固体火箭发动机复合材料壳体裙黏接性能分析

Analysis of the skirt bonding properties of solid rocket motor composite case

采用数值计算方法研究复合材料壳体裙连接结构的黏接性能。通过建立纤维缠绕壳体的有限元模型,采用内聚力模型定义裙黏接面的接触关系,引入黏接界面的损伤失效准则,模拟黏接界面的脱黏行为,以此预测裙连接结构的极限承载。同时,研究壳体的轴向和环向应变及黏接面上的剪应力分布情况,以及弹性层的弹性模量与黏接长度对黏接性能的影响。数值算例表明,计算结果与实验数据相吻合,验证了该方法的正确性。所提方法可用于裙连接结构的优化设计中。

The skirt bonding properties of the composite case was analyzed by using the numerical method. The finite element model of the filament wound case was established. The contact of the skirt bonding interface was defined with the cohesive zone model. The damage failure criterion was employed and the debonding of the interface was simulated to predict the ultimate load of the skirt structure. Moreover,the distributions of the axial strain and the hoop strain on the case and the shear stress in the interface were investigated. The effects of the elastic modulus and the bonding length on the ultimate tensile load were studied. Numerical example shows that the results have a good agreement with the experimental data,which can provide validity for the present method. The proposed method can be applied to the optimal design of the skirt structure.