固体火箭技术2024，Vol.47Issue(4)：478-484,7.DOI:10.7673/j.issn.1006-2793.2024.04.006
HTPB推进剂/衬层单轴拉伸及损伤特性试验研究
Experimental study of uniaxial tensile and damage characteristics of HTPB propellant/liner
冯伟杰 1强洪夫 1王学仁 1邹子杰 1陆传军1
作者信息
- 1. 火箭军工程大学 智剑实验室,西安 710025
- 折叠
摘要
Abstract
In order to study the mechanical behavior of solid motor rectangular bonded specimens with different sizes of open cracks and loading rates during uniaxial tensile process,as well as the microscopic damage characteristics of the propellant/liner/insulation layer in the case of debonding of bonding interface,the uniaxial tensile tests of HTPB(hydroxyl-terminated polybuta-diene)propellant/liner rectangular bonded specimens with opening crack sizes of 15 mm,20 mm,25 mm and 35 mm and loading rates of 3.85 mm/min,77.14 mm/min and 385.71 mm/min were carried out.The mechanical properties of rectangular bonded speci-mens under uniaxial tension were analyzed,and the changes of maximum tensile strength and interface energy under uniaxial tension test were deduced and calculated.And micro-CT was used to extract and analyze the micro-morphology and internal pore character-istics of the fracture end surface of the specimen under the condition of 20 mm opening crack and 77.14 mm/min loading rate.The results show that the mechanical properties of the rectangular specimen under uniaxial tension are related to the loading rate,and the maximum tensile strength is 1.46 MPa under the conditions of 20 mm opening crack size and 385.71 mm/min loading rate,and the interfacial bonding energy reaches 17.66 J.The cross section of propellant mainly exhibits obvious large holes,pores and particles.The propellant damage is mainly manifested as particle matrix dehumidification and pore aggregation.During the tensile process,the damage of liner/insulation layer mesoscopic scanning is mainly manifested as large matrix tearing.关键词
固体火箭发动机/粘接界面/单轴拉伸/细观损伤特性Key words
solid rocket motor/bonding interface/uniaxial tensile/microscopic damage characteristics分类
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冯伟杰,强洪夫,王学仁,邹子杰,陆传军..HTPB推进剂/衬层单轴拉伸及损伤特性试验研究[J].固体火箭技术,2024,47(4):478-484,7.
