基于统计学的旋转火箭发动机喷管热结构分析  

Thermo-structural analysis based on statistic of spinning SRM nozzle

作　　者：孙林[1] 阎海生 鲍福廷[1] 

机构地区：[1]西北工业大学燃烧热结构与内流场重点实验室,西安710072 [2]淮海工业集团有限公司,长治046012

出　　处：《固体火箭技术》2015年第3期356-361,371,共7页Journal of Solid Rocket Technology

基　　金：国家自然科学基金(51005179)

摘　　要：以某型号固体火箭发动机喷管为研究对象,基于统计学聚类分析方法,研究了该型号喷管内流场、温度场及应力场对旋转的响应。采用流动-传热-热结构的顺序耦合方法,得到了各转速条件下的稳态流场及瞬态温度场、应力场情况。将流场、温度场、应力场原始数据标准化并构造关系矩阵,再通过聚类分析,将结果分别划分为类间差异明显的5类。由于喷管结构与旋转的耦合作用,流场与温度场及应力场聚类分析结果均存在差异。温度场与应力场聚类分析结果一致,说明旋转产生的离心力对喷管应力情况影响不大,热应力仍是该型喷管应力的主要来源。分别研究各类别中任意工况的应力情况,可得到不同战术指标下喷管热应力特征,提高了该型号喷管设计水平。该分析方法得到了统一的变化规律,可有效降低实验成本。另外,对于具有旋转特征的发动机喷管工作过程中的故障诊断、失效行为等的预示有指导意义。Based on clustering analysis, a numerical study on nozzle of a solid rocket motor was conducted to analyze the flow, heat transfer and thermo-structure performance under spinning. By adopting a flow-thermal-structure sequential coupling method, steady flow field,transient temperature field and transient stress fields were obtained. By standardizing original data, making up relation matrix and clustering analysis,5 categories were obtained. Because of the coupling effect of the nozzle structure and spinning, the flow-field result was different from that of both the temperature field and stress field. The consistency of the clustering analysis results of temperature field and stress field shows that centrifugal force has little effect on stress field and thermal expansion is still the main source of nozzle stress. By analyzing either condition of the categories, thermal-stress property can be obtained for different tactical indexes.The analysis method obtains unified changing law, which can reduce experimental cost. It can also benefit fault di-agnosis and failure judgment during nozzle working process with rotation characteristic.

关 键 词：统计学 聚类分析 旋转 固体火箭发动机喷管 流场仿真 热结构耦合 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]