固体火箭技术Issue(3)：372-377,395,7.DOI:10.7673/j.issn.1006-2793.2015.03.014
冲击载荷下CMDB推进剂断裂性能实验研究
Experimental research on CMDB propellant fracture under impact load
摘要
Abstract
Fracture occuring in solid propellant under high impact load is one of the main ways leading to the failure of the rocket motor structural integrity.In this paper, the impact fracture experiments of CMDB propellant were performed with the SHPB technology. The experimental data was directly imported into the simulation model to verify whether the specimen is under the dy⁃namic balance condition, which is the method of simulation⁃experiment,and the mode I dynamic initiation fracture toughness was obtained. The fracture surface morphology of specimens were examined by scanning electron microscope (SEM).The experiment re⁃sults indicate that the CMDB propellant is a significant loading⁃rate⁃dependent material between 60 000 and 100 000 MPa·m1/2/s, and the dynamic fracture initiation toughness threshold value ( 3. 96 MPa · m1/2 ) occuring after the loading rate reaches up to 100 000 MPa·m1/2/s.The CMDB propellant shows brittle fracture and loading⁃rate⁃dependent characteristic under dynamic loads are directly related to the degree of damage of matrix and AP particles impaired by stress wave.关键词
固体推进剂/高过载冲击/动态起裂韧性/率敏感性Key words
solid propellant/high impact load/dynamic initiation fracture toughness/rate sensitivity分类
航空航天引用本文复制引用
汪文强,陈雄,郑健,赵超,许进升,周长省..冲击载荷下CMDB推进剂断裂性能实验研究[J].固体火箭技术,2015,(3):372-377,395,7.基金项目
总装重点预研项目（20101019）。 （）
