高速飞行条件下激波对激光引信探测性能的影响分析

doi:10.12382/bgxb.2024.1131

摘要/Abstract

摘要：

为了提高弹载前向脉冲激光引信的定距精度,有必要研究高速飞行条件下弹前激波带来的影响。基于传统的脉冲激光回波模型,提出一种半解析方法对受激波干扰的脉冲激光回波信号建模,并引入最优置信区间的概念来构建测距数据分布和误差评价模型。以典型破甲弹为研究对象,基于雷诺平均纳维-斯托克斯方程求解器进行气动流场计算,获得弹体周围密度场分布。以光程差和斯特列尔比为气动光学效应评价标准,采用高精度的4阶Runge-Kutta法对穿过弹前非均匀流场的激光束进行光线追迹。仿真分析了不同飞行马赫数、目标倾角和探测距离对脉冲激光回波波形与定距精度的影响。仿真结果表明:3Ma以下脉冲激光引信的测距性能受到轻微影响,探测系统误差和随机误差分别在4Ma时达到最小和最大。所得研究成果为抑制高速飞行条件下脉冲激光引信的气动光学效应提供了理论依据。

关键词: 脉冲激光引信, 高速飞行, 光线追迹, 激波, 定距精度

Abstract:

The impact of shock waves in front of projectile under high-speed flight conditions is studied to improve the ranging accuracy of projectile-borne pulse laser fuze. Based on the traditional pulse laser echo model,a semi-analytical method is proposed to model the pulse laser echo signals disturbed by shock waves,and the concept of the optimal confidence interval is introduced to construct a ranging data distribution and error evaluation model. A Reynolds average navier-stokes (RANS) solver is used for aerodynamic flow field calculation to obtain the density field distribution around the projectile by taking a typical high-explosive anti-tank cartridge as the research object. The optical path difference (OPD) and Strehl ratio (SR) are used as the evaluation criteria for the aerodynamic optical effects,and a high-precision fourth-order Runge-Kutta method is employed to trace the laser beam passing through the non-uniform flow field in front of the projectile. The effects of different flight Mach numbers,target angles,and detection distances on the pulse laser echo waveforms and detection accuracy are analyzed through simulation. The simulated results show that the ranging performance of pulse laser fuzes below 3 Mach is slightly affected,and the systematic error and random error reach the minimum and maximum,respectively,at 4 Mach. This study provides theoretical foundations for suppressing the aerodynamic optical effects of pulse laser fuzes under high-speed flight conditions.

Key words: pulse laser fuze, high-speed flight, ray tracing, shock wave, ranging accuracy

中图分类号:

TJ43+4.2

查继鹏, 张祥金, 华抟, 沈娜, 康杨. 高速飞行条件下激波对激光引信探测性能的影响分析[J]. 兵工学报, 2025, 46(6): 241131-.

ZHA Jipeng, ZHANG Xiangjin, HUA Tuan, SHENG Na, KANG Yang. Analysis of the Influence of Shock Waves on the Detection Performance of Laser Fuze under High-speed Flight Conditions[J]. Acta Armamentarii, 2025, 46(6): 241131-.

图/表 15

图1 高速飞行中弹载激光引信探测过程(红色光束为穿过非均匀流场的激光束,黄色光束为虚拟的未受干扰的激光束)

Fig.1 Detection process of projectile-borne laser fuzes during high-speed flights (the yellow beam is the laser beam passing through the non-uniform flow field,and the red beam is the virtual unaffected laser beam)

图2 基于半解析法的脉冲激光回波建模方法原理图

Fig.2 Schematic diagram of the proposed laser echo modeling method

图3 计算模型与计算网格

Fig.3 Computational models and computational grids

表1 边界条件设置

Table 1 Boundary condition of aerodynamic flow field

参数	数值
高度/km	0.1
马赫数/Ma	1.5~4.0
压力远场/Pa	101325
温度/K	300
攻角/(°)	0

图4 光线追迹算法示意图(网格表示计算范围)

Fig.4 Schematic diagram of ray tracing algorithm(the mesh indicates the calculation range)

图5 不同马赫数下的破甲弹流场密度分布

Fig 5 Density distribution of flow field of high-explosive anti-tank cartridge under different Mach numbers

图6 不同马赫数下发射光束沿光学窗口的光程差分布

Fig.6 OPD distribution of the emitted beam along the optical window under different Mach numbers

图7 不同马赫数下接收光束沿光学窗口的斯特列尔比分布

Fig.7 SR distribution of received beam along the optical window under different Mach numbers

图8 不同马赫数对应的回波波形

Fig.8 Echo waveforms under different Mach numbers

图9 不同目标倾角下的回波波形及不同目标倾角下的脉冲宽度

Fig.9 Echo waveforms and pulse widths at different target inclination angles

图10 不同探测距离下的回波波形

Fig.10 Echo waveforms at different detection distances

图11 不同马赫数下测距概率密度

Fig.11 Ranging PDF distributions under different Mach numbers

图12 不同目标倾角下测距概率密度

Fig.12 Ranging PDF distribution at different target inclination angles

图13 不同马赫数下测距误差随目标倾角的变化

Fig.13 Variation of ranging error with target inclination angle under different Mach numbers

图14 不同马赫数下测距误差随探测距离的变化

Fig.14 Variation of ranging error with detection distance under different Mach numbers

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