论文部分内容阅读
利用有限元法计算了固体火箭发动机绝热层在移动边界条件下的二维温度场.采用碳化层-热解面-原始材料的二维碳化烧蚀模型;推导了将热解气体对流项作为源项的有限元计算方法;采用当量对流换热系数和当量热流的方法处理复杂边界条件.采用无限插值法获得移动边界条件下的三角形网格,提高了网格生成速度和网格质量.计算结果表明,利用有限元法计算固体火箭发动机绝热层的温度场收敛性和稳定性都较好.
The two-dimensional temperature field of the solid rocket motor heat insulation layer under moving boundary condition is calculated by the finite element method. The two-dimensional carbonation ablation model of the carbonization layer-pyrolytic surface-original material is adopted. The convection term of pyrolysis gas is derived as the source Terms of the finite element method; Equivalent convection heat transfer coefficient and equivalent heat flow method to deal with complex boundary conditions. By using the infinite interpolation method to obtain the triangular grid under moving boundary conditions, improve the grid generation speed and grid quality. It shows that the finite element method is better than the finite element method to calculate the temperature field convergence and stability of the solid rocket engine heat insulation layer.