摘要
为了系统研究迫击炮弹的攻角系数,给迫击炮弹引信弹道炸分析提供参数,应用FLUENT软件数值模拟不同攻角、不同马赫数下迫击炮弹的空气动力特性,并通过Matlab软件拟合数值仿真结果,给出了多种型号迫击炮尾翼稳定弹的攻角系数及其变化规律与取值范围。亚音速下攻角系数是马赫数的函数,随马赫数变化在小范围内变化;不同口径、不同外形的迫击炮弹其攻角系数不同;60~100 mm口径迫击炮尾翼稳定弹攻角系数取值范围为18.2~29.1。
In order to systematically investigate the angle-of-attack coefficient of mortar projectiles and provide a reference for analysis on ballistic blasting of the fuze in mortar projectiles,aerodynamic characteristics of mortar projectiles at different angle-of-attack and Mach number were simulated by FLUENT,and Matlab was used to fit results of numerical simulation. Change rule and the range of angle-of-attack coefficient of mortar projectiles in varied forms were given. The results indicate that the angle-of-attack coefficient of mortar projectiles is a function of Mach number in subsonic,ranging small with variety of mach numbers. The angle-of-attack coefficients are different in diameter and shape of mortar projectiles,ranging from 18. 2 to 29. 1 for the diameter from 60 mm to 100 mm.
出处
《弹箭与制导学报》
CSCD
北大核心
2014年第2期139-141,156,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
迫击炮弹
空气动力特性
攻角系数
数值仿真
曲线拟合
mortar projectile
aerodynamic characteristic
angle-of-attack coefficient
numerical simulation
curve fitting
