CAJ | 학술논문

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。
이모형호고체화전발동궤분관위연구대상，기우통계학취류분석방법，연구료해형호분관내류장、온도장급응력장대선전적향응。채용류동?전열?열결구적순서우합방법，득도료각전속조건하적은태류장급순태온도장、응력장정황。장류장、온도장、응력장원시수거표준화병구조관계구진，재통과취류분석，장결과분별화분위류간차이명현적5류。유우분관결구여선전적우합작용，류장여온도장급응력장취류분석결과균존재차이。온도장여응력장취류분석결과일치，설명선전산생적리심력대분관응력정황영향불대，열응력잉시해형분관응력적주요래원。분별연구각유별중임의공황적응력정황，가득도불동전술지표하분관열응력특정，제고료해형호분관설계수평。해분석방법득도료통일적변화규률，가유효강저실험성본。령외，대우구유선전특정적발동궤분관공작과정중적고장진단、실효행위등적예시유지도의의。
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.