本文对航天飞机机头的碳-碳热防护层,在再入的气动加热条件下,采用气动热化学烧蚀模型建立烧蚀方程,采用单元体能量平衡法建立各向异性、变物性材料的瞬态热传导方程,通过坐标变换处理烧蚀移动边界,并从物理平面转换到计算平面中去,然后成功地进行了烧蚀和温度场的耦合求解。计算结果表明了航天飞机机头碳-碳热防护层中的烧蚀和温度分布规律。 In this paper, the carbon-carbon thermal protection layer of a space shuttle’s nose is aerodynamically heated by reentrant aerodynamic thermo-chemical ablation model to establish the ablation equation. The energy balance method of the unit body is used to establish the anisotropic and variable material Transient heat conduction equations are transformed by coordinate transformation to ablate the moving boundary and transformed from the physical plane to the computational plane. Then, the coupling between ablation and temperature field is successfully solved. The calculation results show the ablation and temperature distribution of the spacecraft’s carbon-carbon thermal protection layer.