摘要
高过载冲击载荷下,固体推进剂出现断裂行为是影响箭弹发动机装药结构完整性的重要原因之一。采用霍普金森实验技术（SHPB）,对CMDB推进剂进行了冲击断裂实验。运用实验-仿真的方法,将实验数据直接输入仿真模型中,验证了实验条件下试件满足动态平衡前提假设,获得了推进剂的I型动态起裂韧性;利用扫描电镜设备（SEM）,对推进剂断面形貌进行了观察和讨论。结果表明,CMDB推进剂动态起裂韧性在60 000-100 000 MPa·m^1/2/s加载率范围内表现出明显的线性率敏感特性,并在加载率达到100 000 MPa·m^1/2/s后出现极值3.96 MPa·m^1/2;CMDB推进剂在高过载条件下表现出明显的脆性起裂特性以及动态起裂韧性存在率敏感性,直接与应力波对基体和AP颗粒损伤程度相关。
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 results indicate that the CMDB propellant is a significant loading-rate-dependent material between 60 000 and 100 000 MPa·m^1/2/s, and the dynamic fracture initiation toughness threshold value （ 3. 96 MPa·m^1/2 ） occuring after the loading rate reaches up to 100 000 MPa·m^1/2/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.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2015年第3期372-377,395,共7页
Journal of Solid Rocket Technology
基金
总装重点预研项目(20101019)
关键词
固体推进剂
高过载冲击
动态起裂韧性
率敏感性
solid propellant
high impact load
dynamic initiation fracture toughness
rate sensitivity
