温度载荷下装药内外径比和长径比对结构完整性影响的规律研究  

Research on influence of diameter ratio and length-diameter ratio on structural integrity of solid propellant under temperature loading

作　　者：于洋[1] 王宁飞[2] 张平[2] 

机构地区：[1]大连海事大学机电与材料工程学院,大连116026 [2]北京理工大学宇航科学技术学院,北京100081

出　　处：《航空动力学报》2007年第9期1565-1568,共4页Journal of Aerospace Power

基　　金：国防基础科研项目(K1305060614)

摘　　要：在固体火箭发动机装药设计中通常将药柱的外径与内径之比定义为m数(m=R/r)为研究装药设计参数m数和药柱长径比在温度载荷下对装药结构完整性的影响,采用基于Total Lagrangian方法的热粘弹性大变形增量本构关系,通过选取9种m数以及8种药柱长径比,共72个计算模型,对装药结构完整性进行了计算,结果表明温度载荷下药柱最大Von Mises等效应力、应变值受药柱m数以及长径比共同影响.并得出当长径比大于3时,药柱最大等效应力、应变值主要取决于m数的结论.To investigate the influence of number m and length-diameter ratio on structural integrity of solid propellant under temperature loading,the thermoviscoelastic large deformation incremental constitutive equation was derived from Total Lagrangian method. Nine different numbers m and eight length-diameter ratios for calculation 72 models were selected to measure the effects on the structural integrity. The results show that, number rn and length-diameter ratio have cooperative effects on the maximum value of equivalent Von Mises stress and strain. If the length-diameter ratio is larger than 3, it＇s concluded that the maximum value of equivalent Von Mises stress and strain are mainly determined by number m of solid propellant.

关 键 词：航空、航天推进系统 固体火箭发动机 结构完整性 内外径比 长径比 热粘弹性 大变形 增量本构关系 

分 类 号：V435.21[航空宇航科学与技术—航空宇航推进理论与工程]