单兵火箭燃气消焰设计的试验研究与数值模拟  

The Experimental Research and Numerical Simulation of Flame Damper Design of Shoulder Launched Rocket

作　　者：武瑞清 阮文俊[2] 李昕[2] 马宏伟[2] 

机构地区：[1]中国兵器工业第208研究所,北京102202 [2]南京理工大学动力工程学院,南京210094

出　　处：《弹箭与制导学报》2009年第3期153-156,160,共5页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为了有效实现单兵火箭武器的燃气消焰,可以从火箭发动机的结构原理设计上加以改进。文中根据单兵火箭武器的消焰机理,给出燃气消焰的结构设计方案;同时搭建试验平台进行消焰装置的试验研究;根据试验装置及装药条件,建立内弹道数学模型并进行数值模拟。试验测试结果与数值模拟数据有较好的一致性,证明该燃气消焰的方法是可行的。研究结果对未来单兵火箭武器的设计与试验有很大的指导作用。In order to control the flame of exhausted jet efficiently, the principle and structural design of rocket engine can be further improved. In this paper, according to the mechanism research on the flame damper of shoulder launched rocket, the design scheme structure has been given. Moreover, a principle experiment was also been carried out on the test-bed. Considering test facilities and charging condition, the numerical analysis of interior ballistics was completed based on a mathematic model. With the good consistency between the simulation results and experimental data, the design of flame damper is proved to be feasible. The research contributes a lot to the design and experiment of shoulder launched rocket in the future.

关 键 词：火箭发动机 结构设计 消焰 内弹道 数值计算 

分 类 号：TJ711.1[兵器科学与技术—武器系统与运用工程]