合试验系统,并对耐高温C/SiC复合材料结构在1 500℃等高温氧化环境下的断裂强度以及出现断裂时的时间点等关键性能参数进行了试验测试,当试验温度从1 000℃上升至1 500℃,C/SiC复合材料试验件的断裂强度下降了47.5％,断裂时间缩短50.1％.本极端高温载荷试验系统为高超声速飞行器结构热强度研究提供了重要的氧化环境下的热/力联合试验测试手段.研究结果表明：通过高温预加载可以明显提高C/SiC复合材料结构的断裂强度,增幅为38％,承载时间提高61.1％.试验结果为高超声速飞行器复合材料部件在极端热环境下的安全可靠性设计以及强度性能的改进提供了重要依据.

英文摘要：

In order to satisfy the urgent demand to test the mechanics/thermal/oxidization key performance parameters for new ultra-high temperature structures of hypersonic flight vehicles, a self-designed radiation type thermal- mechanical joint test system that can perform fracture property test of structures under extremely high-temperature/ oxidization environment up to 1 500 ＊C was established. By using this system, key performance parameters, such as fracture strength and fracture time, for C/SiC high-temperature-resistant composite material were tested in hightemperature/oxidization environments up to 1 500 ℃. The results show that the C/SiC specimen＇s fracture load decreases 47.5 % when the temperature rises from 1 000 ℃ to 1 500 ℃, and the time to failure reduces to 50.1% of that at 1 000 ℃. This extreme high-temperature experimental system provides important test method for thermalmechanical research on thermal strength of structures in oxidization environments. In this thermal-mechanical test, the phenomenon that the preloading process in high temperatures can increase the fracture strength obviously for C/ SiC composite structure is observed, and the fracture strength increases by 38% and the time to failure increases by 61.1%. The results provide important basis for the safety and reliability design as well as improvements of material strength properties of composite structures for hypersonic flight vehicles under extreme thermal environments.