摘要
为了预测推进剂药柱中裂纹的起裂和扩展过程,建立了HTPB推进剂的粘聚区本构模型和数值仿真方法。粘聚区本构模型参数分别使用单边裂纹拉伸实验、单轴拉伸实验和数值仿真的方法获取。在有限元分析软件ABAQUS基础上开发出粘结单元,建立了模拟复合型裂纹扩展的嵌入粘结单元方法。进行了复合裂纹试样拉伸实验,获得了裂纹扩展路径和载荷时间曲线,同时用数值仿真方法对结果进行了预测。通过仿真和实验结果对比发现,所建立的粘聚区模型可完整地模拟出HTPB推进剂的失效过程;嵌入粘结单元的方法可准确地预测复合型裂纹的扩展路径。
In order to predict the crack initiation and propagation in propellant grain, a cohesive zone constitutive model and a numerical simulation method were established. The cohesive zone constitutive parameters were obtained by single edged notched sample tension test, uniaxial tension test, and numerical simulation respectively. The cohesive element was developed based on finite element analysis software ABAQUS, and an embedding cohesive element method was established to simulate the mixed-mode crack propagation. A mixed-mode crack sample tension test was conducted, and the crack propagation trajectory and load-time curve were obtained. Meanwhile,a prediction was made by numerical simulation. By comparison between simulated and experimental results, the established cohesive zone model can model the failure process for HTPB propellant;the embedding cohesive element method can predicate the mixed-mod crack propagation trajectory well.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2013年第1期89-93,共5页
Journal of Solid Rocket Technology
基金
装备预先研究项目(No.20101019)
关键词
推进剂
断裂
有限元法
propellant
fracture
finite element method
