某固体火箭发动机药柱温度场有限元分析

Finite element analysis of grain temperature field for a solid rocket motor

为探索环境温度变化条件下固体火箭发动机药柱温度场的一种简单而有效的技术途径,利用有限元传热分析法,对某固体火箭发动机在温度循环条件下的燃烧室药柱温度场进行了研究。针对不同的药柱结构分别建立了二维和三维传热模型,通过对比计算值与试验测试值可知,与三维模型相比,二维传热计算方法可提高药柱温度场的计算效率,且计算结果与试验测试值吻合度较高,可满足试验预测要求。因此在工程分析中,为快速得到有效的分析结果,可采用二维传热模型分析发动机药柱温度场,其中二维无翼槽模型适于模拟药柱远离翼槽部位的温度场,二维有翼槽模型适于模拟药柱翼槽部位的温度场。

In order to explore a simple and effective technical approach to the temperature field of solid rocket motor grain under variable ambient temperature, the grain temperature field of a solid rocket motor under temperature circulating test was studied by means of finite element heat transfer analysis.Two-dimension and three-dimension heat transfer models were established for different grain structures.By comparing the calculated results with the test results, the two-dimensional heat transfer method can improve the calculation efficiency of the grain temperature field, and the calculation results are in good agreement with the test results, which can meet the test prediction requirements.Therefore, in the engineering analysis, in order to obtain the effective analysis results quickly, the two-dimensional heat transfer model can be used to analyze the grain temperature field of solid rocket motor.The two-dimensional non-fin grain model is suitable for simulating the temperature field of the grain far away from the fin, and the two-dimensional fin-having grain model is suitable for simulating the temperature field near the grain fin.