| 白云,廖茂雄,甄慧强,李健,杜弘明,周三合,张韬.小型发射箱激波开盖过程数值仿真[J].装备环境工程,2024,21(7):74-81. BAI Yun,LIAO Maoxiong,ZHEN Huiqiang,LI Jian,DU Hongming,ZHOU Sanhe,ZHANG Tao.Numerical Simulation for Opening Process of Small Missile Launcher Cover Based on Shock Wave[J].Equipment Environmental Engineering,2024,21(7):74-81. |
| 小型发射箱激波开盖过程数值仿真 |
| Numerical Simulation for Opening Process of Small Missile Launcher Cover Based on Shock Wave |
| 投稿时间：2024-02-27 修订日期：2024-04-02 |
| DOI：10.7643/issn.1672-9242.2024.07.010 |
| 中文关键词: 小型发射箱 激波 数值仿真 计算流体 易碎盖 燃气射流中图分类号:TJ768.2 文献标志码:A 文章编号:1672-9242(2024)07-0074-08 |
| 英文关键词:small missile launcher shock wave numerical simulation computational fluid fragile cover gas jet |
| 基金项目:大连理工大学工业装备结构分析优化与CAE软件全国重点实验室基金(GZ23118) |
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| Author | Institution |
| BAI Yun | School of Mechatronical Engineering, Beijing Institute of Technology, Beijing 100081, China |
| LIAO Maoxiong | School of Mechatronical Engineering, Beijing Institute of Technology, Beijing 100081, China;Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China |
| ZHEN Huiqiang | Beijing Xinfeng Aerospace Equipment Co., Ltd., Beijing 100039, China |
| LI Jian | School of Mechatronical Engineering, Beijing Institute of Technology, Beijing 100081, China |
| DU Hongming | School of Mechatronical Engineering, Beijing Institute of Technology, Beijing 100081, China |
| ZHOU Sanhe | Beijing Xinfeng Aerospace Equipment Co., Ltd., Beijing 100039, China |
| ZHANG Tao | School of Mechatronical Engineering, Beijing Institute of Technology, Beijing 100081, China;State Key Laboratory of Structural Analysis, Optimization and CAE Software for Industrial Equipment, Dalian University of Technology, Liaoning Dalian 116024, China |
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| 中文摘要: |
| 目的 研究极小尾部空间发射箱内部的激波分布，通过数值仿真方法计算某导弹在小型发射箱发射时的内外流场。方法 在Fluent中建立导弹和发射箱的三维计算模型，通过多组分运输模型模拟燃气和空气域，利用动网格技术模拟外流场，使用二阶迎风格式进行求解。结果 获得了激波开盖过程中小型发射箱内流场的压力分布和导弹出箱后外流场的压力和温度，通过与同类文献比较，证明了结果可靠。其中，小型发射箱内的激波传播规律与常规箱体一致，但前盖压力峰值下降较大，该结论与前人研究中尾部距离对后盖所受冲击力的影响规律结论一致。结论 过小的尾部距离减少了燃气射流在后盖上的垂直反射，导致传播到前盖的压力峰值降低，有前盖开启失败的风险。该研究为小型发射箱激波开盖技术提供了参考。 |
| 英文摘要: |
| The work aims to study the internal shock wave distribution of a small tail space launcher, and obtain the internal and external flow fields in the small missile launcher through numerical simulation. A three-dimensional computational model of the missile and the launcher was established in Fluent, and the gas and air domains were simulated using a multi-component transport model. The external flow field was simulated with the dynamic grid technology, and solved with the second-order upwind scheme. The pressure distribution of the flow field inside the small launcher during the opening process and the pressure and temperature of the external flow field after the missile exited the launcher were obtained, and the results were compared with similar literature to prove their reliability. Among them, the propagation law of shock waves inside the small launcher was consistent with that of a conventional launcher, but the peak pressure of the front cover decreased significantly. This conclusion was consistent with the previous research on the influence of tail distance on the impact force on the rear cover. The small tail distance causes less reflection of the gas jet on the rear cover, resulting in a decrease in the pressure peak propagated to the front cover and a risk of failure to open the front cover. This study provides a reference for the opening technology of small launcher cover based on the shock wave. |
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