导弹尾焰对周边发射筒前端盖表面流场的影响研究

赵志; 朱睿; 吕志超; 武伟; 温雄飞

doi:10.15892/j.cnki.djzdxb.2025.02.012

弹箭与制导学报 >

2025 , Vol. 45 >Issue 2: 215 - 222

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.02.012

导弹尾焰对周边发射筒前端盖表面流场的影响研究

赵志 ,
朱睿 ,
吕志超 ,
武伟 ,
温雄飞

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上海航天动力技术研究所, 上海 201109

赵志(1991—), 男, 工程师, 硕士研究生。

收稿日期: 2024-09-26

网络出版日期: 2025-05-15

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Study on the Influence of Missile Tail Flame on the Surface Flow Field of the Front Cover of the Surrounding Launch Tube

ZHAO Zhi ,
ZHU Rui ,
LYU Zhichao ,
WU Wei ,
WEN Xiongfei

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Shanghai Space Propulsion Technology Research Institute, Shanghai 201109, China

Received date: 2024-09-26

Online published: 2025-05-15

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摘要

针对导弹离开发射筒矩阵过程中, 发动机燃气气流对周边发射筒易碎前端盖的影响, 建立了三维仿真模型, 利用动网格方法, 模拟弹体运动, 对周边前端盖的表面瞬态流场进行数值仿真计算。通过分析气体流线和流场云图, 得到导弹运动过程中, 发动机膨胀压缩波系的发展对前端盖表面气流流向和压强分布的影响。根据不同时刻前端盖内外压强差的变化, 结合试验得到的压强差安全范围, 辅助判断前端盖是否会提前破裂, 并通过改变临近发射筒之间的距离, 计算前端盖内外压强差的变化幅度, 得到发射筒之间的安全距离, 为前端盖的结构优化设计和多个发射筒单位的排列方案提供仿真预测和数据支持。

关键词： 尾流场; 发射筒前端盖; 动网格; 数值计算

本文引用格式

赵志 , 朱睿 , 吕志超 , 武伟 , 温雄飞 . 导弹尾焰对周边发射筒前端盖表面流场的影响研究[J]. 弹箭与制导学报, 2025 , 45(2) : 215 -222 . DOI: 10.15892/j.cnki.djzdxb.2025.02.012

Abstract

A three-dimensional simulation model is established to investigate the impact of engine gas flow on the fragile front cover of surrounding launch tube during the process of a missile leaving its launch tube matrix. The dynamic grid method is used to simulate the motion of the missile body, and the transient flow field on the surface of the surrounding front cover is numerically simulated and calculated. By analyzing the gas streamline and flow field contours, the influence of the engine expansion and compression wave on the airflow direction and pressure distribution on the surface of the front cover during missile motion is obtained. Based on the changes in pressure difference between the inside and outside of the front cover at different times, combined with the safe range of pressure difference obtained from experiments, it assists in determining whether the front cover will rupture prematurely. By changing the distance between adjacent launch tubes, the magnitude of the change in pressure difference between the inside and outside of the front cover is calculated, and the safe distance between launch tubes is obtained. This provides simulation prediction and data support for the structural optimization design of the front cover and the arrangement scheme of multiple launch tube units.

Key words： wake field; front cover of launch tube; dynamic grid; numerical calculation

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参考文献

原文顺序 | 文献年度倒序 | 文中引用次数倒序

[1]	孙同生, 于存贵, 秦予铮, 等. 多管火箭武器储运发射箱长期储存蠕变性能预测[J]. 国防科技大学学报, 2020, 42(5):60-67. SUN T S, YU C G, QIN Y Z, et al. Prediction of creep performance for multiple launch rocket canister under long-term storage[J]. Journal of National University of Defense Technology, 2020, 42(5):60-67.

[2]	邓春丽, 袁森, 张秀华. 导弹热发射燃气射流对发射筒的影响[J]. 科学技术与工程, 2020, 20(13):5117-5122. DENG C L, YUAN S, ZHANG X H. The effect of missile thermal emission gas jet on the launch tube[J]. Science Technology and Engineering, 2020, 20(13):5117-5122.

[3]	杨鑫宇, 冷子凌, 李伟, 等. 易碎式导弹发射箱盖研究进展[J]. 工程塑料应用, 2022, 50(12):142-148. YANG X Y, LENG Z L, LI W, et al. Research progress of fragile missile launching box cover[J]. Engineering Plastics Application, 2022, 50(12): 142-148.

[4]	姜毅, 耿峰, 张强. 导弹发射筒盖开启过程数值计算及试验[J]. 弹道学报, 2008, 20(3):33-35. JIANG Y, GENG F, ZHANG Q. Numerical calculation & experiments for the opening process of missile launcher's cover[J]. Journal of Ballistics, 2008, 20(3): 33-35.

[5]	徐志明, 徐澧明, 范棋鑫, 等. 具有系留功能的分瓣顶破式易碎盖试验与数值研究[J]. 固体火箭技术, 2022, 45(6):860-868. XU Z M, XU L M, FAN Q X, et al. Experimental and numerical research of split top-bursting frangible cover with mooring function[J]. Journal of Solid Rocket Technology, 2022, 45(6): 860-868.

[6]	柯贤朝, 林彬, 杨薛军, 等. 某发射筒端盖密封失效分析[J]. 理化检验-物理分册, 2019, 55(10):730-732. DOI KE X C, LIN B, YANG X J, et al. Failure analysis on sealability of a canister cover[J]. Physical Testing and Chemical Analysis(Part A: Physical Testing), 2019, 55(10): 730-732.

[7]	靖建全, 傅德彬, 王新星, 等. 易碎盖开启过程流场计算与分析[J]. 弹箭与制导学报, 2016, 36(4):80-82. JING J Q, FU D B, WANG X X, et al. Simulation and analysis for fluid field of frangible cover opening by gas jet[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2016, 36(4):80-82.

[8]	王岩, 景磊, 李树茂, 等. 复合材料发射筒前盖的研究进展[J]. 纤维复合材料, 2019, 36(3):49-52. WANG Y, JING L, LI S M, et al. Research progress of front cover of composite launcher[J]. Fiber Composites, 2019, 36(3):49-52.

[9]	麻小明, 刘馨心, 史耀祖, 等. 发射箱易碎盖分离仿真与试验分析[J]. 弹箭与制导学报, 2022, 42(3):74-77. DOI MA X M, LIU X X, SHI Y Z, et al. Simulation and experiment analysis of frangible cover separation of a launcher[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2022, 42(3):74-77.

[10]

刘宇盖, 蔡亮, 蔡振杰, 等. 基于有限元分析的前易碎盖外压承载能力的改进设计[J]. 理化检验-物理分册, 2019, 55(1):1-4.

DOI

LIU

Y G

, CAI

Z Z

, et al. Improved design of the bearing capacity under external pressure for the front fragile cover based on finite element analysis[J]. Physical Testing and Chemical Analysis(Part A:Physical Testing), 2019, 55(1):1-4.

[11]	张宝振, 王汉平, 窦建中, 等. 发射筒易碎前盖开盖过程的流体与固体耦合仿真方法[J]. 兵工学报, 2021, 42(8):1660-1669. ZHANG B Z, WANG H P, DOU J Z, et al. Fluid-structure coupling simulation method for the opening process of fragile front cover of canister launcher[J]. Acta Armamentarii, 2021, 42(8):1660-1669. DOI

[12]

王学智, 刘少伟, 王伟, 等. 倾斜发射导弹燃气流对发射箱前盖冲击数值仿真[J]. 弹箭与制导学报, 2017, 37(5):95-98.

WANG

X Z

, LIU

S W

, WANG

, et al. Numerical simulation about the impact of inclined launching missile jet flow on the front covers of launch canisters[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2017, 37(5):95-98.

[13]	郭锦炎, 赵衡柱, 吴新跃, 等. 发动机建压速率对易碎盖开盖的影响[J]. 弹道学报, 2015, 27(3):76-78. GUO J Y, ZHAO H Z, WU X Y, et al. Research on effect of the rising rate of rocket motor's pressure on friable lid opening process[J]. Journal of Ballistics, 2015, 27(3): 76-78.

[14]	傅德彬, 姜毅. 某导弹易碎盖的开启过程[J]. 固体火箭技术, 2007(4):275-277. FU D B, JIANG Y. Opening process of friable lid of one missile[J]. Journal of Solid Rocket Technology, 2007(4): 275-277.

[15]	许寿彭, 马大为, 乐贵高, 等. 某火箭炮易碎盖瞬态动力学与实验研究[J]. 弹箭与制导学报, 2006, 26(S2):418-420. XU S P, MA D W, LE G G, et al. Transient dynamics and experiment of a rocket frangible cap[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2006, 26(S2):418-420.

[16]	李文龙, 周光明, 蔡登安. 复合材料多瓣易碎盖分离过程研究[J]. 弹箭与制导学报, 2019, 39(1):21-24. LI W L, ZHOU G M, CAI D A. Separation process of a composite multi-part fragile cover[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2019, 39(1): 21-24.

[17]	蔡泽, 武丽丽, 柯贤朝. 某发射筒端盖开盖性能异常原因[J]. 理化检验-物理分册, 2022, 58(7):38-40. DOI CAI Z, WU L L, KE X C. Reasons for abnormal opening performance of the end cover of a launch tube[J]. Physical Testing and Chemical Analysis(Part A:Physical Testing), 2022, 58(7):38-40.

[18]	李仙会, 倪妮. 导弹贮运发射箱易碎盖燃气流冲击波开盖技术[J]. 理化检验-物理分册, 2023, 59(5):69-74. DOI LI X H, NI N. Fragmented technology by gas flow shock wave for fragile cover of missile launcher[J]. Physical Testing and Chemical Analysis(Part A:Physical Testing), 2023, 59(5): 69-74.

[19]	王伟, 王学智, 刘少伟. 导弹燃气射流对多联装发射箱前盖影响数值模拟[J]. 计算机测量与控制, 2013, 21(10):2747-2749. WANG W, WANG X Z, LIU S W. Numerical simulation on the influence of missile jet flow on the multi-launch box top[J]. Computer Measurement & Control, 2013, 21(10):2747-2749.

[20]	张立坤, 焦胜海, 孙朝翔, 等. 降低发动机羽流对飞行器干扰的研究[J]. 导弹与航天运载技术(中英文), 2023(4):128-131. ZHANG L K, JIAO S H, SUN Z X, et al. Study on reducing the interference of engine plume to aircraft[J]. Missiles and Space Vehicles, 2023(4):128-131.

[21]	李敏, 王学智, 李超. 某车载导弹发射筒动力学仿真研究[J]. 弹箭与制导学报, 2018, 38(1):165-168. LI M, WANG X Z, LI C. Simulation and study on the dynamics of a vehicle missile launcher[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2018, 38(1):165-168.

[22]	李四超. 导弹发射筒筒底压力场仿真[J]. 海军航空工程学院学报, 2016, 31(1):89-94. LI S C. Cylinder bottom pressure field simulation of missile launch tube[J]. Journal of Naval Aeronautical and Astronautical University, 2016, 31(1):89-94.

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