Thermal hazard assessment of TKX-50-based melt-cast explosive

In the present study, thermal hazards of TNT and DNAN used as the molten binder in TKX-50-based melt-cast explosives were comparatively studied through accelerating rate calorimeter (ARC) and Cook-off experiments. Two kinds of ARC operation modes were performed to investigate the thermal safety performance under adiabatic conditions (HWS mode) and constant heating (CHR mode). The obtained results demonstrated that at both heating modes, DNAN/TKX-50 outperformed TNT/TKX-50 from the thermal safety point of view. However, the sensitivity to heat of the samples was reverse because of the different heating modes. In addition, the results of thermal hazard assessment obtained from the cook-off experiment complied with ARC analysis which indicated the molten binder TNT replaced by DNAN would reduce the hazard of the TKX-50 melt cast explosive. Furthermore, the results of cook-off experiments also showed that DNAN/TKX-50 outperformed TNT/TKX-50 from the aspect of thermal stability, which was consistent with the result of CHR mode because of the similar heating process.     

Analysis on damage characteristics and detonation performance of solid rocket engine charge subjected to jet

To further explore the damage characteristics and impact response of the shaped charge to the solid rocket engine (SRE) in storage or transportation, protective armor was designed and the shelled charges model (SCM)/SRE with protective armor impacting by shaped charge tests were conducted. Air overpressures at 5 locations and axial acceleration caused by the explosion were measured, and the experimental results were compared with two air overpressure curves of propellant detonation obtained by related scholars. Afterwards, the finite element software AUTODYN was used to simulate the SCM impacted process and SRE detonation results. The penetration process and the formation cause of damage were analyzed. The detonation performance of TNT, reference propellant, and the propellant used in this experiment was compared. The axial acceleration caused by the explosion was also analyzed. By comprehensive comparison, the energy released by the detonation of this propellant is larger, and the HMX or Al particles contained in this propellant are more than the reference propellant, with a TNT equivalent of 1.168–1.196. Finally, advanced protection armor suggestions were proposed based on the theory of woven fabric rubber composite armor (WFRCA).     

弹道修正弹射程偏差预测与阻力板展开时机优化

根据弹道修正弹阻力板的展开控制对于射程偏差预测要求的实时性,提出基于摄动原理的射程偏差预测算法.为解决阻力板修正能力在线计算数据量大的问题,提出在弹载计算机上装定阻力板修正能力表格的方法,给出发射前计算修正能力表格的过程和飞行中使用修正能力表格的步骤,提出阻力板展开时机的优化判断条件,并采用该方法对某型弹道修正火箭弹射程修正控制进行仿真试验和飞行试验.仿真试验结果表明,当目标射程为33 565.4m时,经修正后火箭弹的射程偏差能控制在20m以内;飞行试验结果表明,弹道修正火箭弹的射程偏差实测为24m,射程精度得到明显提高.     

钢丝增强复合条带抗弹性能数值分析

为研究钢丝增强聚合物基复合条带的抗弹性能,基于冲击动力学理论分析其抗弹机理,再借助ANSYS/LS-DYNA软件和LS-PrePost前后处理器模拟有无增强钢丝2种工况下,条带对7.62 mm弹体的冲击响应。分析表明：条带的弹性模量、剪切模量和面密度会影响其能量吸收性能,能量吸收量随三者的增大而增大;由于聚合物基体的正交各向异性,应力云图显示出扁平椭圆状是合理的;在聚合物基复合条带中嵌入增强钢丝对条带整体的抗弹性能有积极的影响,但嵌入过量的钢丝会导致重量和成本的增加,因此需要对合理的钢丝配比率作进一步研究。研究结果可为钢丝增强聚合物基复合条带在野战防护结构中的应用提供参考。     

舰艇作战系统电磁兼容的综合预测

分析了针对舰艇作战系统中电子系统的电磁兼容性的预测方法。针对舰载电子设备的电磁兼容问题,采用了一种综合分析的方法,通过综合考虑发射接收对之间的响应,利用发射机、接收机的辐射响应特性以及信道条件的数学模型,分析电子设备之间的电磁兼容性,对分析预测电子设备间的电磁兼容性具有一定的意义。     

可供实用的舰船风浪中摇荡时历预报的模式

舰船在风浪中摇荡时历的极短期预报 ,具有多方面的实用价值 .现有的各种预报方法中 ,以卷积法和时间序列法中的ARMA模型较为常用 ,但如何测量艏前波是上述方法实施的前提条件 ,则未能解决 .文中提出的在舰船舯部装塔克测波仪 ,将所测波形时历转换为艏前任意点波形时历的方法 ,可解决上述矛盾 .再采用ARMA建模、依AIC法则估计模型阶数的预报方式 ,即可用于实船进行摇荡时历短期预报     

综合飞行/火力控制系统性能评价

详细介绍了综合飞行 /火力控制系统 (IFFCS)性能评价的方法。该方法把评价过程分为单元评价、组合评价和系统性能评价 ,将系统性能指标逐层分解 ,以保证闭合系统最终能完成自动攻击任务。以高性能控制系统仿真软件MATTRIXX6 .0为平台 ,按此方法开发的评价软件获得了用户的认可     

高原环境对军用油料装备柴油动力性能影响分析

针对青藏高原特殊地理环境和气候条件特点,通过某大型群车加油车在高原地区的训练使用,分析海拔高度与大气压力、空气密度和温度的对应关系,探讨了在高原环境条件下使用油料装备其柴油动力的动力性、经济性及低温起动性能受到的影响,提出了相应的改进措施。     

电磁干扰预测在频率方案选择中的应用

应用电磁干扰预测的原理 ,针对一体化通信指挥系统中 ,多部电台集中使用所带来的频率管理问题 ,进行了干扰多级预测 ,得出了保证电磁兼容性系统各电台之间应满足的频率间隔 ,提出了通信网中通信频率方案     

基于频谱分析的飞行模拟器飞行性能验证

介绍频谱分析用于仿真系统模型验证的原理和方法,提出一种应用频谱分析进行飞行模拟器飞行性能验证的方案。结合飞行试验和仿真模型的输出数据,分别采用窗谱估计和最大熵谱估计方法对某型飞行模拟器的飞行性能进行验证,并对验证结果进行分析。结果表明,频谱分析法用于飞行模拟器飞行性能的验证是有效的,可为其他训练模拟器的性能验证提供参考。