导弹从发射箱热发射过程的数值分析

梁晓扬; 苏逸飞; 乐贵高

doi:10.13224/j.cnki.jasp.20210308

导弹从发射箱热发射过程的数值分析

doi: 10.13224/j.cnki.jasp.20210308

南京理工大学机械工程学院，南京 210094

详细信息

作者简介:
梁晓扬（1989-），男，博士生，研究领域导弹发射过程热力环境。E⁃mail：Mr_Liangxiao@163.com

通讯作者:
乐贵高（1964-），男，教授，博士，主要从事火箭导弹发射系统流体力学数值模拟。E⁃mail：leguigao@njust.edu.cn

中图分类号: V231.1
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出版历程
- 收稿日期: 2021-06-17

Numerical analysis of hot launch of missile from a launch canister

School of Mechanical Engineering，Nanjing University of Science and Technology，Nanjing 210094，China

摘要

摘要:
采用三维可压缩雷诺平均Navier⁃Stokes方程和k⁃ε湍流模型，研究了导弹出箱过程中，弹体姿态偏转后弹底周围环境及发射箱内的流场特性。首先，以超声速欠膨胀射流撞击平板实验为算例，对数值方法的有效性进行验证。其次，分别对导弹在约束期和半约束期箱内流动特性展开研究。研究表明：喷管尾流在发射箱内会形成强烈的引射效应。同时，在弹底会出现明显的回流区域，使导弹出箱时受到额外的阻力。考虑偏转后，发射装置受到的冲击载荷增大2倍以上，发射箱壁面受到的压力增加40%。而且，在半约束期，箱内的流场分布不再对称，会使得导弹受到额外的不平衡力矩。
- 射流冲击 /
- 非同时离轨 /
- 发射箱 /
- 引射效应 /
- 二次流
Abstract:
Based on the three⁃dimensional compressible Reynolds⁃averaged Navier⁃Stokes equation and the k⁃ε turbulence model，the environment around the bottom of the missile and the flow field characteristics in the launch canister after deflection of the missile attitude were investigated.Firstly，the effectiveness of the numerical method was verified by the experiment of supersonic jet impinging on a flat plate.Secondly，the flow characteristics of the launch canister in the constrained and semi⁃confined periods were investigated respectively.The results showed that significant entrainment effect of the exhaust gas can be found in the launch canister.Meanwhile，a backflow area near the bottom of the missile can be observed，which may cause additional drag force on the missile during the launching process.After considering the deflection，the impact load on the launcher was increased by more than two times and the pressure on the launch box wall was increased by 40%.Moreover，the flow field distribution inside the box was no longer symmetrical during the semi⁃confinement period，making the missile subject to additional unbalanced moments.
- jet impingement /
- non simultaneous derailment /
- launch canister /
- ejection effect /
- secondary flow
注释:

1) 张雪

HTML

图 1 发射箱模型图

Figure 1. Schematic diagram of the launch canister

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图 2 导弹出箱过程（单位：mm）

Figure 2. Missile out of the box process （unit:mm）

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图 3 计算域模型

Figure 3. Computational domain

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图 4 计算网格

Figure 4. Computational grid

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图 5 Grid a~Grid d沿喷嘴轴线上的压力分布

Figure 5. Pressure distributions along the nozzle axis of the Grid a~Grid d

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图 6 实验结果与本文计算结果流场对比图

Figure 6. Flow field comparison between experimental results and calculation results

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图 7 数值结果与实验结果比较

Figure 7. Numerical results compared with experimental results

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图 8 在对称平面和Z=2.0D,Z=6.3D处马赫数分布

Figure 8. Mach number distribution in the symmetry plane and Z=2.0D,Z=6.3D

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图 9 全约束期对称平面上速度矢量

Figure 9. Velocity vector in the symmetry plane during full constraint period

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图 10 $X =$ 0.6D和 $X =$ 2.0D处的速度矢量

Figure 10. Velocity vector at $X =$ 0.6D and $X =$ 2.0D

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图 11 对称平面和 $X =$ 2.0D， $X =$ 6.3D横截面上的马赫数分布

Figure 11. Mach number distribution in the symmetry plane and $X =$ 2.0D, $X =$ 6.3D cross section

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图 12 发射箱上表面温度分布

Figure 12. Temperature distribution on the upper surface of the launch canister

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图 13 对称平面上速度矢量图

Figure 13. Velocity vector in the symmetry plane

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