【摘要】 基于碳基材料烧蚀双平台理论，结合烧蚀动边界下的瞬态传热有限元计算，建立了碳基材料三维烧蚀传热计算方法。使用该方法开展了对碳/碳复合材料圆柱模型风洞试验状态的计算分析，在验证烧蚀量预测准确性的同时，详细分析了不同加热条件下整个加热进程中烧蚀量的变化规律，发现烧蚀量的变化是由来流条件、壁面温度共同作用的结果，且不同条件下对应了不同反应机制，耦合结构温度场计算对烧蚀量的准确预测至关重要。进一步将所发展的烧蚀外形-结构传热耦合计算方法用于类联盟号返回舱沿飞行轨迹的三维烧蚀温度场计算，获得了综合考虑飞行热环境、结构传热的返回舱整体三维烧蚀外形变化规律，并详细阐释了返回舱不同位置、沿飞行轨迹不同阶段所对应的烧蚀反应机理。更多还原

【Abstract】 Based on the dual-platform theory of ablation of carbon-based materials and the finite element calculation of transient heat transfer under the dynamic boundary of ablation, a three-dimensional ablation heat transfer calculation method of carbon-based materials is established. The method is used to calculate and analyze the wind tunnel test of carbon/carbon composite cylindrical model. While verifying the prediction accuracy of ablation amount, the variation law of ablation amount during the whole heating process under different heating conditions is analyzed in detail. It is found that the change of ablation amount is the result of the combined action of incoming flow conditions and wall temperature, and different conditions correspond to different reaction mechanisms. The calculation of coupled structure temperature field is very important for accurate prediction of ablation amount. Furthermore, the three-dimensional ablation temperature field of Soyuz-like return capsule along the flight trajectory is calculated by using the developed coupling calculation method of ablation profile and structure heat transfer. The variation law of the overall three-dimensional ablation profile of the return capsule considering the flight thermal environment and structure heat transfer is obtained, and the corresponding ablation reaction mechanism at different positions of the return capsule and different stages along the flight trajectory is explained in detail.更多还原