固体发动机低温点火条件下药柱结构完整性分析  

Structural integrity analysis on grains of solid rocket motor at low temperature ignition

作　　者：刘中兵[1] 周艳青[1] 张兵[2] 

机构地区：[1]中国航天科技集团公司四院四十一所,西安710025 [2]中国航天科技集团公司四院,西安710025

出　　处：《固体火箭技术》2015年第3期351-355,共5页Journal of Solid Rocket Technology

摘　　要：分别采用三维弹性和三维线粘弹性模型,对固体发动机药柱在低温和点火升压2种载荷下的结构完整性进行了计算分析。研究了推进剂弹性模量E、泊松比μ、药柱m数等参数对结构完整性的影响。结果表明,在发动机低温点火条件下,药柱内孔表面是最危险部位;固化降温和点火升压2种载荷引起的最大等效应变在此是相互叠加的;药柱m数对固化降温和点火升压载荷下的应变分布有重要影响。Using three-dimensional linear elasticity and viscoelasticity models,the calculation analysis of structural integrity for solid rocket motor grains at low temperature and ignition pressurization loading was completed. The influences of propellant elastic modulus E,Poisson ratio μ,m number （ the ratio of outer diameter to inner diameter） of grain on calculation results were studied. The results show that grain perforation surface is the most dangerous position at low temperature ignition pressurization. The maxi-mums of equivalent strain induced by low temperature and ignition pressurization loading are added to each other at grain perforation surface.The m number of grain has important influence on the strain distribution induced by low temperature and ignition pressurization loading.

关 键 词：固体火箭发动机 推进剂药柱 低温点火 结构完整性 粘弹性 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]