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带尾翼弹丸的膛口流场三维数值模拟

Zhigang JIAO, Chong SUN,Hao QIU

Transactions of Shenyang Ligong University（2017）

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Abstract
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.
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Key words
muzzle flow field,moving-grid technology,fin-stabilized device,projectile
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