摘要
针对固体火箭发动机在舰船运动影响下损伤难以评估的问题,以某固体火箭发动机为例,建立了摇摆载荷作用下发动机药柱粘接界面的疲劳损伤评估方法。通过推进剂粘接界面定应力往复剪切试验获得了其粘接界面的疲劳损伤特性;利用有限元分析方法计算得到了发动机界面剪切应力较大部位的应力谱;运用雨流计数法和Miner线性累积损伤原理对发动机粘接界面的疲劳损伤进行了评估。试验与仿真结果表明,推进剂粘接界面应力幅值和疲劳破坏次数的自然对数满足指数型方程,并且在给定舰载条件下发动机海上战备值班一年的寿命比仓库贮存时至少降低8.62%.
It is very difficult to evaluate SRM （solid rocket motor） damage due to ship motion. In order to solve this problem, a fatigue damage evaluation method of interface between propellant and liner under swing loading was established for some SRMs. The damage property between propellant and liner was ac- quired by using cyclic loading test with fixed shear stress. The nodes＇ shear stress spectra of SRM were obtained by means of finite element analysis method. A rain-flowing counting method and Miner＇s linear cumulative damage theory were applied to evaluate the interface fatigue damage. The test and simulation results show that the shear stress amplitude and logarithmic number of damage accords with exponential e- quation; the life of SRM under certain shipboard conditions is at least 8.62% shorter than that under storage situation.
出处
《兵工学报》
EI
CAS
CSCD
北大核心
2012年第8期986-990,共5页
Acta Armamentarii
基金
海军航空工程学院青年基金项目(4142D22)
关键词
固体力学
舰载导弹
固体火箭发动机
粘接界面
有限元分析
疲劳损伤
solid mechanics
ship-based missile
solid rocket motor
bonding interface
finite elementanalysis
fatigue damage
