固体火箭发动机喷管结构完整性分析

Analysis on nozzle structure integrality of solid rocket motors

通过计算温度场和应力场,分析了喷管在发动机工作过程中的结构完整性。将燃气简化为一维等熵流,以确定喷管内型面所承受的温度和压强载荷。基于三维有限元模型,计算了喷管的瞬时温度场。然后,将温度场分析结果导入结构分析模型,用点-点接触单元模拟喷管材料之间的接触状态,对温度和压强载荷联合作用下的应力场进行了分析。结果表明,喷管结构是安全的。

Structure integrality of nozzle during the working process of motor was analyzed by calculating temperature field and stress field. In order to determine temperature and pressure on nozzle inner contour, the gas was regarded as one-dimension isoentropic flow. Based on three-dlmension finite element model, transient temperature field in nozzle was calculated. Then analysis results were input into structure model and point-point contact elements were used to simulate contact state of different nozzle materials. Under the temperature and working pressure loading, stress field of nozzle was analyzed. The results show that nozzle structure is of safety.