Shock initiation performance of NTO-based polymer bonded explosive

3-nitro-1,2,4-tri-azol-5-one (NTO) is a high energy insensitive explosive. To study the shock initiation process of NTO-based polymer bonded explosive JEOL-1 (32%octahydro-1,3,5,7-tetranitro-1,3,5,7-tetrazocine (HMX), 32% NTO, 28% Al and 8% binder system), the cylinder test, the gap experiments and numerical simulation were carried out. Firstly, we got the detonation velocity (7746 m/s) and the parameters of Jones-Wilkins-Lee (JWL) equation of state (EOS) for detonation product by cylinder test and numerical simulation. Secondly, the Hugoniot curve of unreacted explosive for JEOL-1 was obtained calculating the data of pressure and time at different Lagrangian positions. Then the JWL EOS of unreacted explosive was obtained by utilizing the Hugoniot curve as the reference curve. Finally, we got the pressure growth history of JEOL-1 under shock wave stimulation and the parameters of the ignition and growth reaction rate equation were obtained by the pressure-time curves measured by the shock-initiation gap experiment and numerical simulation. The determined trinomial ignition and growth model (IG model) parameters can be applied to subsequently simulation analysis and design of insensitive ammunition with NTO-based polymer bonded explosive.     

A study on the surface overpressure distribution and formation of a double curvature liner under a two-point initiation

The formation mechanism of an EFP(explosively formed projectile) using a double curvature liner under the overpressure effect generated by a regular oblique reflection was investigated in this paper.Based on the detonation wave propagation theory,the change of the incident angle of the detonation wave collision at different positions and the distribution area of the overpressure on the surface of the liner were calculated.Three-dimensional numerical simulations of the formation process of the EFP with tail as well as the ability to penetrate 45# steel were performed using LS-DYNA software,and the EFP ve-locity,the penetration ability,and the forming were assessed via experiments and x-ray photographs.The experimental results coincides with those of the simulations.Results indicate that the collision of the detonation wave was controlled to be a regular oblique reflection acting on the liner by setting the di-mensions of the unit charge and maintaining the pressure at the collision point region at more than 2.4 times the CJ detonation when the incident angle approached the critical angle.The distance from the liner midline to the boundary of the area within which the pressure ratio of the regular oblique reflection pressure to the CJ detonation pressure was greater than 2.5,2,and 1.5was approximately 0.66 mm,1.32 mm,and 3.3 mm,respectively.It is noted that pressure gradient caused the liner to turn inside out in the middle to form the head of the EFP and close the two tails of the EFP at approximately 120μs.The penetration depth of the EFP into a 45# steel target exceeded 30 mm,and there was radial expansion between the head and tail of the EFE increasing the penetration resistance of the EFP.Therefore,the structural size of the unit charge and the liner can be further optimized to reduce resistance to increase the penetration ability of the EFP.     

Formation of explosively formed penetrator with fins and its flight characteristics

The ultimate goal of weapon system employing an explosively formed penetrator (EFP) is to defeat a target at the longest standoff. In order to do this, an EFP must be aerodynamically stable so as to strike the target at a small angle of obliquity, and the decay velocity per meter of EFP must be smaller at extended standoff. As the angle of attack increases, the penetration ability of EFP greatly reduces. The fins improve the EFP aeroballistic characteristics and decrease the flight drag of EFP as well. EFP with fins formed by three-point initiation is presented. The formation of EFP with fins is studied by LS-DYNA, and the aeroballistics is studied through experiment. The experimental results show that the decay velocity per meter of EFP with fins is much smaller than that of normal EFP, and the attitude angle steadily decreases.     

反潜机采用阿基米德螺旋线搜潜问题研究

反潜机是重要的反潜力量,根据反潜机搜潜情况,建立了反潜飞机采用阿基米德螺旋线样式搜潜的数学模型和目标运动模型,讨论了螺旋线采用的三种轨迹间隔,通过仿真验证,确立了反潜机搜潜最优轨迹间隔,以达到提高发现目标潜艇概率、优化反潜效能的目的,为反潜飞机采用阿基米德巡逻线搜潜样式搜潜时提供战术参考。     

卫星导航接收机捕获和跟踪抗干扰能力分析

卫星导航抗干扰技术是接收机研制中的热点问题,不同的干扰模式对接收机的影响各不相同。通过建立非相干高斯白噪声、单频干扰和扫频干扰等3种常见干扰模型,分析了干扰对码分多址卫星导航接收机常用的并行码相位捕获和科斯塔斯环路跟踪阶段的影响,获得了其在2个阶段的抗干扰能力。研究表明,不同频率变换方式的单频干扰对接收机环路的影响区别不大,而与干扰频点接近信号中心频点的长短密切相关,同时接收机对非相关高斯白噪声干扰的抗击能力要远大于单频干扰。研究结论对码分多址卫星导航接收机和干扰机的设计具有一定的参考意义。     

利用时间窗权重进行航迹关联

提出一种利用传感器测量数据的时间窗权重进行航迹关联的方法,将目标运动状态的多维向量(如距离、方位角、俯仰角等)分解为多个一维状态标量;根据每个状态标量与时间的关系,提取两条航迹的共同测量时间区间,将其划分为若干个时间窗,计算对应时间窗内的权重;根据时间窗权重差计算每一个状态标量的航迹相似度;应用DS理论或Bayes理论进行航迹关联决策。     

复杂环境下多雷达点迹融合

针对系统误差、杂波干扰等对点迹融合处理系统的影响,结合工程实践,提出了一种处理复杂环境下多雷达点迹融合结构框架,给出了存在系统误差情形下的多雷达航迹起始、虚假目标抑制、雷达误差配准等模型和算法。仿真结果表明,提出的框架、模型和算法能够有效处理多雷达点迹融合问题。     

通信受限下分布式多传感器协同跟踪算法

在分布式多传感器目标跟踪系统中,由于局部融合中心(LFC)的物理限制(如:有限的频率信道、处理器容量有限等),只能接收有限个传感器的传送数据。此外,信息传输的方式也将影响传感网的使用寿命,因此,研究了通信受限下的分布式多传感器目标协同跟踪问题。首先对监视区内分布的传感器进行聚类分簇形成若干个子网,接着从通信能耗的角度出发,对传感器采集信息的传递路径进行最优路径规划;进而对子网局部状态进行估计,在子网信息融合中,分别采用最大距离和、最大化信息增量两种准则进行最佳传感器选择,最后通过各子网全局航迹融合实现分布式多传感器协同跟踪。仿真验证了算法的有效性。     

源和流：中国特色社会主义理论体系形成发展的轨迹探究

从党的创新理论发展史的角度,回顾了建党90年来中国特色社会主义理论体系形成与发展的历史轨迹,力求从历史与逻辑相统一中反映出从邓小平理论到科学发展观的历史演进过程。     

面向时差定位无源雷达的空情想定设计系统

针对时差定位无源雷达操作演练和性能检测时的空情想定设计问题,设计开发空情想定设计系统.基于距离方位标尺部署无源雷达各站,采用样条插值方法和航向平滑算法绘制目标航迹,能够实现在一定战术背景条件下,覆盖多种布站方式,针对多种类型和多批次目标的时差定位无源雷达防空预警作战的空情想定设计.最后给出了一个设计实例.