基于舰船摇摆载荷的推进剂粘接界面疲劳损伤模型  

Interface Fatigue Damage Model of Solid Rocket Propellant Under Ship Motion Loading

作　　者：袁胜智[1] 宋扬[2] 曲凯[3] 刘铁[3] 

机构地区：[1]海军航空工程学院科研部,山东烟台264001 [2]海军装备部,北京100083 [3]海军航空工程学院飞行器工程系,山东烟台264001

出　　处：《海军航空工程学院学报》2013年第1期58-62,共5页Journal of Naval Aeronautical and Astronautical University

摘　　要：以某固体火箭发动机为例,建立了舰船摇摆载荷作用下发动机药柱粘接界面的疲劳损伤模型。通过推进剂粘接界面定应力往复剪切试验获得了界面的疲劳损伤S-N曲线;选取残余应变为损伤变量,并根据试验数据建立了推进剂粘接界面的疲劳损伤演化模型。试验及研究结果表明,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方程Y=0.748exp(-X/5.663)-0.0261。推进剂粘接界面在舰船摇摆载荷作用下的疲劳损伤量与循环加载比满足方程D=0.1517(1-exp(-β/0.0386))+0.8483(1-(1-β)1.1)。The interface fatigue damage evaluation method of propellant under swing loading was established for some SRM （solid rocket motor）. The interface fatigue damage S-N curve of composite solid propellant was ac- quired by fixed stress amplitude cycle loading shear experiment. The remain strain was selected as damage vari- able. Fatigue damage model was established according to analyzing the test data. The experiment results show ed that the shear stress and InN of interface accorded with equation Y=O.748exp（-X/5.663）-0.0261. Interface fatigue damage model of solid rocket motor under ship motion loading accorded with equation D = 0.1517（1 - exp（-β/0.0386）） ＋ 0.8483（1 -（1 -β）11）.

关 键 词：舰载导弹 固体火箭发动机 粘接界面 疲劳损伤 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]