子母式穿甲弹子弹发射过程研究

对子母式穿甲弹子弹的发射过程进行详细的分析,得出了子弹长度与子弹飞离母弹速度的关系、子弹长度与火药燃烧率的关系、子弹长度与母弹弹头部发射孔内最大压力的关系以及子弹的长度与子弹发射所需时间的关系,为子母式穿甲弹设计提供了依据。     

包带式星箭紧锁预紧力分析

根据星箭连接处受力情况及紧锁装置的特点,分析了星箭连接处发生松动的可能性,导出了星箭紧锁所需包带预紧力计算公式,提出了解决包带应力分布不均匀的方法。通过与两种型号的实验结果对比,证明了本文分析方法的正确性和计算公式的可信性。本文所得结论为包带式星箭紧锁结构设计提供了依据。     

舰载导弹垂直发射系统的综合测控系统

通过对舰载导弹垂直发射系统中贮运发射箱内环境监控、导弹综合测试、发射过程控制、射击参数装定以及应急状态自动处理等需求分析,提出建立综合测控系统方案,并探讨了以LONworks总线为核心的综合测控系统基本结构、组成和功用.     

Parametric study of single confined fragment launch explosive device

In this article, parametric study of single confined fragment launch device was carried out. The configuration proposed was further studied to derive the empirical relationship for effect of fragment size, charge size, confinement thickness on fragment velocity. The simulations were carried out using ANSYS-AUTODYNE explicit solver. Fragment velocities were estimated as a function of different parametric combinations of explosive quantities, charge length to diameter ratio, fragment height to diameter ratio, confinement thickness, fragment material and fragment mass. The data was further converted to charge to metal ratio under fragment and confinement. It was observed that, increase in confinement thickness, charge quantity and decrease in fragment height increases the fragment velocity. It is also noted that, charge to metal mass ratio under fragment significantly affects the fragment velocity. At the end, an empirical relationship for fragment velocity interms of all these parameters was established. Using these relations, two velocities 1831.92 m/s and 2523.9 m/s required for NATO STANAG 4496 IM test were estimated. The design parameters for these velocities are presented. Also, the results estimated using the empirical relationship has been compared with published experimental data. Error in the predicted velocities is within the acceptable range. The empirical relationship proposed will be useful for finalization of design of the fragment launch device.     

小型固体运载器一、二级分离动力学与仿真研究

某低成本小型固体运载器采用侧喷流和栅格舵联合进行姿态控制。针对该布局,设计引入闭环姿态控制的一、二级级间冷分离方案。在描述级间分离过程的基础上,建立了分离运动学与动力学模型,解锁与分离冲量装置模型,气动力模型以及分离姿态控制律模型,讨论了碰撞判断条件,通过Monte Carlo仿真验证了参数不确定条件下分离姿态控制律设计对于避免碰撞和减小上面级初始姿态偏差的有效性。结果表明所设计的分离方案在充分发挥冷分离优势的同时能够弥补由冷分离时间长引起的上面级初始姿态偏差,能够有效避免级间碰撞。为该运载器的级间分离方案提供了一种可能的选择。     

On the availability of R out of N repairable systems

An R out of N repairable system consisting of N components and operates if at least R components are functioning. Repairable means that failed components are repaired, and upon repair completion they are as good as new. We derive formulas for the expected up‐time, expected down‐time, and the availability of the system, using Markov renewal processes. We assume that either the repair times of the components are generally distributed and the components' lifetimes are exponential or vice versa. The analysis is done for systems with either cold or warm stand‐by. Numerical examples are given for several life time and repair time distributions. © 2002 Wiley Periodicals, Inc. Naval Research Logistics 49: 483–498, 2002; Published online in Wiley InterScience (www.interscience.wiley.com). DOI 10.1002/nav.10025     

航母舰载机对空防御作战出航保障指挥决策建模

基于Agent的航母舰载机对空防御作战出航保障指挥决策系统,由数据部分和Agent组织部分组成.前者又含数据库、模型库、知识库、相关管理系统和MIS.后者包括五大决策Agent,通过界面Agent与用户进行交互,而与数据部分的交互则由DB监理Agent统一完成.对于系统内决策Agent的设计,可首先针对五大决策Agent的模板进行设计,再对其功能层进行实例化.     

某型车载导弹发射制导装置现场快速检测方法

某型装甲车载反坦克导弹系统的发射制导装置,集光、机、电多种技术于一体,技术状态易受装载、运输等因素的影响。在导弹射击前,一般应在现场对发射制导装置进行快速检测以确定其技术状态。为了解决现场快速检测问题,分析了该型导弹系统发射制导装置的结构和技术特点,确定了现场快速检测的内容：用点光源的电视图像检测两个光轴不平度;用电压比较法检测点火电压和点火程序正确性;用指令频率变化检测控制指令正确性。开发了适于现场快速检测的装置,为部队射击保障提供了一种决策支持方法。     

地理社交网络位置推荐

地理社交网络将地理位置信息融合进传统社交网络,将人们的现实生活和虚拟世界的生活连接在一起。作为地理社交网络的一个重要应用,位置推荐可以向人们推荐其可能感兴趣的位置,为人们的出行提供参考,极大地便利了人们的生活。在此背景下,论文研究了地理社交网络位置推荐的基本概念,分析了位置推荐常用的方法,描述了典型的数据集及推荐效果的评估方法,指出了位置推荐面临的主要问题,并展望了未来可能的研究方向,为相关领域的研究提供参考。     

风载荷对某发射装置待发射状态的影响

应用冯.卡门功率谱和谐波合成法生成了考虑脉动效应的瞬时风速时程曲线;计算了发射筒各段的等效风压及等效力矩,给出了作用于发射筒迎风面的风压总值及等效力矩;最后将载荷作为输入条件,进行动力学分析,获得了风载荷作用下发射装置的动态响应。通过分析可知:由于发射装置具有刚度强、质量大的特点,风载荷作用下发射装置的速度、加速度响应均较低,因此,风载荷主要影响发射筒的倾斜程度。