Heat transfer and ablation of carbon/carbon composites based on multi-field coupling
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摘要: 碳/碳復合材料作為熱防護材料多用在高超聲速飛行器鼻錐、機翼前緣等位置。為準確預測其傳熱及燒蝕響應，采用多場耦合策略，考慮外部流場熱化學非平衡效應、固體材料傳熱以及材料表面燒蝕，建立高超聲速氣動熱環境下碳/碳復合材料的流?熱?燒蝕多場耦合模型，預測碳/碳復合材料瞬態溫度場分布、燒蝕速率以及燒蝕外形變化等。計算得到材料模型駐點區壁面溫度和熱流值隨著時間的推移發生了顯著的變化，初始時刻熱流值較大，1 s時駐點熱流密度為17.22 MW?m?2，隨著時間推移，壁面溫度增大，駐點區溫度梯度減小，熱流值也減小，30 s時駐點熱流密度為10.22 MW?m?2。材料模型駐點區的溫度較高，材料表面反應活躍，燒蝕較為嚴重，而模型側面只發生少量燒蝕，燒蝕前后材料模型外形發生一定的變化，前緣半徑增大，30 s時材料駐點燒蝕深度為17.47 mm。結果表明：在高超聲速氣動熱環境下，碳/碳材料模型發生一定的燒蝕后退，導致外部流場以及熱載荷發生變化，采用流?熱?燒蝕多場耦合模型可有效預測不同時刻材料的傳熱及燒蝕響應，為熱防護系統的設計提供一定的參考。Abstract: With the development of hypersonic technology, the demand for thermal protection material is continuously increasing. Carbon/carbon composites are widely used as thermal protection materials in the nose and in the leading edge of hypersonic vehicles owing to their high latent heat and good resistance to high temperatures. The flow field around the aircraft affects the heat transfer and ablation of carbon/carbon composites, changing the thickness and shape of the thermal protection layer. The ablation of carbon/carbon composites alters the flow field distribution, thus conversely affecting the ablation of carbon/carbon composites. To predict the heat transfer and ablation of carbon/carbon composites, a multi-field coupling model was established to predict the transient temperature distribution, ablation rate, and ablation profile of carbon/carbon composites in hypersonic aerothermal environments. The thermochemical non-equilibrium effects of the flow field, heat transfer of the material, and ablation of the material surface were considered in the modeling. The wall temperature and heat flux in the stagnation area change significantly. The initial heat flux is higher and the stagnation heat flux at 1 s is 17.22 MW?m?2. As time passes, the wall temperature increases, the temperature gradient in the stagnation area decreases, the heat flux decreases, and the stagnation heat flux at 30 s is 10.22 MW?m?2. As the temperature of the stagnation area is high, the material at the surface reacts actively and the ablation is more serious, whereas only a small amount of ablation occurs on the side of the model. The shape of the material model changes after the ablation, the leading-edge radius increases, and the ablation depth at the material stagnation point is 17.47 mm at 30 s. The results show that, in the hypersonic aerodynamic thermal environment, the carbon/carbon composites have a certain ablation recession, which leads to change in the external flow field and thermal load. The multi-field flow-heat-ablation coupling model can be used to predict the response of thermal protection materials, which can provide some reference for the design of thermal protection systems.
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圖 2 流固耦合示意及界面數據傳遞。（a）流固耦合示意圖；（b）非匹配網格間的數據傳遞
Figure 2. Fluid structure coupling and data transfer at the interface: (a) fluid structure coupling; (b) data transfer between unmatched grids
圖 5 外部流場及材料模型網格劃分。（a）流場網格示意圖；（b）材料前緣模型網格示意
Figure 5. External flow field grids and material model: (a) external flow field grids; (b) leading edge model grids
圖 6 流場馬赫數（a）和溫度（b）云圖分布
Figure 6. Mach (a) and temperature (b) distribution of the flow field
表 1 碳/碳材料性能參數
Table 1. Performance parameters of carbon/carbon materials
Density/
(kg·m?3)Specific heat/
(J·kg?1·K?1)Thermal conductivity/
(W·m?1·k?1)Radiation coefficient Modulus of elasticity/
GPaPoisson’s
ratio1800 840 15 0.8 69 0.3 
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