平头射弹前体参数对弹道稳定性及射程的影响

doi:10.12382/bgxb.2023.0236

摘要/Abstract

摘要：

为研究超空泡射弹前体参数对弹道稳定性和射程的影响规律,建立一种基于模态动力学的流场与弹道高效耦合仿真方法,提出超空泡射弹尾拍过程稳定度和有效射程的量化评价方法,完成针对泡型计算方法和尾拍弹道求解方法的合理性验证。在此基础上,分析射弹不同前体头径和锥段长度组合条件下的弹道稳定性和有效射程变化规律。研究结果表明: 随着前体头径和锥段长度的增大,射弹稳定性越来越高,失稳弹道存在“直接失稳”和“振荡失稳”两种模式;射弹各头径对应的最大射程随着头径的增大先增加后减小,设计域内最大射程和最小射程相差3.8倍,前体参数对弹道有效射程有较大影响。

关键词: 超空泡射弹, 前体参数, 弹道, 稳定性, 射程

Abstract:

The influences of forebody parameters on the trajectory stability and range of supercavitating projectile are studied in the paper. A high efficiency coupling method of flow field and trajectory is established based on modal dynamics, a quantitative evaluation method for the trajectory stability and efficient range of supercavitating projectile during tail-slapping is proposed, and the simulated cavity shape and tail-slapping trajectory are validated. On this basis, the change law of trajectory stability and range of the projectiles with different lengths and diameters of forebody are analyzed. Results show that the trajectory stability increases with the increase in the diameter and length of forebody, and the trajectory instability mode can be divided into direct instability and oscillate instability. With the increase in diameter, the maximum range increases at first and then decreases, the maximum range is 3.8 times of the minimum range in the design domain, which means the forebody parameters have a relatively large influence on the range of projectile.

Key words: supercavitating projectile, forebody parameter, trajectory, stability, range

中图分类号:

TJ630

许云涛, 檀大林, 杨超, 戴玉婷, 王震霄, 周鹏. 平头射弹前体参数对弹道稳定性及射程的影响[J]. 兵工学报, 2024, 45(6): 1933-1941.

XU Yuntao, TAN Dalin, YANG Chao, DAI Yuting, WANG Zhenxiao, ZHOU Peng. The Influences of Forebody Parameters of Flat-nosed Projectile on Trajectory Stability and Range[J]. Acta Armamentarii, 2024, 45(6): 1933-1941.

图/表 14

图1 本文泡型与试验数据及经验公式对比

Fig.1 Comparison of cavity shape in this paper with experimental data and empirical formula

图2 超空泡射弹模型图

Fig.2 Supercavitating projectile model

图3 两种方法尾拍流体动力与俯仰角对比

Fig.3 Comparison of loads and pitch angle by two different methods during tail-slapping

图4 流体计算域及边界条件示意图

Fig.4 Schematic diagram of fluid calculation domain and boundary conditions

图5 流场网格图

Fig.5 Mesh of flow field

图6 计算工况的质量、质心及初始速度

Fig.6 Mass,center of gravity and initial velocity of calculation cases

图7 射弹各工况稳定性分布

Fig.7 Distribution of projectile stability under all working conditions

图8 弹道俯仰角典型曲线

Fig.8 Typical curves of pitch angle of trajectile

图9 典型工况尾拍峰值时刻受力分布

Fig.9 Force distribution at time of peak tail-slap under typical working conditions

图10 射弹稳定度分布

Fig.10 Distribution of projectile stability

图11 典型工况射弹动能衰减曲线

Fig.11 Curves of projectile kinetic energy decay of typical cases

图12 射弹有效射程分布图

Fig.12 Distribution of efficient range of projectile

表1 与有效射程的相关系数

Table 1 Correlation coefficient of efficient range

变量	与S相关系数	与SA_n相关系数
A_n	-0.85	—
m	-0.18	0.99
x_g	-0.34	0.97

图13 射弹有效射程散点图

Fig.13 Scatter diagram of efficient range of projectile

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