本项目以准确描述固体火箭发动机内高温熔融氧化铝沉积条件下三元乙丙绝热材料的传热与烧蚀过程，深入揭示其烧蚀机理为研究目的，采用理论分析和实验研究相结合的手段，建立能够模拟发动机颗粒沉积状态的实验装置，开展不同沉积状态对绝热材料内部温度、压力影响以及烧蚀率影响的实验研究，并采用微米CT、微米三维成像仪、XRD、电镜分析等先进设备，对试验后熔融层和炭化层进行详细分析测量，分别建立基于炭化层表面真实粗糙度的接触热传导模型、熔融氧化铝和炭化层内的Al-O-C反应动力学模型、熔融氧化铝覆盖条件下的绝热层热分解和炭化模型，最终形成能够准确描述熔融氧化铝沉积下绝热层传热和烧蚀过程的耦合模型，最终建立基于多孔介质特征的统一模型并进行实验验证和修正，揭示高温高压熔融氧化铝沉积条件下，熔融层与炭化层之间如何传热，发生什么化学反应、材料如何热解等传热和烧蚀的本质问题。

The ablation process and mechanism of EPDM (Ethylene-Propylene-Diene Monomer) insulator in SRM (Solid Rocket Motor) under molten alumina deposition condition is focused. The influence of deposited alumina on temperature, pressure and ablation rate of EPDM is studied theoretically and experimentally. The micron CT, micron 3D imager, XRD and SEM are used to analyze the melting layer and charred layer of post-test EPDM specimen. The reaction kinetics of fused alumina and charred layer in high temperature and high pressure condition, the contact thermal conduction model based on surface roughness, and the pyrolysis model of thermal insulator covered by molten alumina are established. Thus, the unified ablation model of porous media is obtained, and the intrinsic ablation mechanism of EPDM insulator under molten alumina deposition condition is revealed.