Comparison on thermal protection performance and mechanisms of low-ablation and non-ablative materials
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摘要:
轻质热防护材料是当前飞行器大面积热防护系统的重要材料。通过耦合气动传热及热化学过程建立热响应模型，对比研究了纳米孔树脂基低微烧蚀材料和非烧蚀型陶瓷瓦在两种典型热环境下的防隔热性能，揭示了其能量耗散路径及贡献权重。结果表明：相较于陶瓷瓦，低微烧蚀材料通过热阻塞、热沉、热解气体逸散与热解反应的多机制协同作用，实现了10%～15%的综合能量耗散，展现出其多途径散热的优越性。辐射散热是两类材料共有的核心防隔热机制，其贡献随热载荷的加剧而显著增大。此外，低微烧蚀材料凭借其纳米孔结构赋予的低热导率优势，以及更高的比定压热容和密度，在相同条件下能够更有效地将热量阻滞在上层区域，显著抑制热量向内部传递，从而获得比陶瓷瓦更低的背温。研究证实树脂基材料通过动态调节能量耗散机制的配比与厚度方向的热沉分布，实现了宽域热环境下的高效防隔热性能。
Abstract:Lightweight thermal protection materials are a key solution for large-area thermal protection systems in modern aerospace vehicles. A thermal response model coupling aerodynamic heat transfer and thermochemical processes was developed to comparatively investigate the thermal protection performance of nanoporous resin-based low-ablation materials and non-ablative ceramic tiles under two typical of thermal environments. It revealed the energy dissipation pathways and their respective contribution weights. Results showed that, compared with ceramic tiles, low-ablation materials achieved an overall energy dissipation of approximately 10%—15% through a synergistic combination of mechanisms including thermal blockage, heat sink effects, pyrolysis gas release, and pyrolysis reactions, demonstrating superior multi-path heat dissipation capabilities. Radiative heat dissipation was identified as a core mechanism shared by both materials, with its contribution significantly increasing under intensified thermal loads. Moreover, the nanoporous structure of the low-ablation material presented low thermal conductivity, along with higher specific heat capacity and density, enabling more effective heat confinement in the upper layer and significantly reducing heat transfer to the interior, thus resulting in a lower backside temperature compared with ceramic tiles. The study confirmed that resin-based materials can dynamically regulate the proportion of energy dissipation mechanisms and the distribution of heat sinks along the thickness direction, achieving efficient thermal protection across a wide range of thermal environments.
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图 1 烧蚀材料和非烧蚀材料的热响应示意图
Figure 1. Schematic thermal response of ablative and non-ablative materials
图 2 材料三维热响应的建模流程
Figure 2. Modeling flow of three-dimensional thermal response of materials
图 5 不同工况下两种材料热响应温度对比图
Figure 5. Comparison of the thermal response temperatures of the two materials under different operating conditions
图 6 不同表面辐射率下材料的响应温度随时间的变化趋势
Figure 6. Response temperature trends of materials with time for different surface emissivities
图 7 质量残留率对热阻塞效应的影响
Figure 7. Influence of mass residue rate on thermal blocking effects
图 8 材料物性变化及热沉的分布图
Figure 8. Plot of material physical property changes and heat of deposition
图 9 不同热导率和比定压热容下材料的响应温度随时间的变化趋势
Figure 9. Response temperature trends with time for materials with different thermal conductivities and specific heat capacities
表 1 IPC-50和陶瓷瓦的材料参数
Table 1. Material parameters for IPC-50 and ceramic tiles
物性参数 IPC-50 陶瓷瓦 密度/（g/cm3） 0.5 0.35 基体质量残留率/% 84 热导率/（W/（m·K）） 0.05 0.046 比定压热容/（J/（g·K）） 1.1 0.9 表面辐射率 0.85 0.85 
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表 2 用于材料防隔热性能分析的两种典型热环境
Table 2. Two typical thermal environments for material thermal insulation analysis
工况 任务 时长/s 1 飞行马赫数为6，27 km高空巡航轨迹 1000 2 航天飞机再入地球大气层[38] 1500
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表 3 陶瓷瓦和IPC-50防隔热机制的贡献权重
Table 3. Contribution weights of ceramic tiles and IPC-50 for thermal insulation mechanisms
防隔热
机制贡献权重/% 工况1 工况2 陶瓷瓦 IPC-50 陶瓷瓦 IPC-50 辐射散热 93.8 85.8 97.6 89.2 热沉 6.2 7.7 2.4 3.8 热阻塞 3.1 4.6 热解气体 2.8 2.1 热解反应 0.6 0.3
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表 4 IPC-50防隔热机制的贡献权重随辐射率的变化
Table 4. Variation of the contribution weights of the IPC-50 thermal insulation mechanism with emissivity
防隔热
机制贡献权重/% 工况1 工况2 δ=0.85 δ=0.95 δ=0.85 δ=0.95 辐射散热 85.8 87.0 89.2 90.3 热沉 7.7 7.0 3.8 3.5 热阻塞 3.1 2.9 4.6 4.2 热解气体 2.8 2.6 2.1 1.8 热解反应 0.6 0.6 0.3 0.2
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表 5 陶瓷瓦防隔热机制的贡献权重
Table 5. Contribution weighting of thermal insulation mechanisms for ceramic tiles
防隔热
机制贡献权重/% 工况1 工况2 δ=0.7 δ=0.85 δ=0.7 δ=0.85 辐射散热 93 93.8 97.4 97.6 热沉 7 6.2 2.6 2.4
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表 6 不同基体质量残留率下IPC-50防隔热机制的贡献权重
Table 6. Contribution weights of IPC-50 thermal insulation mechanisms at different matrix mass retention rate
防隔热
机制贡献权重/% 工况1 工况2 γ=84 γ=70 γ=60 γ=50 γ=84 γ=70 γ=60 γ=50 辐射散热 85.8 81.5 77.8 75.5 89.2 84.9 80.4 78.4 热沉 7.7 7.1 7.0 6.6 3.8 3.4 3.5 3.2 热阻塞 3.1 5.5 7.3 8.7 4.6 7.7 10.7 12.2 热解气体 2.8 4.9 6.4 7.6 2.1 3.5 4.7 5.4 热解反应 0.6 1.1 1.4 1.7 0.3 0.5 0.6 0.7
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