基于SEM原位拉伸的HTPB推进剂/衬层粘接界面破坏过程分析  

HTPB Propellant/Liner Adhesive Interface Failure Behavior Based on SEM In Situ Tension

作　　者：杨明[1] 李高春 邱欣[1] 姜爱民 

机构地区：[1]海军航空工程学院研究生管理大队,山东烟台264001 [2]海军航空111程学院飞行器工程系,山东烟台264001

出　　处：《含能材料》2015年第6期553-557,共5页Chinese Journal of Energetic Materials

摘　　要：采用扫描电镜（SEM）原位拉伸试验系统对端羟基聚丁二烯（HTPB）推进剂/衬层粘接界面试件拉伸破坏过程进行了观察,实时采集了界面变形破坏过程的SEM图像,结合粘接界面的宏观应力-应变曲线,分析其在拉伸过程中细观变形破坏机理。结果表明：推进剂/衬层粘接界面拉伸的过程可以分为斜率较大的线性段（应变为0~5%）、斜率较小的线性段（应变为5%~25%）、非线性段（应变为25%~29%）和破坏段（应变为29%~35%）四个阶段,且验证试验所用试件的推进剂/衬层粘接界面分别在应变为25%和30%达到极限应力。研究发现试件内部颗粒的脱湿和基体间的脱粘是导致其力学性能变化及失效的主要原因,同时,可用推进剂相颗粒脱湿尺寸随应变的变化表现粘结界面失效的变化规律：脱湿尺寸随应变线性增大表示粘接界面还未破坏,当脱湿尺寸增大速率减小或不增大时,表示粘接界面已经破坏。The damage process of hydroxyl-terminated polybutadiene（HTPB）propellant/liner adhesive interface was observed by scanning electron microscope（SEM）in situ tension system.The real-time SEM images of deformation and failure for interface were collected.The micro mechanism of deformation and failure of adhesive interface was analyzed combining with the macroscopic stress（σ）-strain（ε）curve.Results show that the tensile failure process of adhesive interface can be separated into four stages：l inear interval with larger slope（0ε5%）,linear interval with smaller slope（5%ε25%）,nonlinearity interval（25%ε29%）and failure interval（29%ε35%）.The two specimens used in verification test reach their ultimate stress when strain arrives at 25% and 30%,respectively.It is also found that dehumidification of internal grain and interfacial debonding have much to do with the change of mechanical property and interface failure.And the interface failure can be reflected by the laws between dehumidification size and strain：when dehumidification size increases linearly with strain,the specimen does not failure.If the increasing rate decreases or the size does not increase,the specimen are damaged.

关 键 词：端羟基聚丁二烯(HTPB)推进剂 粘接界面 微观 脱湿 破坏 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]