固体火箭技术Issue(6)：819-823,5.DOI:10.7673/j.issn.1006-2793.2014.06.015
基于损伤的HTPB推进剂／衬层界面内聚法则构建
Construction of HTPB propellant/insulation CZM base on damage
摘要
Abstract
In order to raise the precision of the numerical simulation result of HTPB propellant/insulation,firstly,the SLJ test was improved and conducted to obtain the interface parameters. Then the bilinear CZM and the exponential CZM were adopted to conduct the numerical analysis,separately.At last,an influence analysis was made and a customized CZM model was built base on damage variable,which gave the model a significant physical meaning.The result shows that the improved SLJ test can determine the interface parameters of ductile adherends.The CZM law has a similar trend to the simulation curve,and the CZM based on damage can better simulate mode⁃II interface fracture properties between HTPB propellant and insulation than bilinear CZM and exponential CZM.关键词
内聚力模型/推进剂/衬层/数值研究/脱粘Key words
cohesive zone model/propellant/insulation/numerical research/debond分类
航空航天引用本文复制引用
钮然铭,陈雄,周长省,周清春..基于损伤的HTPB推进剂／衬层界面内聚法则构建[J].固体火箭技术,2014,(6):819-823,5.基金项目
装备预先研究基金（20101019）。 （）
