挂载飞行温度边界下固体发动机药柱结构响应分析  

Structural analysis of SRM grains under mounted flight temperature boundary conditions

作　　者：程吉明 李进贤[1] 冯喜平[1] 朱国强[1] CHENG Jiming;LI Jinxian;FENG Xiping;ZHU Guoqiang(Science and Technology on Combustion,Internal Flow and Thermal.structure Laboratory,Northwestern Polytechnical University,Xi’an 710072,China)

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

出　　处：《固体火箭技术》2019年第3期351-355,364,共6页Journal of Solid Rocket Technology

摘　　要：为了研究机载导弹发动机在挂载飞行温度边界条件下药柱的结构响应特性,针对六角星形装药发动机建立了有限元分析模型,采用线粘弹性本构模型描述固体推进剂的力学响应,计算分析了不同挂载飞行高度和飞行速度条件下发动机药柱的结构响应特性,并结合渐近损伤模型分析了发动机在多次挂载飞行条件下药柱的损伤特性。结果表明,药柱最大等效应变随飞行高度的增大而增大,而挂载飞行速度对药柱结构响应影响相对较小。随挂载飞行次数的增加,药柱产生累积损伤,且损伤值随单次挂载飞行时间和飞行次数的增加而逐渐增大。In this paper, the structural response of airborne missiles grain under mounted flight conditions has been analyzed.A finite element analysis model has been established for the star grain of SRM.The structural response of propellant grain under differ ent flight altitudes and flight speeds has been investigated.In addition,the damage characteristics of the propellant grain under multi ple mounted flight conditions have been analyzed in combination with the cumulative damage model. The results show that the maxi mum equivalent strain and stress of the propellant grain increases with the increase of flight altitude.Meantime,the structure re sponse of propellant grain is less dependent on the flight speed.The cumulative damage in the propellant grain would occur during flights,and the damage accumulates gradually with the increase of the mount flight time and the number of flights.

关 键 词：固体发动机 推进剂 挂载飞行 结构响应 累积损伤 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]