发射箱后盖构型对箱内初始冲击波形成的影响

doi:10.12382/bgxb.2022.0066

摘要/Abstract

摘要：

为解决某型号发射装置工作过程中箱内冲击波强度不足的问题,采用数值模拟方法,结合动态网格自适应技术,对燃气冲击波开盖技术中涉及到的流动现象和箱内初始冲击波的产生机制进行研究。通过与相关试验结果对比分析验证所提数值方法的精度,以及当前自适应方法在对关心的流场特征,如冲击波阵面、接触间断等,进行动态加密或稀疏时有可靠的性能。以平板型后盖为例(原始设计)详细阐述了箱内冲击波的演化机制,为更好地认识该技术的工作机制提供帮助;进一步对比了穹顶型后盖对箱内冲击波形成的影响。研究结果表明,与平板型后盖相比,采用穹顶型后盖结构后,可影响气流与箱体尾部侧壁撞击时的角度,减缓该位置湍流区域的形成,从而显著提升箱内初始冲击波强度,使作用在前盖上的超压峰值增加约48%。所得研究结果对发射箱总体方案的设计具有重要的理论意义和工程应用价值。

关键词: 发射箱, 后盖构型, 网格自适应, 易碎盖, 冲击波

Abstract:

In order to address the problem of inadequate intensity of the shock wave within the launch canister during its working process, the numerical approach is combined with the dynamic mesh adaptation method to study the generation mechanism of the initial shock wave within the canister and the flow phenomena involved in the technique of cover opening by gas detonation shock waves. First, the experimental results are comparatively analyzed to verify the accuracy of the proposed numerical approach and the reliability of the dynamic mesh refinement or unrefinement of the characteristics of the flow field of interest, such as the shock wave front and contact discontinuity. On that basis, the flat rear cover (primitive design) is taken as an example to expound on the evolution mechanism of the shock wave within the canister, which helps deepen the understanding of the working mechanism behind this technique. Then, the impact of the dome-shaped rear cover on the formation of shock waves within the canister is analyzed. The research results indicate that compared with the flat rear cover, the dome-shaped one can change the angle of collision between the air flow and the side wall at the canister tail, thus slowing down the formation of the turbulence area at this position, which significantly increases the initial shock wave intensity within the canister and increases the peak overpressure exerted on the front cover by around 48%. The findings of this study is of theoretical significance and engineering value to the overall launch canister design.

Key words: launch canister, rear cover configuration, adaptive mesh refinement, fragile cove, shock wave

梁晓扬, 陆辰昱, 乐贵高. 发射箱后盖构型对箱内初始冲击波形成的影响[J]. 兵工学报, 2023, 44(5): 1277-1287.

LIANG Xiaoyang, LU Chenyu, LE Guigao. Effect of the Launch Canister’s Rear Cover Configuration on the Formation of Initial Shock Waves in the Canister[J]. Acta Armamentarii, 2023, 44(5): 1277-1287.

图/表 14

图1 某发射箱模型及监测面分布示意图

Fig.1 Schematic diagram of structure and monitoring surface distribution of a launch canister model

表1 发射箱内监测面位置分布

Table 1 Position distribution of monitoring surfaces in launch canister

相对位置	监测面0 (S-0)	监测面1 (S-1)	监测面2 (S-2)	监测面3 (S-3)	监测面4 (S-4)	监测面5 (S-5)
L/m	0.0	0.967	2.849	4.731	6.143	7.368

图2 计算区域网格和边界条件

Fig.2 Computational domain and boundary conditions

图3 发动机燃烧室总压-时间变化曲线

Fig.3 Curve of total pressure varying with time of rocket engine combustion chamber

表2 发动机热力学参数

Table 2 Thermodynamic parameters of rocket engine

参数	取值
燃烧室总压p₀/MPa	总压-时间曲线
燃烧室总温T₀/K	3400
出口温度T/K	2253
定压比热c_p/(J·kg^-1·K^-1)	3866
比热比γ	1.1601
出口质量流量/(kg·s^-1)	86.98
燃气分子量/(kg·kmol^-1)	20.52
动力黏性系数μ/(N·s·m^-2)	9.34×10^-5

图4 网格无关性验证

Fig.4 Grid independence verification

图5 二维网格自适应过程及数据结构示意图

Fig.5 2D mesh adaptation process and data structure

图6 试验结果与本文计算结果流场对比图

Fig.6 Flow field comparison between test results and calculated results

图7 试验结果与数值结果平板上压强分布的比较

Fig.7 Comparison of test results with numerical results of pressure distribution on the plate

图8 射流发展过程中网格动态自适应

Fig.8 Dynamic mesh adaptation during jet development

图9 不同时刻箱内冲击波发展过程

Fig.9 Developing process of the shock wave in the launch canister at different times

图10 冲击波在箱内传播及与前盖相互作用过程

Fig.10 Shock wave propagation in the launch canister and interaction with the front cover

图11 不同后盖构型箱内冲击波形成对比 (左为平板型,右为穹顶型)

Fig.11 Comparison of shock wave formation in the caniser with different cover configurations (Left is plate type, right is dome type)

图12 发射箱内各监测面及前盖上超压曲线

Fig.12 Overpressure curves of each monitoring surface and the front cover of the launch canister

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