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总览 评价 姚学锋 * ， 马寅佶 ， 苏蕴荃 （ 清华大学工程力学系应用力学实验室，北京100084； ） 摘要： 超高温材料（如ZrB2/SiC陶瓷）是高超声速飞行器尖缘热防护结构的重要组成材料，其高温力学性能及热力耦合行为直接关系高超声速飞行器的服役安全及可靠
姚学锋*， 马寅佶， 苏蕴荃
（
清华大学工程力学系应用力学实验室，北京100084； ）
摘要：
超高温材料（如ZrB2/SiC陶瓷）是高超声速飞行器尖缘热防护结构的重要组成材料，其高温力学性能及热力耦合行为直接关系高超声速飞行器的服役安全及可靠性。鉴于高超声速飞行器在入轨或返回地面时，其尖端鼻锥结构遭受严重气动力和气动热环境，鼻锥尖端工作温度达几千K，致使鼻锥复合结构内部应力状态以及破坏模式与热力烧蚀耦合场的关系十分复杂。
关键词：
固体力学；热力耦合；高温力学；热障涂层
YAO Xuefeng*， MA Yinji， SU Yunquan
（
Department of Engineering Mechanics, Applied Mechanics Lab, Tsinghua University, Beijing, 100084； ）
Abstract：
The ultra-high-temperature materials (such as ZrB2/SiC ceramics) are the important component materials of the sharp edge thermal protection structure for the hypersonic vehicles, whose high temperature mechanical properties and thermo-mechanical coupling behaviors are directly related to the safety and the reliability of the hypersonic reentry vehicles. When the hypersonic reentry vehicles enter into the orbit or return to the ground, its tip nose complex structure will be suffered from harsh aerodynamic loads and aerodynamic heating. The temperature at the tip of the nose cone will elevate at several thousand K, which leads to the complicated relationships among the internal complex stress state of the nose cone, the failure mode and the thermal ablation coupled field.
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