段苏宸 , 姜毅 , 牛钰森 , 等 . 发射箱易碎后盖开启过程的数值计算 [J ] . 兵工学报 , 2018 , 39 ( 6 ): 1117 - 1124 . DOI: 10.3969/j.issn.1000-1093.2018.06.011 http://doi.org/10.3969/j.issn.1000-1093.2018.06.011 易碎盖技术在箱式或筒式发射中具有明显的优势，其开启过程涉及冲击波传播及射流运动等复杂的物理现象。利用动网格技术，以固体火箭发动机为研究对象，研究了易碎后盖开启过程，得到了后盖开启过程中流场压强和温度分布，并对开盖过程中燃气射流流场情况进行了分析。结果表明：冲击波在发动机射流径向一定范围内有较高的超压峰值，会对发射装置和周边设备产生破坏作用；后盖运动对燃气射流流动产生了影响，表现为燃气射流随着后盖向下运动而向下方传播的同时，由于受到后盖的阻挡发生反射回流现象；运动过程燃气流冲击作用逐渐变小，除核心区外后盖上的温度和压强也逐渐变小；后盖运动的仿真实验结果与实际试验数据一致，获得了较好相似性。

DUAN S C , JIANG Y , NIU Y S , et al. Numerical calculation of opening process of frangible rear cover of a launcher [J ] . Acta Armamentarii , 2018 , 39 ( 6 ): 1117 - 1124 . (in Chinese)

于邵祯 , 姜毅 , 周笑飞 , 等 . 耦合尾喷管堵盖运动的发射箱内流场研究 [J ] . 兵工学报 , 2014 , 35 ( 11 ): 1805 - 1812 . DOI: 10.3969/j.issn.1000-1093.2014.11.011 http://doi.org/10.3969/j.issn.1000-1093.2014.11.011 利用初始冲击波超压完成前后盖开启过程的贮运发射箱已得到广泛应用。为研究含尾喷管堵盖的冲击波超压形成过程及对后易碎盖的作用效果，应用有限元方法并结合动网格技术建立了导弹点火后堵盖的运动模型，并通过实验方法对仿真结果进行了验证。结合计算结果可清晰地看到尾焰流场的形成过程，并得到了冲击波超压在后易碎盖表面的随时间变化曲线。研究表明：受堵盖的影响，冲击波超压首先形成并冲击后易碎盖，燃气由堵盖的边缘向中心汇聚形成主流，在对后易碎盖的冲击时间和作用位置上与冲击波作用有明显的不同；后易碎盖主要受到冲击波超压作用实现碎裂变形，在堵盖运动的投影区域首先达到最大受力，瞬时峰值达5×10⁵ Pa.

YU S Z , JIANG Y , ZHOU X F , et al. Research on distribution of flow field in launching canister with the effect of nozzle closure [J ] . Acta Armamentarii , 2014 , 35 ( 11 ): 1805 - 1812 . (in Chinese)

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 ( 5 ): 73 - 79 . DOI: 10.19936/j.cnki.2096-8000.20210528.011 http://doi.org/10.19936/j.cnki.2096-8000.20210528.011 针对某型发射箱前盖综合性能要求高且弹体轴线与发射箱箱体几何中心线不重合问题,通过需求分析、结构设计、材料选择及确定成型工艺,再通过仿真分析、样件试验验证,最终确定了以环氧泡沫材料为主承载结构、冲破点位置相对盖体几何中心偏心的冲破式异型结构易碎前盖技术方案。试验结果表明,该易碎前盖具有良好的综合技术性能,满足设计需求。

AN 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 ( 5 ): 73 - 79 . (in Chinese)

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:物理分册 , 2019 , 55 ( 3 ): 145 - 150 ,164..

ZHANG Y , LI X H , ZHUANG X . Research progress on frangible cover of missile launchcontainer [J ] . Physical Testing and Chemical Analysis(Part A:Physical Testing) , 2019 , 55 ( 3 ): 145 - 150 ,164. (in Chinese)

HAGHDOOST M R , EDGINTON-MITCHELL D , NADOLSKI M , et al. Dynamic evolution of a transient supersonic trailing jet induced by a strong incident shock wave [J ] . Physical Review Fluids , 2020 , 5 ( 7 ): 073401 . DOI: 10.1103/PhysRevFluids.5.073401 http://doi.org/10.1103/PhysRevFluids.5.073401 https://link.aps.org/doi/10.1103/PhysRevFluids.5.073401 https://link.aps.org/doi/10.1103/PhysRevFluids.5.073401

KLEINE H , LE C V , TAKEHARA K , et al. Time-resolved visualization of shock-vortex systems emitted from an open shock tube [J ] . Journal of Visualization , 2010 , 13 ( 1 ): 33 - 40 . DOI: 10.1007/s12650-009-0009-2 http://doi.org/10.1007/s12650-009-0009-2 http://link.springer.com/10.1007/s12650-009-0009-2 http://link.springer.com/10.1007/s12650-009-0009-2

HAGHDOOST M R , EDGINGTON-MITCHELL D M , PASCHEREIT C O , et al. High-speed schlieren and particle image velocimetry of the exhaust flow of a pulse detonation combustor [J ] . AIAA Journal , 2020 , 58 ( 1 ): 1 - 18 . DOI: 10.2514/1.J059285 http://doi.org/10.2514/1.J059285 https://arc.aiaa.org/doi/10.2514/1.J059285 https://arc.aiaa.org/doi/10.2514/1.J059285

CHAUDHURI A , HADJADJ A , SADOT O , et al. Numerical study of shock-wave mitigation through matrices of solid obstacles [J ] . Shock Waves , 2013 , 23 ( 1 ): 91 - 101 . DOI: 10.1007/s00193-012-0362-2 http://doi.org/10.1007/s00193-012-0362-2 http://link.springer.com/10.1007/s00193-012-0362-2 http://link.springer.com/10.1007/s00193-012-0362-2

HALL R , KAPFUDZARUWA S , SKEWS B , et al. Shock wave propagation past a gap in a pipeline [J ] . Experiments in Fluids , 2017 , 58 ( 8 ): 93 . DOI: 10.1007/s00348-017-2372-4 http://doi.org/10.1007/s00348-017-2372-4 http://link.springer.com/10.1007/s00348-017-2372-4 http://link.springer.com/10.1007/s00348-017-2372-4

MASSONI J , BIAMINO L , JOURDAN G , et al. Experimental and numerical investigation of blast wave interaction with a three level building [J ] . Journal of Fluids Engineering , 2017 , 139 ( 11 ): 111106 . DOI: 10.1115/1.4037172 http://doi.org/10.1115/1.4037172 https://asmedigitalcollection.asme.org/fluidsengineering/article/doi/10.1115/1.4037172/372471/Experimental-and-Numerical-Investigation-of-Blast https://asmedigitalcollection.asme.org/fluidsengineering/article/doi/10.1115/1.4037172/372471/Experimental-and-Numerical-Investigation-of-Blast The present work shows that weak blast waves that are considered as being harmless can turn to become fatal upon their reflections from walls and corners inside a building. In the experimental part, weak blast waves were generated by using an open-end shock tube. A three level building model was placed in vicinity to the open-end of the used shock tube. The evolved wave pattern inside the building rooms was recorded by a sequence of schlieren photographs; also pressure histories were recorded on the rooms' walls. In addition, numerical simulations of the evolved flow field inside the building were conducted. The good agreement obtained between numerical and experimental results shows the potential of the used code for identifying safe and dangerous places inside the building rooms penetrated by the weak blast wave.

BIAMINO L , JOURDAN G , MARIANI C , et al. Experimental investigation of door dynamic opening caused by impinging shock wave [J ] . Shock Waves , 2011 , 21 ( 1 ): 19 - 28 . DOI: 10.1007/s00193-010-0294-7 http://doi.org/10.1007/s00193-010-0294-7 http://link.springer.com/10.1007/s00193-010-0294-7 http://link.springer.com/10.1007/s00193-010-0294-7

苗佩云 , 袁曾凤 . 同心发射筒燃气开盖技术 [J ] . 北京理工大学学报 , 2004 , 24 ( 4 ): 283 - 285 .

MIAO P Y , YUAN Z F . Techniques for the automatic cover opening in concentric canister launcher [J ] . Transactions of Beijing Institute of Technology , 2004 , 24 ( 4 ): 283 - 285 . (in Chinese)

姜毅 , 耿锋 , 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 . 为了研究导弹发射时燃气产生的压力开启前后易碎盖的方式，利用计算流体技术和试验方法对某型导弹发射时开盖技术进行了数值模拟和试验，建立了导弹和发射筒的二维和三维计算模型，研究结果表明，某型导弹采用易碎前后盖技术，后易碎盖由发动机燃气直接冲破，前易碎盖靠发射时产生的扰动波打开，通过合理配置发射筒前后易碎盖开盖条件，能可靠保证发射筒盖的正常开启.

JIANG Y , GENG F , ZHANG Q . Numerical calculation and experiments for the opening process of missile launcher’s cover [J ] . Journal of Ballistics , 2008 , 20 ( 3 ): 33 - 35 . (in Chinese) In order to study the method of opening the pre and post fragile cover by gas pressure when the missile was launched, the numerical simulation and experiment for a certain missile’s opening cover technology were carried out by computational fluid technology and experiment method. The 2D model of missile and firing tube, as well as 3D model, was built. The research shows that the post fragile cover of the missile with pre and post fragile cover technology was cracked directly by the rocket jet flow, and the pre fragile cover was opened by the disturbance wave. Through configuring the pre and post fragile cover’s opening condition reasonably, the launcher cover can open normally.

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 . (in Chinese)

党海燕 , 贺卫东 , 鲁志刚 , 等 . 激波开盖中后盖开盖压力对前盖压力的影响研究 [J ] . 战术导弹技术 , 2012 ( 1 ): 54 - 57 ,68.

DANG H Y , HE W D , LU Z G , et al. Research on the effect for the opening-pressure of post-cover to the pressure of pre-cover in the shock wave opening [J ] . Tactical Missile Technology , 2012 ( 1 ): 54 - 57 ,68. (in Chinese)

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 ,90. 为了研究导弹箱式热发射中导弹发动机建压速率对发射箱易碎盖开盖的影响,通过对动力源进行假设,建立了发动机建压速率与易碎盖开盖能量之间的关系,分析了发动机建压速率对易碎盖开盖的影响; 利用数值仿真得到不同速率下的箱内压力曲线,仿真结果表明,建压速率越高前盖开盖风险越大。对比分析了不同导弹飞行试验中发射箱内压力数据,试验验证了仿真结果的正确性。该研究为前、后易碎盖开盖压力指标的优化提供了参考。

GUO J Y , ZHAO H Z , WU X Y , et al. Research on effect of the rising rate of rocketmotor’s pressure on friable lid opening process [J ] . Journal of Ballistics , 2015 , 27 ( 3 ): 76 - 78 ,90. (in Chinese)

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 . (in Chinese) DOI: 10.3969/j.issn.1000-1093.2021.08.010 http://doi.org/10.3969/j.issn.1000-1093.2021.08.010 The opening process of fragile front cover of canister launcher in the pressure wave is a typical fluid-structure interaction problem. In order to study this opening process, the static tensile and compression test，and the dynamic tensile and compression test are carried out on the polyurethane composite material of fragile front cover，respectively. The subroutine VUSDFLD is used to expand the concrete damage plasticity (CDP) constitutive model to describe the loading and cracking conditions of the fragile front cover. Based on the computational fluid dynamics (CFD) simulation results of the flow field in the canister launcher, an Euler’s method-based model of the same case is built and verified, and the opening process of the fragile front cover is simulated by the coupled Eulerian-Lagrangian (CEL) algorithm. It shows that the simulated results based on the developed CDP model are in good agreement with the experimental data; and the simulation method combining CFD and CEL algorithms can effectively solve the fluid-structure interaction problem of opening process of fragile front cover and has higher accuracy.

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SHIH T H , LIOU W W , SHABBIR A , et al. A new k-e eddy viscosity model for high Reynolds number turbulent flows [J ] . Computers Fluids , 1995 , 24 ( 3 ): 227 - 238 . DOI: 10.1016/0045-7930(94)00032-T http://doi.org/10.1016/0045-7930(94)00032-T https://linkinghub.elsevier.com/retrieve/pii/004579309400032T https://linkinghub.elsevier.com/retrieve/pii/004579309400032T

LIJO V , KIM H D , SETOGUCHI T . Numerical investigation of the effects of base size on supersonic flow through a sudden duct enlargement [J ] . Proceedings of the Institution of Mechanical Engineers,Part G:Journal of Aerospace Engineering , 2012 , 226 ( 12 ): 1562 - 1572 . DOI: 10.1177/0954410011424984 http://doi.org/10.1177/0954410011424984 http://journals.sagepub.com/doi/10.1177/0954410011424984 http://journals.sagepub.com/doi/10.1177/0954410011424984 An abrupt increase in duct cross-section is often found in pressure-reducing devices, valves of internal-combustion engines, flow control devices in pipe systems of power plants, launch tubes of the ballistic ranges, thrust augmentation systems for cruise missiles, zero secondary flow ejectors, etc. The objective of this study is to revisit the classical base flow fields in a wall-bounded supersonic flow past a sudden expansion, to study and exploit their dependence on the size of the enlarged part – termed as the base size. Two-dimensional numerical simulations are performed for a nozzle flow, which is suddenly expanded in a larger rectangular channel. Five different turbulence models have been utilized in this study. Flow determination near the base is influenced by the proper selection of the turbulence model. The numerical solutions are compared with available experimental data and good agreement is achieved with renormalization group k–ε turbulence model. This investigation is concerned with the determination of the base size, for which the jet characteristics and the base pressure become independent of the size of the enlarged part. For a given duct, base pressure tends to a minimum for a particular pressure ratio. In this study, the authors have been able to link the jet characteristics to the base size by both analytical and numerical methods. This has led to the conclusion that for a constant driving pressure, the base pressure asymptotically decreases when the base size is increased up to a critical value, and it becomes independent of the base size thereafter. It is believed that the results of this study can provide a better understanding of the wall-bounded supersonic flow past a sudden expansion. The relevance of the present observations in some of the engineering applications is also discussed.

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GANESH N , BALAKRISHNAN N . A h-adaptive algorithm using residual error estimates for fluid flows [J ] . Communications in Computational Physics , 2013 , 13 ( 2 ): 461 - 478 . DOI: 10.4208/cicp.170811.210212a http://doi.org/10.4208/cicp.170811.210212a https://www.cambridge.org/core/product/identifier/S1815240600003820/type/journal_article https://www.cambridge.org/core/product/identifier/S1815240600003820/type/journal_article Algorithms for adaptive mesh refinement using a residual error estimator are proposed for fluid flow problems in a finite volume framework. The residual error estimator, referred to as the ℜ-parameter is used to derive refinement and coarsening criteria for the adaptive algorithms. An adaptive strategy based on the ℜ-parameter is proposed for continuous flows, while a hybrid adaptive algorithm employing a combination of error indicators and the ℜ-parameter is developed for discontinuous flows. Numerical experiments for inviscid and viscous flows on different grid topologies demonstrate the effectiveness of the proposed algorithms on arbitrary polygonal grids.

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WU J , TANG L , LUKE E A , et al. Comprehensive numerical study of jet-flow impingement over flat plates [J ] . Journal of Spacecraft and Rockets , 2002 , 39 ( 3 ): 357 - 366 . DOI: 10.2514/2.3834 http://doi.org/10.2514/2.3834 https://arc.aiaa.org/doi/10.2514/2.3834 https://arc.aiaa.org/doi/10.2514/2.3834