摘要
为了研究适用于描述固体火箭发动机粘接界面的界面力学模型及其修正方法,分别采用虚拟裂纹闭合技术(VCCT)、内聚力模型(CZM)和扩展有限元法(XFEM),模拟了固体火箭发动机推进剂/衬层界面的I型脱粘试验。其中,自编译了多项式型和指数型内聚力模型,采用XFEM-CZM耦合的方法解决了XFEM无法在界面边界扩展的问题,并对比分析了各个模型加载点处的载荷-位移曲线与试验曲线的吻合度,发现利用VCCT、CZM和XFEM方法构建的界面模型可以较好地预估裂纹的扩展过程,能够反映粘接界面的力学特性。同时,为探索模型优化所需研究的参数,通过调整各个模型相关的界面参数值,分析了界面参数对数值仿真曲线的影响,并采用了基于Hooke-Jevees算法的反演识别。研究结果表明,界面力学参数对界面模型具有显著的影响,基于Hooke-Jevees算法的反演识别能够实现对三种模型相关参数的修正。
In order to investigate the interface mechanical models and their correction methods suitable for describing the bonding interface of solid rocket motors, the virtual crack closure technique(VCCT), cohesive zone model(CZM) and extended finite element method(XFEM) were used to simulate the mode I interface debonding test of the propellant/liner interface by the finite element software ABAQUS in this paper, in which the polynomial and exponential cohesive zone models were compiled by myself and the XFEM-CZM coupling method was used to solve the problem that the XFEM model cannot expand at the interface boundary. Moreover, the consistency between the load-displacement curve of each model and the test curve at the loading point was compared and analyzed. It was found that the interface models constructed by VCCT, CZM and XFEM can better predict the crack propagation process and reflect the mechanical properties of the bonding interface. At the same time, in order to explore the parameters needed for model optimization, the influences of interface parameters on numerical simulation curves were analyzed by adjusting the relevant interface parameters of each model, and the inversion identification based on Hooke-Jevees algorithm was carried out. The results show that the interface mechanical parameters have a significant impact on the interface models, and the inversion identification based on Hooke-Jevees algorithm can further modify the relevant parameters of the three models.
作者
王鹏博
郑健
许进升
周长省
WANG Pengbo;ZHENG Jian;XU Jinsheng;ZHOU Changsheng(School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China)
出处
《固体火箭技术》
CAS
CSCD
北大核心
2022年第2期207-215,共9页
Journal of Solid Rocket Technology
基金
江苏省研究生科研与实践创新计划项目(KYCX20_0382)。
关键词
推进剂/衬层界面
虚拟裂纹闭合技术
内聚力模型
扩展有限元
propellant/insulation interface
virtual crack closure technique
cohesive zone model
extended finite element method
