迫击炮弹引信精确制导组件气动外形优化

Aerodynamic Shape Optimization for Mortar Guidance Kit

为了给二维弹道修正精确制导组件气动外形设计提供参考,将Fluent流体仿真与编制的外弹道解算程序相结合.利用Fluent所得到的升力系数、阻力系数、俯仰力矩系数、赤道阻尼力矩系数以及稳定储备量等弹丸气动参数导入弹丸运动方程,分析其外弹道特性,对该二维弹道修正精确制导组件所使用固定鸭舵的舵截面翼型、面积、形状、斜置角、位置以及弹丸尾翼的形状和面积进行了气动优化设计.仿真验证结果表明,鸭舵添加后明显增大了弹丸阻力系数,并且鸭舵的位置越靠近弹体顶部,越不利于弹丸的稳定.对于所配用的迫击炮弹,鸭舵截面翼型取低速翼型系列中相对弯度为0,最大弯度为0,相对厚度为12%的NACA0012翼型,单个鸭舵面积为723mm^2、控制舵斜置角为4°、差动舵斜置角为6°、单个尾翼面积为4567mm2,在弹丸初速341m/s,射角45°时的最大横向修正距离可达112 61m,满足设计要求.

In order to provide reference for the aerodynamic shape design of the two-dimensional ballistic correction precision guidance kit,combined Fluent fluid simulation and programmed external ballistic calculation program to analyze its external ballistic process by introducing the aerodynamic parameters of the projectile such as lift coefficient,drag coefficient,pitching moment coefficient,equatorial damping torque coefficient and stable reserves obtained by Fluent,into the equation of the projectile s motion.Optimized designed the fixed rudder s rudder profile airfoil,area,shape,slant angle,position,and tail area,tail shapes the two-dimensional ballistic correction precision guidance module used.Simulation verification results show that after the addition of the rudder,the resistance?coefficient of the projectile is obviously increased,and the closer position of the rudder is to the top of the projectile,the worse the stability of the projectile.And for the mortar projectile used,the duck;rudder cross-section airfoil takes the NACA 0012 airfoil with a relative camber of 0,a maximum camber of 0,and a relative thickness of 12%in the low-speed airfoil series.The individual rudder has a rudder size of 723 mm^2,control rudder slant angle is 4°,differential rudder slant angle is 6°,the single tail area is 4567 mm^2,maximum lateral correction distance up to 112.61 m at projectile muzzle velocity 341 m/s,the angle of attack 45°.Meet the design requirements.