摘要
为研究某立贮式固体火箭发动机在海洋值班条件下推进剂/衬层粘接界面的损伤情况,对固体火箭发动机在实际振动载荷与重力耦合作用下的疲劳损伤进行了评估。对监测的发动机振动数据进行了预处理;利用有限元软件先后模拟了发动机固化降温过程和值班振动过程;运用三点雨流循环计数和 Miner 理论对粘接界面危险点处累积损伤值进行了计算。结果表明,固化降温过程中,药柱两端与人工脱粘层脱开,推进剂/衬层粘接界面剪应力变化过程可由幂函数τ=a tb+c表示;以固化降温结果作为原始条件,振动初始时刻粘接界面剪应力发生剧烈变化,约15s后剪应力稳定变化,最大值点位于界面头部;在某特定海情下连续值班一年时,重力和振动载荷造成的某固体发动机寿命损伤为 14.84%。
In order to study the damage of the propellant/ liner bonding interface of a vertical storage solid rocket motor under o cean conditions, the fatigue damage of the solid rocket motor under the actual vibration loading and gravity coupling has been evalu ated. The monitored motor vibration data has been pre processed. The finite element software was used to simulate the motor curing, cooling process and the vibration process. The cumulative damage values at the dangerous points of the bonding interface have been calculated using three point rain flow cycle counting and Miner theory. The results show that during the curing and cooling process, both ends of the column are separated from the artificial debonding layer, and the shear stress change process of the propellant/ liner bonding interface can be represented by the power function τ=a tb+c. With the curing temperature changed to the original condi tion, the shear stress of the bonding interface changes sharply at the initial moment of vibration, and the shear stress changes stably after about 15s. The maximum point is located at the interface header. The damage of a solid rocket motor caused by gravity and vi bration loads is for a continuous duty in a specific marine environment.
作者
刘磊
李高春
李金飞
王鑫
宋佳明
LIU Lei;LI Gaochun;LI Jinfei;WANG Xin;SONG Jiaming(Coast Defense College, Naval Aviation University, Yantai 264001, China)
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2019年第3期389-395,共7页
Journal of Solid Rocket Technology
关键词
固体火箭发动机
振动损伤
有限元
雨流计数法
solid rocket motor
vibration damage
finite element
rain flow counting
