固体火箭技术Issue(3)：356-361,371,7.DOI:10.7673/j.issn.1006-2793.2015.03.011
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
摘要
Abstract
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 re⁃lation 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Key words
statistics/cluster analysis/spinning/SRM nozzle/flow field simulation/thermo-structure coupled analysis分类
航空航天引用本文复制引用
孙林,阎海生,鲍福廷..基于统计学的旋转火箭发动机喷管热结构分析[J].固体火箭技术,2015,(3):356-361,371,7.基金项目
国家自然科学基金（51005179）。 （）
