小口径修正弹尾翼斜置角对修正能力影响

Influence of Small-Caliber Correction Projectile Fin Oblique Angle on Correction Capability

为了研究小口径修正弹尾翼斜置角对修正能力影响,建立了不同尾翼斜置角下弹丸的三维模型,利用滑移网格技术对其进行了气动仿真,得出了阻力、升力、翻转力矩、滚转力矩等空气动力数据,并对其气动特性进行了分析;利用气动和动力学多学科联合仿真的方法,得到了不同尾翼斜置角下弹丸飞行稳定性特征;同时,研究了不同尾翼斜置角对弹丸修正能力的影响;结果表明:在满足全弹气动布局、飞行稳定、弹丸修正能力的基础上,尾翼斜置角越大修正能力越强。

In order to study small-caliber projectile tail correction oblique angle on correction capability, we established the 3D model of different fin deflections of the projectile, and used sliding grid technology on the aerodynamic simulation, and came to drag, lift, overturning moment, rolling moment and so aero- dynamic data and analyzed its aerodynamic characteristics. Used the method of multidisciplinary joint pneumatic and dynamics simulation, we obtained different fin deflections stability characteristics of the pro- jectile. At the same time, we studied the influence of different fin deflections on the projectile correction ability. The results show that, based on the aerodynamic layout, flight stability, effective control and motor projectile correction ability, the bigger of the fin oblique angle, and the stronger of the correction.