摘要
为了研究固体火箭发动机推进剂/衬层/绝热层粘接界面的细观损伤特点,建立了其细观代表性体积单元。针对推进剂内部颗粒夹杂的特点,采用分子动力学方法对其进行了颗粒填充处理。将基于表面粘结损伤的粘性接触算法用于粘接界面推进剂一侧内部颗粒脱湿的模拟,采用最大主应力准则用于模拟粘合剂基体的损伤与失效过程。研究结果表明,数值模拟结果的损伤形貌与试验结果吻合良好,建立的数值模型能较好地反映粘接界面细观损伤过程;对于初始粘接良好的粘接界面,颗粒的脱湿与粘合剂基体的损伤导致了拉伸过程中粘接界面应力应变曲线的非线性;为了提高粘接界面抵抗脱粘的能力,一方面应提高推进剂内部颗粒与粘合剂基体的粘接强度,另一方面颗粒脱湿之后,提高粘合剂基体的最大失效应力。
In order to study the microscopic damage characteristics of propellant/liner/insulator adhesive interface of solid rocket motor,a meso-scale model of the solid rocket motor's adhesive interface was established.According to the characteristics of particle inclusions in propellant,molecular dynamics method was used to fill the particles.A surface-based cohesive contact algorithm was applied to simulate the dewet proccess of internal particles on the propellant side of the adhesive interface.The maximum principal stress criterion was used to simulate the damage and failure process of the matrix.The results show that the damage morphology of the numerical simulation results is in good agreement with the experimental results,and the established numerical model can reflect the meso-damage process of the bonding interface well;For the adhesive interface with good initial bonding condition,the dewetting of particles and the damage of the adhesive matrix lead to the nonlinearity of the stress-strain curve of the bonding interface during the tension process;For improving the ability of the adhesive interface to resist debonding,the bonding strength between the internal particles of the propellant and the adhesive matrix should be improved,and after the particles have dewetted,the maximum failure stress of the adhesive matrix should be increased.
作者
伍鹏
李高春
钱仁军
WU Peng;LI Gaochun;QIAN Renjun(Naval Aeronautical University,Yantai 264001,China)
出处
《固体火箭技术》
CAS
CSCD
北大核心
2021年第3期343-349,共7页
Journal of Solid Rocket Technology
基金
基础加强领域基金(2019061)。
关键词
固体火箭发动机
粘接界面
细观损伤
数值模拟
solid rocket motor
adhesive interface
microscopic damage
numerical simulation
