端羟基聚丁二烯推进剂/衬层脱粘的断裂机理与断裂能获取研究

doi:10.3969/j.issn.1000-1093.2014.07.008

摘要/Abstract

摘要： 推进剂/衬层界面脱粘是破坏固体火箭发动机装药结构完整性的主要形式之一。采用双悬臂夹层梁实验对端羟基聚丁二烯(HTPB)推进剂/衬层粘接界面的I型断裂进行研究，实验观察到裂纹尖端存在包含孔洞和纤维的银纹损伤区，裂纹萌发和扩展本质上是局部银纹萌生、面增厚和微纤断裂。界面脱粘的失效机理则是尖端近处孔洞的形成和合并，典型的界面失效模式包含胶黏剂的内聚破坏、界面破坏和混合破坏。裂纹稳定传播时，裂尖的损伤区形状与外界对其施加的约束有关。采用有效裂纹长度的概念可以修正裂尖塑性变形和钝化的影响，较为准确地获取了I型断裂能。

关键词: 兵器科学与技术, 推进剂/衬层界面, 裂纹萌发, 裂纹扩展, 双悬臂夹层梁

Abstract: Debonding along the propellant/liner interface is one of the major forms in which rocket motor structural integrity can fail. The double cantilever sandwich beam experiments are performed to investigate the mode-I fracture of HTPB propellant/ linear interface. These experiments show that a craze damaged zone which is consisted of voids and fibers exists in the crack tip.The crack initiation and extension are essentially to be local crazing initiation, thickening and micro-fiber fracture.The failure mechanism of the interfacial debond is the growth and coalescence of near-tip voids, while the typical fracture mode of the interface includes the cohesive failure within the adhesive, interfacial failure and mixed failure. The shape of the damaged zone ahead of the crack tip is found to be related to the constraints imposed by the adjacent components when the crack propagates stably. The concept of the effective crack length could be used to eliminate the effects of the plastic deformation and blunting ahead of the crack tip on the fracture energy.

Key words: ordnance science and technology, propellant/liner interface, crack initiation, crack extension, double cantilever sandwich beam

中图分类号:

V512⁺.2

周清春，鞠玉涛，韦震，周长省. 端羟基聚丁二烯推进剂/衬层脱粘的断裂机理与断裂能获取研究[J]. 兵工学报, 2014, 35(7): 990-995.

ZHOU Qing-chun， JU Yu-tao， WEI Zhen， ZHOU Chang-sheng. Investigation of Fracture Mechanism and Fracture Energy of HTPB Propellant/liner Interface Debonding[J]. Acta Armamentarii, 2014, 35(7): 990-995.

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