废放射源处置方法研究

针对防化部（分）队应用放射源与含源装备仪器过程中产生大量废放射源的问题,根据国家和军队相关法规和标准,提出关于废放射源分类、收集、包装、运输、建库、储存和最终处置的贴近部队实际的处置方法要求．     

烟幕弹弹丸可视化设计系统建模方法研究

介绍了对烟幕弹弹丸进行可视化设计可行性的研究,以某型号烟幕弹弹丸为实例阐述了参数化模型的建立方法及特征数自动计算的实现,并对该可视化设计程序进行了验证。     

CR-39中子探测效率的模拟研究

利用蒙特卡罗（MC）方法计算了CR-39探测器对中子的探测效率,并与文献结果进行比较,得出了一致的结论;同时以^252Cf自发裂变源为模拟中子源,通过MCNP程序计算,得出了中子探测效率随CR-39探测器厚度变化的曲线。     

次氯酸钙乳液消毒剂模拟剂的研究

研究了一种次氯酸钙乳液消毒剂的模拟剂,以及一些影响稳定性因素．该模拟剂是以氢氧化钙为分散相,水为分散介质,表面活性剂和无机盐为稳定剂组成．实验结果表明,该模拟剂具有与次氨酸钙消毒乳液相同的物理性能,并且无污染,可用于教育、作训之中．     

分布共享存储系统中程序访存行为对性能的影响

本文首先提取了分布共享存储系统（ＤＳＭ）中程序访存行为的几个重要参数,并以此建立了一个处理机效率模型。在此模型基础上分析了访存行为的各种因素对处理机效率的影响情况,文章最后给出了提高处理机效率的几种技术途径。     

球面聚焦超声场计算与测量实验

研究了球面聚焦超声场的声压场计算.应用物理声学方法,推导了聚焦超声场声压的积分表达式,并通过数值分析法进行了计算和仿真,同时讨论了两种特殊情况下的声压近似解析式.最后推出了测量高强度聚焦超声装置声压的实例,其结果与理论仿真结果相近,偏差不大于3%.     

定数截尾的恒定应力加速寿命试验的优化设计

在指数分布场合下讨论了恒加试验的最优设计问题 ,得到了一系列与步加试验相对应的结果 .这里的最优准则是指正常应力水平下产品对数平均寿命估计的方差的极小化 .     

超临界航速船舶水压场

在浅水条件下,采用船舶水动力学理论,导出了一个包含色散效应的船舶水压场控制方程.通过求解,得到了考虑色散效应的船舶水压场计算公式,计算结果反映了实际船舶水压场的变化规律.     

基于改进Morison公式的海上漂浮软管波浪载荷计算

针对海上漂浮软管波浪载荷计算,分析了软管在海上的形态和受力特点,建立了海上漂浮软管力学分析模型,指出直接运用现有Morison方程计算漂浮软管波浪载荷存在的不足,并根据基本原理提出了改进Morison方程。对海上软质管线处于一定海况,分别运用改进Morison方程与现有Morison方程计算海上波浪载荷,并运用ANSYS软件建立软管模型,结果表明现有Morison方程不适用于计算海上漂浮软管波浪载荷,载荷计算结果偏高约15%,从而验证了改进Morison方程的精确性,有利于准确分析波浪载荷对海上漂浮软管的作用情况。     

Controllable combustion behaviors of the laser-controlled solid propellant

Microsatellites have been widely applied in the fields of communication,remote sensing,navigation and science exploration due to its characteristics of low cost,flexible launch mode and short development period.However,conventional solid-propellant have difficulties in starting and interrupting combustion because combustion is autonomously sustained after ignition.Herein,we proposed a new type of solid-propellant named laser-controlled solid propellant,which is sensitive to laser irradiation and can be started or interrupted by switching on/off the continuous wave laser.To demonstrate the feasibility and investigate the controllable combustion behaviors under different laser on/off conditions,the combus-tion parameters including burning rate,ignition delay time and platform pressure were tested using pressure sensor,high-speed camera and thermographic camera.The results showed that the increase of laser-on or laser-off duration both will lead to the decrease of propellant combustion performance during re-ignition and re-combustion process.This is mainly attributed to the laser attenuation caused by the accumulation of combustion residue and the change of chamber ambient temperature.Simultaneously,the multiple ignition tests revealed that the increased chamber ambient temperature after combustion can make up for the energy loss of laser attenuation and expansion of chamber cavity.However,the laser-controlled combustion performance of solid propellant displayed a decrease trend with the addi-tion of ignition times.Nevertheless,the results still exhibited good laser-controlled agility of laser-controlled solid propellant and manifested its inspiring potential in many aspects of space missions.