立式贮存固体发动机药柱结构有限元分析  

Structural Finite Element Analysis of Solid Motor Grain Under Vertical Storage

作　　者：王鑫 赵汝岩 王康 WANG Xin;ZHAO Ruyan;WANG Kang(Institute Naval Aviation University Department, Yantai 264001, China)

机构地区：[1]海军航空大学,山东烟台264001

出　　处：《兵器装备工程学报》2020年第8期45-51,102,共8页Journal of Ordnance Equipment Engineering

基　　金：原总装备部预研重点基金项目(9140A28010215JB14073)。

摘　　要：为了研究立式固体发动机长时贮存时药柱应力、应变与位移变化规律,结合实际贮存环境,开展了固体发动机装药在温差、重力和内压载荷联合作用下的有限元仿真,对不同加载阶段的发动机仿真结果进行分析,并从应力和位移角度,分别获得了关键点的时间历程变化规律以及关键路径的分布规律。结果表明,联合载荷作用下,药柱向尾部下移,轴向位移从头部至尾部依次减少,药柱最大应力发生在前翼与中孔交汇处,粘接结构最大应力发生在前人工脱粘层根部;且随着贮存时间的增加,药柱应力不断减小,粘接结构应力不断增加,轴向位移不断增加,立式贮存半年发动机满足结构完整性要求。In order to study the variation rules of stress,strain and displacement of solid rocket motor(SRM)under long-time vertical storage,considering its actual storage environment,the finite element simulation of SRM grain of combined loadings of temperature difference,gravity and inner pressure was carried out,and the time process variation rules of key points and distribution rules of key paths were also obtained.The results show that the whole grain tends to sink,the radial displacement from the head to tail decreases successively after initial and long-time gravity,and the biggest equivalent stress of grain occurs on the intersection of fore wing and perforation,the biggest equivalent stress of adhesive structure occurs on the intersection of fore release boot.The stress of grain,adhesive structure and the axial displacement respectively decreases,increases and decreases gradually with the storage time,the motor under vertical storage of half a year satisfies the structural integrity requirements.

关 键 词：固体火箭发动机 装药 立式贮存 有限元分析 结构完整性 

分 类 号：V435.1[航空宇航科学与技术—航空宇航推进理论与工程]