其他检测

A coaxial jet was actively controlled by a MEMS-fabricated micro flap actuator nozzle. The effect of different control modes on secondary azimuthal instabilities and the evolution of streamwise vortices were investigated by applying stereoscopic PIV to the cross-stream plane of the jet. Forcing with non-symmetric modes, in particular the least-stable helical mode, accelerates the evolution of the streamwise vortices through the enhancement of azimuthal instabilities. Although forcing is applied to the outer shear layer of the outer jet, the control effect is most pronounced in the inner shear layer of the inner jet. Unlike in the natural jet, streamwise vortices appear in the inner shear layer of the controlled jet. For forcing with the fundamental axisymmetric mode, a Strouhal number of the order of unity maximise the azimuthal instabilities and hence the counts of the streamwise vortices. The present result is in accordance with our previous experimental findings in the longitudinal plane, where the evolution of the primary vortices and mixing between the inner and the outer jets were examined through 2D-PIV and PLIF (Kurimoto et al., 2004, Active control of coaxial jet mixing with arrayed micro actuators. Transactions of the Japanese Society of Mechanical Engineers, pp. 31–38.) This emphasises the connection between primary and streamwise vortices and their significance in the mixing enhancement process. It is also found that the azimuthal wavelength under the present control scheme is almost the same as that of the natural jet and independent of the streamwise position.

相位多普勒干涉测量术探测区域和粒子粒径比值小于一（第二部分 该技术的应用）。采用最新型的DPSSL激光器取代传统的氩离子激光器，具有光束相干性好，干涉条纹对比度强，测量精度和数据有效率高，调试简单快捷的突出优点。

高效液相色谱法（High Performance Liquid Chromatography \ HPLC）是一种有效可靠的技术，目前已成为许多实验室研究的重要工具。HPLC最常见的一个问题就是溶剂中的污染物对分析结果的影响。

环境试验箱主要用于电子、电工、仪器、仪表、汽车、家电、各种电子元器件及零部件、化工原材料及涂层、镀层等,主要客户群体有汽车行业,半导体行业,国防军工等。 在选择环境试验箱时，我们先按照需要的试验环境与场地,以及具体分析对待试验物品的使用要求，环境试验箱在国防军工方面主要对模拟环境试验场及实验室的使用较为突出 ，且有对环境试验标准的制定。所有武器装备、零部件和材料以及弹药都必须先送到环境实验室进行模拟环境试验，再送到环境试验场进行实地环境试验，只有通过了这些试验 才能正式交付部队使用。国防部已把环境试验作为试验与鉴定工作的一部分。国外已将环境试验标准化，许多国家还制定了环境试验标准，这些标准都大同小异。

您还在为得到一个优秀的 EBSD样品而进行各类电解液的配方调制而发愁吗？您还在为得到一个优秀的 EBSD样品，而花费大量时间泡在实验室进行各类机械抛光处理而苦恼吗？您还在为使用 FIB技术得到的优秀小面积 EBSD样品所花费的高额费用而担心吗？

As part of the FARWAKE project, subtask 2.1.1, wake vortex flow experiments are performed using the PIV measurement technique in a water tank. The wake generating model consists of a simple wing/flap model that can be equipped with water jets to simulate propulsion effects. The model was tested at a speed of 3m/s and two angles of attack: 0and 6. Chord Reynolds number of approximately 225.000 and Vortex Reynolds numbers of approximately 150.000 and 220.000 were obtained during the tests. The main objective of the present study is to investigate the influence of a jet on the flap end vortex and the wake vortex formation. The investigation focuses on the direct influence of the jet on the flap end vortex and the (merged) vortex characteristics in the near to mid field. The main vortex characteristics addressed in this report are: the vortex trajectory, the maximum tangential velocity, the peak vorticity and the vortex core radius. The vortex information is obtained from Stereo-PIV experiments performed in a fixed plane perpendicular to the towing direction. The measurements return the 3 components of the velocity in that plane and the streamwise component of the wake vorticity. A submergible moving camera system is used in order to keep the moving vortex in the field of view during the vortex downward motion.

室内机的流场结构会因为不同的压损值以及搭配的不同转速时会有所不同，主要分成兩种形式。当压损较小时，通过横流扇而被提供动能的流体，大多能沿著背板的几何形狀朝下游移动。若当压损逐渐提高，在低转速下的流场结构会产生明显的差異，在葉輪侧靠近出口处区域与舌部下方的之间，回流区范围有显著的扩大趋势，在靠近葉輪部分流体的运动方向可被观测出有被卷吸回葉輪的情形，大多是受到高速旋转的葉輪在通过舌部後，产生的低压结构所引致的现象。此时若提高葉輪的转速，将有助於提供流体更多的动量，可使舌部附近的回流区结构缩小，同时在横流扇入口上方的回流区结构也明显受到抑制。 然而，当压损值提高时，不同转速下的流场结构相当類似，葉輪上方的入风口处，都有明显的回流结构，部分情形下甚至可达近一半的入口面积。另外，出风口处的回流区结构相当大，速度较大的区域皆集中在弧形背板处，并且造成出口处的气流速度产生骤降的现象。当压损在特定范围以上时，本研究之横流扇的出风特性有明显的变化，即便再提高转速，仍无法提供流体产生足够的动量，以形成有效的气流流动，风扇运转已偏離有效操作点。 经由上述的实验结果中得知，此横流扇结构在低压损或是高转速下的出风流场结构多能沿著背板进而流至出风口。倘若压损提高或转速降低时，出口风速锐减，室内机的送风性能明显降低。因此，此室内机的几何形狀应针对不同的压损下的送风性能讨論，进行改良设计，本文以PIV进行量测，提供一种快速有效的研究方法。

用PIV方法实验研究了5.5米宽，13.5米长水槽内浅表湍流，剪切流动中大尺度漩涡结构的产生和消失机理。

Invention of the 3D detector approach for extending the measurement range and signal validation, W.D. Bachalo 1982.

恒温恒湿箱与恒温恒湿培养箱的差别 恒温恒湿箱与恒温恒湿培养箱的区别在哪呢？ 首先了解这两款产品都有控制湿度的功能,但是控湿的范围不一样,温度控制范围也有差别. 我们先来介绍一下恒温恒湿箱的控湿范围与控温范围,通过了解这些技术参数就能区分出来。 恒温恒湿培养箱的控温与控湿范围: 控温范围:4～60℃ (控湿范围:55%R.H～90%R.H) 用途范围:恒温恒湿培养箱广泛用于药物，纺织，食品加工，生物工程等做各项温湿度测试，是生物、遗传工程、医学、卫生防疫、环境保护、农林畜牧等行业的科研机构、大专院校、生产单位实验室的重要试验设备，应用于低温恒温试验、培养试验、环境试验等。 恒温恒湿箱均使用304不锈钢制造的内循环大容量水箱,而恒温恒湿培养箱一般都是外置加湿器。

本文采用甲酸铵和乙腈梯度以及 Agilent InfinityLab Poroshell 120 HILIC 2.1 × 150 mm，1.9 μm 色谱柱对 12 种游离氨基酸进行了 LC/MS 分析。550 bar 下，同质异位亮氨酸和异亮氨酸在 11 分钟内达到基线分离 (Rs = 1.9)。

Numerical simulations of particle image velocimetry (PIV) experiments con- ducted with vortex generating jets (VGJs) on a °at plate, at a Reynolds number based on plate length of 50,000, were performed for three °ow conditions using a time-accurate hybrid Navier-Stokes solver. Time-averaged steady blowing of angled jets, subjected to a zero pressure gradient, yielded excellent agreement with the PIV data in terms of vortex formation and strength. Observed °ow features include pri- mary and secondary vortices, where the primary vortex eventually dominates the downstream region. A shell wall structure, created by smaller vortical structures sur- rounding the developing vortices, was also observed. A pulsed jet in a zero pressure gradient was then initialized from a no-control case. A qualitative comparison be- tween averaged experimental and instantaneous numerical results was performed with good agreement in terms of the convected size and distance of the wake. Analysis of the instantaneous numerical °ow ¯eld agreed well with various °ow visualization experiments describing the formation of \kidney" vortices. Various indicators point to the production of a primary vortex by the reduced mass °ow of the pulsed jet. Finally, an adverse pressure gradient was applied, inducing a laminar separation zone on the plate. A pulsed angled jet induced strong spanwise vortices in the separated shear layer which appear to weaken the separation zone and allow the bulk jet °uid to °ush the remaining low-momentum °uid out of the domain. It is reasonable to assume that reduced blowing ratios and duty cycles would produce similar shear layer vortices and comparable loss reductions. In°uences of both turbulent transition and dominant vortical structures were observed, though the spanwise shear layer vortices appear to be critical to the laminar separation reduction scenarios observed in this study.

This is an experimental study to evaluate the development of the boundary layer thickness, δ, and momentum thickness, θ, along long thin flexible cylinders (L/a=1.5*105 and 3.0*105 where δ/a>>1, a=radius). The experiments use conventional test methods in conjunction with Stereo Particle Image Velocimetry (SPIV) measurement techniques to evaluate the flow in the boundary region of a small diameter flexible cylinder towed in the high speed towing basin at the Naval Surface Warfare Center Carderock Division (NSWCCD). The flexible cylinders are approximately neutrally buoyant and have an initial length of 152 m and radii of 0.45 mm and 1.25 mm. The first objective for this experiment is to evaluate the streamwise development of wall shear stress (τw) and momentum thickness (θ) in axisymmetric turbulent boundary layers using drag measurements at 3.1, 5.2, 9.3 and 14.4 m/s for comparison to existing data. The second and primary objective for this experiment is to determine the streamwise development of the axisymmetric boundary layer flow and to evaluate relevant boundary layer parameters at 3.8, 7.7, 12.9 and 15.4 m/sec using SPIV images acquired over the entire length of the cylinders. Drag measurements reveal that the wall shear stress is large and that the momentum thickness grows slowly when compared to flat plate boundary layers. The velocity field data shows that the boundary flow remains turbulent over the entire length of the flexible cylinder and that the turbulent profile is different from that of flat plate boundary layers.

离子色谱（IC）起源于1975年，是高效液相色谱的一种，是一种分析阴离子和阳离子的液相色谱方法。由于IC能够同时且简便地分离、定量多种无机离子，离子色谱法已经广泛地用于环境、食品、材料、工业、生物和医药等许多领域。离子色谱法除了能够检测常规的无机阴离子和阳离子外，如今其应用已扩展到检测有机酸（如甲酸、乙酸）、氨基酸和低分子胺类物质等。 本资料分别对IC的基本原理、检测方法、样品前处理操作等进行说明介绍。 - 目录 - 1.前言 2.分离原理 2-1 离子色谱的定义 2-2 分离方式 2-3 填料的特性 2-4 IC仪器的构成 2-5 检测方法 3.检测方法 3-1 样品检测过程 3-2 色谱柱的选择 3-3 淋洗液的选择 3-4 柱温的影响 3-5 前处理 3-6 检测限和定量值 3-7 成分检测 3-8 标准液 3-9 定量计算 3-10 分析样品的保存 3-11 高通量分析 4.结束语 附录-1 应用数据 附录-2 故障排除

对于微量样品和固体样品的测量，HORIBA Scientific（Jobin Yvon光谱技术）提供相应的解决方案。针对生物分析中的蛋白，酶等微量液体样品分析，我们提供不同规格的比色皿（20μL，50μL，250μL,1mL）；针对材料领域中的单微晶或聚合物分析，我们提供可转角度的固体样品支架；针对血液、颜料、荧光增白剂、活细胞等样品，我们提供前置式荧光测量方案。

利用 Agilent InfinityLab Poroshell 120 HILIC-Z 色谱柱通过梯度和等度洗脱分离 11 种糖化合物。考察了 pH 和温度对葡萄糖端基异构体分离的影响。研究发现强碱和低温的组合为峰形和柱寿命提供了最佳解决方案。最终分离使用氢氧化铵流动相和 35 °C 的柱温。

The flow of an air curtain mounted above a doorway in which was placed a mannequin was studied using stereo particle image velocimetry. The study revealed that the interference of the air curtain flow was limited to a region near the doorway. The air curtain flow stagnates around the top surfaces of the mannequin. A high level of turbulence also existed in this region. The turbulence diminished rapidly past the mannequin and increased in a thin region near the floor as the flow entered the floor vents

在LAMBDA 950/1050中安装马达驱动动变角的通用反射附件和马达驱动的偏振器附件，可轻松实现增强型镜面反射膜性能的自动验证。由于增强型镜面反射膜的厚度极薄且柔软，因此，要想在常规分光光度计系统和附件中专为硬质滤光片和玻璃设计的垂直样品架上妥当地固定超薄增强型镜面反射膜的难度极大。通用反射附件的独特设计（即，无样品架设计，样品只需平放在顶板的测样口上）能够确保精确地测量增强型镜面反射膜的镜面反射率。

In this work, we report on the direct measurement of heat release rates via simultaneous laser-induced fluorescence of OH and CH2O radicals using planar laserinduced fluorescence (PLIF). The product of the two images is shown to correlate with the forward production rate of the HCO radical, which in turn has been found to correlate well with heat release rates in premixed hydrocarbon flames. Heat release rate measurements were also taken with OH* for comparisons with the results from the laser-based technique. The measurements were made in a lean turbulent premixed flame subject to acoustic forcing; this flame mimics the instabilities encountered in lean premixed pre-vaporized combustors (LPP). As the scheme is based on probing radical species that participate in the major heat release reactions, it is the closest nonintrusive measure of heat release rate currently available and thus presents a very useful diagnostic tool in combustion research.

Detailed schlieren and laser lightsheet visualizations of the near wake of micro vortex generator (MVG) revealed large structures that were different from those of the undisturbed turbulent boundary layer. These structures were attributed to the rapid breakdown of the primary trailing vortex pair. The breakdown was thought to arise from a cylindrical Kelvin–Helmholtz-like instability surface. The structures appear to be hairpin or ring-like in nature that showed eruptions into the freestream flow, entraining it.

光致发光和拉曼光谱是材料研究的重要技术手段，但样品可能具有多种形状和大小，或不易移动。采用光纤耦合、能够适合特殊样品的光学探头进行探测显得尤为重要。 由Superhead光纤耦合的探头、iHR光谱仪及CCD探测器组成的模块化光致发光、拉曼测量系统，可进行在线、远程的光致发光和拉曼分析测量，大大拓展了测量系统的灵活性。

5、 在空气中和在油中做电压击穿试验有什么区别： A：测试介质空气—是指把被测试样和电极放置在空气中做耐压和击穿实验 B；测试介质油----是指把被测试样和电极完全放置在油中做耐压和击穿实验，通常使用25#变压器油做试验介质 C：无论在空气中还是在油中做实验对测试数据没有影响，如果被测样品没有特殊要求通常默认在空气中做实验，有两种情况需要在油中做实验，一是标准里有规定，必须在油中做实验，二是在空气中做实验时，被测试样出现爬电、释放电火花而导致无法击穿时必须放置在油中做实验

Flow and far-field noise measurements are taken on a conical Convergent- Divergent nozzle similar to the nozzles employed on high-performance tactical jets. Matching flow and far-field computations are presented, produced by Large Eddy Simulation and the Kirchhoff integral method. The conditions examined are those in which the nozzle is operated at its design Mach number of 1.56 while forward flight is simulated at Mach numbers of 0.1, 0.3 and 0.8. Both measurement and LES show that increasing forward flight Mach number to the high subsonic range shortens the initial shock cell size, and weakens the shock cells induced by the nozzle throat relative to the shock cells induced by the nozzle lip. LES shows that high forward flight speed substantially reduces the noise radiated into the forward quadrant where shock noise is dominant. It also removes the screech tone entirely.

Various types of capacitively coupled radio frequency (CCRF) discharges are frequently used for different applications ranging from chip and solar cell manufacturing to the creation of biocompatible surfaces. In many of these discharges electron heating and electron dynamics are not fully understood. A powerful diagnostic to study electron dynamics in CCRF discharges is phase resolved optical emission spectroscopy (PROES). It is non-intrusive and provides access to the dynamics of highly energetic electrons, which sustain the discharge via ionization, with high spatial and temporal resolution within the RF period. Based on a time dependent model of the excitation dynamics of specifically chosen rare gas levels PROES provides access to plasma parameters such as the electron temperature, electron density and electron energy distribution function (EEDF). In this work the method of PROES is reviewed and some examples of its application are discussed. First, the generation of highly energetic electron beams by the expanding sheath in geometrically symmetric as well as asymmetric discharges and their effect on the EEDF are investigated. Second, the physical nature of the frequency coupling in dual frequency discharges operated at substantially different frequencies is discussed. Third, the generation of electric field reversals during sheath collapse in single and dual frequency discharges is analysed. Then excitation dynamics in an electrically asymmetric novel type of dual frequency discharge is studied. Finally, limitations of PROES are discussed.

Polarization null angle (PNA) method is an accurate alternative to the commonly used polarization intensity ratio method in determination of molecular orientation at interfaces with sum frequency generation vibrational spectroscopy (SFG-VS). Here, the accuracy and sensitivity of PNA method is tested on different experimental configurations. It is found that its accuracy and sensitivity are more sensitive to the incident angle of the visible beam than the IR beam, and the range of the optimal experimental configurations is identified. This development makes better understanding of the polarization measurement in SFG-VS, and should find more applications for interface studies.

The efficacy of dielectric barrier discharge (DBD) plasmas driven by repetitive nanosecond (NS) pulses for flow separation control is investigated experimentally on an airfoil leading edge up to Re=1x106 (62 m/s). The NS pulse driven DBD plasma actuator (NS-DBD hereafter) transfers very little momentum to the neutral air, but generates compression waves similar to localized arc filament plasma actuators. Experimental results indicate that NS-DBD plasma performs as an active trip at pre-stall angles of attack and provides high amplitude perturbations that manipulate flow instabilities and generate coherent spanwise vortices at post-stall angles. These coherent structures entrain freestream momentum thereby reattaching the normally separated flow to the suction surface of the airfoil. Such devices which are believed to function through thermal effects could result in a significant improvement over AC-DBD plasmas that rely on momentum addition which limits their performance at high speeds.

A review of the work conducted on particle interactions with turbulent flows provides a basis for the continued development of the diagnostics. Flow visualization techniques have provide insights to the global characteristics of the particle interaction with large scale eddies. Recent experiments conducted by a number of researchers in the field were reviewed. These data served to evaluate merits of the current theories and set a basis for future research. The development of particle size and velocity instrumentation has allowed the detailed probing of these flows and offers a potential for in-depth studies of particle interactions with the turbulent flows and the mechanisms of particle dispersion. Advances in the PDPA instrument and the data acquisition technology are described. Particle response correlations are given along with some experimental verifications using the Phase Doppler Particle Analyzer (PDPA) Examples of data obtained with the instrument are presented.

低加速电压成像在扫描电镜成像中有着重要的作用。采用低加速电压成像，低能电子束受到散射的扩散区域小，相互作用区接近表面，有利于表面精细形貌成像。对于某些热敏或导电性能差的样品，如半导体和器件、合成纤维、溅射或氧化薄膜、纸张、动植物组织、高分子材料等，有时不允许进行导电处理，而要求直接观察，采用低加速电压成像可以减小或消除此类样品的荷电效应同时减小电子束辐照损伤。下图为氧化锌样品在5KV 和15KV 下的图像对比，由图像可知，在5KV 低加速电压下，样品表面细节特征清晰，有利于表面精细形貌的观察。

To gain some more understanding of the flapping wing aerodynamics and aeroelasticity associated with biological flyers and micro air vehicles (MAVs), a combined computational and experimental study of a well characterized flapping wing structure was conducted. In particular, the coupling between aerodynamics and structural dynamics plays an important role in such flyers but to date has not been adequately addressed. An aeroelasticity framework based on a co-rotational shell finite element solver with a Navier-Stokes solver is developed. Experimentally, a customized digital image correlation system measures the wing deformation, a load sensor attached to the flapping mechanism records the forces produced by the flapping motion, and a stereo digital particle image velocimetry measures the flow velocities. Computational efforts with insight into the fluid physics are reported. Relevant fluid physics are documented including the counter-rotating vortices at the leading and the trailing edge which interact with the tip vortex during the wing motion. Overall, good correlations between experiment and computation are attained. Furthermore, studies on hypothetical flexible flapping wing configurations showed that wing flexibility can be tailored to alter the aerodynamics of a flapping wing.

原子力显微镜（Atomic Force Microscope ，AFM），一种可用来研究包括绝缘体在内的固体材料表面结构的分析仪器。它通过检测待测样品表面和一个微型力敏感元件之间的极微弱的原子间相互作用力来研究物质的表面结构及性质。将一对微弱力极端敏感的微悬臂一端固定，另一端的微小针尖接近样品，这时它将与其相互作用，作用力将使得微悬臂发生形变或运动状态发生变化。扫描样品时，利用传感器检测这些变化，就可获得作用力分布信息，从而以纳米级分辨率获得表面结构信息。 它主要由带针尖的微悬臂、微悬臂运动检测装置、监控其运动的反馈回路、使样品进行扫描的压电陶瓷扫描器件、计算机控制的图像采集、显示及处理系统组成。微悬臂运动可用如隧道电流检测等电学方法或光束偏转法、干涉法等光学方法检测，当针尖与样品充分接近相互之间存在短程相互斥力时，检测该斥力可获得表面原子级分辨图像，一般情况下分辨率也在纳米级水平。AFM测量对样品无特殊要求，可测量固体表面、吸附体系等。