气相爆轰波温度界面折射问题的数值模拟

doi:10.12382/bgxb.2025.0377

摘要/Abstract

摘要：

为探究气相介质中冲击波及爆轰波传播与毁伤过程中所呈现的折射行为,使用耦合两步化学反应模型的二维反应欧拉方程,结合有限体积法和自适应网格编制了相关的计算程序,研究激波和爆轰波在气体温度斜界面处的折射过程。通过理论分析和数值模拟研究对激波在温度界面的折射过程开展研究,给出透射激波速度和波后状态随界面温度幅值的变化规律,得到激波折射过程的典型波系结构。以激波研究为基础,进一步研究爆轰波在温度斜界面上的折射现象,通过数值纹影和烟膜技术分析胞格爆轰波的波面演化过程。研究结果表明,激波折射进入低温气体时在界面处形成马赫杆和斜激波,进入高温气体时形成双三波点结构和前凸波面;胞格爆轰波折射进入低温气体时在界面处形成倾斜波面,进入高温气体时形成前凸波面和退化的双三波点结构,胞格爆轰波的传播表现出明显的时空演化特征。

关键词: 气相爆轰波, 反射, 胞格结构, 马赫反射, 数值模拟

Abstract:

The refractive behaviors of shock waves and detonation waves during their propagation and damage processes in gaseous media are studied. A computation program with finite volume method and adaptive mesh refinement method is developed based on the reactive Euler equations coupled with a two-step chemical reaction model. The transmission and refraction processes of shock waves and detonation waves at temperature interfaces are determined through theoretical analysis and numerical simulations. The variations of the transmitted shock wave speed and post-wave state with the amplitude of interface temperature are presented, and the typical shock wave structure is obtained. The refraction phenomenon of detonation waves at the temperature interface is further studied, and then the evolution process of cellular detonation wave is analyzed using numerical schlieren and smoked foil method. The results indicate that a shock wave forms a Mach stem and oblique shock wave at the interface when it refracts into low-temperature gas, and it generates a double triple-point structure and a convex wave front when entering high-temperature gas. The cellular detonation wave forms an inclined wave front at the interface when it refracts into low-temperature gas. In contrast, when entering high-temperature gas, it generates a convex wave front and a degenerated double triple point structure. The propagation of cellular detonation waves exhibits distinct spatio-temporal evolution properties.

Key words: gaseous detonation wave, reflection, cellular structure, Mach reflection, numerical simulation

中图分类号:

O382

刘曦, 马天宝, 李健. 气相爆轰波温度界面折射问题的数值模拟[J]. 兵工学报, 2025, 46(10): 250377-.

LIU Xi, MA Tianbao, LI Jian. Numerical Simulation of Refraction of Gaseous Detonation Waves at Temperature Interfaces[J]. Acta Armamentarii, 2025, 46(10): 250377-.

图/表 27

表1 气体参数设置

Table 1 Parameters of gas

参数	数值	参数	数值
R/(J·kg^-1·K^-1)	218.79	γ	1.44
p₀/kPa	50	M_C-J	5.6
θ₀/K	295	E_I/RT_S	4.8
c₀/(m·s^-1)	304.86	E_R/RT_S	1.0
ρ₀/(kg·m^-3)	0.775	k₁$\sqrt{\gamma }$/c₀	1.387 5
Q/(RT₀)	19.7	k_R$\sqrt{\gamma }$/c₀	2.0

图1 块结构网格自适应细分过程

Fig.1 Block adaptive mesh refinement

图2 计算域示意图

Fig.2 Schematic diagram of computational domain

图3 网格收敛性测试

Fig.3 Grid convergence test

图4 透射激波的距离-时间曲线

Fig.4 x-t plots of post states of the transmitted shock wave

图5 激波在不同温度界面处透射的温度曲线

Fig.5 Temperature curves at different temperature interfaces

图6 透射波后气体的状态

Fig.6 Post-wave state of transmitted wave

图7 两种折射波系和对应的极曲线图

Fig.7 Regular and irregular refraction structures and their corresponding polar plots

图8 激波在不同温度界面上的折射结构

Fig.8 Refraction of shock waves (calculated by GSD theory)

图9 295~50K界面处折射的温度云图

Fig.9 Temperature contour of refraction at 295~50K interface

图10 台阶信号模型

Fig.10 Step signal model

图11 295~100K界面处折射的温度云图

Fig.11 Temperature contour of refraction at 295~100K interface

图12 波后温度分布曲线

Fig.12 Post-shock temperature

图13 折射和反射的χ角对比

Fig.13 Comparison of χ in refraction and reflection

图14 295~800K界面处折射的温度云图

Fig.14 Temperature contour of refraction at 295~800K interface

图15 295~600K界面处折射的温度云图

Fig.15 Temperature contour of refraction at 295~600K interface

图16 波后温度分布曲线

Fig.16 Post-shock temperature

图17 折射和反射的χ角对比

Fig.17 Comparison of χ in refraction and reflection

图18 T1=200K,θ=20°的波结构

Fig.18 Wavefront structure for T1=200K and θ=20°

图19 T1=200K,θ=20°的爆轰波数值烟膜

Fig.19 Numerical smoked foil of detonation wave for T1=200K and θ=20°

图20 T1=200K,θ=20°时的激波数值烟膜

Fig.20 Numerical smoked foil of shock wave for T1=200K and θ=20°

图21 T1=200K,θ=30°波面和烟膜

Fig.21 Wavefront and smoked foil for T1=200K and θ=30°

图22 T1=220K时的数值烟膜

Fig.22 Numerical smoked foil for T1=220K

图23 T1=600K时的波面结构

Fig.23 Wavefront structure for T1=600K

图24 T1=600K,θ=20°时的数值烟膜

Fig.24 Numerical smoked foils of detonation and shock waves for T1=600K and θ=20°

图25 界面马赫杆的3个发展阶段

Fig.25 Three development phases of Mach stem development

图26 温度界面马赫杆高度的演变历程

Fig.26 Height evolution of Mach stem at temperature interface

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