董恒 , 黄风雷 , 武海军 , 等 . 异形弹体高速侵彻/穿甲机理研究进展 [J ] . 兵工学报 , 2024 , 45 ( 9 ): 2863 - 3887 . DOI: 10.12382/bgxb.2024.0040 http://doi.org/10.12382/bgxb.2024.0040 为支撑超高声速武器终点毁伤效应评估,满足异形弹体侵彻力学理论发展需求,异形弹体侵彻机理是当前亟需研究的关键基础科学问题。对异形弹体侵彻行为、弹靶作用机制、弹道稳定性与结构响应研究现状进行全面综述,对现有研究工作进行梳理与总结,搭建异形弹体侵彻问题研究的基本框架;以异形弹体侵彻/穿甲过程中出现的新质弹靶作用现象、机理为脉络,突出异形弹体结构对载荷环境表征、弹道及结构稳定性控制等方面带来的新挑战,并提出了异形弹体未来研究的3个建议,供相关研究者参考。

HAI Y , HUANG F L , WU H J , et al . Penetration and perforation mechanism of high-speed non-circular projectiles a-state-of-the-art review [J ] . Acta Armamentarii , 2024 , 45 ( 9 ): 2863 - 3887 . (in Chinese)

崔玉红 , 徐艺哲 , 吕凡熹 , 等 . 临近空间高超声速飞行器武器投放影响因素 [J ] . 航空学报 , 2023 , 44 ( 24 ): 128539 . DOI: 10.7527/S1000-6893.2023.28539 http://doi.org/10.7527/S1000-6893.2023.28539 为了深入分析临近空间高超声速飞行器武器投放的可行性，解决地面试验难以模拟复杂工况的难题，对临近空间高超声速飞行器的飞行高度、载机攻角和导弹初始安装角、弹射力大小和弹射力作用时间5个影响因素进行研究。数值模拟利用动网格流体-动力学双向耦合方法，求解了不同工况下导弹投放的姿态变化。结果表明：负攻角有利于快速和安全地完成机弹分离任务，当载机攻角由4°调整为-4°时，X轴方向角位移由5.49°减小到-6.98°，导弹抬头趋势完全消失。随着飞行高度的增加，导弹抬头趋势逐渐消失，飞行高度35 km时导弹位移和角位移都有利于机弹分离。初始安装角对导弹位移和角位移的影响显著，初始安装角从5°调整为-3°时，导弹Z轴负向位移提升了36.23%，Z轴负向角位移提升了184.24%，负初始安装角各个方向位移和角位移都具有显著的优势。弹射力大小和作用时间直接影响导弹投放姿态，弹射力大小20 kN、作用时间0.05 s是最佳的弹射力组合。研究可为临近空间高超声速飞行器武器投放的可行方案及科学预测提供参考。

CUI Y H , XU Y Z , LYU F X , et al . Influencing factors of weapon separation of hypersonic vehicles in near space [J ] . Acta Aeronautica et Astronautica Sinica , 2023 , 44 ( 24 ): 128539 . (in Chinese) DOI: 10.7527/S1000-6893.2023.28539 http://doi.org/10.7527/S1000-6893.2023.28539 To thoroughly analyze the feasibility of hypersonic vehicle weapon separation in near space and address the challenge of simulating complex conditions in ground tests， we investigate five influencing factors： Flight altitude， aircraft angle of attack， initial installation angle of missile， ejection force magnitude， and ejection force action time. The attitude change of the missile launch under different operating conditions is solved by numerical simulation with the dynamic grid fluid-dynamics two-way coupling method. The results show that the negative angle of attack is conducive to the fast and safe completion of aircraft-missile separation tasks. When the aircraft angle of attack is adjusted from 4° to -4°， the angular displacement in the X -axis direction decreases from 5.49° to -6.98°， and the missile head-up trend disappears completely. As the altitude increases， the missile head-up trend gradually disappears， and both the missile displacement and angular displacement at the flight altitude of 35 km are favorable to aircraft-missile separation. The effect of the initial installation angle on the missile displacement and angular displacement is significant. When the initial installation angle is adjusted from 5° to -3°， the missile negative displacement in the Z -axis increases by 36.23%， the negative angular displacement in the Z -axis increases by 184.24%， and the negative initial installation angle has significant advantages in all directions of displacement and angular displacement. Ejection force magnitude and ejection force action time directly affect missile launch attitudes. The optimal combination is the ejection force magnitude of 20 kN and the ejection force action time of 0.05 s. This research can provide a reference for feasible options and scientific prediction for weapon separation of hypersonic vehicle in near space.

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闫铭 . 高超声速气动加热下战斗部装药侵彻安定性研究 [D ] . 北京 : 北京理工大学 , 2025 .

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WANG X Y , WANG Z C , FANG Y D . Cook-off characteristics of NTO/HMX-based plastic-bonded explosives in a shaped charge [J ] . Propellants,Explosives,Pyrotechnics , 2023 , 48 ( 3 ): e202200206 .

白孟璟 , 段卓平 , 白志玲 , 等 . 内/外隔热复合结构炸药装药快速烤燃热防护效应 [J ] . 兵工学报 , 2024 , 45 ( 5 ): 1555 - 1563 . DOI: 10.12382/bgxb.2023.0065 http://doi.org/10.12382/bgxb.2023.0065 为了研究快速烤燃(火烧)条件下炸药装药内/外隔热复合结构(内隔热材料/外阻燃材料)的热防护效应,对多种内/外隔热复合结构的炸药装药进行多点测温快速烤燃试验,得到火焰场和炸药装药各测点的温度-时间曲线及装药点火响应时间。开展内/外隔热复合结构炸药装药快速烤燃数值模拟,获得内/外隔热复合结构对装药快速烤燃点火响应时间的影响规律。研究结果表明:在快速烤燃过程中,外阻燃材料由于火烧变性存在导热增强及隔热减弱效应,在数值模拟中需考虑该效应;无论使用单独的隔热/阻燃材料还是使用内/外隔热复合结构,炸药装药的点火响应时间均随着材料涂覆厚度增加而延后,其中内/外隔热复合结构具有更好的热防护能力;点火位置均发生在装药端面棱角处,装药点火后反应烈度不受内/外隔热复合结构影响,反应等级均为爆燃;对于一定热防护性能范围内的隔热阻燃材料,壳体外表面涂层材料是耐高温纳米隔热材料、壳体内表面涂层材料是高效隔热防护材料时复合结构的隔热效果最好,并且当需求的隔热效果给定时,可考虑优先增加壳体外表面涂层的涂覆厚度,实现以最小涂覆厚度的内/外隔热复合结构满足所需的隔热效果。研究成果可为提升弹药热安全性设计提供参考。

BAI M J , DUAN Z P , BAI Z L , et al . Fast cook-off thermal protection effects of inner and outer heat-insulating composite structures of explosive charge [J ] . Acta Armamentarii , 2024 , 45 ( 5 ): 1555 - 1563 . (in Chinese) DOI: 10.12382/bgxb.2023.0065 http://doi.org/10.12382/bgxb.2023.0065 In order to study the thermal protection effects of the inner and outer heat-insulating composite structures (inner heat-insulating material/outer combustion-insulating material) of explosive charges under the condition of fast cook-off (burning), the multi-point temperature measurement fast cook-off experiments are carried out on explosive charges with various forms of inner and outer heat-insulating composite structures. The temperature-time curves of flame and each measuring point of explosive charge and the ignition response time of the charge are obtained. The fast cook-off ignition of explosive charges with different inner and outer heat-insulating composite structures is numerically simulated to obtain the influence law of inner and outer heat-insulating composite structures on the ignition response time of charge under fast cook-off. The results show that the thermal conductivity of the outer combustion-insulating material is increased and its thermal insulation is weakened due to the burning and denaturation of the material during the process of fast cook-off experiment. This effect should be considered in numerical simulation. The ignition response time of explosive charge is delayed with the increase in the coating thickness of both heat-insulating and combustion-insulating materials, whether using separate insulating/combustion-insulating materials or inner and outer heat-insulating composite structures. The inner and outer heat-insulating composite structures have better thermal protection ability and can significantly delay the ignition response time of the charge. The ignition position all occurs at the corner of the end face of the charge, and the reaction intensity after ignition is not affected by the inner and outer heat-insulating composite structures and is always the deflagration. For insulating/combustion-insulating materials within a certainprotection performance range, the composite structure has the best heat-insulating effect when the coating material on the outer surface of the shell is HGN and the coating material on the inner surface of the shell is GXTI, and when the required heat-insulating effect is given, it is possible to consider increasing the coating thickness of the outer surface coating of the shell first to achieve the optimal thermal protection effect of inner and outer heat-insulating composite structures with minimum coating thickness. The research results provide reference for improving ammunition thermal safety design.

肖有才 , 王瑞胜 , 范晨阳 , 等 . 带壳JH-14C传爆药烤燃实验及响应特性数值模拟 [J ] . 爆炸与冲击 , 2023 , 43 ( 7 ): 40 - 51 .

XIAO Y C , WANG R S , FAN C Y , et al . Cook-off experiment on the JH-14C booster explosive with a shell and the relevant numerical simulation [J ] . Explosion and Shock Waves , 2023 , 43 ( 7 ): 40 - 51 . (in Chinese)

刘瑞峰 , 王昕捷 , 黄风雷 , 等 . 2,4-二硝基苯甲醚基熔铸炸药宏细观烤燃响应特性数值分析 [J ] . 兵工学报 , 2022 , 43 ( 2 ): 287 - 296 .

LIU R F , WANG X J , HUANG F L , et al . Macro-meso-scale cook-off simulations of DNAN-based melt-cast explosives [J ] . Acta Armamentarii , 2022 , 43 ( 2 ): 287 - 296 . (in Chinese) DOI: 10.3969/j.issn.1000-1093.2022.02.006 http://doi.org/10.3969/j.issn.1000-1093.2022.02.006 The melting of DNAN and the phase transformation of HMX crystal occur in 2,4-dinitroanisole (DNAN)/octogen (HMX) melt-cast explosives during cook-off test. A melting reaction kinetics model is developed for DNAN, and a four-step reaction kinetics model of HMX is used to study the melting, phase transformation and ignition response of DNAN-based melt-cast explosives at the macro-meso scale. Macroscale calculation shows that DNAN melts at about 377.00 K, HMX undergoes a phase transformation at about 450.00 K, and the ignition temperature is 531.34 K. The ignition position locates at the annular area between the upper and lower ends and the side of the explosive, the error between the calculated and experimental ignition times is 0.5%. The mesoscale calculation results based on the macroscopic ignition area show that the ignition position locates at HMX crystal, and the evolution rules of DNAN melting and HMX phase transformation are obtained: at different times, the statistical distribution of liquid-phase DNAN is U-shaped, and δ-HMX is approximately normal. The macro-meso scale cook off simulations of DNAN-based melt-cast explosives are of great significance for understanding the thermal ignition mechanism of energetic materials.

寇永锋 , 杨坤 , 张斌 , 等 . 基于烤燃实验和数值模拟的战斗部装药热安全性 [J ] . 兵工学报 , 2023 , 44 ( 增刊1 ): 41 - 49 .

KOU Y F , YANG K , ZHANG B , et al . Research on thermal safety of warhead charge based on cook-off experimental and numerical simulation [J ] . Acta Armamentarii , 2023 , 44 ( S1 ): 41 - 49 . (in Chinese) DOI: 10.12382/bgxb.2023.0917 http://doi.org/10.12382/bgxb.2023.0917 In order to study the thermal safety of the warhead charge, a method is proposed for calculating and analyzing the thermal safety of warhead charge and determining the parameters of the reaction modelbased on the temperature of explosive cook-off, the speed of driving piston and the reaction pressureof cook-off. Taking RDX/Al/Binder explosives as an example, the thermal reaction temperature of charge before ignition and the moving speed of piston and the combustion pressure after ignition are measured using the cook-off experiments designed of multi-point temperature measurement and the speed and combustion pressure of driving piston measurement. The thermal decomposition reaction kinetics and combustion reaction model parameters of explosives are calibrated for the quantitative description of the reaction severity through numerical simulation calculation. The cracking of warhead shell is calculated by using the grid node separation calculation method, and the whole cook-off process of warhead charge is numerically simulated. The results show that, for the warhead RDX/Al/Binder explosive charge, the slower the heating rate is, the longer the charge ignition time is, the closer the ignition area is to the center of charge, the more serious the shell rupture is, the greater the kinetic energy of shell is, the greater the kinetic energy of charge is, and the stronger the charge reaction is.

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LI G Q , HU L , ZHANG K . Synthesis of Al 2 O 3 -SiO 2 aerogels with low thermal conductivity and high strength by methyltriethoxysilane as a silica precursor [J ] . Journal of Sol-Gel Science and Technology , 2023 , 108 ( 1 ): 35 - 46 .