Development of cost effective personnel armour through structural hybridization

The objective of the present study is to develop cost effective thermoplastic hybrid laminate using Dyneema® HB50 and Tensylon®HSBD 30A through structural hybridization method. Laminates having 20 mm thickness were fabricated and subjected to 7.62 × 39 mm mild steel core projectile with an impact velocity of 730 ± 10 ms⁻¹. Parameters such as energy absorption, back face deformation and rate of back face deformation were measured as a function of hybridization ratio. It was observed that hybrid laminate with 50:50 ratio (w/w) of Tensylon® and Dyneema® with Tensylon® as front face showed 200% more energy absorption when compared to 100% Tensylon® laminate and showed equal energy absorption as that of expensive 100% Dyneema® laminate. Moreover, hybrid laminate with TD50:50 ratio showed 40% lower in terms of final back face deformation than Dyneema® laminate. Rate of back face deformation was also found to be slow for hybrid laminate as compared to Dyneema® laminate. Dynamic mechanical analysis showed that, Tensylon® laminate has got higher stiffness and lower damping factor than Dyneema® and hybrid laminates. The interface between Tensylon® and Dyneema® layers was found to be separating during the penetration process due to the poor interfacial bonding. Failure behaviour of laminates for different hybridization ratios were studied by sectioning the impacted laminates. It was observed that, the Tensylon® laminate has undergone shear cutting of fibers as major failure mode whereas the hybrid laminate showed shear cutting followed by tensile stretching, fiber pull out and delamination. These inputs are highly useful for body armour applications to design cost effective armour with enhanced performance.     

音圈式快速伺服刀架的分析与设计

自由曲面光学零件面形复杂,快刀伺服车削加工是其高效加工手段.针对压电陶瓷型伺服刀架行程小,加工能力有限的问题,提出一种基于音圈式直线电机驱动的快刀伺服方案.音圈式快速伺服刀架行程大,可大大拓宽快刀伺服加工范围.以典型光学零件加工为例,对快速伺服刀架所应具备的关键性能指标进行分析,给出了音圈电机的结构,对音圈式伺服刀架进行了理论建模、控制器设计以及实际性能测试.测试结果表明,所设计的音圈式伺服刀架行程大、频响高,在刀架行程为±100μm时可达到300Hz的频响能力,同样行程下的频响指标优于国外同类产品.     

超声冲击处理改善22SiMn2TiB装甲钢抗应力腐蚀性能研究

采用超声冲击处理工艺对22SiMn2TiB装甲钢试样进行了表面冲击强化,采用四点弯曲加载装置将处理和未处理的试样在3.5%NaCl溶液中进行了150 d的应力腐蚀试验。用X射线应力测定仪测定了应力腐蚀试验前试样表面的残余应力,用扫描电镜和透射电镜观察了处理后试样的断面组织。分析了超声冲击处理引起的残余应力和断面组织变化对改善装甲钢抗应力腐蚀性能的作用。结果表明,超声冲击处理引入的残余压应力和表层晶粒细化可以大大提高22SiMn2TiB装甲钢的抗应力腐蚀性能。     

导弹制导控制与目标杀伤

采用协方差分析描述函数技术 (CADFT)对寻的导弹的制导精度进行了研究 ,提出了空气动力控制、直接侧向力控制的寻的导弹飞行末端的制导精度的一种新的解析模型 ,并研究了导弹直接碰撞杀伤目标的必要条件 ,该理论研究成果具有简单、实用、精度高的特点 ,为寻的导弹制导控制特性研究和揭示寻的理论普遍规律提供了一种新途径     

Characteristics structure analysis on debris cloud in the hypervelocity impact of disk projectile on thin plate

In this paper, the gauge points setting is introduced in the SPH simulation to analyze the debris cloud structure generated by the hypervelocity impact of disk projectile on thin plate. Compared with the experiments, more detailed information of the debris cloud structure can be classified from the numerical simulation. However, due to the solitary dispersion and overlap display of the particles in the SPH simulation, accurate comparison between numerical and experimental results is difficult to be performed. To track the velocity and spatial distribution of the particles in the debris cloud induced from disk and plate, gauge points are locally set in the single-layer profile in the SPH model. By analyzing the gauge points’ spatial coordinate and velocity, the location and velocity of characteristic points in the debris cloud are determined. The boundary of debris cloud is achieved, as well as the fragments distribution outside the main structure of debris cloud.     

利用MSC/DYTRAN程序仿真分析导弹战斗部立方体破片的侵彻威力

对反辐射导弹的破片杀伤战斗部中较为常见的立方体破片的 3种典型姿态侵彻 (尖端、棱边及正面侵彻 ) 4mm厚 94 5钢的侵彻过程进行仿真数值计算 .通过仿真计算 ,结合实验结果比较 ,得出结论 :不同初始侵彻姿态的立方体破片在侵彻过程中 ,由于旋转角速度的作用及稳定性的要求 ,破片的侵彻姿态将趋于正面侵彻 .不同姿态的侵彻 ,侵彻威力相差不大     

燃气射流引起的火箭发射系统振动特性分析

以火箭发射系统为研究对象,对其56°射角工况下发射过程中的振动特性进行分析。创新点在于确定发射过程中动态载荷的加载方法,即首先根据发射系统有限元分析结果确定迎气面上试验测量点的具体位置,然后测得燃气射流冲击压强随时间变化的数值,并对试验测得数据进行处理,最后推导冲击压力对于径向距离的直线公式。所采用的冲击压强分析方法为研究其他武器系统受燃气射流冲击的影响提供了重要的指导意义。     

自行火炮扭力轴载荷谱的测量及疲劳寿命预测

为预测自行火炮扭力轴寿命，对某型自行火炮在不同工况下进行实车试验，获得了多工况下扭力轴的载荷谱。受力分析表明，表面最大拉应力是扭力轴的破坏应力；提出基于随机响应面对扭力轴寿命进行预测的方法，将低周疲劳寿命表达式中的随机参数表示为标准随机变量，引人随机响应的Hermite多项展开式进行拟合，建立了扭力轴疲劳寿命的显式函数。通过对实测载荷谱进行统计分析，依据寿命表达式可以预测扭力轴疲劳寿命，并给出概率分布。该方法弥补了传统响应面法以一般多项式拟合时不能保证收敛性的缺陷。     

A two‐echelon inventory‐location problem with service considerations

We study the problem of designing a two‐echelon spare parts inventory system consisting of a central plant and a number of service centers each serving a set of customers with stochastic demand. Processing and storage capacities at both levels of facilities are limited. The manufacturing process is modeled as a queuing system at the plant. The goal is to optimize the base‐stock levels at both echelons, the location of service centers, and the allocation of customers to centers simultaneously, subject to service constraints. A mixed integer nonlinear programming model (MINLP) is formulated to minimize the total expected cost of the system. The problem is NP‐hard and a Lagrangian heuristic is proposed. We present computational results and discuss the trade‐off between cost and service. © 2009 Wiley Periodicals, Inc. Naval Research Logistics 2009     

空降车-气囊系统着地缓冲过程仿真分析

为了给空降车及其气囊的优化设计提供技术支持,采用有限元方法对空降车气囊缓冲过程进行仿真分析。计算了正常着地工况下的气囊缓冲过程,得到速度、加速度以及气囊内压等时间特性曲线。结果表明:空降车在该工况下着地速度小于3m/s,该气囊符合空降车着地的缓冲性能要求。车体加速度和冲击应力在误差许可范围内,验证了采用此种方法进行空降车气囊缓冲过程的虚拟测试是可行的。