蜂窝增强低密度硅基烧蚀防热材料性能
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1.航天材料及工艺研究所,北京 100076;2.北京空间飞行器总体设计部,北京 100094

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TB332

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Thermo-mechanical Properties of Honeycomb-enhanced Silica-based Low Density Ablative Thermal Protection Material
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Affiliation:

1.Aerospace Research Institute of Materials & Processing Technology,Beijing 100076;2.Beijing Institute of Spacecraft System Engineering, Beijing 100094

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    摘要:

    高速再入飞行器通常采用烧蚀防热材料作为外表面大面积的热防护材料。本文对两种蜂窝增强低密度硅基烧蚀防热材料的力学性能、热物理性能和烧蚀性能进行了测试,并结合试验结果对烧蚀机理进行了研究分析。结果表明,材料的密度越高、拉伸强度就越高,但拉伸模量相近;两种材料的隔热性能参数都较低。两种材料在不同热流密度条件下的电弧风洞烧蚀后退速率都较低,在部分烧蚀条件下有轻微膨胀。两种材料的烧蚀背温都较低,烧蚀表面形貌良好,能满足设计指标要求,是一种适用范围较广的烧蚀防热材料。

    Abstract:

    Ablative thermal protection material is usually applied as the heat shield of high speed reentry vehicle. The mechanical properties, thermophysical properties and ablation properties of two kinds of honeycomb enhanced silica-based low density ablative thermal protection materials are investigated, with the analysis of the ablation mechanism. The results show that the tensile strength increases with the density, with the same tensile modulus. The thermal insulation performance parameters of the two kinds of materials are both relatively low. The linear ablation rates of the two kinds of materials are relatively low under different heat flux in the arc wind tunnel, and some materials expand slightly under certain conditions. The back temperature of two materials are relatively low, with a good surface morphology. The research shows that the materials meet the target requirements with a wide range of applications.

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方洲,梁馨,邓火英,董彦芝,代晓伟.蜂窝增强低密度硅基烧蚀防热材料性能[J].宇航材料工艺,2021,51(5):79-83.

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历史
  • 收稿日期:2021-05-27
  • 最后修改日期:2021-07-10
  • 录用日期:2021-06-30
  • 在线发布日期: 2021-10-26
  • 出版日期: