Numerical analysis of hot launch of missile from a launch canister

Xiaoyang LIANG; Yifei SU; Guigao LE

doi:10.13224/j.cnki.jasp.20210308

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Numerical analysis of hot launch of missile from a launch canister

Rocket Engine | 更新时间：2025-03-14

- Numerical analysis of hot launch of missile from a launch canister
- Journal of Aerospace Power Vol. 37, Issue 8, Pages: 1643-1653(2022)
- 作者机构：
  
  南京理工大学机械工程学院，南京 210094
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.20210308
  CLC：
- 稿件说明：
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Xiaoyang LIANG, Yifei SU, Guigao LE. Numerical analysis of hot launch of missile from a launch canister[J]. Journal of Aerospace Power, 2022, 37(8): 1643-1653.
DOI：

Xiaoyang LIANG, Yifei SU, Guigao LE. Numerical analysis of hot launch of missile from a launch canister[J]. Journal of Aerospace Power, 2022, 37(8): 1643-1653. DOI： 10.13224/j.cnki.jasp.20210308.

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。

Abstract

Based on the three⁃dimensional compressible Reynolds⁃averaged Navier⁃Stokes equation and the

⁃

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.

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Keywords

references

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