固体火箭发动机粘接界面剪切蠕变特性分析与快速预测模型

Characteristic analysis and rapid prediction model of shear creep at bonding interface of solid rocket motors

固体火箭发动机在立式贮存期间,受自重载荷影响,在侧壁粘接界面会产生剪切蠕变行为,威胁发动机的结构安全性和贮存寿命。为研究粘接界面剪切蠕变特性,对某型发动机剪切界面试验件进行了多种温度与应力下的剪切蠕变实验,获得其剪应变-时间关系,分析了粘接界面力学性能随温度与剪切蠕变载荷变化的响应和规律,最终构建了一种适用于线性粘弹性阶段的发动机粘接界面剪切蠕变快速预测模型。结果表明,该快速预测模型构建方式简单,且预测值与实验值相差低于10%,可以较好地预测线性粘弹性阶段粘接界面短期蠕变行为。

During vertical storage of solid rocket motors,shear creep behavior occurred at the sidewall bonding interface due to self-weight load,threatening the structural safety and storage life of the motor.To study the shear creep characteristics of the bonding interface,shear creep tests were conducted on a certain motor shear interface test piece under various temperatures and stresses,and the shear strain-time relationship was obtained.The response and regularity of the mechanical properties of the bonding interface to temperature and shear creep load changes were analyzed,and a rapid prediction model for the shear creep of the bonding interface in the linear viscoelastic stage was finally constructed.The results show that the rapid prediction model is simple to construct and the difference between the predicted value and the experimental value is less than 10%,and it can predict the short-term creep behavior of the adhesive interface in the linear viscoelastic stage.