弹头引信飞行气动热数值模拟及传热规律研究  

Numerical Simulation for Aerodynamic Heating and Heat Transfer Laws of Warhead Fuze

作　　者：娄文忠[1] 周宇[2] 徐祥红[1] 齐斌[1] 张海良 

机构地区：[1]北京理工大学宇航科学技术学院,北京100081 [2]总装装备指挥技术学院,北京102200 [3]山西北方惠丰机电有限公司,山西长治046012

出　　处：《中北大学学报（自然科学版）》2008年第4期316-320,共5页Journal of North University of China(Natural Science Edition)

摘　　要：炮弹、火箭弹增程后射击精确度明显下降,并且出现瞎火甚至早炸问题,而飞行气动热是火箭弹弹头引信热特性的主要影响因素.以某型号火箭弹为研究对象,通过Fluent软件仿真,获得了火箭弹引信在弹道飞行过程中,各个时刻的驻点温度和锥面空气附面层温度分布.通过对内部传热模型的建立和瞬态解算,揭示了弹头引信内部各关键点的热变化规律.仿真结果显示:温度变化对速度变化具有很好的跟随性,并能为引信电源热利用提供依据.With the range of bomb or rocket increasing, attacking precision is decreased obviously even misfiring and early burst happening. Flying aerodynamic heating makes great effect on thermal characteristics of rocket warhead fuze. Taking a type rocket to a research object, Fluent software was used to simulate the flying progress, and the temperature, the temperature of the stationary point and the temperature distribution data of air boundary layer for every key time-point were obtained. Through the interior model of heat transfer and transient solution, thermal variety laws of all key points inside the fuze were illustrated. Simulation results indicate, that temperature variety has a good following behavior to velocity variety. It can provide basis for the heat utilization of fuse power.

关 键 词：火箭弹 引信 气动热 有限元仿真 温度场 

分 类 号：TJ430.1[兵器科学与技术—火炮、自动武器与弹药工程]