固体火箭发动机喷管结构缝隙设计

通过热和结构计算，对固体火箭发动机喷管缝隙设计进行了分析。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力载荷．基于三维有限元模型．计算了喷管的瞬时温度场。导入温度场分析结果，并用点一点接触单元模拟不同材料之间的接触状态，计算了温度和压力载荷联合作用下喷管的位移场和应力场。综合多个时刻的计算结果得到发动机工作过程中喷管结构缝隙和接触应力的变化趋势，并据此对设计缝隙提出了修改意见，结果可为发动机喷管设计提供参考。

Gap design of solid rocket motor nozzle structures

Gap design of solid rocket motor nozzle was analysized through thermal and structure analysis. In order to determine thermal loading and working pressure of nozzle inner contour, the gas was regarded as one dimensional isentropie flow, and temperature field of nozzle was colnputed based on three-dimension finite element model. Thermal analysis result was imported into structural model and point-point contact elements were used to simulate contact state of different material, and displacement and stress field of nozzle was calculated under thermal loading and working pressure. Variation tendency of nozzle gap and contact stress was obtained in terms of lnuhi-time computational results, and some modification suggestions, which are available for designers of solid rocket motor nozzle, were presented by the tendency.