摘要
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.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2005年第3期180-183,共4页
Journal of Solid Rocket Technology
关键词
固体推进剂火箭发动机
喷管
有限元法
接触状态
结构完整性
solid propellant rocket engine
nozzle
finite element method
contact state
structure integrity
