摘要
基于固体火箭发动机药柱的热黏弹模型,利用有限元方法对不同外界环境温度降温条件以及材料属性下的药柱温度应力进行了分析,研究了不同降温幅度、降温速率、初始温度及推进剂平衡模量、泊松比、热膨胀系数对药柱温度应力的影响.结果表明,降温幅度、降温速率、初始温度对药柱温度应力影响显著,但不管降温幅度、降温速率、初始温度如何,温度应力随着温度的下降不断增加.在温度下降初期,温度应力增长缓慢,而在后期温度应力增长较快;推进剂材料参数对危险点的应力也有显著影响,推进剂膨胀系数和平衡模量对应力的影响有相同的趋势.
The stress of propellant grain under different cooling conditions was analyzed by using finite element method in consideration of thermo-viscoelasticity of propellant grain.The effects of cooling range,cooling rate,initial temperature and modulus,Poisson＇s ratio,thermal expansion on temperature stress were studied.The results indicate that,the cooling range,cooling rate and initial temperature distinctly influence the temperature stress field.The thermal stress increases continuously with temperature cooling whatever changes of these factors.At early stage of cooling course,the temperature stress increases slowly,but then rapidly at late stage of cooling course.The temperature stress is influenced distinctly by the material parameter of propellant.The effect of the change of thermal expansion on stress is the same as that of the change of modulus.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2010年第11期2606-2611,共6页
Journal of Aerospace Power
关键词
固体火箭发动机
药柱
有限元方法
降温
热应力
黏弹性
solid rocket motor； grain； finite element method； cooling； thermal stress； viscoelasticity；
