Impact of Shock Waves on Safe Exit of Vehicle Nose Cap During Thermal Launch Process
-
摘要: 针对同心筒热发射过程中燃气流场作用下产生的冲击波对火箭助飞航行体头罩安全出筒的影响, 采用计算流体力学软件数值仿真点火发射过程, 详细分析了固体火箭发动机产生的冲击波和燃气在同心筒内的传播规律, 得到了冲击波作用下头罩受力变化曲线, 揭示了头罩在冲击波作用下的受力机理。结合试验数据进一步验证了头罩在冲击波作用下的受力过程，明确了其“先压—后拔—再压”的受力特征。研究结果清晰阐明了同心筒热发射过程冲击波对头罩的受力影响机制, 可为航行器头罩出筒安全性设计提供理论依据和参考。Abstract: In response to the impact of shock waves generated under the action of the gas flow field on the safe exit of the rocket-projected vehicle nose cap during the thermal launch process of a concentric canister, a numerical simulation of the ignition and launch process was carried out using computational fluid dynamics (CFD) software. The propagation laws of shock waves and gas generated by the solid rocket motor in the concentric canister were analyzed in detail, and the force variation curve of the nose cap under the action of shock waves was obtained. The force mechanism of the nose cap under the action of shock waves was revealed. Combined with test data, the force process of the nose cap under the action of shock waves was further verified, and its force characteristic of “first compression, then pulling, and then re-compression” was clarified. The research results clearly illustrate the force impact mechanism of shock waves on the nose cap during the thermal launch process of concentric canister and can provide a theoretical basis and reference for the safety design of the vehicle nose cap’s exit.
-
Key words:
- rocket-projected vehicle /
- nose cap /
- thermal launch /
- shock wave /
- gas flow field /
- concentric canister
-
图 3 筒内马赫数分布云图(t=19.24 ms)
Figure 3. Contour of Mach number distribution inside the cylinder (t=19.24 ms)
图 4 筒内压强分布云图(t=19.24 ms)
Figure 4. Contour of pressure distribution inside the cylinder (t=19.24 ms)
图 5 筒内燃气质量分数云图(t=19.24 ms)
Figure 5. Contour of gas mass fraction inside the cylinder (t=19.24 ms)
图 6 筒内压强分布云图(t=26.62 ms)
Figure 6. Contour of pressure distribution inside the cylinder (t=26.62 ms)
图 7 筒内燃气质量分数云图(t=26.62 ms)
Figure 7. Contour of gas mass fraction inside the cylinder (t=26.62 ms)
图 8 筒内压强分布云图(t=29.85 ms)
Figure 8. Contour of pressure distribution inside the cylinder (t=29.85 ms)
图 9 头罩内外压强分布云图(t=29.85 ms)
Figure 9. Contour of pressure distribution inside and outside the nose cap (t=29.85 ms)
图 10 筒内燃气质量分数云图(t=29.85 ms)
Figure 10. Contour of gas mass fraction inside the cylinder (t=29.85 ms)
图 11 筒内燃气质量分数云图(t=38 ms)
Figure 11. Contour of gas mass fraction inside the cylinder (t=38 ms)
图 12 筒内马赫数分布云图(t=38 ms)
Figure 12. Contour of Mach number distribution inside the cylinder (t=38 ms)
图 13 筒内压强分布云图(t=38 ms)
Figure 13. Contour of pressure distribution inside the cylinder (t=38 ms)
图 14 筒内燃气质量分数云图(t=44.4 ms)
Figure 14. Contour of gas mass fraction inside the cylinder (t=44.4 ms)
图 16 筒内压强分布云图(t=44.4 ms)
Figure 16. Contour of pressure distribution inside the cylinder (t=44.4 ms)
图 15 筒内马赫数分布云图(t=44.4 ms)
Figure 15. Contour of Mach number distribution inside the cylinder (t=44.4 ms)
图 17 试验头罩内外压力无量纲曲线
Figure 17. Dimensional pressure curves inside and outside the test nose cap
-
[1] 孙常存, 袁鹏, 闫雪, 等. 反潜助飞鱼雷命中概率影响因素仿真分析[J]. 兵工自动化, 2023, 42(10): 40-44.SUN C C, YUAN P, YAN X, et al. Simulation analysis of influence factors on hit probability of anti-submarine assisted torpedo[J]. Ordnance Industry Automation, 2016, 39(5): 729-734. [2] 王中, 石小龙, 李建芬. 助飞鱼雷总体技术[M]. 北京: 国防工业出版社, 2023. [3] 郑榆淇, 傅德彬, 王新星, 等. 异形截面同心筒燃气流动特性数值研究[J]. 固体火箭技术, 2016, 39(5): 729-734. doi: 10.7673/j.issn.1006-2793.2016.05.023ZHENG Y Q, FU D B, W X X, et al. Numerical investigation of exhaust flows for missile launching in an irregular section concentric canister launcher[J]. Journal of Solid Rocket Technology, 2016, 39(5): 729-734. doi: 10.7673/j.issn.1006-2793.2016.05.023 [4] 钱立新, 刘飞, 屈明, 等. 鱼雷头罩入水破坏模式研究[J]. 鱼雷技术, 2015, 23(4): 257-261.QIAN L X, LIU F, QU M, et al. Failure model of torpedo nose cap in water-entry[J]. Torpedo Technology, 2015, 23(4): 257-261. [5] 钱立新, 刘飞, 胡艳辉, 等. 鱼雷头罩设计可行域规划及影响因素[J]. 鱼雷技术, 2016, 24(3): 161-165. doi: 10.11993/j.issn.1673-1948.2016.03.001QIAN L X, LIU F, HU Y H, et al. Feasible region programming method and analysis of influential factors for design of torpedo nose cap[J]. Torpedo Technology, 2016, 24(3): 161-165. doi: 10.11993/j.issn.1673-1948.2016.03.001 [6] 张英琦, 乐贵高, 马大为, 等. 同心筒热发射非线性热传导研究[J]. 工程热物理学报, 2018, 39(10): 2251-2259.ZHANG Y Q, LE G G, MA D W, et al. Research on nonlinear thermal conduction of concentric canister launcher[J]. Journal of Engineering Thermophysics, 2018, 39(10): 2251-2259. [7] 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. doi: 10.3969/j.issn.1001-3539.2022.12.024YANG 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. doi: 10.3969/j.issn.1001-3539.2022.12.024 [8] 安庆升, 孙立东, 阎金贞, 等. 冲破式异型结构易碎前盖设计研究[J]. 复合材料科学与工程, 2021, 39(5): 73-79. doi: 10.19936/j.cnki.2096-8000.20210528.011AN Q S, SUN L D, YAN J Z, et al. Design of special-shaped structures front cover of launch canister with breakthrough[J]. Composites Science and Engineering, 2021, 39(5): 73-79. doi: 10.19936/j.cnki.2096-8000.20210528.011 [9] 梁晓扬, 陆辰昱, 乐贵高. 发射箱后盖构型对箱内初始冲击波形成的影响[J]. 兵工学报, 2023, 44(5): 1277-1289. doi: 10.12382/bgxb.2022.0066LIANG X Y, LU C Y, LE G G. Effect of the launch canister’s rear cover configuration on the formation of initial shock waves in the canister[J]. Acta Armamentarii, 2023, 44(5): 1277-1289. doi: 10.12382/bgxb.2022.0066 [10] 张艳, 李仙会, 庄辛. 导弹贮运发射箱易碎端盖研究进展[J]. 理化检验, 2019, 55(3): 145-164. doi: 10.11973/lhjy-wl201903001ZHANG Y, LI X H, ZHUANG X. Research progress on frangible cover of missile launch container[J]. Physical Testing and Chemical Analysis, 2019, 55(3): 145-164. doi: 10.11973/lhjy-wl201903001 [11] 徐强, 李军. 燃气射流起始冲击波形成机理的实验研究[J]. 推进技术, 2000, 21(3): 16-18. doi: 10.3321/j.issn:1001-4055.2000.03.005XU Q, LI J. Experimental study on the mechanism of initial shock wave in jet flow[J]. Journal of Propulsion Technology, 2000, 21(3): 16-18. doi: 10.3321/j.issn:1001-4055.2000.03.005 [12] 牛钰森, 姜毅, 史少岩, 等, 与燃气射流耦合的易裂后盖开启过程数值分析[J]. 兵工学报, 2015, 36(1): 87-93.NIU Y S, JIANG Y, SHI S Y, et al. Numerical analysis of fragile back cover opening process coupling with jet flow[J]. Acta Armamentarii, 2015, 36(1): 87-93. [13] 王成彬, 陈劲草, 陈继刚, 等. 导弹同心筒发射时导弹头部压强环境研究[J]. 兵器装备工程学报, 2023, 44(10): 236-242. doi: 10.11809/bqzbgcxb2023.10.032WANG C B, CHEN J C, CHEN J G, et al. Research on the pressure environment of missile head during concentric tube launch[J]. Journal of Ordnance Equipment Engineering, 2023, 44(10): 236-242. doi: 10.11809/bqzbgcxb2023.10.032 [14] 陈二云. 间断有限元数值方法研究及复杂冲击流畅的数值模拟[D]. 南京: 南京理工大学, 2008. [15] 郝继光, 姜毅, 韩书永, 等. 一种新的动网格更新技术及其应用[J]. 弹道学报, 2007, 19(2): 88-92. doi: 10.3969/j.issn.1004-499X.2007.02.024HAO J G, JIANG Y, HAN S Y, et al. A new dynamic mesh update method and its aplication[J]. Journal of Ballistics, 2007, 19(2): 88-92. doi: 10.3969/j.issn.1004-499X.2007.02.024 [16] 张程, 夏智勋, 马超, 等. 基于k-ω SST模型的同心筒发射装置流场数值模拟[J]. 航空动力学报, 2019, 34(11): 2331-2338. doi: 10.13224/j.cnki.jasp.2019.11.004ZHANG C, XIA Z X, MA C, et al. Based on k-ω numerical simulation of flow field of concentric canister launcher based on k-ω SST turbulence model[J]. Journal of Aerodynamics, 2019, 34(11): 2331-2338. doi: 10.13224/j.cnki.jasp.2019.11.004 [17] 郑榆淇. 异型截面同心筒气体流动特性研究[D]. 北京: 北京理工大学, 2016. -
下载:
点击查看大图
计量
- 文章访问数: 221
- HTML全文浏览量: 109
- PDF下载量: 61
- 被引次数: 0
