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来源：百度知道 编辑：UC知道 时间：2024/07/02 06:57:36
在航空航天领域，飞行器结构所处的环境及其恶劣，如导弹的端头部、固体火箭发动机的喷管喉衬等都工作在超高温的环境中。在这些部位所使用的材料工作时，通过烧蚀引起自身质量的损失，吸收并带走大量的热量，阻止热量的传递。根据热防护材料的热化学烧蚀机理建立合理的数学-力学模型，分析体积烧蚀引起材料的性能随温度的变化规律是非常重要的。
通过对高温环境下防热材料内部热化学烧蚀机理的分析，利用Eshelby等效夹杂方法研究了组元材料的烧蚀-相变特性及高温力学性能和热物理性能的变化规律。假设材料热化学反应后热解生成的相介质统计均匀分布，考虑了烧蚀反应产生的气孔与固体相介质之间的相互作用，预报了基体、增强纤维、单向纤维增强复合材料的细观结构与宏观力学热物理性能之间的变化关系，并进行了数值模拟。研究结果表明：单向复合材料纵向杨氏模量随温度升高而衰减，并与加温速率有关。典型热防护材料的高温性能的理论预报与实验数据进行比较，结果吻合较好，说明理论模型正确，为防热复合材料热结构分析奠定了基础。
关键词：防热复合材料；细观力学；体积烧蚀；高温性能

In the aerospace domain, the environment which the flight vehicle structure locates and bad, like the missile end forehead, the solid propellant engine nozzle throat lining and so on all works in the superhigh temperature environment.Uses in these spots when material work, causes own quality loss through the ablation, absorbs and carries off the massive quantity of heats, the impediment quantity of heat transmission.According to the hot shielding material thermochemistry ablation mechanism establishment reasonable mathematics aerodynamics model, the analysis volume ablation causes the material performance along with the temperature change rule is extremely important.
Through guards against heat the material interior thermochemistry ablation mechanism analysis to the high temperature environment under, studied the component material ablation using the Eshelby equivalent mixture method - to change the characteristic and the high temperature mechanics performance and the hot