载波条纹图的处理及应用

本文提出一种载波条纹的处理方法，将变形前、后的载波条纹图分别经过条纹细化、抽取中心、级数编码、全场拟合等处理，首先求出全场每个像素点上的条纹级数，然后再对应相减，以得到仅仅由于变形引起的干涉条纹的全场分布，文中应用该方法分析处理了差分干涉条纹图，测量了水平热管周围的温度场、温度梯度场及壁面换热系数。     

固体火箭发动机燃烧室光弹性分析

本文运用光弹性法研究了某型固体火箭发动机燃烧室内端燃型药柱和星柱型药柱两种形状的固体复合推进剂的残余应力场,测定了光弹材料的弹性模量、泊松比、线胀系数、材料条纹值和冻结温度,获得了光弹材料在压应力和温度应力下的等差线条纹图,分析了应力分布情况.     

基于轮廓法测量钛合金激光熔覆中的残余应力

由于激光熔覆过程中有温度变化快、局部温度梯度大和伴随固液相快速转化等特性,在熔池和热影响区会产生很大的残余应力和变形,不利于金属增材制造和局部修复的精确可控。本文对Ti-6Al-4V(TC4)合金开展激光熔覆实验,采用轮廓法测量了激光熔覆所产生的残余应力;通过三维热力耦合有限元模型计算了温度场和残余应力场,仿真计算结果与轮廓法测量的残余应力趋势一致。结果表明,残余应力在熔覆位置有最大拉伸应力,随着远离焊缝急剧变成压缩应力并逐渐减小。上述工作有利于研究熔覆过程中的温度分布规律及残余应力的生成机制,可为熔覆过程的工艺控制提供参考。     

电子剪切散斑图像处理的相移技术

本文从理论上分析了电子剪切散斑干涉(ESSPI)实现相移的可行性,推导了相移的 ESSPI 光强表达式;采用机械放大式相移器得到相移 ESSPI 条纹图;用计算机图像处理技术精确地获得位相图;用去包裹技术得到等位移梯度曲线和离面位移分布曲线,使 ESSPI 图像处理的过程简单化,快速化,提高了测试的自动化程度。     

激光引爆起爆药的机理及其爆轰流场的干涉法研究

本文从实验上研究小型脉冲YAG激光引爆或引燃起爆药的可能性;在理论上,从激光热引爆的机理简述了激光引燃或引爆的判据。并采用大口径长程FP型干涉仪,外调制序列脉冲激光源和高速记录装置,获得了起爆药爆轰流场和燃烧温度场的时间序列干涉图,定量计算了爆轰冲击波的传播速度。     

散斑光弹性干涉法

全息干涉法和普通光弹性法相结合产生了全息光弹性法。与此类似,本文建议将散斑干涉法和光弹性相结合形成具有一定特点的散斑光弹干涉法。近十几年来,散斑干涉法得到了很快的发展,可以获得面内或离面位移,错位散斑干涉法则可获得位移梯度场。本文建议将光弹性透明模型置于双光束散斑干涉光路中,通过两次曝光法可以获得模型的应力条纹图案。但和全息光弹性法相比,只要选择合适的漫反射器,用散斑光弹干涉法可以获得不受等差线干扰的、单纯的等和线条纹图。同样的理由,也可以获得三维应力模型冻结切片的等和线条纹图。更有意义的是采用双光片散光穿透模型的散斑光弹性干涉法将有可能获得整体三维应力模型内部的绝对光程应力条纹图,这将为三维应力分析提供一种新的实验方法。     

电子散斑干涉和Video全息干涉

本文综述了有关电子散斑干涉法(ESPI)和Vidco全息干涉技术的一些近期成果.主要包括:有机玻璃模型中主应力和的测量,二维气体温度场和轴对称气体温度场的测量,三维物体表面形状和三维位移场的测量.条纹图均用数字图象处理系统处理.文中介绍了各种测量光路和操作技术,分析了可能出现的误差,提供了部分实验结果.     

三种工况下SiC/Al梯度功能材料紧凑拉伸试件的应变测试

SiC/Al梯度功能材料试件各梯度单层由不同体积浓度的铝合金和陶瓷SiC复合而成,由于材料组分梯度变化,有效缓和了双材料界面的应变跳跃问题,从而能够获得了优异的使用性能,本文从实验的角度采用激光云纹干涉法,对具有四个梯度层的SiC/Al梯度功能材料紧凑拉伸试件在三种工况下进行实验研究.通过实验采集试件在各工况下的位移场云纹图,根据位移与条纹级数的关系以及小变形条件下应变与条纹级数关系式,获得梯度功能材料紧凑拉伸试件预制裂纹区的应变分布.通过实验结果与文献对比分析,在有关梯度功能材料的裂纹扩展准则的适用性方面取得一致结论;同时,就实验获得的应变结果,讨论了梯度功能材料的材料参数变化规律,以及材料组分和梯度层结构对FGM材料整体力学性能的影响.     

电子错位散斑研究

本文从理论上分析了错位散斑实现电子干涉的可行性,推导了摄象机光靶接收的错位散斑的光强表达式,分析了电子干涉条纹的可见度,提出并实现了电子错位散斑技术的三种方法,即实时法,双曝光法和实时时间差法。获得了位移梯度等值条纹的电子干涉图。     

干涉条纹图处理的等值线窗口滤波和摄像测量在国防试验的应用

对图像进行滤波或称平滑是干涉条纹图像处理中的一项重要工作。一幅未经处理的原始图像或多或少存在着不同程度的噪声干扰,特别是散斑和Insar干涉条纹图,信噪比很低,难以处理。本文针对光测力学中光学干涉方法得到的条纹图,提出了一种新的滤波方法条纹等值线窗口滤波,并对这种滤波方法进行了研究讨论,提出了几种确定等值线窗口的不同方法。这种滤波方法根据干涉条纹图不同断面上灰度分布的不同特点,选择沿条纹走向的条纹等值线窗口进行滤波,在最大消除条纹图噪声的同时,也能保证对条纹损伤最小。摄像测量技术正在迅速发展和得到广泛应用,在国防试验和航天飞行任务中发挥着不可替代的作用。本文也介绍了作者近年来在该领域所做的应用研究,包括在火箭、导弹发射试验,冲击、碰撞等过程中的动态目标运动测量;针对航天航空和力学工程领域的视频图像实时分析;飞行器三维运动测量;基于投影条纹的物体三维形貌精密测量方法研究;以及对接航天器位置和姿态的实时测量。在这些应用中都实现了高精度测量。     

The discrete heat source approach to dust cloud combustion

In the present paper, combustion of dust clouds from the discrete point heat source method has been addressed. Time-place temperature profile generated by single particle burning has been obtained to study the dust combustion. The summation of the temperature profiles of burned and burning particles predict the temperature in the preheating zone so that the ignition time of layer in flame front can be determined. Consequently the flame propagating speed was obtained based on the dust concentration corresponding to particles spacing and particle diameter. This method has been validated with aluminum dust cloud combustion. Decrease in the dust concentration leads to the lean limit of dust combustion. Increase in particles diameter or reduction in the dust concentration causes higher lean limit and also reduction in the flame propagating speed. Adding the ignition energy as igniter to this system, provides the path to study the effects of ignition energy in the dust combustion.     

Numerical modeling of the processes within the combustion chamber of a solid propellant rocket engine during the stabilization of the design operation mode

Comprehensive numerical modeling of the processes occurring in the combustion chamber of a solid propellant rocket engine during the stabilization of the design operation mode is performed. The self-consistent problem considered includes nonstationary operation of an ignition device, warmup and ignition of a solid propellant charge followed by its nonstationary burning, nonstationary threephase homogeneous-heterogeneous flow of the combustion products in the combustion chamber, in the nozzle, and behind the engine nozzle unit, engine depressurization, and nozzle unit plug blowing-out. The results of the calculations are presented.     

Cycle resolved multi-planar flow measurements in a four-valve combustion engine

The non-reacting flow in a one-cylinder four-valve combustion engine is measured via cycle resolved two-component/two-dimensional (2C/2D) particle-image velocimetry (PIV). The three-dimensional structure of the velocity field is analyzed based on the flow field measured in eight planar planes within the cylinder for several crank angles during the intake and compression phase. Using the mean and statistical values of the single planes quasi three-dimensional flow fields are reconstructed for crank angles of 80°, 160°, and 240° atdc. This enables the detailed analysis of the spatial distribution of the large and small scale flow structures, e.g., by visualizing large vortical structures and the distribution of the turbulent kinetic energy. It was found that two ring vortices evolving beneath the inlet valves are the dominant large scale structures that seem to be of major concern for the mixing process in the cylinder of a four-valve combustion engine operated at 1500 rpm. Furthermore, the temporal evolution of the flow field within the symmetry plane of the cylinder, measured for crank angles between 40° and 320° atdc in steps of 20°, is discussed. The results give new insight into the complex three-dimensional flow in the combustion chamber of a one-cylinder four-valve combustion engine. That is, the tumble vortex only seems to be of secondary importance for the flow concerning the mixing process at 1500 rpm. This is an essential result for future work considering the fluid mechanics of fuel-air-interaction processes and mixing principles in combustion engines.     

Stereoscopic multi-planar PIV measurements of in-cylinder tumbling flow

The non-reacting flow field within the combustion chamber of a motored direct-injection spark-ignition engine with tumble intake port is measured. The three-dimensionality of the flow necessitates the measurement of all three velocity components via stereoscopic particle-image velocimetry in multiple planes. Phase-locked stereoscopic PIV is applied at 15 crank angles during the intake and compression strokes, showing the temporal evolution of the flow field. The flow fields are obtained within a set of 14 axial planes, covering nearly the complete cylinder volume. The stereoscopic PIV setup applied to engine in-cylinder flow and the arising problems and solutions are discussed in detail. The three-dimensional flow field is reconstructed and analyzed using vortex criteria. The tumble vortex is the dominant flow structure, and this vortex varies significantly regarding shape, strength, and position throughout the two strokes. The tumble vortex center moves clockwise through the combustion chamber. At first, the tumble has a c-shape which turns into an almost straight tube at the end of the compression. Small-scale structures are analyzed by the distribution of the turbulent kinetic energy. It is evident that the symmetry plane only represents the 3D flow field after 100 CAD. For earlier crank angles, both kinetic energy (KE) and turbulent kinetic energy (TKE) in the combustion chamber are well below the KE and TKE in the symmetry plane. This should be taken into account when the injection and breakup of the three-dimensional fuel jet are studied. The mean kinetic energy is conserved until late compression by the tumble motion. This conservation ensures through the excited air motion an enhancement of the initial air-fuel mixture which is of interest for direct-injection gasoline engines.     

Stabilization of propane combustion in a supersonic air flow using a nonequilibrium longitudinal discharge and a coaxial local low-pressure zone

The results of the experimental investigation of the flow in the vicinity of an electric-discharge module having a low aerodynamic drag and intended for igniting hydrocarbon fuel and stabilizing its burning in a supersonic flow at low initial static temperature and pressure are presented. The distinctive feature of the module is that the combustion zone is not attached to the combustion chamber walls. Due to a certain geometric connection between different regions of the module anode, an interference of shock and expansion waves occurs in its vicinity. This leads to the formation of a local longitudinal low-pressure zone behind the anode, the convergence of individual fuel jetlets injected through orifices in the anode in this zone, the formation precisely there of a longitudinal nonequilibrium discharge, and the intensification of fuel mixing and plasmochemical reactions. The gasdynamic features of supersonic flow past the module are numerically investigated. The dynamics of electrical discharge formation and the combustion zones thus formed are studied under particular conditions. The data on the stagnation temperature distribution in the discharge wake are obtained.     

基于光学诊断的某新型含铝推进剂燃烧特性分析

为探究某新型含铝固体推进剂燃烧特性和规律,在模拟固体发动机的高压条件下,采用可调功率激光器结合高速摄影、发射光谱等光学诊断技术对该新型含铝固体推进剂开展了系统的点火及燃烧过程研究。通过对该推进剂的点火延迟、退移速率、燃烧温度以及团聚物颗粒尺寸的定量测量和分析,明确了该推进剂的点火延迟量级;证实此推进剂的退移速率严格遵循Summerfield燃速公式;判断出其最高燃烧温度高于3 300 K,且随压力增大而升高;通过对燃烧过程中发光凝聚相产物面积的量化分析得出推进剂产物中团聚物粒径尺寸受环境参数的影响规律。     

甲烷/空气预混气体火焰的传播特征

利用高速纹影摄像等技术探讨了密闭管道内不同当量比的甲烷/空气预混气体火焰的传播特征。结果表明,当甲烷含量接近当量值时,预混气体火焰传播中会发生火焰阵面由向未燃区弯曲到向已燃区弯曲的转折过程,逐渐由层流燃烧转变成湍流燃烧,并形成Tulip火焰结构;当甲烷含量偏离当量值一定程度时,预混火焰呈现出典型的层流燃烧特征,不会发生火焰阵面由向未燃区弯曲到向已燃区弯曲的转折过程。Tulip火焰结构形成于火焰传播速度迅速降低的区间里,且只有当减速阶段的最大加速度的绝对值大于某一数值时才能形成;Tulip火焰结构是预混火焰由层流燃烧向湍流燃烧转变的一个中间过程。     

Laser measurement techniques applied to turbulent combustion in piston engines

The application of experimental laser diagnostic techniques to the study of turbulent flame propagation in homogeneous-charge internal combustion engines is demonstrated. A variety of laser refraction and scattering techniques are employed: the qualitative shape and detailed internal turbulence structure of the flame surface is investigated using laser schlieren photography; the flame location and local flame speed are measured using multibeam laser refraction; the instantaneous flame thickness is measured using Rayleigh scattering; gas temperatures are measured using Rayleigh and Raman scattering; gas velocity, turbulence intensities, and time scales of turbulence are measured using laser Doppler velocimetry. The problem of cyclic variation bias in turbulence measurements is addressed using conditional sampling procedures that involve the simultaneous implementation of multiple diagnostics. This paper focuses on the thermodynamic and fluid mechanic properties of interest to turbulence combustion studies, illustrating how laser diagnostics can be used to research the critical areas of interest.A version of this paper was presented at the ASME Winter Annual Meeting of 1984 and printed in AMD, Vol. 66     

高速液体受限射流扩展形态研究

采用一种火药燃烧驱动液体喷射的新装置及其测试系统，研究受限空间中高速惰性液体射流的扩展结构。观察了环境反压、液体粘性、喷嘴结构等参量对射流扩展形态的影响，分析了射流雾化机理。研究结果对改进燃烧室设计及控制燃烧稳定性有一定的指导意义。