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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。
Aiming at the urgent need of the test of the new hyperthermia structural force / heat / oxidation critical performance parameters of hypersonic vehicle, the radiation heat / force which can be used to test the structural rupture performance under the extreme high temperature oxidation environment up to 1500 ℃ is designed and established. Joint test system and the key performance parameters of the high temperature C / SiC composite structure under the high temperature oxidation environment of 1 500 ℃ and the time point when the fracture occurs are tested. When the test temperature rises from 1 000 ℃, At 1 500 ℃, the breaking strength of C / SiC composites decreased by 47.5% and the breaking time by 50.1%. This extreme high temperature load test system provides an important thermal / force joint test method for the study of thermal strength of hypersonic vehicle structures. The results show that the breaking strength of C / SiC composites can be obviously increased by high temperature preloading, with an increase of 38% and a carrying time of 61.1%. The test results provide an important basis for the design of the safety and reliability of hypersonic composite parts in extreme heat environment and the improvement of the strength performance.