摘要
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 of insulation layer of solid rocket motor with moving boundary condition was computed. Charred layer-pyrolysis surface original material model was applied and temperature computation formulas were calculated by taking convection heat transfer between pyrolysis gas and charred layer as heat source. The complicated boundary conditions were transformed into equivalent convection heat transfer and equivalent heat flux. Triangle grid was produced by transfinite interpolation to quicken grid generation and improve the quality of grid. The calculation results show that the astringency and stability of finite element method is good in calculating the temperature of insulation layer of solid rocket motor.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2009年第6期1407-1412,共6页
Journal of Aerospace Power
关键词
温度场
固体火箭发动机
绝热层
烧蚀
有限元
temperature
solid rocket motor
insulation layer
ablation
finite element method
