发动机喷管喉衬烧蚀及热结构工程计算  

Engineering calculation for erosion and thermal structure of throat-insert of a SRM nozzle

作　　者：付鹏[1] 蹇泽群[1] 张钢锤[1] 高波[1] 

机构地区：[1]中国航天科技集团公司四院设计部,西安710025

出　　处：《固体火箭技术》2005年第1期15-19,共5页Journal of Solid Rocket Technology

摘　　要：给出了一种理论模型和基本计算方法。采用有限元法对某固体火箭发动机喉衬结构的烧蚀量、瞬态温度场和应力场进行了理论计算,计算结果与实测值比较一致,喉部直径实测值与计算值相对误差约为 2%。A theoretical model and fundamental calculation method were developed. By using finite element method, the erosion, instantaneous temperature field and stress field for the throat-insert of a solid rocket motor nozzle were calculated theoretically. The calculation results of the erosion accord with actual measurement value. The relative error between the actual measurement value of throat diameter and the calculation value is about 2%.

关 键 词：发动机喷管 工程计算 喉衬 热结构 固体火箭发动机 瞬态温度场 计算方法 理论模型 有限元法 理论计算 计算结果 相对误差 实测值 烧蚀量 应力场 计算值 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程] TB115[理学—数学]