微波器件微放电阈值计算的快速单粒子蒙特卡罗方法

为了计算微波器件的微放电阈值,提出了一种快速单粒子蒙特卡罗方法.该方法对二次电子出射能量、出射角度和相位等参数进行随机处理,结合四阶龙格库塔法和Furman模型模拟了电子运动和二次电子发射系数,并以多次连续碰撞的二次电子发射系数的算数平均值作为微放电效应发生的判据.以平板传输线横电磁模式为研究对象,分别采用快速单粒子蒙特卡罗方法、统计模型、传统蒙特卡罗方法以及粒子模拟方法计算其微放电阈值和敏感区域.计算结果表明,该方法不仅具有与统计模型和粒子模拟方法相当的计算精度,而且比统计模型方法的适应性更强,比传统蒙特卡罗方法的稳定性更好,比粒子模拟方法的计算效率高几十倍以上.     

电子回旋共振放电的电离特性PIC/MCC模拟(Ⅰ)——物理模型与理论方法

采用粒子模拟与蒙特卡罗相结合(PIC/MCC)的方法对电子回旋共振(ECR)放电中的电离过程进行了模拟，其中带电粒子与微波的相互作用由PIC方法的电磁模型描述，粒子间的碰撞过程由MCC方法描述.考虑的碰撞类型有电子与中性粒子的弹性、激发、电离碰撞，离子与中性粒子的弹性、电荷交换碰撞，碰撞截面均依赖于能量而变化.阐述了理论分析的过程，为数值模拟ECR放电奠定了基础. 关键词： 电子回旋共振放电 粒子模拟 蒙特卡罗 电离     

一种补偿时间步长限制的粒子模拟-蒙特卡罗碰撞模型

 从碰撞次数的概率分布出发,推导出一种补偿蒙特卡罗碰撞模型,采用以正态分布计算得到的平均碰撞次数作为碰撞概率,来补偿传统方法中忽略的多次碰撞。通过模拟不同折合电场强度条件下He气放电产生电子的运动规律,验证了补偿蒙特卡罗碰撞模型的正确性。计算结果表明:补偿蒙特卡罗碰撞模型可以有效地提高计算效率,特别适用于高气压气体放电现象的粒子模拟。     

二维直通道内气固两相流动的实验研究

本文利用频闪激光片光源摄像和图象处理技术，对二维直通道内气固两相流动进行了实验研究，定量测定了固体粒子的运动参数、运动速度、方向．测得了粒子的运动轨迹．并得出一些有价值的结论：在本实验范围内粒子基本上沿直线运动，并处于不断加速的状态；粒子与壁面碰撞的时间极短，反弹角小于碰撞角，反弹速率小于碰撞速率．从而获得了在不同的进口气流速度及不同的通道倾角下固体粒子与固体壁面碰撞的某些规律．得到了粒子与壁面相互作用的关系表达式．为理论计算打下了基础．     

用区域分解算法结合蒙特卡罗法求坦克温度场和红外辐射出射度

本文将区域分解算法和蒙特卡罗法相结合，求坦克温度场和红外辐射出射度．采用蒙特卡罗法计算辐射传递系数，可以考虑界面的复杂辐射特性，如：镜反射、各向异性发射、各向异性反射等；可直接考虑界面的复杂几何特性，如:相互遮挡、太阳入射方向上的投影面积等．引入辐射传递系数，分离了计算的难点，使得在时间域（计算步骤）上能把整个问题分解为若干个子问题并行处理、在空间域（计算区域）上将坦克分解为若干个子区域，缩小计算规模，并可使用多个处理器并行计算；同时减轻了蒙特卡罗法编程的难度，缩短了计算时间．     

基于负氢离子源的全三维PIC/MCC模拟算法研究

在分析负氢离子源中等离子体物理机理基础下, 研究并优化粒子模拟算法, 设计高效的粒子存储方法. 研究并运用粒子碰撞蒙特卡罗方法, 考虑等离子体势以及带电粒子间库仑碰撞, 研制了全三维粒子模拟/蒙特卡罗算法(PIC/MCC). 采用磁荷模型, 运用时域有限差分方法计算多峰磁场, 并结合国外负氢离子源JT-60U, 考虑负氢离子源中主要反应, 对全三维PIC/MCC模拟算法模拟验证.     

电子回旋共振放电中电子与微波互作用特性的粒子模拟和蒙特卡罗碰撞模拟

对电子回旋共振（ECR）放电电离过程中的电子与微波互作用特性进行了理论分析与数值模拟.采用粒子模拟（PIC）方法描述带电粒子与微波的互作用,采用蒙特卡罗碰撞（MCC）方法描述粒子间碰撞过程及带电粒子与边界的相互作用.编写了准三维的PIC/MCC数值模拟程序,并对放电过程中电子能量与微波场随时间、空间的演化进行了数值诊断. 关键词： 电子回旋共振放电 粒子模拟 蒙特卡罗方法 电离     

2.1AGeVNe NaF碰撞中的粒子群关联与集体性

提出了粒子群关联概念，并以此建立了一种检测集合流的新方法，采用新方法对２．１ＡＧｅＶＮｅ＋ＮａＦ碰撞的Ｂｅｖａｌａｃ流光室４π实验事件粒子群的关联进行了研究．通过与蒙特卡罗结果进行比较，推测该实验事件集合流的集体性约在７５％－９５％之间。     

部分子相互作用与(S_(NN))~(1/2)=130GeV Au-Au碰撞中两粒子的横向动量关联(英文)

采用蒙特卡罗模型AMPT 究了(S_(NN))~(1/2)=130GeV Au Au碰撞中部分子相互作用对两粒子横向动量关联的影响,结果表明部分子相互作用对两粒子的横向动量关联有重要的贡献．还计算了AMPT模型中(S_(NN))~(1/2)=130GeV Au Au碰撞的两粒子横向动量关联与碰撞对心性的依赖关系并与来自STAR的实验数据进行了比较,发现AMPT的理论预言很好地符合实验数据．     

基于理想流体对称碰撞模型的爆炸焊接流场角变形计算

 采用理想流体对称碰撞模型,分析了爆炸焊接流场中沿流线的物理变形,推导出了角变形的理论计算公式,并采用Visual C++语言对其进行了编程计算,获得了驻点近区角变形的大小及变化规律。结果表明,在驻点近区,沿来流至出流方向角变形逐步增大,其变化率在驻点附近最大;沿出流方向,给定碰撞角,角变形随来流速度的增加而增大;给定来流速度,角变形随碰撞角的增大而减小。从理论和实验方面,间接地将计算结果与前人的结论进行了对比验证,结果是一致的,以此为基础配合驻点近区的应变率场,讨论了其对爆炸焊接波状界面形成的影响。     

Aerothermodynamic Analysis of a Reentry Brazilian Satellite

This work deals with a computational investigation on the small ballistic reentry Brazilian vehicle SAtélite de Reentrada Atmosférica (SARA). Hypersonic flows over the vehicle SARA at zero-degree angle of attack in chemical equilibrium and thermal nonequilibrium are modeled by the direct simulation Monte Carlo method, which has become the main technique for studying complex multidimensional rarefied flows, and which properly accounts for the nonequilibrium aspects of the flows. The emphasis of this paper is to examine the behavior of the primary properties during the high-altitude portion of SARA reentry. In this way, velocity, density, pressure, and temperature field are investigated for altitudes of 100, 95, 90, 85, and 80?km. In addition, comparisons based on geometry are made between axisymmetric and planar two-dimensional configurations. Some significant differences between these configurations were noted on the flowfield structure in the reentry trajectory. The analysis showed that the flow disturbances have different influence on velocity, density, pressure, and temperature along the stagnation streamline ahead of the capsule nose. It was found that the stagnation region is a thermally stressed zone. It was also found that the stagnation region is a zone of strong compression, high wall pressure. Wall pressure distributions are compared with those of available experimental data, and good agreement is found along the spherical nose for the altitude range investigated.     

再入飞行器等离子体预测与气体组分相关性

对一类大钝头再入飞行器,理论分析电子密度预测与气体组分的相关性,使用经验证的数值模拟方法研究化学反应模型对等离子体预测的影响.研究发现:马赫数是影响等离子体预测与气体组分相关性的重要参数,马赫数越高,不同气体组分模型所得电子密度差异越大.气体组分模型对等离子体预测的影响在驻点强压缩区域和身部位置基本一致.对于大钝头再入飞行器,高度H=60 km,马赫数大于23时应该采用11组分化学反应模型.     

Particle formation in opposed-flow diffusion flames of ethylene: An experimental and numerical study

An experimental and numerical study on particles inception and growth is performed in opposed-flow diffusion flames of ethylene and air characterized by different sooting tendencies. Spectrally resolved UV-visible laser induced fluorescence, laser induced incandescence and laser light scattering measurements are used to characterize different classes of combustion-generated compounds. A detailed kinetic model accounting for both gas-phase and particle formation is used. Comparison between experimental results and numerical predictions gives a qualitative view of the mechanism of particle formation in opposed-flow flames.Particle inception is the result of both chemical growth and coagulation of aromatic compounds. In the region close to the flame front where the temperature is relatively high and radicals are abundant, the particle inception is due to a chemical growth mechanism by which aromatic molecules add aromatic radicals leading to the formation of biphenyl-like structures. The growth process continues as high-molecular mass aromatics are moved away from the flame zone towards the stagnation plane by the addition of acetylene and other aromatics forming particles of increasing sizes. Graphitization of these particles and thermal annealing lead to the formation of soot particles. At relatively lower temperatures, found across the stagnation plane, particles growth still occurs and it is mainly due to a process of physical coagulation of PAHs.The experimental and numerical results obtained in this work demonstrate and explain the sensibility of inception and growth of particles to radical concentration and temperature in opposed-flow flame configurations.     

火星进入热环境预测的热力学模型数值分析

采用数值模拟目的 研究不同热力学模型中火星飞行器表面的热环境.研究发现,驻点区域流动近似为热力学平衡,随着飞行高度增加,流动逐渐偏向热力学非平衡.当壁面为非催化壁时,不同热力学模型所得热流基本一致,当壁面为完全催化壁时,热力学非平衡模型所得热流更高,这种差异由化学反应特征温度差异引起,并随着流动的热力学非平衡特性增加而增加.     

高超声速飞行器磁控热防护系统建模分析

针对高超声速飞行器防热, 搭建了螺线管磁控热防护系统的物理模型. 采用低磁雷诺数磁流体数学模型, 分析了外加磁场强度及磁场形态对磁控热防护效果的影响. 对比了三种磁场类型(磁偶极子、螺线管、均布磁场)下磁控热防护效果的差异, 分析了螺线管几何参数对磁控热防护效果的影响. 研究表明, 磁场降低表面热流作用存在“饱和现象”; 三种磁场形态的磁控热防护能力从小到大依次为磁偶极子、螺线管、均布磁场; 相同驻点磁感应强度条件下, 增大螺线管半径有利于提高磁控热防护效果, 缩短螺线管与驻点距离不利于驻点和肩部防热, 螺线管长度对磁控热防护效果影响相对较小.     

可重复使用飞行器热走廊物理建模研究

对再入热走廊的物理含义进行了定义分析,为使防热层温度不超过热防护系统所允许使用的极限温度,可重复使用飞行器的飞行轨道必须在再入走廊热之内。建立了可重复使用飞行器再入热走廊的物理模型,给出该物理模型下热走廊的控制方程和求解方法。通过对航天飞机轨道器典型位置的再入热走廊与传统方法的验证分析,说明本文建立的可重复使用飞行器再入热走廊物理模型和求解方法是正确的,同时探讨了表面材料承受温度和发射系数对热走廊的影响规律。     

Ion temperature and hydrodynamic-energy measurements in a Z-pinch plasma at stagnation

The time history of the local ion kinetic energy in a stagnating plasma was determined from Doppler-dominated line shapes. Using independent determination of the plasma properties for the same plasma region, the data allowed for inferring the time-dependent ion temperature, and for discriminating the temperature from the total ion kinetic energy. It is found that throughout most of the stagnation period the ion thermal energy constitutes a small fraction of the total ion kinetic energy; the latter is dominated by hydrodynamic motion. Both the ion hydrodynamic and thermal energies are observed to decrease to the electron thermal energy by the end of the stagnation period. It is confirmed that the total ion kinetic energy available at the stagnating plasma and the total radiation emitted are in balance, as obtained in our previous experiment. The dissipation time of the hydrodynamic energy thus appears to determine the duration (and power) of the K emission.     

Particle size effect on thermal conductivity of AlN films with embedded diamond particles

Fabricating composite thin films is an effective and economic solution to improve the thermal performance of the films. The diamond particles of different sizes were successfully embedded in AlN thin films by a chemical solution approach, which was confirmed by scanning electron microscope, x-ray diffraction analysis and x-ray photoelectron spectroscopy. The thermal properties of the films embedded with different diamond particles were studied by using a 3-omega method, which was observed to be strongly dependent on the particle size. A 19 % enhancement in thermal conductivity can be achieved by embedding diamond particles of 1-μm radius in AlN thin films. However, the thermal conductivity decreases after embedding with 10-nm radius diamond particles. The results are discussed with high volume model, which confirms that the interface thermal resistance between the embedded materials and the films plays an important role in determining the thermal conductivity of the as-grown carbon material embedded AlN films.     

SHROUD TECHNIQUE USING THE TRANSIENT METHOD FOR LOCAL HEAT TRANSFER MEASUREMENTS

A new technique for measuring local heat transfer coefficients on complex-shaped models is described. This technique is referred to as the shroud technique and is a variation on the well-known transient method. The technique involves preheating a model inside a shroud while it is installed in a wind tunnel. The shroud is then ejected, exposing the model to ambient temperature air. The transient temperature on the surface of the model is measured using liquid crystals and recorded with a video system. Although an infinite variety of model shapes can be used, measurements on a cylinder in cross-flow are used to demonstrate this technique. The measurements are compared with earlier measurements, which used different techniques. Good agreement is found at the stagnation point and in the front laminar boundary-layer region. In the separation region, the heat transfer rate is dependent an the thermal boundary condition, which in the transient method is affected by the selection of the nondimensional liquid crystal temperature. In the wake region, it was found that the results depend on the flow development time relative to the transient measurement time.     

高超声速飞行器前缘疏导式热防护结构的实验研究

针对高超声速飞行器前缘疏导式防热结构的特点,设计前缘内嵌高导热率材料结构和一体化层板热管结构两类对比实验,用于验证前缘疏导式防热结构的可行性.利用球形短弧氙灯作为辐射热源模拟气动加热,分别对钢质前缘、内嵌铜材料的钢质前缘和一体化层板式热管前缘进行加热,测量前缘驻点区域和尾部翼面区域的温度变化.实验结果表明:内嵌高导热率材料的前缘疏导结构能够降低头部驻点区的温度,提高尾部低温区的温度,实现对前缘结构的热防护;以蒸馏水作为工质一体化层板式热管前缘结构,在较低热流条件下也能够实现对前缘驻点区的疏导式热防护,但在较高热流条件下,由于水蒸气压力过大使得层板式前缘结构发生破坏,体现出热管内部工作介质对结构防热效果和应用范围都起到的关键作用.