推进剂高应变率力学行为与数值仿真方法研究  

The Numerical Simulation Method and Mechanical Behavior of Propellant at High Strain Rate

作　　者：王蓬勃[1] 王向东 王政时[1] 鞠玉涛[1] 孙朝翔[1] 

机构地区：[1]南京理工大学机械工程学院,南京210094 [2]晋西工业集团有限责任公司,太原030027

出　　处：《弹箭与制导学报》2013年第2期71-74,共4页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：中央高校基本科研业务费专项资金(NUST 2011XQTR13)资助

摘　　要：为了获得推进剂在不同应变率下的力学特性,利用万能材料试验机和分离式霍普金森压杆(SHPB)实验技术,对推进剂进行了10-3～103s-1应变率的单轴压缩试验。结果表明,推进剂存在明显的应变率效应。采用朱王唐(ZWT)本构描述推进剂的力学行为,通过最小二乘法得到本构方程的系数,然后把得到的数据应用在数值模拟中,通过数值仿真与实验对比,实验证明通过仿真能够较好的描述推进剂在小应变下的高应变率力学特性。In order to obtain mechanical properties of propellant under different strain rate, with the universal testing machine and the split Hopkinson pressure bar （SHPB） , the uniaxial compression tests of propellant have been performed at the strain rate from10^-3 to 10^3s^-1. The results show that the propellant has significant strain rate effect. Zhu Wang Tang（ZWT） constitutive was adopted to describe the me-chanical behavior of the propellant; the coefficients of the constitutive equation were obtained by the least square method and used in the numerical simulation. Compared with the numerical simulation, experiments show that numerical simulation may well describe mechanical properties of the propellant under high strain rate.

关 键 词：推进剂 分离式霍普金森压杆 高应变率 朱王唐本构模型 数值仿真 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]