火箭弹弹头引信空气附面层热特性数值仿真研究  

Numerical Simulation Method for Thermal Characteristic of Air Boundary Layer of Rocket Fuze

作　　者：娄文忠[1] 齐斌[1] 

机构地区：[1]北京理工大学机电工程学院,北京100081

出　　处：《兵工学报》2007年第4期406-410,共5页Acta Armamentarii

摘　　要：飞行气动热对弹头引信可靠性影响极大。建立了弹头引信空气附面层计算模型,借助有限元分析方法,充分考虑引信内部不同材料特性,建立相关数学模型。采用软件进行仿真。其结果达到了较高的精度,为弹头引信的热管理奠定了基础。Flying aerodynamic heating makes great effect on the reliability of nose fuze. The computational model of air boundary layer of rocket fuze was established. Considering different material characteristics, correlative mathematic model was built by finite element analysis. The simulation was conducted by Fluent software. The simulation results show that the method possesses high accuracy and lays the foundation for thermal supervision of nose fuze.

关 键 词：热学引信 热特性仿真 有限元方法 

分 类 号：TJ430.1[兵器科学与技术—火炮、自动武器与弹药工程]