摘要
为了研究低温条件下固体推进剂的细观损伤,采用Cohesive单元描述推进剂材料的颗粒/基体界面,基于ABAQUS软件,开发了模拟基体开裂的VUMAT本构子程序,仿真了常温和低温条件下其损伤破坏过程。结果表明,低温对单颗粒推进剂影响较小,推进剂损伤从界面脱粘开始,沿颗粒赤道方向由脱粘面向基体扩展,规律与常温情况相同。随着推进剂颗粒增加,虽然大颗粒仍然首先发生界面脱粘,但是低温会对推进剂界面脱粘和基体断裂的时机、位置和损伤程度造成显著影响,导致推进剂破坏形式更加复杂。
In order to study the microstructure damage of solid propellant at low temperature, the particle/matrix interface of propellant material was described by Cohesive element, based on ABAQUS software, and the VUMAT constitutive subroutine was developed to simulate the cracking of matrix.The damage and failure processes of ambient and low temperature were simulated.The results show that the low temperature has little effect on the single particle propellant, and the damage of the propellant start from the interface debonding,which is extended from the matrix to the matrix in the direction of the particle equator, whose law is the same as normal temperature. With the increase of propellant particles, the interracial debonding of the large particles is still the first.Howev- er, the low temperature has a significant impact on the timing, location, and damage of the matrix cracking and propellant interfacial debonding , which lead to more complex failure modes.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2017年第6期736-740,共5页
Journal of Solid Rocket Technology
关键词
固体推进剂
低温
细观损伤
仿真
solid propellant
low temperature
microstmcture damage
simulation
