计算机模拟升降法试验随机序列产生与统计检验

阐述了计算机模拟升降法试验中随机序列产生的基本原理。从参数分布、均匀性和不相关性三个方面对该随机序列进行了统计检验 ,并以该随机序列为基础 ,通过计算机模拟升降法试验 ,求得了感度分布标准差估计值的纠偏因子表 ,实例证明该纠偏因子表是有效的。     

用计算机模拟法对Langlie试验程序的研究

运用计算机模拟方法,研究了Ｌａｎｇｌｉｅ感度试验程序的不同初始试验参数选择对参数估计精度的影响,得出了Ｌａｎｇｌｉｅ法的最有利试验条件、不利试验条件和混合结果区出现规律。     

静电火花法表征塑料导爆管起爆感度探索

提出了塑料导爆管轴向静电火花感度的概念、测试原理。用标准的静电感度测试仪配以一定结构的起爆针 ,建立了可用于导爆管感度测试的实验装置 ,采用升降法测出导爆管起爆所需静电能量并用它来表征导爆管的感度。用三种导爆管进行了感度测试 ,实验条件下其感度值E0 .50 分别为 0 .4 3、1.0 8、1.94J。     

静电火花法表征塑料导爆管起爆感度探索

提出了塑料导爆管轴向静电火花感度的概念、测试原理.用标准的静电感度测试仪配以一定结构的起爆针,建立了可用于导爆管感度测试的实验装置,采用升降法测出导爆管起爆所需静电能量并用它来表征导爆管的感度.用三种导爆管进行了感度测试,实验条件下其感度值E0.50分别为0.43、1.08、＞1.94J.     

用水下卡片间隙试验法测定炸药冲击波感度

将炸药的水下爆炸能量测试方法与冲击波感度测试方法（小隔板法）相结合,研究了一种测试炸药冲击波感度的方法水下卡片间隙试验法,并用该方法得到了6种炸药冲击波感度的相对排序（从高到低）:炸药泰安、黑索金、8701、钝化黑索金、梯恩梯、膨化硝酸铵的冲击波感度依次降低,该试验结果与文献值、传统隔板试验结果一致,表明水下卡片间隙试验法的测试结果是可信的,水下卡片间隙试验法用于测定炸药冲击波感度是可行的,在一定程度上可代替传统的隔板试验法,此方法还可用于研究炸药装药密度对其冲击波感度的影响。     

测定疲劳强度的双细节串联升降法

指定寿命下的疲劳强度是无法直接测定的,自从测定疲劳强度的小子样升降法被提出以后,这种方法被广泛地应用于测定材料疲劳强度的随机特征。本文提出一种用于疲劳强度测定的双细节串联试件,给出了一个新的升降法流程。试件两个细节的疲劳强度在统计上是相互独立的,一个细节的破坏不会影响另一个细节,当一个细节破坏后,另一个细节的疲劳试验仍可以继续进行。为验证方法的有效性,本文进行了一系列的数值模拟。同时,这种方法还被用于飞机结构模拟件的疲劳强度试验。数值模拟结果和实际试验过程均表明,串联双细节升降法可以显著地节约试验时间。     

升降法试验全样本参数估计式

本文对升降法非线性似然方程组进行线性化处理,得到参数估计式.该式可充分利用试验信息,甚至对较小样本也相当接近计算机数值解.     

高能炸药摩擦感度的数值模拟

为了研究炸药摩擦安全性,利用熔化摩擦模型对几种高能炸药的摩擦感度进行了数值模拟,结果符合实验,并根据热分解反应速率分析了感度规律。由于炸药熔点一般低于点火温度,所以基于一个考虑熔化现象的炸药摩擦模型,在炸药感度实验条件下进行了一维数值模拟,给出了炸药熔化结果和摩擦点火的时间:4种摩擦感度较弱的炸药包括DATB、NQ、TATB和TNT的点火时间的顺序即感度顺序符合实验结果,说明摩擦点火模型适应性。进一步结合炸药热分解反应速率的大小顺序,数值模拟证明,在一定摩擦强度下,点火顺序会发生交换,说明摩擦感度实验不能完全说明炸药摩擦感度强弱顺序。     

?????????????????????????????????

为降低用来确定疲劳极限的升降法试验的工作量，以热力学为基础，引入损伤驱动力，构建 损伤演化方程. 积分此方程得到疲劳寿命与应力或应变的理论关系. 对光滑试件，根据成组 法疲劳试验结果利用最小二乘法拟合包括疲劳极限在内的材质参数. 利用损伤力学方法求得 高应力区的疲劳寿命曲线，由此递推得到低应力区寿命值和疲劳极限. 所得理论疲劳极限值 与升降法疲劳试验结果十分吻合. 节约了疲劳试验的机时、费用与人力.     

飞片撞击炸药感度试验方法研究

利用电炮驱动Mylar膜飞片加速冲击炸药的方式，研究了炸药的飞片起爆感度试验方法，并进行了部分试验。试验结果表明，该方法的建立是可行的，并对研究和评价炸药的安全性能和可靠性有着重要的意义和价值。当前，飞片撞击炸药感度试验方法的建立还不太成熟，有待于进一步研究和探讨。     

Analog simulation of magnetic hysteresis and its application

An analog simulation of hysteresis phenomena based on the magnetic domain theory is proposed. Hysteresis curves are simulated by superposition of a number of backlash elements which are followed by output limiters. The interaction of magnetization between domains is taken into account. This consideration makes it possible to simulate individual characteristics of various magnetic materials. A satisfactory performance of the simulator is obtained for an arbitrary form of the input; thus, the simulation of initial magnetizing curves, hysteresis loops and minor loops is found to agree with experimental observation. As an application of the simulator, the author applied this simulator to the analog computer setup and carried out a computer analysis of the series resonant circuit including a saturable core. The frequency response curves and the regions of initial conditions leading to the various oscillations which are obtained by the simulation found to agree with the experimental results.     

特征向量导数计算的Lanczos方法

本文对特征向量导数计算的Ｌａｎｃｚｏｓ法进行了改进，指出Ｌａｎｃｚｏｓ法对方程的缩阶效率取决于初始向量的选择，介绍了Ｌａｎｃｚｏｓ方法的发展，提出采用频率移位法选择初始Ｌａｎｃｚｏｓ向量。通过理论分析及计算机仿真说明移位Ｌａｎｃｚｏｓ方法可以将较大的方程组缩为一阶方程，在计算精度与效率上大大优于任选向量Ｌａｎｃｚｏｓ法和迭代Ｌａｎｃ－ｚｏｓ法     

充满液体弹塑性圆柱壳轴向冲击屈曲的数值模拟

基于对充满液体的弹塑性圆柱壳轴向冲击屈曲的实验观察 ,建立了相应的计算模型 ,借用 LS-DYNA软件包 ,在 HP-C36 0工作站上完成了数值模拟 ,得到了动画显示 ,给出的屈曲模态及一些特征量的时程曲线与实验结果相当一致。文中对壳的几何、物理参数对屈曲性能的影响进行了较详细的讨论     

On new effects of wheel-rail interaction

The paper is devoted to the experimental, theoretical analysis and computer simulation of influence of elastic properties of contact stiffness and wheel-plate stiffness on the forces of vehicle-track interaction. Three types of wheels are considered with different contact stiffness and wheel-plate design. Exemplary simulation of freight car interaction with track which posses one corrugated rail for each type of wheel is presented.     

双目视觉技术在高超声速颤振风洞试验中的应用

以验证高超声速颤振风洞试验技术为目标,为了获取试验模型在风洞流场激励下的位移形貌,运用风洞试验的方法研究了某翼面模型的颤振特性。采用一种基于双目视觉系统的试验方法,系统主要由CCD相机、图像采集卡和控制计算机组成,通过立体视觉标定和数字图像处理技术解算出模型变形的形貌。试验结果表明,该方法应用成功,与CFD/CSD数值计算结果比对良好,验证了该技术在高超声速风洞试验中应用的可行性。     

DSMC方法与稀薄气流计算的发展

直接模拟ＭｏｎｔｅＣａｒｌｏ（ＤＳＭＣ）方法是依赖物理的概率模拟方法．在求解过渡领域流动的众多解析、数值和模拟方法中,目前只有ＤＳＭＣ方法是可以模拟三维复杂真实气体流动的方法．从宏观参量到细观速度分布函数的水平上,该方法均能得到实验的支持．本文综述了ＤＳＭＣ方法的最近发展,包括我们在检验模型、处理内能松弛模拟和化学反应模拟以及求解三维绕流的通用方法等方面的工作。      

Assessment of tracked vehicle suspension system using a validated computer simulation model

A non-linear, in-plane computer simulation model of a typical high-mobility tracked vehicle is developed for suspension dynamic analysis and ride quality assessment. The Langrangian model formulation of the tracked vehicle is derived considering an arbitrary rigid terrain profile and constant vehicle speed. The model incorporates detailed representations of a trailing arm suspension system and dynamic wheel-track-terrain interactions. The computer model predictions are validated against field measurements, which were gathered from tests of an armoured personnel carrier traversing a discrete half-round bump and a random course. A parametric sensitivity analysis was carried out using the validated computer model in order to assess the influence of conventional suspension parameters on the ride performance of the test vehicle. In addition, the ride performance potentials of an alternate hydrogas suspension configuration were investigated.     

Creep buckling of axially compressed circular cylindrical shells of a zirconium alloy: Experiment and computer simulation

Experiments were performed to study the deformation and buckling of axially compressed circular cylindrical shells of Zr2.5Nb zirconium alloy under creep conditions. Computer simulation using the MSC.Marc 2012 software was conducted by step-by-step integration of the equations of quasistatic deformation of thin shells using Norton’s law of steady creep. The results of the experiment and computer simulation show that the buckling modes are a combination of axisymmetric bulges located near one end or both ends of the shell and axisymmetric buckling modes with the formation of three or four waves in the circumferential direction. A comparison is made of the time dependences of the axial strain of the shells obtained in the experiment and by computer simulation. It is shown that for large axial compressive stresses, these dependences are in satisfactory agreement. For lower values of these stresses, the difference between the theoretical and experimental dependences is greater.