多尾翼式高超声速制导炮弹气动布局设计与特性分析

Aerodynamic Layout Design and Characteristic Analysis of Multi-Tailed Hypersonic Guided Projectile

设计了一种采用"一"字平面鸭舵的尾翼式制导炮弹气动布局,并针对其高超声速特性进行了适配的气动参数计算。炮弹头部采用阻力较小的冯卡门形母线,长度为口径d的3.5倍,弹身中段为长5d的圆柱段,尾部长3d,收缩比0.8;设计了八片尾翼的稳定结构,为减小气动热,钝化了头部鼻尖及翼前缘,分析并计算了弹翼的安装位置、面积及几何尺寸;利用牛顿理论对该制导炮弹的高超声速气动特性进行工程计算,获得升力系数、阻力系数、静稳定系数等相关气动参数。结果表明:本文设计的高超声速制导炮弹的气动布局具有良好的高超声速特性及可控性,满足设计要求。研究结果可为高超声速制导炮弹总体设计提供参考。

A guided projectile with one pair of canards was designed,and the aerodynamic calculation for its hypersonic characteristics was carried out.To reduce the aerodynamic drag,the von Karman generatrix was used on the head of the projectile with the length of 3.5 times of the caliber d.The middle section is a cylinder with the length of 5 d,the tail is 3 d long,and the contraction ratio is 0.8.Eight tail fins were designed to stabilize the projectile,and the nose and wings were passivated to reduce the aerodynamic heat.The installation position,area and geometrical parameters of wings were calculated.Newton theory was used to predict the aerodynamic characteristics of the projectile.The lift coefficient,drag coefficient,stability coefficient,etc.were obtained.The results show that the aerodynamic layout of the hypersonic guided projectile designed in this paper has good hypersonic characteristics and controllabolity,and meets the design requirements.The research results may provide reference for the overall design of the hypersonic guided projectiles.