头部喷射曳光火箭靶弹气动耦合效应研究
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摘要
目前常将火箭弹改为靶弹,作为低成本的靶标。为了增强士兵的可观测性,现在弹体上开喷孔加装曳光管,使其在飞行过程中向外喷射强光以显示航迹信息。文中运用CFD仿真软件对曳光火箭靶弹的三维绕流流场进行了数值模拟分析,研究不同开孔方式的气动耦合效应对气动特性及稳定性影响,得出结论:火箭靶弹曳光喷孔处产生负的滚转力矩作用在尾翼上,使翼片的压力和密度分布不对称;导致弹丸阻力系数、静力矩系数增大,升力系数减小,稳定储备量降低。
At present, rockets are often modified as low-cost targets. In order to enhance the observability of the target, a light pipe is now installed on the opening of the body to emit strong light during flight to display track information. In this paper, the three-dimensional flow field around the rocket target tracer is simulated using CFD simulation software. The effect of aerodynamic coupling on aerodynamic characteristics and stability in different opening modes is studied. It is concluded that the negative rolling torque generated by the rocket target tracer at the trailing orifice acts on the tail wing to make the pressure and density distribution of the blade asymmetric. As a result, the resistance coefficient and static moment coefficient of the projectile are increased, the lift coefficient is decreased, and stable reserve is reduced.
At present, rockets are often modified as low-cost targets. In order to enhance the observability of the target, a light pipe is now installed on the opening of the body to emit strong light during flight to display track information. In this paper, the three-dimensional flow field around the rocket target tracer is simulated using CFD simulation software. The effect of aerodynamic coupling on aerodynamic characteristics and stability in different opening modes is studied. It is concluded that the negative rolling torque generated by the rocket target tracer at the trailing orifice acts on the tail wing to make the pressure and density distribution of the blade asymmetric. As a result, the resistance coefficient and static moment coefficient of the projectile are increased, the lift coefficient is decreased, and stable reserve is reduced.
引文
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[6]张维,郝秀平.基于旋转稳定和尾翼稳定的弹丸飞行稳定性研究[J].装备制造技术,2014(1):155-156.
[2]郭彦江.防空武器系统发展历程概述[J].军事文摘,2016(1):38-40.
[3]张弛.导弹类靶标主要技术要素分析与发展战略研究[J].飞航导弹,2012(5):44-47.
[4]王福军.计算流体动力学分析——CFD软件原理与应用[M].北京:清华大学出版社,2004:99.
[5]李鹏飞,徐敏义,王飞飞.精通CFD工程仿真与案例实战[M].北京:人民邮电出版社,2011:30-31.
[6]张维,郝秀平.基于旋转稳定和尾翼稳定的弹丸飞行稳定性研究[J].装备制造技术,2014(1):155-156.