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MA Y L , JIANG Y , WANG W C , et al. Study on impact effect of combustion gas jet during concentric canister launching process [J ] . Journal of Solid Rocket Technology , 2011 , 34 ( 2 ): 140 - 145 . (in Chinese)

裴畅贵 , 刘国志 , 金寅翔 , 等 . 基于COMSOL的电磁发射一体化弹丸动力学分析 [J ] . 火炮发射与控制学报 , 2024 , 45 ( 1 ): 104 - 112 .

PEI C G , LIU G Z , JIN Y X , et al. Dynamic analysis of electromagnetically launched integrated projectiles based on COMSOL [J ] . Journal of Gun Launch and Control , 2024 , 45 ( 1 ): 104 - 112 . (in Chinese)

李嘉麒 , 魏曙光 , 廖自力 , 等 . 陆战平台全电化关键技术发展综述 [J ] . 兵工学报 , 2021 , 42 ( 10 ): 2049 - 2059 . DOI: 10.3969/j.issn.1000-1093.2021.10.001 http://doi.org/10.3969/j.issn.1000-1093.2021.10.001 为进一步推进陆战平台全电化技术的发展，介绍了全电化陆战平台的基本特点和主要技术，面向未来陆战战场和新型战争形态阐述全电化技术在提高陆战平台机动性能、持续作战、战斗能力等方面的功能和作用，分析陆军装备轻型化、智能化、无人化的发展趋势。结合我军陆战装备的发展概况，从全电化陆战平台的驱动电机及其控制技术、车载综合电力系统、电磁武器、电磁装甲防护4个方面详细剖析陆战平台全电化的主要内容和关键技术，探究以上关键技术的研究现状，揭示全电化陆战平台持续发展的技术瓶颈，提出陆战平台在电机、电力系统、电磁等方向的发展思路，探索陆战平台全电化技术的运用前景。

LI J Q , WEI S G , LIAO Z L , et al. Review on the key technologies and development of all-electric land warfare platform [J ] . Acta Armamentarii , 2021 , 42 ( 10 ): 2049 - 2059 . (in Chinese) DOI: 10.3969/j.issn.1000-1093.2021.10.001 http://doi.org/10.3969/j.issn.1000-1093.2021.10.001 The basic characteristics and key technologies of an all-electric land warfare platform are introduced， and the importance of the all-electric technologies for improving the performance of land warfare platform is elaborated in terms of vehicular mobility，sustainability，and combat capability. The development tendency of light-weight, intelligent and unmanned land warfare platform is further analyzed. The key technologies of all-electric land warfare platform are investigated in terms of drive motor and its control，integrated power system，electromagnetic weapon，and electromagnetic armor. The technical background and current bottlenecks are studied，and the developing direction of land warfare platform，which includes motor，power system，electromagnetism，are put forward. Finally，the potential future applications of all-electric technologies are explored.

陈学慧 , 孟昭福 , 邹本贵 , 等 . 三级同步感应线圈炮的模型及控制研究 [J ] . 现代防御技术 , 2014 , 42 ( 1 ): 31 - 35 ,55.

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郭灯华 , 史铎林 , 关晓存 , 等 . 电容驱动型多级感应线圈炮模型简化 [J ] . 电机与控制学报 , 2022 , 26 ( 5 ): 8 - 16 .

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刘越 , 赵子杰 , 戴琪 , 等 . 航行体水下高膛压与高速发射载荷特性 [J ] . 兵工学报 , 2023 , 44 ( 4 ): 1126 - 1138 .

LIU Y , ZHAO Z J , DAI Q , et al. Load characteristics of high chamber pressure and high speed launch of underwater vehicle [J ] . Acta Armamentarii , 2023 , 44 ( 4 ): 1126 - 1138 . (in Chinese) DOI: 10.12382/bgxb.2021.0802 http://doi.org/10.12382/bgxb.2021.0802 The multiphase flow field formed behind a vehicle under high-chamber pressure and high-speed launch in water is complex, and the load effect is not clear yet. The launch load characteristics of a small-caliber underwater vehicle during cold launch under high chamber pressure and high initial velocity were investigated. The flow field and dynamic characteristics during interior ballistics, interaction between overflow gas and water, and hydrodynamic ram effect stage during the launch of the vehicle were analyzed. A numerical model of the high-speed cold launch process of the underwater vehicle was established, while a numerical multicomponent gas-vapor-liquid simulation was performed using a multiphase flow model and a dynamic grid approach. The load characteristics of launcher and their causes in different phases were then analyzed. The results showed that: large impact loads were mainly from the internal ballistic process and the hydrodynamic ramhydrodynamic ram effect, while a relatively small load was from the low-pressure area caused by overflowing gas; more specifically, the hydrodynamic ram hydrodynamic rampeak pressure decreased significantly because the mixed gas spilled out in large quantities under high chamber pressure, which was different from the low chamber-pressure launch condition.

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施瑶 , 鲁杰文 , 杜晓旭 , 等 . 航行体水下发射过程气幕降载特性 [J ] . 上海交通大学学报 , 2024 , 58 ( 2 ): 211 - 219 . DOI: 10.16183/j.cnki.jsjtu.2022.323 http://doi.org/10.16183/j.cnki.jsjtu.2022.323 水下发射过程中在筒口附近形成气幕通道,可有效降低航行体出筒过程中表面高频脉动载荷.基于流体体积(VOF)均质多相流理论、标准的RNG k-ε湍流模型及重叠网格技术,研究筒口气幕对航行体表面脉动载荷的影响规律,分析气幕环境下的流场结构及流体动力演变特性,对比不同横流强度、燃气质量流率下气幕流场结构演变和出筒降载效果.结果表明,航行体出筒过程中,喷嘴喷出的高速燃气近似覆盖了航行体表面,并逐渐在发射筒口周围形成一个气体通道,显著降低了航形体表面载荷;有气幕条件下,航行体所受力矩与表面载荷均出现明显降低,其中所受力矩峰值降低了80.3%,航行体表面压力峰值最大降低了81.2%;提高横流速度,航行体表面压力峰值最大增加了56.7%;在质量流率由2 kg/s提高到16 kg/s时,航行体所受力矩降低了80.8%,表面压力峰值最大降低了82.8%.

SHI Y , LU J W , DU X X , et al. Load-reducing characteristics of gas screen during underwater launch of the vehicle [J ] . Journal of Shanghai Jiao Tong University , 2024 , 58 ( 2 ): 211 - 219 . (in Chinese)

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刘传龙 , 张宇文 , 王亚东 , 等 . 考虑适配器弹性的潜射导弹出筒载荷特性研究 [J ] . 兵工学报 , 2015 , 36 ( 2 ): 379 - 384 . DOI: 10.3969/j.issn.1000-1093.2015.02.027 http://doi.org/10.3969/j.issn.1000-1093.2015.02.027 同心筒水下垂直发射导弹时潜艇是具备一定艇速的，相当于给弹体增加了侧向横流，其影响在弹体出筒阶段尤为显著，带来发射安全性和弹体结构载荷相关的诸多问题。为获得在时间和空间维度上置信度更高的导弹出筒载荷特性，并采用较少的假设，首次提出并建立了考虑适配器弹性约束和弹体三自由度的耦合求解流场和弹体运动的非定常数值模型。阐述了筒口气泡弹性对弹体载荷特性的影响，同时获得了出筒过程中的弹体运动、受载及适配器变形情况。仿真结果表明：由艇速产生的横流造成的振荡特性对导弹发射产生不利影响。结果可为同心筒水下垂直发射安全性评估和弹性结构设计提供研究方法。

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李海东 , 齐江辉 , 吴述庆 . 横流扰动下的鱼雷超空泡及水动力特性研究 [J ] . 兵器装备工程学报 , 2021 , 42 ( 12 ): 117 - 122 .

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袁馨 , 周标军 , 戴琪 , 等 . 剪切来流下超空泡射弹空化与水动力特性的数值研究 [J ] . 弹道学报 , 2023 , 35 ( 1 ): 42 - 51 . DOI: 10.12115/j.issn.1004-499X(2023)01-007 http://doi.org/10.12115/j.issn.1004-499X(2023)01-007 为研究剪切来流下超空泡射弹空化与水动力特性,采用Mixture多相流模型、Schnerr and Sauer空化模型和Realizable k-ε湍流模型,对水下剪切来流中的超空泡射弹进行数值模拟研究,来流平均速度为600 m/s,剪切率为0～7 500 s^-1。均匀来流中,包裹射弹的超空泡上下对称,阻力以压差阻力为主,升力系数为0。剪切来流下,超空泡不对称,并向低速侧偏斜,压差阻力略微增加,致使阻力系数增大。由于高速侧绕流更快,低速侧的涡旋产生更显著的卷吸作用,使得射弹受到朝向低速侧法向黏性力的作用,升力系数减小为负值。当剪切率进一步增大时,弹肩高速侧出现沾湿,弹体周围黏度增加,导致阻力系数显著增加,且水压显著大于饱和蒸汽压,压力的法向分量更加剧烈地作用到低速侧方向,升力系数进一步减小。

YUAN X , ZHOU B J , DAI Q , et al. Numerical simulation of cavitation and hydrodynamic characteristics of supercavitating projectile in shear flow [J ] . Journal of Ballistics , 2023 , 35 ( 1 ): 42 - 51 . (in Chinese) DOI: 10.12115/j.issn.1004-499X(2023)01-007 http://doi.org/10.12115/j.issn.1004-499X(2023)01-007 In order to study the cavitation and hydrodynamic characteristics of supercavitating projectile in shear flow,the Mixture multiphase model,Schnerr-Sauer cavitation model and Realizable <i>k-ε</i> turbulence model were used to simulate the underwater supercavitating projectile in shear flow. The inflow average velocity was 600 m/s,and the shear rates range from 0 to 7 500 s^-1. In the uniform flow,the supercavity surrounding the projectile is symmetrical. The drag is dominated by pressure drag,and the lift coefficient is 0. In the shear flow,the supercavity is asymmetric and deviates towards the low-speed side. Besides,the pressure drag increases slightly,leading to the increment of the drag coefficient. Because the flow around the high-speed side is faster,the vortex at the low-speed side produces a more significant entrainment effect,which makes the projectile suffer from the normal viscous force orientating towards the low-speed side,and the lift coefficient becomes negative. When the shear rate increases further,the shoulder on the high-speed side contacts the water. The viscosity around the projectile increases,resulting in a significant increase in the drag coefficient. The water pressure is substantially greater than the saturated steam pressure,and the normal component of pressure acts more strongly towards the low-speed side,resulting in the further decrement of the lift coefficient.

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