带尾翼弹丸的膛口流场三维数值模拟

Three-dimensional Numerical Simulation on Muzzle Flow Field with Gun and Fin-stable Device

针对带稳定装置的弹丸发射时形成的膛口流场进行数值模拟计算。采用三维Navier-Stokes方程及S-A模型建立流场的计算模型,应用动网格技术计算划分网格,通过数值仿真计算得到气流在流场中压力、速度的参数值和分布图,根据仿真结果分析气流速度、压力的分布规律和对尾翼受力情况的影响。结果表明:弹底截面到达制退器起始截面后经0.4ms,由于制退器开孔的不对称性,使其内尾翼片两侧表面的压力不均衡,压力差达7MPa左右。计算结果为尾翼结构设计提供必要的参考。

The muzzle flow field of the gun with fin-stable device was simulated, the muzzle flow field model was described by the method of three-dimensional N-S equation to combine with the standard S-A model. The grid was divided by moving-grid technology. By three-dimensional numerical simulation, the pressure and velocity legible parameter distribution of the initial and main flow field was obtained. According to the results of numerical simulation, the muzzle flow field impacted on empennage force and motion state was analyzed. The results show that projectile bottom cross section arrived at the muzzle brake starting section after 0. 4ms, because of the asymmeter with the muzzle brake open pore, the pressure of the fin both sides was unbalanced,the pressure difference was 7MPa. The result can provide the necessary reference of fin-stabilized device design.