某端燃固体火箭发动机脱粘面临界尺寸的研究  

Investigation for the critical size of debond in a solid rocket motor of end burning

作　　者：邢耀国[1] 李亚飞[1] 董可海[1] 刘海峰[1] 

机构地区：[1]海军航空工程学院机械工程系,烟台264001

出　　处：《固体火箭技术》2003年第4期48-51,共4页Journal of Solid Rocket Technology

摘　　要：建立了含脱粘面的某固体火箭发动机工作过程的数学模型,根据脱粘面不扩展条件下得到的发动机工作过程中压力变化仿真曲线,进行了装药应力应变场的三维粘弹性有限元计算,并采用J积分断裂判据,预估了在发动机工作过程中脱粘面可能发生扩展时的临界尺寸。The model to describe the operating process of a SRM with debond is established. According to the pressure curve from simulating operating process of the solid propellant rocket motor without the debond propagation, the stress-strain field of grain is calculated by using three-dimension viscoelastic finite element method. With the J-integral fracture criterion, the critical size for debond propagation is predicted during the operating process of SRM.

关 键 词：端面燃烧 固体火箭发动机 脱粘面 临界尺寸 导弹 有限元法 燃面面积 装药应力 

分 类 号：V435.1[航空宇航科学与技术—航空宇航推进理论与工程]