关于小口径尾翼弹修正方法的研究

Study on Trajectory Correction Technique for Small Caliber Fin Stabilized Projectile

进行了小口径尾翼修正弹气动外形设计,并对其进行气动仿真,得出了阻力、升力、翻转力矩、导转力矩等空气动力数据.在分析小口径尾翼修正弹气动特性的基础上,对其大量气动数据进行方程拟合.通过气动和动力学仿真,模拟修正弹修正过程,对小口径尾翼修正弹飞行稳定性和修正能力进行分析.仿真结果表明,在满足全弹气动布局、飞行稳定、电机有效控制的条件下,经气动外形设计的小口径尾翼修正弹具有良好的飞行稳定性和修正能力.

Conducted are a small-caliber bullet tail correction aerodynamic design, and its aerodynamic simulation. Such aerodynamic data as the drag, lift, turning torque, roll torque are obtained and the aerodynamic characteristics are analyzed, the equations for large pneumatic data fitting; Use pneumatic and multidisciplinary joint dynamics simulation method to simulate bomb correction process, and small-caliber proiectile flight stability and tail correction capability for analysis. The simulation results have showed that, based on the aerodynamic layout, flight stability, effective control, the small-caliber projectile tail correction has good flight stability and correction capabilities.