固体火箭技术2024，Vol.47Issue(4)：458-467,10.DOI:10.7673/j.issn.1006-2793.2024.04.004
考虑温度与围压的HTPB固体推进剂细观结构损伤演化机制
Mesostructure damage evolution mechanism of HTPB solid propellant considering temperature and pressure
摘要
Abstract
To investigate the influence of loading environment on the damage evolution mechanism of solid propellant,the me-sostructure of solid propellant under the different porosity and strain rates was studied by means of tensile test,SEM and micro-CT.The damage characteristics of propellants were quantitatively analyzed under different temperatures,confining pressures and strain rates.The results show that the maximum tensile strength and elongation of HTPB propellant increase significantly at high confining pressure(10 MPa).Under low temperature and high confining pressure(-45℃,10 MPa),"dewetting"damage is suppressed,which makes the interface bonding intimately between AP particles and matrix,and the microcracks are more likely to aggregate to form cavities,and then the particle breakage damage mechanism occurs.In the meso-deformation stage,cracks appear prior to reac-hing the maximum tensile strength on the stress-strain curve.In the macro-crack stage,only a small percentage of the pores exhibit high sphericity,while most of the pores are irrqular and low-sphericiyt damage crackes,accounting for approximately 75% .The re-lationship between damage pore diameter and sphericity conforms to power-law correlation,with a power-law index of-0.246.In the failure stage,the damage mechanism of propellant includes particle breakage,"dewetting"damage and matrix adhesion.关键词
HTPB推进剂/细观结构/损伤演化机制/"脱湿"损伤/孔隙率Key words
HTPB solid propellant/mesostructure/damage evolution mechanism/dewetting/porosity分类
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张慧慧,李海阳,申志彬..考虑温度与围压的HTPB固体推进剂细观结构损伤演化机制[J].固体火箭技术,2024,47(4):458-467,10.基金项目
国家自然科学基金(12372203,12302028) （12372203,12302028）
中国博士后科学基金(2022M723916,2023M744327). （2022M723916,2023M744327）
