固体火箭发动机枪击过程数值模拟  

Numerical simulation of the gunshot process of solid rocket motor

作　　者：庄建华[1] 毛佳[1] 张为华 王占利[1] 胡峰[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《固体火箭技术》2009年第4期422-426,共5页Journal of Solid Rocket Technology

摘　　要：为研究固体火箭发动机枪击安全性,对7.62 mm子弹射击过程进行了数值模拟。根据高速变形条件下功-热转化理论,计算出子弹穿透壳体温升,对灼热弹体与推进剂高速摩擦生热条件下的瞬态热传导问题,建立了相关理论模型,并进行了数值模拟。研究结果表明,子弹以750 m/s初速射击发动机,能使固体推进剂内形成高温热点,为发动机枪击过程模拟提供了新方法。The armour-piercing process of solid rocket motor case by 7.62 mm projectile was simulated numerically using LSDYNA in order to study gunshot security. The rise of the projectile＇s temperature during penetrating process was calculated based on work-heat transforming theory under high-rate distortion. A theoretical model was established for transient heat-conduction resulted from friction between hot projectile and solid propellant, and numerical simulation performed. The results indicate that hot spot can be generated inside the propellant under the initial projectile velocity of 750 m/s, and the new method can be used for simulating gunshot process.

关 键 词：固体火箭发动机 枪击 数值模拟 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]