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.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
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)
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
aerospace propulsion system
solid rocket motor
structural integrity
diameter ratio
length-diameter ratio
thermoviscoelasticity
large deformation
incremental constitutive equation