固体火箭发动机喷管结构缝隙设计

推进技术 ›› 2005, Vol. 26 ›› Issue (5): 448-451.

固体火箭发动机喷管结构缝隙设计

田四朋,唐国金,李道奎,袁端才

国防科技大学航天与材料工程学院湖南长沙410073;国防科技大学航天与材料工程学院湖南长沙410073;国防科技大学航天与材料工程学院湖南长沙410073;国防科技大学航天与材料工程学院湖南长沙410073

发布日期:2021-08-15

Gap design of solid rocket motor nozzle structures

Inst.of Aerospace and Material Engineering,National Univ.of Defence Technology,Changsha 410073,China;Inst.of Aerospace and Material Engineering,National Univ.of Defence Technology,Changsha 410073,China;Inst.of Aerospace and Material Engineering,National Univ.of Defence Technology,Changsha 410073,China;Inst.of Aerospace and Material Engineering,National Univ.of Defence Technology,Changsha 410073,China

Published:2021-08-15

摘要/Abstract

摘要： 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-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。

关键词: 固体火箭发动机;三维分析+;喷管;缝隙+;接触应力

Abstract: 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 isentropic flow,and temperature field of nozzle was computed 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 multi-time computational results,and some modification suggestions,which are available for designers of solid rocket motor nozzle,were presented by the tendency.

Key words: Solid propellant rocket engine;Three-dimension analysis~+;Nozzle;Gap~+;Contact stress

田四朋,唐国金,李道奎,袁端才. 固体火箭发动机喷管结构缝隙设计[J]. 推进技术, 2005, 26(5): 448-451.