为研究变温环境对固体火箭发动机的影响,基于热粘弹性模型和累积损伤模型,对某HTPB推进剂药柱在变温环境下的应力响应和累积损伤进行了分析计算。结果表明,药柱损伤随着环境严酷度的增大而增大,温度冲击环境比温度循环对药柱产生的损伤要大。在温度冲击环境下,温度范围、推进剂材料参数对药柱的损伤有较大的影响,平衡模量和膨胀系数的影响有相同的趋势。研究结果可为固体火箭发动机的贮存和使用寿命预估提供技术支持。

In order to study the effects of changing temperature condition on solid rocket motor, the thermal stress of solid rocket motor under temperature cycling and temperature shock was analyzed. The cumulative damage model of HTPB propellant grain was built and the cumulative damage of this grain under temperature changing condition was computed. The results indicate that, the damage degree increases with the strictness of environments. The damage under temperature shock was greater than that of under temperature cycling. Under temperature shock condition, the cumulative damage of grain was influenced by temperature range and parameters of propellant, and the effect of equilibrium modulus of propellant on cumulative damage was as same as the effect of expansion coefficient. The results can afford available reference for research on properties of HTPB propellant in storage and use.