文中以固体火箭发动机复合喷管为研究对象,测试了背壁材料的热解响应特性及随温度及压强变化的接触热阻,用有限元法进行了二维轴对称喷管瞬态热分析。然后给出考虑与不考虑背壁热解效应情况下的温度场计算结果,并进行了验证试验。最终将计算结果与实验结果进行比较,结果表明,背壁热解效应可以降低喉衬组件的温度,考虑背壁热解效应的喉衬组件温度场分析更符合实验值。

In this paper, composite nozzle of solid rocket motor was considered as research object, pyrolysis characteristics of back surface material and contact thermal resistance changing with temperature and pressure were tested, finite element method was used for transient thermal analysis of two-dimensional axisymmetric nozzle. The pyrolytic effect of the back surface was considered, then calculation results of the temperature field with expected and unexpected pyrolytic effect of the back surface were given, and validation test was done. Finally, the calculated results were compared with the experimental results, the results show that, pyrolysis effect of the back surface can reduce temperature of the throat lining components, and temperature field analysis with consideration of pyrolysis effect of the back surface of the throat lining components accords more with the experimental value.