低温状态点火瞬间固体发动机药柱结构响应分析  

Structural analysis of solid rocket motor grain at ignition transient under low temperature

作　　者：宋仕雄 史宏斌[1] 刘中兵[1] 沙宝林[1] SONG Shixiong;SHI Hongbin;LIU Zhongbing;SHA Baolin(The 41st Institute of the Fourth Academy of CASC,Xi＇an 710025,China)

机构地区：[1]中国航天科技集团公司四院四十一所,西安710025

出　　处：《固体火箭技术》2018年第3期278-283,共6页Journal of Solid Rocket Technology

摘　　要：采用线粘弹性模型,针对固体发动机低温状态点火瞬间的推进剂相关力学特性对固体发动机药柱进行了低温状态点火瞬间的结构响应分析。点火瞬间的推进剂模量变化不大,对药柱的结构响应影响较小;而推进剂在不同状态下其泊松比并非一定值:低温状态下推进剂泊松比的值较小,点火升压下推进剂泊松比迅速增大至接近0.5,推进剂泊松比的微小变化对药柱的结构响应有很大影响。分别计算分析了低温状态点火瞬间推进剂泊松比为定值时与推进剂泊松比为非定值时的药柱结构响应仿真结果。分析结果表明,低温状态点火瞬间的药柱应变呈不断增高而应变率则逐渐降低;计算得圆管型模拟发动机的安全系数为1.48,这比推进剂泊松比为定值时计算得到的安全系数的值减小了13.5%。Based on the linear viscoelastic model,the structural response of the grain of the SRM at ignition transient under low temperature was analyzed.The modulus of the propellant was almost constant and had little effect on the structural response of the grain at ignition transient.The Poisson ratio of the propellant in different states was not necessarily constant： it was relatively small under low temperature,and could be increased rapidly to near 0.5 under higher pressure.The small change of the Poisson＇s ratio of the propellant had a great effect on the structural response of the grain.The simulation results of structural response of the grain when the Poisson＇s ratio of the propellant was fixed at ignition transient under low temperature and the Poisson＇s ratio of the propellant was not constant were calculated and analyzed.The results show that the strain of the propellant grain is increased,whereas the strain rate is decreased.The safety factor of the SRM is calculated to be 1.48,which is 13.5% lower than the safety factor calculated when the Poisson＇s ratio of the propellant is fixed.

关 键 词：低温点火 固体火箭发动机 药柱 结构完整性 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]