卧式储油罐罐体变位模型与罐容表标定

针对储油罐罐体变位影响油品计量精度的问题,建立了球冠形封头卧式储油罐罐体变位模型,将罐体变位后的油位高度转换成无变位时的油位高度,再利用罐体无变位时的储油体积计算模型得到变位后储油体积与油位高度的关系。分析了罐体变位对罐容表的影响,提出了一种基于最小二乘原理的变位参数识别算法,最后对该变位模型进行了检验,并采用插值算法重新标定了变位后的罐容表。结果表明:该变位模型与实际情况基本相符,变位参数识别算法能估计出罐体倾斜角度和偏转角度。     

分布式干扰下雷达组网探测效能分析

针对雷达和干扰机两种重要组网体系的战术对抗应用,采用等效噪声功率谱密度表征干扰特性,推导出多干扰源下的雷达探测距离方程;并提出了区域网格融合算法,实现了分布式干扰下雷达网不规则探测区域绘制;对于评估雷达网作战效能具有重要工程应用价值。     

Pressure relief of underground ammunition storage under missile accidental ignition

Safety of underground ammunition storage is an important issue, especially during the accidental ignition of missiles. This work investigates the pressure and temperature distribution of the multi-layer underground ammunition storage with a pressure relief duct during the accidental ignition process of the missile. A large-scale experiment was carried out using a multi-layered restricted space with a pressure relief duct to simulate the underground ammunition store and a solid rocket motor to simulate the accidental ignition of the missile. The results show that when the motor gas mass flow increased by 5.6 times, the maximum pressure of the ammunition storage increased by 5.87 times. At a certain motor flow rate, when the pressure relief exhaust area at the end of the relief duct was reduced by 1/2, the maximum pressure on the first layer did not change. But the rate of pressure relief was reduced and the time delayed for the pressure of ammunition store to drop to zero. In this experiment, when the motor ignition position was located in to the third layer ammunition chamber, the maximum pressure was reduced by 32.9％ and also reduced the rate of change of pressure. In addition, for the experimental conditions, the theoretical analysis of the pressure relief of the ammunition storage is given by a simplified model. Based on the findings, some suggestions to the safety protection design of ammunition store are proposed.     

A novel launch dynamics measurement system for multiple launch rocket system and comparative analysis with numerical simulations

In this paper,a novel launch dynamics measurement system based on the photoelectric sensor pair is built.The actual muzzle time(i.e.a time duration that originates from the initial movement to the rocket's departure from the muzzle)and the muzzle velocity are measured.Compared with the classical methods,the actual muzzle time is obtained by eliminating the ignition delay.The comparative analysis method is proposed with numerical simulations established by the transfer matrix method for multibody systems.The experiment results indicate that the proposed measurement system can effectively measure the actual muzzle time and reduce the error of classical methods,which match well with the simulation results showing the launch dynamics model is reliable and helpful for further analysis and design of the MLRS.     

长期贮存的固体发动机药柱脱粘界面裂纹分析

为了分析长期贮存的固体导弹发动机药柱脱粘层界面裂纹在燃气内压和轴向过载联合作用下的扩展情况,建立了发动机药柱在包覆层与推进剂之间脱粘的三维有限元计算模型,并于脱粘界面的裂纹尖端设置三维奇异裂纹元,模拟脱粘界面裂纹扩展。在包覆层与推进剂之间设置不同深度脱粘,计算了在燃气内压和轴向过载联合作用下不同贮存期、不同深度的界面裂纹尖端的应力强度因子,得到了界面裂纹应力强度因子随贮存时间、脱粘深度的变化规律,对长期贮存的固体发动机脱粘界面裂纹的扩展进行了分析。     

主星带伴随分布式小卫星雷达系统的波束同步分析

波束同步是主星带伴随分布式小卫星雷达系统的同步问题之一,分析了主星带伴随分布式小卫星雷达系统的波束同步问题。根据主星带伴随分布式小卫星雷达系统的特点,结合小卫星天线俯仰向可扫描、姿态可调节,提出了三种波束指向同步方法;分析了分布式小卫星雷达系统的波束覆盖同步问题,分别建立了主星和伴随分布式小卫星的波束覆盖数学模型;仿真分析“干涉车轮”,结果不仅证明这些模型的正确性,同时发现波束指向同步方法2有较好的优越性。     

狭长受限空间火灾临界可燃距离实验研究

油料洞库的安全一直是各级主管部门非常关心的问题。狭长受限空间是地下建筑及地下油料洞库的关键结构,针对狭长受限空间发生火灾能否持续燃烧问题,在公称直径分别为50mm、100mm、150mm和250mm的模拟狭长受限空间上,以柴油作为燃烧工质,置于尺寸、形状各异的3种油盘中,进行了系统实验研究与分析,证实了狭长受限空间临界可燃距离的存在,并在此基础上,提出了计算方法,得出一些有益的结论,对研究油料洞库消防新技术有一定的价值。     

军用导航技术发展趋势

现代战争的高技术特点要求武器系统装备精密导航系统来提供精确的导航信息 ,提高武器的战斗性能。论述了惯性敏感器发展技术、GPS技术、GPS/INS组合与抗干扰问题。发展高精度、低成本、抗干扰能力强的导航系统是未来军用导航系统发展的趋势     

光电对抗技术发展概况及装备需求

阐述了光电对抗的基本概念及其发展状况,针对现代海战的战法特点,论证了发展海军光电对抗系统的紧迫性,指出了光电对抗系统的关键技术．     

仿真网格原型系统的设计与实现

进行仿真网格原型系统的研究是解决仿真网格关键技术的基础。SGE网格引擎是一个构建本地和集群级网格的工具,通过SGE构建基本的网格平台,根据HLA仿真任务的特点,对分布式仿真网格的原型系统进行了研究和设计。提出了仿真网格的双通道通信机制:一个通道负责仿真网格组件的通信,另一个通道负责HLA仿真任务之间的通信。提出了仿真任务在仿真网格中的三种调度模式:以进程为单位的调度、以联邦成员为单位的调度、以联邦为单位的调度等。通过研究初步实现了仿真网格的原型系统,并对HLA仿真任务的三种调度模式进行了简单的测试。