摘要
在对空心弹结构进行设计时,基于有限体积法和重叠网格技术,对不同马赫数条件下空心弹弹体和弹托的分离过程进行了仿真。仿真结果表明:弹托完全分离后,空心弹的马赫数Ma=2.0时,出现阻塞状态,而Ma≥2.5时,空心弹稳定飞行时为非阻塞状态;在Ma=2.5时,由于接近阻塞临界马赫数,脱壳时流场变化较为复杂,弹体空腔内气体经历时间较长的压缩过程,弹体阻力呈先减后增再减的变化趋势;在其他不同马赫数时的空心弹弹托分离过程中,弹体阻力整体上呈先减后增,最终达到稳定。随着马赫数的增大,流场能更快的达到稳定状态,弹体受到的扰动更少。
The structure of hollow projectile was designed and the separation process of sabot were simulated based on finite volume method and overlapping grid technology.The dynamic separation process of hollow projectile and sabot was realized under different Mach numbers.The results show that when the hollow projectile is completely decommissioned,it will be blocked when Ma is 2.0,while when Ma≥2.5,it will be non-blocked when the hollow projectile is in stable flight.At Ma=2.5,the flow field of sabot discard changes slightly complicated due to the approaching blocking critical Mach number.The gas in the cavity of the projectile undergoes a long compression process,and the drag of the projectile decreases first,then increases and then decreases.In the separation process of hollow projectile with different Mach number,the drag of the projectile body decreases first and then increases,and finally reaches stability.With the increase of Mach number,the flow field can reach a stable state faster and the disturbance of the projectile body is more less.
作者
罗驭川
黄振贵
杜宏宝
陈志华
LUO Yuchuan;HUANG Zhengui;DU Hongbao;CHEN Zhihua(National Key Laboratory of Transient Physics, Nanjing University of Science and Technology, Nanjing 210094, China)
出处
《兵器装备工程学报》
CAS
北大核心
2020年第5期5-8,31,共5页
Journal of Ordnance Equipment Engineering
基金
装备预研重点实验室基金项目(614260403041803)
中央高校基本科研业务费专项资金项目(309190112A2,30917012101)。
关键词
空心弹
弹托分离
气动影响
弹体阻力
非阻塞状态
hollow projectile
sabot discard
aerodynamic effect
projectile drag
non-blocking state
