一种多孔热解材料传热过程计算方法

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一种多孔热解材料传热过程计算方法

一种多孔热解材料传热过程计算方法，包括推导复合材料内部各层质量、动量及能量守恒方程，实现多孔介质结构内部固相与气相的质量、动量及能量方程的求解，得到固相温度Ｔ、密度ρ、导热系数ｋ_ｓ、气相密度ρ_ｆ、导热系数ｋ_ｆ、孔隙率φ、热解气体压力ｐ、分解气体溢出速度ｕ_ｎ。本发明能对不同种类的碳化热解材料传热过程进行分析，能三维显示材料内部热解气体热解过程，得到热解气体压力、速度分布，以及热解后形成的多孔介质结构温度分布云图。通过计算多孔热解材料传热过程，解决了高超声速飞行器复合材料温度及舱内环境温度难于准确计算的问题。

Calculation method for heat transfer process of porous pyrolysis material

The invention relates to a calculation method for a heat transfer process of a porous pyrolysis material. The calculation method comprises the following step: deriving the mass, momentum and energy conservation equations of various layers inside a composite material to realize the solution of mass, momentum and energy equations of a solid phase and a gas phase inside a porous medium structure, thus obtaining solid phase temperature T, density ρ, thermal conductivity k_s, gas phase density ρ_f, gas phase thermal conductivity k_f, porosity φ, pyrolysis gas pressure p and decomposition gas overflow velocity u_n. According to the calculation method provided by the invention, the heat transfer processes of different kinds of carbonized pyrolysis materials can be analyzed, and the pyrolysis process of the pyrolysis gas inside the material can be displayed in a three-dimensional manner to obtain the pyrolysis gas pressure, velocity distribution and a temperature distribution cloud diagram of the porous medium structure formed after pyrolysis. By calculating the heat transfer process of the porous pyrolysis material, the problem that the temperature of the composite material of a hypersonic flight vehicle and the ambient temperature inside a cabin are difficult to accurately calculate is solved.