燃气射流多角度倾斜冲击发射平台效应研究

曲普; 陈光辉; 袁伟亮; 梁兴旺; 姜瑞洲

doi:10.15892/j.cnki.djzdxb.2025.02.013

弹箭与制导学报 >

2025 , Vol. 45 >Issue 2: 223 - 231

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.02.013

燃气射流多角度倾斜冲击发射平台效应研究

曲普 ^,¹ ,
陈光辉 ² ,
袁伟亮 ² ,
梁兴旺 ² ,
姜瑞洲 ¹

展开

¹ 中北大学机电工程学院, 山西太原 030051
² 中国北方车辆研究所, 北京 100072

曲普(1979—), 男, 副教授, 博士。E-mail: qupunuc@nuc.edu.cn

收稿日期: 2024-09-06

网络出版日期: 2025-05-15

基金资助

智元实验室基金(ZYL2024015)

收起

Investigations on Effects of Multi-angle Inclined Impact of Gas Jet on Launching Platform

QU Pu ^,¹ ,
CHEN Guanghui ² ,
YUAN Weiliang ² ,
LIANG Xingwang ² ,
JIANG Ruizhou ¹

Expand

¹ School of Mechanical and Electrical Engineering, North University of China, Taiyuan 030051, Shanxi, China
² China North Vehicle Research Institute, Beijing 100072, China

Received date: 2024-09-06

Online published: 2025-05-15

Fold

摘要

针对火箭弹发射时产生的燃气射流对发射系统造成较强冲击, 可能对发射系统造成较大损害问题, 以不同高低射角下火箭弹尾流场为研究对象, 基于计算流体动力学方法, 采用有限体积法进行数值离散, 建立不同高低射角尾流场数学物理模型。在高低射角调整范围内, 选择0°、5°、15°、28°、38°五种角度进行仿真模拟。通过分析射流速度和压力等参数分布随射角及时间变化, 得到不同射角下射流发展规律;通过分析壁面压强分布及最大压强变化情况, 得到不同射角下射流对发射平台冲击效应变化规律。研究结果表明:随射角增大, 壁面压强整体有升高趋势;射角大于15°后, 壁面压强会有较大提高幅度;发射平台各位置受射流冲击影响程度不同, 需采用不同防护策略。本研究为发射平台防护设计提供了理论支撑。

关键词： 高低射角; 尾流场; 冲击效应; 壁面压强; 数值模拟

本文引用格式

曲普 , 陈光辉 , 袁伟亮 , 梁兴旺 , 姜瑞洲 . 燃气射流多角度倾斜冲击发射平台效应研究[J]. 弹箭与制导学报, 2025 , 45(2) : 223 -231 . DOI: 10.15892/j.cnki.djzdxb.2025.02.013

Abstract

The gas jet generated during rocket launching has a strong impact on the launching platform and may cause great damage to the launching platform. Therefore, it is necessary to study the impact effect of gas jet, researching the the wake field of rocket under different elevation angles. Based on computational fluid dynamics method, a finite volume method is used to discrete the rocket wake fields, and mathematical physical models of wake fields at different elevation angles are established for numerical simulation. Within the range of high and low angle adjustment, five angles of 0°, 5°, 15°, 28° and 38° are selected for simulation. By analyzing the distribution of jet velocity and pressure with the change of elevation angles and time, the development law of jet under different elevation angles can be obtained. Based on the analysis of the wall pressure distribution and maximum pressure variation, the impact effect of jet on the launching platform under different elevation angles can be obtained. The research results show that the wall pressure tends to increase with the increase of the elevation angle. And when the elevation angle is greater than 15°, the wall pressure will increase greatly. Each position of the launch platform is affected by jet impact to different degrees, and different protection strategies need to be adopted. The research provides theoretical support for the launch platform protection design.

Key words： elevation angle; wake field; impact effect; wall pressure; numerical simulation

[an error occurred while processing this directive]

参考文献

原文顺序 | 文献年度倒序 | 文中引用次数倒序

[1]	赵晨耕, 王辉, 孙中一, 等. 火箭燃气射流冲击发射平台的流场和热环境研究[J]. 南京理工大学学报, 2024, 48(3):253-261. ZHAO C G, WANG H, SUN Z Y, et al. Investigating the flow field and thermal environment of the rocket gas jet impinging on the launch platform[J]. Journal of Nanjing University of Science and Technology, 2024, 48(3):253-261.

[2]	王惠方, 刘洋佐, 乐贵高, 等. 导流结构对火箭炮冲击载荷的影响[J]. 兵器装备工程学报, 2022, 43(8):74-79. WANG H F, LIU Y Z, LE G G, et al. Influence of deflector structure on rocket launcher impact loads[J]. Journal of Ordnance Equipment Engineering, 2022, 43(8):74-79.

[3]	马杰, 王晓冰, 王红丽, 等. 发动机尾喷焰复燃化学反应模型评价与重构[J]. 红外与激光工程, 2024, 53(7):96-110. MA J, WANG X B, WANG H L, et al. Evaluation and reconstruction of afterburning reaction kinetics of rocket exhaust plume[J]. Infrared and Laser Engineering, 2024, 53(7):96-110.

[4]	张楠, 叶一帆, 潘迎, 等. 固体火箭发动机喉径烧蚀率变化分析[J]. 弹箭与制导学报, 2025, 45(1):108-114. DOI ZHANG N, YE Y F, PAN Y, et al. Analysis of the change of throat diameter ablation rate during the operation of solid rocket motor[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2025, 45(1):108-114.

[5]	TSUTSUMI S, SARAE W, UEDA H, et al. Effect of rocket engine layouts on jet flowfield inside a launch pad[J]. Journal of Spacecraft and Rockets, 2018, 55(6):1537-1544.

[6]	CRAFTON J, CARTER C, ELLIOTT G, et al. The impingement of sonic and sub-sonic jets onto a flat plate at inclined angles[J]. Experiments in Fluids, 2006, 41(5):699-710.

[7]	YENIGELEN E, MORRIS P J. Flow and acoustics in a model rocket flame deflector and deflector cover[J]. International Journal of Aeroacoustics, 2023, 22(5-6):437-458.

[8]	KUROKAWA M, TERAMOTO S, OKAMOTO K. Acoustic wave generation from two-dimensional supersonic inviscid jet impinging on inclined plate[J]. AIAA Journal, 2020, 58(8):3436-3445.

[9]	양영록. A study on impact of an adjacent structure by a rocket plume[J]. Journal of The Korean Society Aeronautical and Space Sciences, 2014, 42(6):488-494.

[10]	樊赫, 张利明, 寇钰, 等. 某防空导弹尾焰对弹箱损伤分析及优化设计[J]. 火炮发射与控制学报, 2024, 45(5):89-94. FAN H, ZHANG L M, KOU Y, et al. Analysis and optimization design of an air defense missile plume to the caisson injury[J]. Journal of Gun Launch & Control, 2024, 45(5):89-94.

[11]	赵晨耕, 乐贵高, 苏逸飞, 等. 双喷管运载火箭起飞阶段发射平台热环境研究[J]. 航空动力学报, 2024, 39(9):396-405. ZHAO C G, LE G G, SU Y F, et al. Investigations on thermal environment of launch pads during the two-nozzle launch vehicle launching[J]. Journal of Aerospace Power, 2024, 39(9):396-405.

[12]	覃晨, 章荣平, 张俊龙, 等. 冲击斜板距离对超声速欠膨胀射流噪声特性的影响[J]. 航空学报, 2022, 43(8):299-313. TAN C, ZHANG R P, ZHANG J L, et al. Acoustic performance of an under-expanded supersonic jet with different impinging distances to an inclined plate[J]. Acta Aeronautica et Astronautica Sinica, 2022, 43(8):299-313.

[13]	齐龙舟, 冯和英, 赵鲲, 等. 凹槽结构对冲击射流流场和声场特性的影响研究[J]. 振动与冲击, 2022, 41(22):105-112. QI L Z, FENG H Y, ZHAO K, et al. Experimental and numerical research on the noise suppression and wake control of impinging jets by virtue of groove structure[J]. Journal of Vibration and Shock, 2022, 41(22):105-112.

[14]	张志. 火箭炮燃气射流冲击力测量方法研究[D]. 南京: 南京理工大学, 2023. ZHANG Z. Research on the impact force measurement method of rocket gun gas jet[D]. Nanjing: Nanjing University of Science & Technology, 2023.

[15]	史亚锋. 航空发动机尾喷管射流对道面影响数值仿真[J]. 郑州航空工业管理学院学报, 2024, 42(3):26-29. SHI Y F. Thenumerical simulation of nozzle jet flow effect on runway surface[J]. Journal of Zhengzhou University of Aeronautics, 2024, 42(3):26-29.

[16]	周君, 江晓瑞, 李卓, 等. 固体发动机水下点火尾流场计算[J]. 计算机仿真, 2024, 41(5):63-70. ZHOU J, JIANG X R, LI Z, et al. Calculation of wake field for underwater ignition of solid rocket motors[J]. Computer Simulation, 2024, 41(5):63-70.

[17]	蔡振涛. 一种带新型分流器的火箭炮尾喷防护性能分析[D]. 太原: 中北大学, 2022. CAI Z T. Analysis on the protection performance of a rocket launcher with a new type of diverter[D]. Taiyuan: North University of China, 2022.

[18]	张恩豪, 樊建龙, 朱亮, 等. 固体火箭发动机燃气射流与超声速来流相互作用数值研究[J]. 弹箭与制导学报, 2024, 44(2):30-35. DOI ZHANG E H, FAN J L, ZHU L, et al. Numerical study on interaction between gas jet and supersonic flow in solid rocket motor[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2024, 44(2):30-35.

[19]	魏胜程, 钱林方, 徐亚栋, 等. 车载炮驾驶室表面炮口冲击波超压特性[J]. 兵工学报, 2024, 45(11):1-14. WEI S C, QIAN L F, XU Y D, et al. Muzzle blast overpressure characteristics on the surface of vehicle-mounted howitzer's crew compartment[J]. Acta Armamentarii, 2024, 45(11):1-14.

[20]	高英杰, 孙铁志, 张桂勇, 等. 回转体高速倾斜入水的流场特性及结构响应[J]. 爆炸与冲击, 2020, 40(12):101-113. GAO Y J, SUN T Z, ZHANG G Y, et al. Flow characteristics and structure response of high-speed oblique water-entry for a revolution body[J]. Explosion and Shock Waves, 2020, 40(12):101-113.

Options

文章导航