摘要
考虑到法向热流远高于气流方向热流的特征,烧蚀层简化为沿法线方向的一维移动相变边界传热模型,用有限差分法求解,而弹身、弹翼等结构则用三维有限元热传导模型求解。为了将专用的一维移动相变边界热传导分析程序与通用的三维结构有限元热传导分析程序相结合,引入了涂层—结构—涂层交替计算方法。通过交替计算,最终使烧蚀层与结构的界面满足温度相等、热流平衡的传热协调条件。采用自行编制的烧蚀层热传导计算程序结合通用有限元程序(NASTRAN)计算带有烧蚀防热涂层的弹身和弹翼两个算例,验证了交替计算的收敛性。
Considering that the heat flux of normal direction is much greater than that of flow direction,the mathematic model of the ablative protection layer is simplified as an one-dimensional heat transfer model with moving boundary and phase transition.The ablation is solved by using the finite difference method.The heat transfer of the structure is solved by using the three-dimension finite element method（NASTRAN）.In order to combine the two different programs,an alternative algorithm between the ablative protection layer and the structure is introduced.With this algorithm,interface temperature and heat flux could satisfy the thermal equilibrium condition finally.Convergence and effectiveness of this alternative algorithm are validated by two examples,missile body and missile wing.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2011年第8期1854-1858,共5页
Journal of Astronautics
关键词
烧蚀
热防护
瞬态热传导
Ablation
Thermal protection
Transient heat transfer
