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再入钝锥体烧蚀热防护内部热响应的数值仿真

张涛 陈德江

张涛, 陈德江. 再入钝锥体烧蚀热防护内部热响应的数值仿真[J]. 航空动力学报, 2013, 28(10): 2248-2255.
引用本文: 张涛, 陈德江. 再入钝锥体烧蚀热防护内部热响应的数值仿真[J]. 航空动力学报, 2013, 28(10): 2248-2255.
ZHANG Tao, CHEN De-jiang. Numerical simulation of internal thermal response of ablative thermal protection for reentry spacecraft[J]. Journal of Aerospace Power, 2013, 28(10): 2248-2255.
Citation: ZHANG Tao, CHEN De-jiang. Numerical simulation of internal thermal response of ablative thermal protection for reentry spacecraft[J]. Journal of Aerospace Power, 2013, 28(10): 2248-2255.

再入钝锥体烧蚀热防护内部热响应的数值仿真

Numerical simulation of internal thermal response of ablative thermal protection for reentry spacecraft

  • 摘要: 研究了烧蚀热防护系统内部热响应的计算模型和计算方法.采用碳化层-热解面-原始材料层模型,建立碳基材料内部热响应物理模型和数学模型,利用有限元法分析和计算再入目标热防护系统轴对称内部热响应.着重研究和分析了轴对称烧蚀过程中热解气体质量流率计算方法和传热机制.将热解气体与碳化层之间的对流换热处理为源项,通过保证刚度矩阵和形函数矩阵的正定对称性可以加速温度场计算收敛.计算表明:热解气体的质量流量主要由厚度方向构成,占80%以上;头部驻点附近最大烧蚀厚度接近10mm,需要采用抗烧蚀能力强的碳-碳材料,身部烧蚀量小于2mm,可以采用密度较小的碳-酚醛材料.

     

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出版历程
  • 收稿日期:  2012-10-26
  • 刊出日期:  2013-10-28

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